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	+ Home		Additions to the NASA Aeronautics and Space Database as of 07/30/2009 20090025974 NASA Langley Research Center, Hampton, VA, United States Rewriting Logic Semantics of a Plan Execution Language Dowek, Gilles; Munoz, Cesar A.; Rocha, Camilo; June 2009; In English Contract(s)/Grant(s): NCC1-02043WBS 015792.04.01.0423 Report No.(s): NASA/TM-2009-215770; L-19700; LF99-8984; Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090025974 The Plan Execution Interchange Language (PLEXIL) is a synchronous language developed by NASA to support autonomous spacecraft operations. In this paper, we propose a rewriting logic semantics of PLEXIL in Maude, a high-performance logical engine. The rewriting logic semantics is by itself a formal interpreter of the language and can be used as a semantic benchmark for the implementation of PLEXIL executives. The implementation in Maude has the additional benefit of making available to PLEXIL designers and developers all the formal analysis and verification tools provided by Maude. The formalization of the PLEXIL semantics in rewriting logic poses an interesting challenge due to the synchronous nature of the language and the prioritized rules defining its semantics. To overcome this difficulty, we propose a general procedure for simulating synchronous set relations in rewriting logic that is sound and, for deterministic relations, complete. We also report on the finding of two issues at the design level of the original PLEXIL semantics that were identified with the help of the executable specification in Maude. Author AUTONOMY; PROGRAM VERIFICATION (COMPUTERS); SEMANTICS Additions to the NASA Aeronautics and Space Database as of 07/31/2009 20090026009 NASA Langley Research Center, Hampton, VA, United States NESC Independent Review of the Mars Reconnaissance Orbiter (MRO) Contamination Thermal/Vacuum (T/V) Anomaly Technical Consultation Report Sutter, James K.; Leidecker, Henning W.; Panda, Binayak; Piascik, Robert S.; Muirhead, Brian K.; Peeler, Debra; March 2009; In English; Original contains color illustrations Contract(s)/Grant(s): WBS 510505.01.07.01.06 Report No.(s): NASA/TM-2009-215573; NESC-RP-05-122/05-038-E; L-19609; LF99-8400; No Copyright; Avail.: CASI: A04, Hardcopy Avail Online: http://hdl.handle.net/2060/20090026009 The NESC eras requested by the NASA Jet Propulsion Laboratory (JPL) to conduct an independent review of the Mars Reconnaissance Orbiter (MRO) Thermal/Vacuum (T/V) Anomaly Assessment. Because the anomaly resulted in the surface contamination of the MRO, selected members of the Materials Super Problem Resolution Team (SPRT) and the NASA technical community having technical expertise relative to contamination issues were chosen for the independent review. The consultation consisted of a review of the MRO Project's reported response to the assessment findings, a detailed review of JPL technical assessment final report, and detailed discussions with the JPL assessment team relative to their findings. Author MARS RECONNAISSANCE ORBITER; CONTAMINATION; ANOMALIES 20090026010 NASA Langley Research Center, Hampton, VA, United States Design of Quiet Rotorcraft Approach Trajectories Padula, Sharon L.; Burley, Casey L.; Boyd, D. Douglas, Jr.; Marcolini, Michael A.; June 2009; In English; Original contains color illustrations Contract(s)/Grant(s): WBS 877868.02.07.07 Report No.(s): NASA/TM-2009-215771; L-19701; LF99-9005; No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090026010 A optimization procedure for identifying quiet rotorcraft approach trajectories is proposed and demonstrated. The procedure employs a multi-objective genetic algorithm in order to reduce noise and create approach paths that will be acceptable to pilots and passengers. The concept is demonstrated by application to two different helicopters. The optimized paths are compared with one another and to a standard 6-deg approach path. The two demonstration cases validate the optimization procedure but highlight the need for improved noise prediction techniques and for additional rotorcraft acoustic data sets. Author GENETIC ALGORITHMS; ROTARY WING AIRCRAFT; NOISE REDUCTION; TRAJECTORIES; HELICOPTERS; ACOUSTIC PROPERTIES; AIRCRAFT DESIGN Additions to the NASA Aeronautics and Space Database as of 08/04/2009 20090026215 NASA Ames Research Center, Moffett Field, CA, United States Workshop Report on Deep Mars: Accessing the Subsurface of Mars on Near Term Missions Langhoff, Stephanie R., Editor; June 2008; In English; Deep Mars: Accessing the Subsurface of Mars on Near Term Missions workshop, 1-2 Mra. 2008, Moffett Field, CA, United States; Original contains color illustrations Contract(s)/Grant(s): WU 292487.01.01.02 Report No.(s): NASA/CP-2008-214586; ARC-E-DAA-TN-142; No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090026215 The workshop encompassed three major themes. The first theme was the scientific objectives of drilling, which center on the search for clues to the existence of past life and to the geological and climate history of Mars. Key questions are where and how deep to drill? Planetary protection issues were stressed as an important consideration in the design of any drilling mission. Secondly, architectures for drilling missions were discussed, including an overview of most of the current drills in operation that would be applicable to drilling on Mars. Considerable emphasis was placed on remote operation and drilling automation technologies. Finally, alternatives to conventional drilling were discussed. These included underground moles, penetrometers, horizontal drilling, impactors, and access to the subsurface from subsurface cavities. Considerable discussion centered on the possible Mars drilling missions that could be performed in both the near and longer term. The workshop participants concluded that useful science could be obtained today using low-cost impactors, with or without a sheperding spacecraft. Author MARS ENVIRONMENT; PENETROMETERS; MARS MISSIONS; GEOLOGY; CLIMATE; PLANETARY PROTECTION Additions to the NASA Aeronautics and Space Database as of 08/05/2009 20090026291 NASA Johnson Space Center, Houston, TX, United States Handbook for Designing MMOD Protection Christiansen, Eric L.; Arnold, Jim; Davis, Alan; Hyde, James; Lear, Dana; Liou, J.-C.; Lyons, Frankel; Prior, Thomas; Ratliff, Martin; Ryan, Shannon; Giovane, Frank; Corsaro, Bob; Studor, George; June 2009; In English; Original contains color and black and white illustrations Report No.(s): NASA/TM-2009-214785; S-1038; Copyright; Avail.: CASI: A08, Hardcopy Avail Online: http://hdl.handle.net/2060/20090026291 Spacecraft are subject to micro-meteoroid and orbital debris (MMOD) impact damage which have the potential to degrade performance, shorten the mission, or result in catastrophic loss of the vehicle. Specific MMOD protection requirements are established by NASA for each spacecraft early in the program/project life to ensure the spacecraft meets desired safety and mission success goals. Both the design and operations influences spacecraft survivability in the MMOD environment, and NASA considers both in meeting MMOD protection requirements. The purpose of this handbook is to provide spacecraft designers and operations personnel with knowledge gained by NASA in implementing effective MMOD protection for the International Space Station (ISS), Space Shuttle, and various science spacecraft. It has been drawn from a number of previous publications, as well as new work. This handbook documents design and operational methods to reduce MMOD risk. In addition, this handbook describes tools and equations needed to design proper MMOD protection. It is a living report in that it will be updated and re-released periodically in future with additional information. Author MICROMETEOROIDS; SPACE DEBRIS; SPACECRAFT SURVIVABILITY; SPACECRAFT DEFENSE; SPACECRAFT SHIELDING; METEOROID PROTECTION 20090026303 NASA Johnson Space Center, Houston, TX, United States An Assessment of Dust Effects on Planetary Surface Systems to Support Exploration Requirements Wagner, Sandra; December 2008; In English; Original contains color illustrations Report No.(s): NASA/TM-2008-213722; S-0979; No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090026303 Apollo astronauts learned, first hand, how problems with dust impact lunar surface missions. After three days, lunar dust contamination on Extravehicular Activity (EVA) suit bearings led to such great difficulty in movement that another EVA would not have been possible. Dust clinging to EVA suits was transported into the Lunar Module. During the return trip to Earth, when microgravity was reestablished, the dust became airborne and floated through the cabin. Crews inhaled the dust and it irritated their eyes. Some mechanical systems aboard the spacecraft were damaged due to dust contamination. Study results obtained by Robotic Martian missions indicate that Martian surface soil is oxidative and reactive. Exposures to the reactive Martian dust will pose an even greater concern to the crew health and the integrity of the mechanical systems. The Advanced Integration Matrix Dust Assessment Team was tasked to identify systems that will be affected by the respective dust, how they will be affected, associated risks of dust exposure, requirements that will need to be developed, identify knowledge gaps, and recommend scientific measurements to obtain information needed to develop requirements, and to design and manufacture the surface systems that will support crew habitation in the lunar and Martian outposts. Author AEROSPACE MEDICINE; EXTRAVEHICULAR ACTIVITY; LUNAR DUST; PLANETARY SURFACES; TECHNOLOGY ASSESSMENT 20090026308 NASA Johnson Space Center, Houston, TX, United States Refinement of Optimal Work Envelope for Extravehicular Activity Suit Operations Jaramillo, Marcos A.; Angermiller, Bonnie L.; Morency, Richard M.; Rajulu, Sudhakar L.; November 2008; In English; Original contains color and black and white illustrations Report No.(s): NASA/TP-2008-214781; S-1032; Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090026308 The purpose of the Extravehicular Mobility Unit Work Envelope study is to determine and revise the work envelope defined in National Space Transportation System (NSTS) 07700 "System Description and Design Data -- Extravehicular Activities" arising from an action item as a result of the Shoulder Injury Tiger Team findings. The aim of this study is to determine a common work envelope that will encompass a majority of the crew population while minimizing the possibility of shoulder and upper arm injuries. There will be approximately two phases of testing: arm sweep analysis to be performed in the Anthropometry and Biomechanics Facility; and torso lean testing to be performed in the Precision Air Bearing Facility. NSTS 07700 defines the preferred work envelope arm reach in terms of maximum reach, and defines the preferred work envelope torso flexibility of a crew member to be a net 45-degree backward lean. This test served two functions: to investigate the validity of the standard discussed in NSTS 07700; and to provide recommendations to update this standard, if necessary. Author EXTRAVEHICULAR MOBILITY UNITS; ASTRONAUT LOCOMOTION; SPACECREWS; HUMAN BODY; ASTRONAUT PERFORMANCE; ANTHROPOMETRY Additions to the NASA Aeronautics and Space Database as of 08/10/2009 20090026374 NASA Johnson Space Center, Houston, TX, United States Solid State Light Evaluation in the US Lab Mockup Maida, James C.; Bowen, Charles; Wheelwright, Chuck; March 2009; In English; Original contains color illustrations Report No.(s): NASA/TM-2009-214784; S-1036; No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090026374 Solid state lights (SSLs) are being developed to potentially replace the general luminaire assemblies (GLAs) currently in service in the ISS and included in designs of modules for the ISS. The SSLs consist of arrays of light emitting diodes (LEDs), small solid state electronic devices that produce visible light in proportion to the electrical current flowing through them. Recent progressive advances in electrical power-to-light conversion efficiency in LED technology have allowed the consideration of LEDs as replacements for incandescent and fluorescent light sources in many circumstances, and their inherent advantages in ruggedness, reliability, and life expectancy make them attractive for applications in spacecraft. One potential area of application for the SSLs is in the US Laboratory Module of the ISS. This study addresses the suitability of the SSLs as replacements for the GLAs in this application. Author LIGHT EMITTING DIODES; LIGHT SOURCES; SOLID STATE DEVICES; LIGHTING EQUIPMENT; LUMINAIRES; HUMAN PERFORMANCE; HUMAN FACTORS ENGINEERING; ILLUMINATING Additions to the NASA Aeronautics and Space Database as of 08/12/2009 20090026521 ATK Space, Hampton, VA, United States Orion Landing Simulation Eight Soil Model Comparison Mark, Stephen D.; June 2009; In English; Original contains color illustrations Contract(s)/Grant(s): NNL07AA00BWBS: 644423.06.31.03.14.04.01 Report No.(s): NASA/CR-2009-215757; LF99-8510; Copyright; Avail.: CASI: A05, Hardcopy Avail Online: http://hdl.handle.net/2060/20090026521 LS-DYNA finite element simulations of a rigid Orion Crew Module (CM) were used to investigate the CM impact behavior on eight different soil models. Ten different landing conditions, characterized by the combination of CM vertical and horizontal velocity, hang angle, and roll angle were simulated on the eight different soils. The CM center of gravity accelerations, pitch angle, kinetic energy, and soil contact forces were the outputs of interest. The simulation results are presented, with comparisons of the CM behavior on the different soils. The soils analyzed in this study can be roughly categorized as soft, medium, or hard, according to the CM accelerations that occur when landing on them. The soft group is comprised of the Carson Sink Wet soil and the Kennedy Space Center (KSC) Low Density Dry Sand. The medium group includes Carson Sink Dry, the KSC High Density In-Situ Moisture Sand and High Density Flooded Sand, and Cuddeback B. The hard soils are Cuddeback A and the Gantry Unwashed Sand. The softer soils were found to produce lower peak accelerations, have more stable pitch behavior, and to be less sensitive to the landing conditions. This investigation found that the Cuddeback A soil produced the highest peak accelerations and worst stability conditions, and that the best landing performance was achieved on the KSC Low Density Dry Sand. Author LANDING SIMULATION; SOILS; CREW EXPLORATION VEHICLE; SPACECRAFT MODULES; SIMULATION; FINITE ELEMENT METHOD 20090026532 NASA Langley Research Center, Hampton, VA, United States Validity of the Aluminum Equivalent Approximation in Space Radiation Shielding Badavi, Francis F.; Adams, Daniel O.; Wilson, John W.; July 2009; In English; Original contains color illustrations Contract(s)/Grant(s): WBS 651549.02.07.01 Report No.(s): NASA/TP-2009-215779; L-19705; LF99-9078; Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090026532 The origin of the aluminum equivalent shield approximation in space radiation analysis can be traced back to its roots in the early years of the NASA space programs (Mercury, Gemini and Apollo) wherein the primary radiobiological concern was the intense sources of ionizing radiation causing short term effects which was thought to jeopardize the safety of the crew and hence the mission. Herein, it is shown that the aluminum equivalent shield approximation, although reasonably well suited for that time period and to the application for which it was developed, is of questionable usefulness to the radiobiological concerns of routine space operations of the 21 st century which will include long stays onboard the International Space Station (ISS) and perhaps the moon. This is especially true for a risk based protection system, as appears imminent for deep space exploration where the long-term effects of Galactic Cosmic Ray (GCR) exposure is of primary concern. The present analysis demonstrates that sufficiently large errors in the interior particle environment of a spacecraft result from the use of the aluminum equivalent approximation, and such approximations should be avoided in future astronaut risk estimates. In this study, the aluminum equivalent approximation is evaluated as a means for estimating the particle environment within a spacecraft structure induced by the GCR radiation field. For comparison, the two extremes of the GCR environment, the 1977 solar minimum and the 2001 solar maximum, are considered. These environments are coupled to the Langley Research Center (LaRC) deterministic ionized particle transport code High charge (Z) and Energy TRaNsport (HZETRN), which propagates the GCR spectra for elements with charges (Z) in the range I <= Z <= 28 (H -- Ni) and secondary neutrons through selected target materials. The coupling of the GCR extremes to HZETRN allows for the examination of the induced environment within the interior' of an idealized spacecraft as approximated by a spherical shell shield, and the effects of the aluminum equivalent approximation for a good polymeric shield material such as genetic polyethylene (PE). The shield thickness is represented by a 25 g/cm spherical shell. Although one could imagine the progression to greater thickness, the current range will be sufficient to evaluate the qualitative usefulness of the aluminum equivalent approximation. Upon establishing the inaccuracies of the aluminum equivalent approximation through numerical simulations of the GCR radiation field attenuation for PE and aluminum equivalent PE spherical shells, we Anther present results for a limited set of commercially available, hydrogen rich, multifunctional polymeric constituents to assess the effect of the aluminum equivalent approximation on their radiation attenuation response as compared to the generic PE. Author ALUMINUM; EXTRATERRESTRIAL RADIATION; RADIATION SHIELDING; SPACECRAFT SHIELDING; IONIZING RADIATION; RADIATION HAZARDS; ESTIMATING; GALACTIC COSMIC RAYS; POLYETHYLENES Additions to the NASA Aeronautics and Space Database as of 08/17/2009 20090026572 NASA Glenn Research Center, Cleveland, OH, United States Core Noise Diagnostics of Turbofan Engine Noise Using Correlation and Coherence Functions Miles, Jeffrey H.; June 2009; In English; 47th Aerospace Sciences Meeting, 5-8 Jan. 2009, Florida, United States; Original contains color and black and white illustrations Contract(s)/Grant(s): WBS: 561581.02.08.03.18.02 Report No.(s): NASA/TM-2009-215609; AIAA Paper 2009-1237; E-16924; No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090026572 Cross-correlation and coherence functions are used to look for periodic acoustic components in turbofan engine combustor time histories, to investigate direct and indirect combustion noise source separation based on signal propagation time delays, and to provide information on combustor acoustics. Using the cross-correlation function, time delays were identified in all cases, clearly indicating the combustor is the source of the noise. In addition, unfiltered and low-pass filtered at 400 Hz signals had a cross-correlation time delay near 90 ms, while the low-pass filtered at less than 400 Hz signals had a cross-correlation time delay longer than 90 ms. Low-pass filtering at frequencies less than 400 Hz partially removes the direct combustion noise signals. The remainder includes the indirect combustion noise signal, which travels more slowly because of the dependence on the entropy convection velocity in the combustor. Source separation of direct and indirect combustion noise is demonstrated by proper use of low-pass filters with the cross-correlation function for a range of operating conditions. The results may lead to a better idea about the acoustics in the combustor and may help develop and validate improved reduced-order physics-based methods for predicting direct and indirect combustion noise. Author ACOUSTICS; COMBUSTION CHAMBERS; ENGINE NOISE; JET AIRCRAFT NOISE; TURBOFAN ENGINES; CORRELATION 20090026575 NASA Glenn Research Center, Cleveland, OH, United States Moisture-Induced Delayed Alumina Scale Spallation on a Ni(Pt)Al Coating Smialek, James L.; June 2009; In English; Original contains color and black and white illustrations Contract(s)/Grant(s): WBS: 984754.02.07.03.16.02 Report No.(s): NASA/TM-2009-215664; E-17006; No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090026575 Delayed interfacial scale failure takes place after cooling for samples of a Ni(Pt)Al-coated CMSX4 single crystal superalloy, cycled at 1150 C for up to 2000 hr. One sample exhibited premature coating grain boundary wrinkling, alumina scale spallation to bare metal, and a final weight loss of 3.3 mg/cm2 . Spallation under ambient conditions was monitored with time after cooldown and was found to continue for 24 hr. This produced up to 0.05 mg/cm2 additional loss for each hold, accumulating 0.7 mg/cm 2 (20 percent of the total) over the course of the test. After test termination, water immersion produced an additional 0.15 mg/cm2 loss. (A duplicate sample produced much less wrinkling and time dependent spalling, maintaining a net weight gain.) The results are consistent with the general phenomena of moisture-induced delayed spallation (MIDS) of mature, distressed alumina scales formed on oxidation resistant M-Al alloys. Relative ambient humidity is discussed as the factor controlling adsorbed moisture, reaction with the substrate, and hydrogen effects on interface strength. Author ALUMINUM OXIDES; HEAT RESISTANT ALLOYS; MOISTURE; NICKEL ALUMINIDES; PLATINUM ALLOYS; COATINGS; SPALLING Additions to the NASA Aeronautics and Space Database as of 08/21/2009 20090027863 NASA Glenn Research Center, Cleveland, OH, United States Advanced Fuel Cell System Thermal Management for NASA Exploration Missions Burke, Kenneth A.; June 2009; In English; Original contains color and black and white illustrations Contract(s)/Grant(s): WBS 038957.04.06.01 Report No.(s): NASA/TM-2009-215426; E-16595; No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090027863 The NASA Glenn Research Center is developing advanced passive thermal management technology to reduce the mass and improve the reliability of space fuel cell systems for the NASA exploration program. An analysis of a state-of-the-art fuel cell cooling systems was done to benchmark the portion of a fuel cell system s mass that is dedicated to thermal management. Additional analysis was done to determine the key performance targets of the advanced passive thermal management technology that would substantially reduce fuel cell system mass. Author TEMPERATURE CONTROL; FUEL CELLS; AEROSPACE SYSTEMS; COOLING SYSTEMS 20090027866 NASA Glenn Research Center, Cleveland, OH, United States Method for Measuring Thermal Conductivity of Small Samples Having Very Low Thermal Conductivity Miller, Robert A.; Kuczmarski, Maria a.; June 2009; In English; Original contains black and white illustrations Contract(s)/Grant(s): WBS 984754.02.07.03.16.02 Report No.(s): NASA/TM-2009-215460; E-16681; No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090027866 This paper describes the development of a hot plate method capable of using air as a standard reference material for the steady-state measurement of the thermal conductivity of very small test samples having thermal conductivity on the order of air. As with other approaches, care is taken to ensure that the heat flow through the test sample is essentially one-dimensional. However, unlike other approaches, no attempt is made to use heated guards to block the flow of heat from the hot plate to the surroundings. It is argued that since large correction factors must be applied to account for guard imperfections when sample dimensions are small, it may be preferable to simply measure and correct for the heat that flows from the heater disc to directions other than into the sample. Experimental measurements taken in a prototype apparatus, combined with extensive computational modeling of the heat transfer in the apparatus, show that sufficiently accurate measurements can be obtained to allow determination of the thermal conductivity of low thermal conductivity materials. Suggestions are made for further improvements in the method based on results from regression analyses of the generated data. Author THERMAL CONDUCTIVITY; AEROGELS; COMPUTATIONAL FLUID DYNAMICS; HEAT TRANSFER; REGRESSION ANALYSIS 20090027867 Case Western Reserve Univ., Cleveland, OH, United States Long Term Measurement of the Vapor Pressure of Gold in the Au-C System Copland, Evan H.; July 2009; In English; Original contains black and white illustrations Contract(s)/Grant(s): NNC07BA13BWBS 599489.02.07.03.02.04.01 Report No.(s): NASA/CR-2009-215498; E-16808; Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090027867 Incorporating the {Au(s,l) + graphite} reference in component activity measurements made with the multiple effusion-cell vapor source mass spectrometry (multicell KEMS) technique provides a fixed temperature defining ITS-90 (T(sub mp)(Au) = 1337.33K) and a systematic method to check accuracy. Over a 2 year period delta H sub(298)Au was determined by the 2nd and 3rd law methods in 25 separate experiments and were in the ranges 362.2 plus or minus 3.3 kJmol(sup -1) and 367.8 plus or minus 1.1 kJmol(sup -1), respectively. This 5 kJmol-1 discrepancy is transferred directly to the measured activities. This is unacceptable and the source of this discrepancy needs to be understood and corrected. Accepting the 2nd law value increases p(Au) by about 50 percent, brings the 2nd and 3rd law values into agreement and removes the T dependence in the 3rd law values. While compelling, there is no way to independently determine instrument sensitivities, S(sub Au), with T in a single experiment with KEMS. This lack of capability is stopping a deeper understanding of this problem. In addition, the Au-C phase diagram suggests a eutectic invariant reaction: L-Au(4.7at%C) = FCC-Au(0.08at%C) + C(graphite) at T(sub e) approximately 1323K. This high C concentration in Au(l) must reduce p(Au) in equilibrium with {Au(s,l) + graphite} and raises some critical questions about the Gibbs free energy functions of Au(s,l) and the Au fixed point (T(sub mp)(Au) = 1337.33K) which is always measured in graphite. Author EUTECTICS; GOLD; VAPOR PRESSURE; KNUDSEN FLOW; MASS SPECTROSCOPY 20090027870 NASA Glenn Research Center, Cleveland, OH, United States A Kalman Approach to Lunar Surface Navigation using Radiometric and Inertial Measurements Chelmins, David T.; Welch, Bryan W.; Sands, O. Scott; Nguyen, Binh V.; June 2009; In English; Original contains color and black and white illustrations Contract(s)/Grant(s): WBS 903184.04.03.02.02 Report No.(s): NASA/TM-2009-215593; E-16883; No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090027870 Future lunar missions supporting the NASA Vision for Space Exploration will rely on a surface navigation system to determine astronaut position, guide exploration, and return safely to the lunar habitat. In this report, we investigate one potential architecture for surface navigation, using an extended Kalman filter to integrate radiometric and inertial measurements. We present a possible infrastructure to support this technique, and we examine an approach to simulating navigational accuracy based on several different system configurations. The results show that position error can be reduced to 1 m after 5 min of processing, given two satellites, one surface communication terminal, and knowledge of the starting position to within 100 m. Author LUNAR SURFACE; SURFACE NAVIGATION; SPACE EXPLORATION; POSITION ERRORS; SYSTEMS ENGINEERING; TELECOMMUNICATION 20090027872 NASA Glenn Research Center, Cleveland, OH, United States Improvements in Modeling 90 degree Bleed Holes for Supersonic Inlets Slater, John W.; June 2009; In English; 47th Aerospace Sciences Meeting and Exhibit, 5-8 Jan. 2009, Orlando, FL, United States; Original contains color illustrations Contract(s)/Grant(s): WBS 984754.02.07.03.13.02 Report No.(s): NASA/TM-2009-215597; AIAA-2009-0710; E-16888; No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090027872 The modeling of porous bleed regions as boundary conditions in computational fluid dynamics (CFD) simulations of supersonic inlet flows has been improved through a scaling of sonic flow coefficient data for 90deg bleed holes. The scaling removed the Mach number as a factor in computing the sonic flow coefficient and allowed the data to be fitted with a quadratic equation, with the only factor being the ratio of the plenum static pressure to the surface static pressure. The implementation of the bleed model into the Wind-US CFD flow solver was simplified by no longer requiring the evaluation of the flow properties at the boundary-layer edge. The quadratic equation can be extrapolated to allow the modeling of small amounts of blowing, which can exist when recirculation of the bleed flow occurs within the bleed region. The improved accuracy of the bleed model was demonstrated through CFD simulations of bleed regions on a flat plate in supersonic flow with and without an impinging oblique shock. The bleed model demonstrated good agreement with experimental data and three-dimensional CFD simulations of bleed holes. Author SUPERSONIC FLOW; SUPERSONIC INLETS; INLET FLOW; COMPUTATIONAL FLUID DYNAMICS; FLOW CHARACTERISTICS; THREE DIMENSIONAL MODELS; STATIC PRESSURE 20090027874 NASA Glenn Research Center, Cleveland, OH, United States Wind-US Code Physical Modeling Improvements to Complement Hypersonic Testing and Evaluation Georgiadis, Nicholas J.; Yoder, Dennis A.; Towne, Charles S.; Engblom, William A.; Bhagwandin, Vishal A.; Power, Greg D.; Lankford, Dennis W.; Nelson, Christopher C.; July 2009; In English; 47th Aerospace Sciences Meeting, 5-8 Jan. 2009, Orlando, Fl, United States; Original contains color illustrations Contract(s)/Grant(s): WBS 5999489.02.07.03.03.02.01 Report No.(s): NASA/TM-2009-215615; AIAA-2009-193; E-16931; Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090027874 This report gives an overview of physical modeling enhancements to the Wind-US flow solver which were made to improve the capabilities for simulation of hypersonic flows and the reliability of computations to complement hypersonic testing. The improvements include advanced turbulence models, a bypass transition model, a conjugate (or closely coupled to vehicle structure) conduction-convection heat transfer capability, and an upgraded high-speed combustion solver. A Mach 5 shock-wave boundary layer interaction problem is used to investigate the benefits of k- s and k-w based explicit algebraic stress turbulence models relative to linear two-equation models. The bypass transition model is validated using data from experiments for incompressible boundary layers and a Mach 7.9 cone flow. The conjugate heat transfer method is validated for a test case involving reacting H2-O2 rocket exhaust over cooled calorimeter panels. A dual-mode scramjet configuration is investigated using both a simplified 1-step kinetics mechanism and an 8-step mechanism. Additionally, variations in the turbulent Prandtl and Schmidt numbers are considered for this scramjet configuration. Author HYPERSONIC FLOW; SUPERSONIC COMBUSTION RAMJET ENGINES; TURBULENCE; CONDUCTIVE HEAT TRANSFER; CONVECTIVE HEAT TRANSFER; BOUNDARY LAYERS 20090027875 NASA Glenn Research Center, Cleveland, OH, United States Large-Eddy Simulation: Current Capabilities, Recommended Practices, and Future Research Georgiadis, Nicholas J.; Rizzetta, Donald P.; Fureby, Christer; July 2009; In English; 47th Aerospace Sciences Meeting, 5-8 Jan. 2009, Orlando, FL, United States Contract(s)/Grant(s): WBS 561581.02.08.03.18.03 Report No.(s): NASA/TM-2009-215616; AIAA-2009-948; E-16932; Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090027875 This paper presents the results of an activity by the Large Eddy Simulation (LES) Working Group of the AIAA Fluid Dynamics Technical Committee to (1) address the current capabilities of LES, (2) outline recommended practices and key considerations for using LES, and (3) identify future research needs to advance the capabilities and reliability of LES for analysis of turbulent flows. To address the current capabilities and future needs, a survey comprised of eleven questions was posed to LES Working Group members to assemble a broad range of perspectives on important topics related to LES. The responses to these survey questions are summarized with the intent not to be a comprehensive dictate on LES, but rather the perspective of one group on some important issues. A list of recommended practices is also provided, which does not treat all aspects of a LES, but provides guidance on some of the key areas that should be considered. Author LARGE EDDY SIMULATION; TURBULENT FLOW; FLUID DYNAMICS; VORTICES; RELIABILITY ANALYSIS; GROUP DYNAMICS 20090027886 NASA Goddard Space Flight Center, Greenbelt, MD, United States Further Studies on the Physical and Biogeochemical Causes for Large Interannual Changes in the Patagonian Shelf Spring-Summer Phytoplankton Bloom Biomass Signorini, Sergio R.; Garcia, Virginia M.T.; Piola, Alberto R.; Evangelista, Heitor; McClain, Charles R.; Garcia, Carlos A.E.; Mata, Mauricio M.; February 2009; In English; Original contains color and black and white illustrations Contract(s)/Grant(s): 50370/02-1; 557305/05-5; CRN2076; GEO-04523 Report No.(s): NASA/TM-2009-214176; 200900836; Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090027886 A very strong and persistent phytoplankton bloom was observed by ocean color satellites during September - December 2003 along the northern Patagonian shelf. The 2003 bloom had the highest extent and chlorophyll a (Chl-a) concentrations of the entire Sea-viewing Wide Field-of-view Sensor (SeaWiFS) period (1997 to present). SeaWiFS-derived Chl-a exceeded 20 mg/cu m in November at the bloom center. The bloom was most extensive in December when it spanned more than 300 km across the shelf and nearly 900 km north-south (35degS to 43degS). The northward reach and the deep penetration on the shelf of the 2003 bloom were quite anomalous when compared with other years, which showed the bloom more confined to the Patagonian shelf break (PSB). The PSB bloom is a conspicuous austral spring-summer feature detected by ocean color satellites and its timing can be explained using the Sverdrup critical depth theory. Based on high-resolution numerical simulations, in situ and remote sensing data, we provide some suggestions for the probable mechanisms responsible for that large interannual change of biomass as seen by ocean color satellites. Potential sources of macro and micro (e.g., Fe) nutrients that sustain the high phytoplankton productivity of the Patagonian shelf waters are identified, and the most likely physical processes that maintain the nutrient balance in the region are discussed. Author SEA-VIEWING WIDE FIELD-OF-VIEW SENSOR; BIOGEOCHEMISTRY; PHYTOPLANKTON; CONTINENTAL SHELVES; CHLOROPHYLLS; WATER COLOR; REMOTE SENSING; BIOMASS 20090027888 NASA Glenn Research Center, Cleveland, OH, United States A Microfabricated Segmented-Involute-Foil Regenerator for Enhancing Reliability and Performance of Stirling Engines. Phase III Final Report for the Radioisotope Power Conversion Technology NRA Ibrahim, Mounir B.; Gedeon, David; Wood, Gary; McLean, Jeffrey; June 2009; In English; Original contains color and black and white illustrations Contract(s)/Grant(s): NAS3-03124WBS 138494.04.01.01 Report No.(s): NASA/CR-2009-215516; E-16681; Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090027888 Under Phase III of NASA Research Announcement contract NAS3-03124, a prototype nickel segmented-involute-foil regenerator was microfabricated and tested in a Sunpower Frequency-Test-Bed (FTB) Stirling convertor. The team for this effort consisted of Cleveland State University, Gedeon Associates, Sunpower Inc. and International Mezzo Technologies. Testing in the FTB convertor produced about the same efficiency as testing with the original random-fiber regenerator. But the high thermal conductivity of the prototype nickel regenerator was responsible for a significant performance degradation. An efficiency improvement (by a 1.04 factor, according to computer predictions) could have been achieved if the regenerator was made from a low-conductivity material. Also, the FTB convertor was not reoptimized to take full advantage of the microfabricated regenerator s low flow resistance; thus, the efficiency would likely have been even higher had the FTB been completely reoptimized. This report discusses the regenerator microfabrication process, testing of the regenerator in the Stirling FTB convertor, and the supporting analysis. Results of the pre-test computational fluid dynamics (CFD) modeling of the effects of the regenerator-test-configuration diffusers (located at each end of the regenerator) are included. The report also includes recommendations for further development of involute-foil regenerators from a higher-temperature material than nickel. Author STIRLING CYCLE; STIRLING ENGINES; REGENERATORS; RELIABILITY; COMPUTATIONAL FLUID DYNAMICS Additions to the NASA Aeronautics and Space Database as of 08/24/2009 20090028003 NASA Goddard Space Flight Center, Greenbelt, MD, United States Modeling the Dynamics and Export of Dissolved Organic Matter in the Northeastern U.S. Continental Shelf Druon, J.N.; Mannino, A.; Signorini, Sergio R.; McClain, Charles R.; Friedrichs, M.; Wilkin, J.; Fennel, K.; February 2009; In English; Original contains color illustrations Report No.(s): NASA/TM-2009-214177; 200900837; Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090028003 Continental shelves are believed to play a major role in carbon cycling due to their high productivity. Particulate organic carbon (POC) burial has been included in models as a carbon sink, but we show here that seasonally produced dissolved organic carbon (DOC) on the shelf can be exported to the open ocean by horizontal transport at similar rates (1-2 mol C/sq m/yr) in the southern U.S. Mid-Atlantic Bight (MAB). The dissolved organic matter (DOM) model imbedded in a coupled circulation-biogeochemical model reveals a double dynamics: the progressive release of dissolved organic nitrogen (DON) in the upper layer during summer increases the regenerated primary production by 30 to 300%, which, in turns ; enhances the DOC production mainly from phytoplankton exudation in the upper layer and solubilization of particulate organic matter (POM) deeper in the water column. This analysis suggests that DOM is a key element for better representing the ecosystem functioning and organic fluxes in models because DOM (1) is a major organic pool directly related to primary production, (2) decouples partially the carbon and nitrogen cycles (through carbon excess uptake, POM solubilization and DOM mineralization) and (3) is intimately linked to the residence time of water masses for its distribution and export. Author BIOGEOCHEMISTRY; CONTINENTAL SHELVES; DISSOLVED ORGANIC MATTER; ECOSYSTEMS; PHYTOPLANKTON; PARTICULATES; ORGANIC MATERIALS; CARBON CYCLE 20090028005 NASA Goddard Space Flight Center, Greenbelt, MD, United States Five Millennium Catalog of Solar Eclipses: -1999 to +3000 (2000 BCE to 3000 CE)-Revised Espenak, Fred; Meeus, Jean; January 2009; In English; Original contains black and white illustrations Report No.(s): NASA/TP-2009-214174; 200900365; No Copyright; Avail.: CASI: A12, Hardcopy Avail Online: http://hdl.handle.net/2060/20090028005 This catalog is a supplement to the "Five Millennium Canon of Lunar Eclipses. "It includes additional information for each eclipse that could not be included in the original publication because of size limits. The data tabulated for each eclipse include the catalog number, canon plate number, calendar date, Terrestrial Dynamical Time of greatest eclipse, (Delta)T, lunation number, Saros number, eclipse type, Quincena Solar Eclipse parameter, gamma, penumbral and umbral eclipse magnitudes, durations of penumbral, partial and total eclipse phases, and geographic coordinates of greatest eclipse(latitude and longitude). The Canon and the Catalog both use the same solar and lunar ephemerides as well as the same values of (Delta)T. This 1-to-1 correspondence between them will enhance the value of each. The researcher may now search, evaluate, and compare eclipses graphically (Canon) or textually (Catalog). Author LUNAR ECLIPSES; CATALOGS (PUBLICATIONS); EPHEMERIDES; COORDINATES; SOLAR ECLIPSES; PENUMBRAS 20090028006 NASA Goddard Space Flight Center, Greenbelt, MD, United States Five Millennium Catalog of Lunar Eclipses: -1999 to +3000 (2000 BCE to 3000 CE) Espenak, Fred; Meeus, Jean; January 2009; In English; Original contains black and white illustrations Report No.(s): NASA/TP-2009-214173; 200900365; Copyright; Avail.: CASI: A13, Hardcopy Avail Online: http://hdl.handle.net/2060/20090028006 This catalog is a supplement to the "FiveMillenniumCanonofLunarEclipses." It includes additional information for each eclipse that could not be included in the original publication because of size limits. The data tabulated for each eclipse include the catalog number, canon plate number, calendar date, Terrestrial Dynamical Time of greatest eclipse, (Delta)T, lunation number, Saros number, eclipse type, Quincena Solar Eclipse parameter, gamma, penumbral and umbral eclipse magnitudes, durations of penumbral, partial and total eclipse phases, and geographic coordinates of greatest eclipse (latitude and longitude). The Canon and the Catalog both use the same solar and lunar ephemerides as well as the same values of (Delta)T. This 1-to-1 correspondence between them will enhance the value of each. The researcher may now search, evaluate, and compare eclipses graphically (Canon) or textually (Catalog). Author CATALOGS (PUBLICATIONS); EPHEMERIDES; SOLAR ECLIPSES; COORDINATES; CYCLES 20090028008 NASA, Washington, DC, United States Rockets and People Volume 3 Hot Days of the Cold War Chertok, Yevseyevich, Boris; Siddiqi, Asif, Editor; May 2009; In English; Original contains black and white illustrations Report No.(s): NASA/SP-2009-4110/VOL3; No Copyright; Avail.: CASI: EA5, Hardcopy Avail Online: http://hdl.handle.net/2060/20090028008 This, the third volume of Boris Chertok's four-volume memoirs, continues the narrative arc which he began in the first volume. If the first volume covered his apprenticeship as an engineer and the second, the birth of the Soviet postwar missile program, in the third volume, we finally have what might be called the full bloom of the Soviet space program. Here, Chertok describes his impressions of the apex of Soviet achievements in space exploration, from the halcyon days of the launch of Yuri Gagarin into orbit in 1961 to the first piloted Soyuz mission in 1967. Chertok devotes a significant portion of the volume to the early years of Soviet human spaceflight. These include a chapter on the Vostok and Voskhod programs, which left an indelible mark on early years of the space race, a lengthy meditation on the origins and early missions of the Soyuz program, and a gripping account of one of the most tragic episodes of the Soviet space program: the flight and death of cosmonaut Vladimir Komarov during the very first piloted Soyuz flight in 1967. Additional chapters cover robotic programs such as the Molniya communications satellite system, the Zenit spy satellite program, and the Luna series of probes that culminated in the world s first survivable landing of a probe on the surface of the Moon. Chertok also devotes several chapters to the development of early generations of Soviet intercontinental ballistic missiles (ICBMs) and missile defense systems; his narrative here skillfully combines technical, political, personal, and strategic concerns, highlighting how these considerations were often difficult to separate into neat categories. In particular, we learn about the Soviet drive to develop a workable solid propellant ICBM and the subsequent arguments over the development of second general ICBMs in the late 1960s, a fight so acrimonious that contemporaries called it the little civil war. Chertok s chapter on the Cuban Missile Crisis provides a radically unique perspective on the crisis, from the point of view of those who would have been responsible for unleashing nuclear Armageddon in 1962 had Kennedy and Khrushchev not been able to agree on a stalemate. Two further chapters cover the untimely deaths of the most important luminaries of the era: Sergey Korolev and Yuriy Gagarin. Each of these chapters is a tour de force, as Chertok uses a vast array of published accounts to enrich his own personal recollections of the episodes. Finally, historians of Soviet science will find much of interest in the concluding chapter focused on the relationship between the space program and the Soviet Academy of Sciences. This chapter represents one of the most insightful descriptions of the formation of a Soviet aerospace elite during the post-World War II era. Derived from text SPACE EXPLORATION; LAUNCH VEHICLES; ROCKET VEHICLES; COMMUNICATION SATELLITES; MANNED SPACE FLIGHT; RUSSIAN SPACE PROGRAM Additions to the NASA Aeronautics and Space Database as of 08/26/2009 20090028622 NASA Langley Research Center, Hampton, VA, United States Head Worn Display System for Equivalent Visual Operations Cupero, Frank; Valimont, Brian; Wise, John; Best. Carl; DeMers, Bob; July 2009; In English; Original contains color and black and white illustrations Contract(s)/Grant(s): NNL07AE08T; NNL06AA05BWBS 609866.02.07.07.02 Report No.(s): NASA/CR-2009-215781; LF99-8901; Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090028622 Head-Worn Displays or so-called, near-to-eye displays have potentially significant advantages in terms of cost, overcoming cockpit space constraints, and for the display of spatially-integrated information. However, many technical issues need to be overcome before these technologies can be successfully introduced into commercial aircraft cockpits. The results of three activities are reported. First, the near-to-eye display design, technological, and human factors issues are described and a literature review is presented. Second, the results of a fixed-base piloted simulation, investigating the impact of near to eye displays on both operational and visual performance is reported. Straight-in approaches were flown in simulated visual and instrument conditions while using either a biocular or a monocular display placed on either the dominant or non-dominant eye. The pilot's flight performance, visual acuity, and ability to detect unsafe conditions on the runway were tested. The data generally supports a monocular design with minimal impact due to eye dominance. Finally, a method for head tracker system latency measurement is developed and used to compare two different devices. Author DISPLAY DEVICES; HUMAN FACTORS ENGINEERING; VISUAL ACUITY; FLIGHT CHARACTERISTICS; EYE (ANATOMY) 20090028625 NASA Glenn Research Center, Cleveland, OH, United States An Excess Broadband Noise Observed with Overexpanded Jets Zaman, K.B.M.Q.; Bridges, James E.; Brown, C.A.; June 2009; In English; 47th Aerospace Sciences Meeting and Exhibit, 5-8 Jan. 2009, Florida, United States; Original contains color illustrations Contract(s)/Grant(s): WBS 984754.02.07.03.17.04 Report No.(s): NASA/TM-2009-215603; AIAA Paper 2009-0289; E-16893; No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090028625 Results of an experiment on the characteristics of an excess noise occurring with convergent-divergent (C-D) nozzles in the overexpanded regime are presented in this paper. Data are obtained with five C-D nozzles and a convergent nozzle, all having the same exit diameter. The results clearly establish that the C-D nozzles are noisier in the low Mach number range of the overexpanded regime. This is evidenced from the directivity patterns as well as overall radiated sound power calculations. The excess noise is broadband in nature and is found to be more pronounced with nozzles having a larger half-angle of the divergent section. It appears to occur when a shock resides within the divergent section and results from random unsteady motion of the shock. Author CONVERGENT-DIVERGENT NOZZLES; NOISE (SOUND); SOUND PRESSURE; JET FLOW; NOZZLE FLOW; AERODYNAMIC NOISE 20090028626 NASA Langley Research Center, Hampton, VA, United States NASA Standard for Models and Simulations (M and S): Development Process and Rationale Zang, Thomas A.; Blattnig, Steve R.; Green, Lawrence L.; Hemsch, Michael J.; Luckring, James M.; Morison, Joseph H.; Tripathi, Ram K.; July 2009; In English; Original contains color and black and white illustrations Contract(s)/Grant(s): WU 869021.01.07.01.01 Report No.(s): NASA/TM-2009-215775; NESC-RP-08-118/06-005-E; L-19719; LF99-9147; No Copyright; Avail.: CASI: A06, Hardcopy Avail Online: http://hdl.handle.net/2060/20090028626 After the Columbia Accident Investigation Board (CAIB) report. the NASA Administrator at that time chartered an executive team (known as the Diaz Team) to identify the CAIB report elements with Agency-wide applicability, and to develop corrective measures to address each element. This report documents the chronological development and release of an Agency-wide Standard for Models and Simulations (M&S) (NASA Standard 7009) in response to Action #4 from the report, "A Renewed Commitment to Excellence: An Assessment of the NASA Agency-wide Applicability of the Columbia Accident Investigation Board Report, January 30, 2004". Author ACCIDENT INVESTIGATION; COLUMBIA (ORBITER) Additions to the NASA Aeronautics and Space Database as of 09/03/2009 20090029908 NASA Glenn Research Center, Cleveland, OH, United States Radioisotope Electric Propulsion Centaur Orbiter Spacecraft Design Overview Oleson, Steve; McGuire, Melissa; Sarver-Verhey, Tim; Juergens, Jeff; Parkey, Tom; Dankanich, John; Fiehler, Doug; Gyekenyesi, John; Hemminger, Joseph; Gilland, Jim; Colozza, Tony; Packard, Tom; Nguyen, Thahn; Schmitz, Paul; Ostdiek, Paul; Gold, Rob; Lisse, Carey; Hibbits, Karl; July 2009; In English; 44th Joint Propulsion Conference and Exhibit, 21-23 Jul. 2008, Hartford, CT, United States; Original contains color illustrations Contract(s)/Grant(s): WBS 346620.02.01.02.03.01 Report No.(s): NASA/TM-2009-215488; AIAA Paper 2008-5179; E-16578-1; Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090029908 Radioisotope electric propulsion (REP) has been shown in past studies to enable missions to outerplanetary bodies including the orbiting of Centaur asteroids. Key to the feasibility for REP missions are long life, low power electric propulsion (EP) devices, low mass radioisotope power systems (RPS) and light spacecraft (S/C) components. In order to determine what are the key parameters for EP devices to perform these REP missions a design study was completed to design an REP S/C to orbit a Centaur in a New Frontiers cost cap. The design shows that an orbiter using several long lived (approximately 200 kg Xenon throughput), low power (approximately 700 W) Hall thrusters teamed with six (150 W each) Advanced Stirling Radioisotope Generators (ASRG) can deliver 60 kg of science instruments to a Centaur in 10 yr within the New Frontiers cost cap. Optimal specific impulses for the Hall thrusters were found to be around 2000 sec with thruster efficiencies over 40%. Not only can the REP S/C enable orbiting a Centaur (when compared to an all chemical mission only capable of flybys) but the additional power from the REP system can be reused to enhance science and simplify communications. Author RADIOISOTOPE HEAT SOURCES; CENTAUR LAUNCH VEHICLE; ELECTRIC PROPULSION; SPACECRAFT DESIGN 20090029909 NASA Glenn Research Center, Cleveland, OH, United States Determination of Chemical Kinetic Rate Constants of a Model for Carbothermal Processing of Lunar Regolith Simulant Using Methane Balasubramaniam, R; Gokoglu, S.; Hegde, U.; July 2009; In English; 47th AIAA Aerospace Sciences Meeting, 5-8 Jan. 2009, Orlando, FL, United States; Original contains color and black and white illustrations Contract(s)/Grant(s): WBS 387498.04.01.05.01.03 Report No.(s): NASA/TM-2009-215617; AIAA-2009-1390; E-16933; No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090029909 We have previously developed a chemical conversion model of the carbothermal processing of lunar regolith using methane to predict the rate of production of carbon monoxide. In this carbothermal process, gaseous methane is pyrolyzed as it flows over the hot surface of a molten zone of lunar regolith and is converted to carbon and hydrogen. Hydrogen is carried away by the exiting stream of gases and carbon is deposited on the melt surface. The deposited carbon mixes with the melt and reacts with the metal oxides in it to produce carbon monoxide that bubbles out of the melt. In our model, we assume that the flux of carbon deposited is equal to the product of the surface reaction rate constant gamma and the concentration of methane adjacent to the melt surface. Similarly, the rate of consumption of carbon per unit volume in the melt is equal to the product of the melt reaction rate constant k and the concentrations of carbon and metal oxide in the melt. In this paper, we describe our effort to determine gamma and k by comparison of the predictions from our model with test data obtained by ORBITEC (Orbital Technologies Corporation). The concentration of methane adjacent to the melt surface is a necessary input to the model. It is inferred from the test data by a mass balance of methane, adopting the usual assumptions of the continuously-stirred-tank-reactor model, whereby the average concentration of a given gaseous species equals its exit concentration. The reaction rates gamma and k have been determined by a non-linear least-squares fit to the test data for the production of carbon monoxide and the fraction of the incoming methane that is converted. The comparison of test data with our model predictions using the determined chemical kinetic rate constants provides a consistent interpretation of the process over the full range of temperatures, pressures, and methane flow rates used in the tests, thereby increasing our confidence to use the model for scale-up purposes. Author LUNAR ROCKS; METHANE; REACTION KINETICS; REGOLITH; MATHEMATICAL MODELS 20090029910 NASA Glenn Research Center, Cleveland, OH, United States Development of a Reactor for the Extraction of Oxygen and Volatiles From Lunar Regolith Kleinhenz, Julie; Yuan, Zengguang; Sacksteder, Kurt; Caruso, John; July 2009; In English; 47th AIAA Aerospace Sciences Meeting, 5-8 Jan. 2009, Orlando, FL, United States; Original contains color and black and white illustrations Contract(s)/Grant(s): WBS 387498.04.01.03.01.03 Report No.(s): NASA/TM-2009-215621; AIAA-2009-1203; E-16937; Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090029910 The RESOLVE (Regolith and Environment Science, Oxygen and Lunar Volatiles Extraction) Project, aims to extract and quantify useful resources from lunar soil. The reactor developed for RESOLVE is a dual purpose system, designed to evolve both water, at 150 C and up to 80 psig, and oxygen, using hydrogen reduction at 900 C. A variety of laboratory tests were performed to verify its operation and to explore the properties of the analog site soil. The results were also applied to modeling efforts which are being used to estimate the apparent thermal properties of the soil. The experimental and numerical results, along with the analog site tests, will be used to evolve and optimize future reactor designs. Author EXTRACTION; LUNAR ROCKS; OXYGEN; REACTOR DESIGN; REGOLITH; VOLATILITY 20090029911 NASA Glenn Research Center, Cleveland, OH, United States Carbothermal Processing of Lunar Regolith Using Methane Balasubramaniam, R.; Hegde, U.; Gokoglu, S.; July 2009; In English; Space Technology and Applications International Forum (STAIF-2008), 10-14 Feb. 2008, Albuquerque, NM, United States; Original contains black and white illustrations Contract(s)/Grant(s): WBS 387498.04.01.04.03 Report No.(s): NASA/TM-2009-215622; E-16616-1; No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090029911 The processing of lunar regolith for the production of oxygen is a key component of the In-Situ Resource Utilization plans currently being developed by NASA. Among various candidate processes, the modeling of oxygen production by hydrogen reduction, molten salt electrolysis, and carbothermal processing are presently being pursued. In the carbothermal process, a portion of the surface of the regolith in a container is heated by exposure to a heat source such as a laser beam or a concentrated solar heat flux, so that a small zone of molten regolith is established. The molten zone is surrounded by solid regolith particles that are poor conductors of heat. A continuous flow of methane is maintained over the molten regolith zone. Our model is based on a mechanism where methane pyrolyzes when it comes in contact with the surface of the hot molten regolith to form solid carbon and hydrogen gas. Carbon is deposited on the surface of the melt, and hydrogen is released into the gas stream above the melt surface. We assume that the deposited carbon mixes in the molten regolith and reacts with metal oxides in a reduction reaction by which gaseous carbon monoxide is liberated. Carbon monoxide bubbles through the melt and is released into the gas stream. Oxygen is produced subsequently by (catalytically) processing the carbon monoxide downstream. In this paper, we discuss the development of a chemical conversion model of the carbothermal process to predict the rate of production of carbon monoxide. Author LUNAR ROCKS; METHANE; OXYGEN PRODUCTION; REGOLITH; IN SITU RESOURCE UTILIZATION; HEAT TREATMENT; PYROLYSIS 20090029912 NASA Glenn Research Center, Cleveland, OH, United States Analytic Confusion Matrix Bounds for Fault Detection and Isolation Using a Sum-of-Squared- Residuals Approach Simon, Dan; Simon, Donald L.; July 2009; In English; Original contains color and black and white illustrations Contract(s)/Grant(s): WBS 645846.02.07.03.12 Report No.(s): NASA/TM-2009-215655; E-16998; Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090029912 Given a system which can fail in 1 or n different ways, a fault detection and isolation (FDI) algorithm uses sensor data in order to determine to have occurred. The effectiveness of an FDI algorithm can be quantified by a confusion matrix, which probability that each fault is isolated given that each fault has occurred. Confusion matrices are often generated with simulation this paper we perform FDI using sums of squares of sensor residuals (SSRs). We assume that the Gaussian, which gives the SSRs a chi-squared distribution. We then generate analytic lower and upper bounds on the generation of optimal sensor sets without numerical simulations. The confusion matrix simulated aircraft engine data. Author COMPLEX SYSTEMS; FAILURE; FAULT DETECTION; ALGORITHMS; FAILURE ANALYSIS; SYSTEMS HEALTH MONITORING; STATISTICAL ANALYSIS 20090029913 NASA Glenn Research Center, Cleveland, OH, United States Synthesis and Stability of Iron Nanoparticles for Lunar Environment Studies Hung, Ching-cheh; McNatt, Jeremiah; July 2009; In English; Original contains color and black and white illustrations Contract(s)/Grant(s): WBS 936374.03.01.03 Report No.(s): NASA/TM-2009-215659; E-17000; No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090029913 Simulant of lunar dust is needed when researching the lunar environment. However, unlike the true lunar dust, today s simulants do not contain nanophase iron. Two different processes have been developed to fabricate nanophase iron to be used as part of the lunar dust simulant: (1) Sequentially treating a mixture of ferric chloride, fluorinated carbon, and soda lime glass beads at about 300 C in nitrogen, at room temperature in air, and then at 1050 C in nitrogen. The product includes glass beads that are grey in color, can be attracted by a magnet, and contain alpha-iron nanoparticles (which seem to slowly lose their lattice structure in ambient air during a period of 12 months). This product may have some similarity to the lunar glassy regolith that contains Fe(sup 0). (2) Heating a mixture of carbon black and a lunar simulant (a mixed metal oxide that includes iron oxide) at 1050 C in nitrogen. This process simulates lunar dust reaction to the carbon in a micrometeorite at the time of impact. The product contains a chemically modified simulant that can be attracted by a magnet and has a surface layer whose iron concentration increased during the reaction. The iron was found to be alpha-iron and Fe3O4 nanoparticles, which appear to grow after the fabrication process, but stabilizes after 6 months of ambient air storage. Author FABRICATION; IRON; LUNAR DUST; LUNAR ENVIRONMENT; NANOPARTICLES; REGOLITH; EXTRATERRESTRIAL ENVIRONMENTS; ANALOGIES 20090029914 NASA Glenn Research Center, Cleveland, OH, United States Simplified Approach to Predicting Rough Surface Transition Boyle, Robert J.; Stripf, Matthias; July 2009; In English; Gas Turbine Technical Congress and Exposition (Turbo Expo 2008), 9-13 Jun. 2008, Berlin, Germany; Original contains color and black and white illustrations Contract(s)/Grant(s): WBS 561581.02.08.03.21.02 Report No.(s): NASA/TM-2009-215662; GT2008-51543; E-17004; Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090029914 Turbine vane heat transfer predictions are given for and rough vanes where the experimental data moving forward on the vane as the surface physical height increases. Consistent with transfer, the transition moves forward roughness height as the Reynolds number increases. experimental roughness Reynolds approach in a statistical obtained from engine environments. equivalent regular geometry. experimental data. developed, and comparisons over the entire Additional comparisons transfer data, regular as well analysis, heat transfer second stage vane of a hypothetical engine conditions. Author HEAT TRANSFER; SURFACE ROUGHNESS; TURBINE BLADES; BOUNDARY LAYER TRANSITION; ROTOR BLADES (TURBOMACHINERY); TURBINES; TURBULENT FLOW Additions to the NASA Aeronautics and Space Database as of 09/07/2009 20090029956 NASA Langley Research Center, Hampton, VA, United States Simple Formulas and Results for Buckling-Resistance and Stiffness Design of Compression-Loaded Laminated-Composite Cylinders Nemeth, Michael P.; Mikulas, Martin M., Jr.; August 2009; In English; Original contains color and black and white illustrations Contract(s)/Grant(s): WBS 136905.02.04.04.16.06 Report No.(s): NASA/TP-2009-215778; LF99-8638; Copyright; Avail.: CASI: A04, Hardcopy Avail Online: http://hdl.handle.net/2060/20090029956 Simple formulas for the buckling stress of homogeneous, specially orthotropic, laminated-composite cylinders are presented. The formulas are obtained by using nondimensional parameters and equations that facilitate general validation, and are validated against the exact solution for a wide range of cylinder geometries and laminate constructions. Results are presented that establish the ranges of the nondimensional parameters and coefficients used. General results, given in terms of the nondimensional parameters, are presented that encompass a wide range of geometries and laminate constructions. These general results also illustrate a wide spectrum of behavioral trends. Design-oriented results are also presented that provide a simple, clear indication of laminate composition on critical stress, critical strain, and axial stiffness. An example is provided to demonstrate the application of these results to thin-walled column designs. Author BUCKLING; CRITICAL LOADING; LAMINATES; THIN WALLS; STRUCTURAL DESIGN; ORTHOTROPIC CYLINDERS 20090029998 NASA Johnson Space Center, Houston, TX, United States International Space Station Science Research Accomplishments During the Assembly Years: An Analysis of Results from 2000-2008 Evans, Cynthia A.; Robinson, Julie A.; Tate-Brown, Judy; Thumm, Tracy; Crespo-Richey, Jessica; Baumann, David; Rhatigan, Jennifer; June 2009; In English; Original contains color and black and white illustrations Report No.(s): NASA/TP-2009-213146-REVA; S-978; JSC-CN-17592; Copyright; Avail.: CASI: A12, Hardcopy Avail Online: http://hdl.handle.net/2060/20090029998 This report summarizes research accomplishments on the International Space Station (ISS) through the first 15 Expeditions. When research programs for early Expeditions were established, five administrative organizations were executing research on ISS: bioastronautics research, fundamental space biology, physical science, space product development, and space flight. The Vision for Space Exploration led to changes in NASA's administrative structures, so we have grouped experiments topically by scientific themes human research for exploration, physical and biological sciences, technology development, observing the Earth, and educating and inspiring the next generation even when these do not correspond to the administrative structure at the time at which they were completed. The research organizations at the time at which the experiments flew are preserved in the appendix of this document. These investigations on the ISS have laid the groundwork for research planning for Expeditions to come. Humans performing scientific investigations on ISS serve as a model for the goals of future Exploration missions. The success of a wide variety of investigations is an important hallmark of early research on ISS. Of the investigations summarized here, some are completed with results released, some are completed with preliminary results, and some remain ongoing. Author BIOASTRONAUTICS; INTERNATIONAL SPACE STATION; RESEARCH FACILITIES; EXOBIOLOGY; EXPEDITIONS Additions to the NASA Aeronautics and Space Database as of 09/10/2009 20090030507 NASA Glenn Research Center, Cleveland, OH, United States Emittance Measurements Relevant to a 250 W(sub t) Class RTPV Generator for Space Exploration Wolford, Dave; Chubb, Donald; Clark, Eric; Pal, Anna Maria; Scheiman, Dave; Colon, Jack; August 2009; In English; 5th International Conference on Solar Concentrators for the Generation of Electricity, 16-19 Nov. 2008, Palm Desert, CA, United States; Original contains color and black and white illustrations Contract(s)/Grant(s): WBS 138494.04.03.01 Report No.(s): NASA/TM-2009-215619; E-16935; Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090030507 A proposed 250 Wt Radioisotope Thermophotovoltaic (RTPV) power system for utilization in lunar exploration and the subsequent exploration of Mars is described. Details of emitter selection are outlined for use in a maintenance free power supply that is productive over a 14-year mission life. Thorough knowledge of a material s spectral emittance is essential for accurate modeling of the RTPV system. While sometimes treated as a surface effect, emittance involves radiation from within a material. This creates a complex thermal gradient which is a combination of conductive and radiative heat transfer mechanisms. Emittance data available in the literature is a valuable resource but it is particular to the test sample s physical characteristics and the test environment. Considerations for making spectral emittance measurements relevant to RTPV development are discussed. Measured spectral emittance data of refractory emitter materials is given. Planned measurement system modifications to improve relevance to the current project are presented. Author EMITTANCE; EMISSION SPECTRA; CONDUCTIVE HEAT TRANSFER; RADIATIVE HEAT TRANSFER; TEMPERATURE GRADIENTS; REFRACTORY MATERIALS; LUNAR EXPLORATION 20090030508 NASA Glenn Research Center, Cleveland, OH, United States The a(4) Scheme-A High Order Neutrally Stable CESE Solver Chang, Sin-Chung; July 2009; In English; 43rd Joint Propulsion Conference, 8-11 Jul. 2007, Cincinnati, OH, United States; Original contains black and white illustrations Contract(s)/Grant(s): WBS 599489.02.07.03.04.03.01 Report No.(s): NASA/TM-2009-215658; AIAA Paper 2007-5820; E-16100-1; No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090030508 The CESE development is driven by a belief that a solver should (i) enforce conservation laws in both space and time, and (ii) be built from a nondissipative (i.e., neutrally stable) core scheme so that the numerical dissipation can be controlled effectively. To provide a solid foundation for a systematic CESE development of high order schemes, in this paper we describe a new high order (4-5th order) and neutrally stable CESE solver of a 1D advection equation with a constant advection speed a. The space-time stencil of this two-level explicit scheme is formed by one point at the upper time level and two points at the lower time level. Because it is associated with four independent mesh variables (the numerical analogues of the dependent variable and its first, second, and third-order spatial derivatives) and four equations per mesh point, the new scheme is referred to as the a(4) scheme. As in the case of other similar CESE neutrally stable solvers, the a(4) scheme enforces conservation laws in space-time locally and globally, and it has the basic, forward marching, and backward marching forms. Except for a singular case, these forms are equivalent and satisfy a space-time inversion (STI) invariant property which is shared by the advection equation. Based on the concept of STI invariance, a set of algebraic relations is developed and used to prove the a(4) scheme must be neutrally stable when it is stable. Numerically, it has been established that the scheme is stable if the value of the Courant number is less than 1/3 Author COMPUTATIONAL GRIDS; SPACE-TIME CE/SE METHOD; INVERSIONS; DEPENDENT VARIABLES; INDEPENDENT VARIABLES 20090030511 NASA Dryden Flight Research Center, Edwards, CA, United States Static Aeroelastic Effects of Formation Flight for Slender Unswept Wings Hanson, Curtis E.; August 2009; In English; Original contains black and white illustrations Report No.(s): NASA/TM-2009-214649; H-2980; DFRC-988; No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090030511 The static aeroelastic equilibrium equations for slender, straight wings are modified to incorporate the effects of aerodynamically-coupled formation flight. A system of equations is developed by applying trim constraints and is solved for component lift distribution, trim angle-of-attack, and trim aileron deflection. The trim values are then used to calculate the elastic twist distribution of the wing box. This system of equations is applied to a formation of two gliders in trimmed flight. Structural and aerodynamic properties are assumed for the gliders, and solutions are calculated for flexible and rigid wings in solo and formation flight. It is shown for a sample application of two gliders in formation flight, that formation disturbances produce greater twist in the wingtip immersed in the vortex than for either the opposing wingtip or the wings of a similar airplane in solo flight. Changes in the lift distribution, resulting from wing twist, increase the performance benefits of formation flight. A flexible wing in formation flight will require greater aileron deflection to achieve roll trim than a rigid wing. Author AERODYNAMIC CHARACTERISTICS; AEROELASTICITY; FORMATION FLYING; ANGLE OF ATTACK; LIFT; SLENDER WINGS Additions to the NASA Aeronautics and Space Database as of 09/11/2009 20090030602 NASA Glenn Research Center, Cleveland, OH, United States Proceedings of the Airframe Icing Workshop Colantonio, Ron O., Editor; July 2009; In English; Airframe Icing Workshop, 9 Jun. 2009, Cleveland, OH, United States; Original contains color and black and white illustrations Contract(s)/Grant(s): WBS 457280.02.07.03.02 Report No.(s): NASA/CP-2009-215797; E-17059; Copyright; Avail.: CASI: A09, Hardcopy Avail Online: http://hdl.handle.net/2060/20090030602 The NASA Glenn Research Center (GRC) has a long history of working with its partners towards the understanding of ice accretion formation and its associated degradation of aerodynamic performance. The June 9, 2009, Airframe Icing Workshop held at GRC provided an opportunity to examine the current NASA airframe icing research program and to dialogue on remaining and emerging airframe icing issues and research with the external community. Some of the airframe icing gaps identified included, but are not limited to, ice accretion simulation enhancements, three-dimensional benchmark icing database development, three-dimensional iced aerodynamics modeling, and technology development for a smart icing system. Author AIRFRAMES; ICE FORMATION; AERODYNAMIC CHARACTERISTICS; THREE DIMENSIONAL FLOW 20090030603 NASA Glenn Research Center, Cleveland, OH, United States NASA Iced Aerodynamics and Controls Current Research Addy, Gene; Proceedings of the Airframe Icing Workshop; July 2009; pp. 35-4; In English; Original contains color and black and white illustrations Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090030603 This slide presentation reviews the state of current research in the area of aerodynamics and aircraft control with ice conditions by the Aviation Safety Program, part of the Integrated Resilient Aircraft Controls Project (IRAC). Included in the presentation is a overview of the modeling efforts. The objective of the modeling is to develop experimental and computational methods to model and predict aircraft response during adverse flight conditions, including icing. The Aircraft icing modeling efforts includes the Ice-Contaminated Aerodynamics Modeling, which examines the effects of ice contamination on aircraft aerodynamics, and CFD modeling of ice-contaminated aircraft aerodynamics, and Advanced Ice Accretion Process Modeling which examines the physics of ice accretion, and works on computational modeling of ice accretions. The IRAC testbed, a Generic Transport Model (GTM) and its use in the investigation of the effects of icing on its aerodynamics is also reviewed. This has led to a more thorough understanding and models, both theoretical and empirical of icing physics and ice accretion for airframes, advanced 3D ice accretion prediction codes, CFD methods for iced aerodynamics and better understanding of aircraft iced aerodynamics and its effects on control surface effectiveness. CASI AERODYNAMICS; AIRCRAFT ICING; AIRCRAFT SAFETY; FLIGHT CONDITIONS; FLIGHT SAFETY; AIRCRAFT HAZARDS 20090030604 Illinois Univ. at Urbana-Champaign, Urbana, IL, United States Academic Airframe Icing Perspective Bragg, Mike; Rothmayer, Alric; Thompson, David; Proceedings of the Airframe Icing Workshop; July 2009; pp. 149-16; In English; Original contains color and black and white illustrations Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090030604 2-D ice accretion and aerodynamics reasonably well understood for engineering applications To significantly improve our current capabilities we need to understand 3-D: a) Important ice accretion physics and modeling not well understood in 3-D; and b) Aerodynamics unsteady and 3-D especially near stall. Larger systems issues important and require multidisciplinary team approach Derived from text AERODYNAMICS; AIRFRAMES; ICE FORMATION 20090030605 NASA Glenn Research Center, Cleveland, OH, United States Icing Simulation Bidwell, Colin; Proceedings of the Airframe Icing Workshop; July 2009; pp. 71-8; In English; Original contains color illustrations Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090030605 A grid block transformation scheme which allows the input of grids in arbitrary reference frames, the use of mirror planes, and grids with relative velocities has been developed. A simple ice crystal and sand particle bouncing scheme has been included.. Added an SLD splashing model based on that developed by William Wright for the LEWICE 3.2.2 software. A new area based collection efficiency algorithm will be incorporated which calculates trajectories from inflow block boundaries to outflow block boundaries. This method will be used for calculating and passing collection efficiency data between blade rows for turbo-machinery calculations. Author ICE FORMATION; COMPUTATIONAL GRIDS; SIMULATION; SPLASHING 20090030606 NASA Glenn Research Center, Cleveland, OH, United States Airframe Icing Research Gaps: NASA Perspective Potapczuk, Mark; Proceedings of the Airframe Icing Workshop; July 2009; pp. 87-10; In English; Original contains color illustrations Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090030606 qCurrent Airframe Icing Technology Gaps: Development of a full 3D ice accretion simulation model. Development of an improved simulation model for SLD conditions. CFD modeling of stall behavior for ice-contaminated wings/tails. Computational methods for simulation of stability and control parameters. Analysis of thermal ice protection system performance. Quantification of 3D ice shape geometric characteristics Development of accurate ground-based simulation of SLD conditions. Development of scaling methods for SLD conditions. Development of advanced diagnostic techniques for assessment of tunnel cloud conditions. Identification of critical ice shapes for aerodynamic performance degradation. Aerodynamic scaling issues associated with testing scale model ice shape geometries. Development of altitude scaling methods for thermal ice protections systems. Development of accurate parameter identification methods. Measurement of stability and control parameters for an ice-contaminated swept wing aircraft. Creation of control law modifications to prevent loss of control during icing encounters. 3D ice shape geometries. Collection efficiency data for ice shape geometries. SLD ice shape data, in-flight and ground-based, for simulation verification. Aerodynamic performance data for 3D geometries and various icing conditions. Stability and control parameter data for iced aircraft configurations. Thermal ice protection system data for simulation validation. Derived from text AIRFRAMES; ICE FORMATION; THERMAL PROTECTION; AERODYNAMIC CHARACTERISTICS; COMPUTATIONAL FLUID DYNAMICS; CONTROL THEORY; ICE PREVENTION 20090030607 NASA Glenn Research Center, Cleveland, OH, United States NASA Airframe Icing Research Overview Past and Current Potapczuk, Mark; Proceedings of the Airframe Icing Workshop; July 2009; pp. 1-3; In English; Original contains color and black and white illustrations Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090030607 This slide presentation reviews the past and current research that NASA has done in the area of airframe icing. Both the history experimental efforts and model development to understand the process and problem of ice formation are reviewed. This has resulted in the development of new experimental methods, advanced icing simulation software, flight dynamics and experimental databases that have an impact on design, testing, construction and certification and qualification of the aircraft and its sub-systems. Author AIRCRAFT DESIGN; AIRFRAMES; COMPUTERIZED SIMULATION; AIRCRAFT ICING; EXPERIMENTATION 20090030608 Cessna Aircraft Co., Wichita, KS, United States Small Airframe Manufacturer's Icing Perspective Hoppins, Jim; Proceedings of the Airframe Icing Workshop; July 2009; pp. 119-14; In English; Original contains color and black and white illustrations Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090030608 This viewgraph presentation describes the icing effects, risk mitigation practices, and icing certifications for various Cessna small aircraft models. NASA's role in the development of simulation tools for icing certifications is also discussed. CASI CESSNA AIRCRAFT; ICE FORMATION; AIRFRAMES; MANUFACTURING; AIRCRAFT MODELS 20090030609 Goodrich (B. F.) Co., Akron, OH, United States An Ice Protection and Detection Systems Manufacturer's Perspective Sweet, Dave; Proceedings of the Airframe Icing Workshop; July 2009; pp. 169-17; In English; Original contains color illustrations Copyright; Avail.: CASI: A02, Hardcopy Avail Online: http://hdl.handle.net/2060/20090030609 Accomplishments include: World Class Aircraft Icing Research Center and Facility. Primary Sponsor/Partner - Aircraft Icing Consortia/Meetings. Icing Research Tunnel. Icing Test Aircraft. Icing Codes - LEWICE/Scaling, et al. Development of New Technologies (SBIR, STTR, et al). Example: Look Ahead Ice Detection. Pilot Training Materials. Full Cooperation with Academia, Government and Industry. Derived from text AIRCRAFT ICING; ICE FORMATION; ICE PREVENTION; PILOT TRAINING; DETECTION; DEICING 20090030610 Federal Aviation Administration, Washington, DC, United States FAA Perspective Bond, Tom; Proceedings of the Airframe Icing Workshop; July 2009; pp. 101-11; In English; Original contains color illustrations Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090030610 This viewgraph presentation describes the Federal Aviation Administration's perspective on improvements on aircraft icing. The most important areas that are discussed include: 1) Improvements in SLD engineering tools to meet concerns about means of compliance (MOC); and 2) 3-D iced aerodynamics. CASI AERODYNAMICS; AIRCRAFT ICING; COMPUTATIONAL FLUID DYNAMICS; AERONAUTICS; AIRFRAMES 20090030611 NASA Glenn Research Center, Cleveland, OH, United States Icing Branch Current Research Activities in Icing Physics Vargas, Mario; Proceedings of the Airframe Icing Workshop; July 2009; pp. 47-8; In English; Original contains color and black and white illustrations Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090030611 Current development: A grid block transformation scheme which allows the input of grids in arbitrary reference frames, the use of mirror planes, and grids with relative velocities has been developed. A simple ice crystal and sand particle bouncing scheme has been included. Added an SLD splashing model based on that developed by William Wright for the LEWICE 3.2.2 software. A new area based collection efficiency algorithm will be incorporated which calculates trajectories from inflow block boundaries to outflow block boundaries. This method will be used for calculating and passing collection efficiency data between blade rows for turbo-machinery calculations. Author COMPUTATIONAL GRIDS; ICE FORMATION; TRAJECTORIES; ALGORITHMS; CRYSTALS 20090030615 NASA Langley Research Center, Hampton, VA, United States Space Transportation System (STS)-117 External Tank (ET)-124 Hail Damage Repair Assessment Wilson, Timmy R.; Gentz, Steven J.; Barth, Timothy S.; Minute, Stephen A.; Flowers, Cody P.; Hamilton, David A.; Null, Cynthia H.; Schafer, Charles F.; August 2009; In English; Original contains color and black and white illustrations Contract(s)/Grant(s): WBS 869021.05.07.02.99 Report No.(s): NASA/TM-2009-215785; NESC-RP-07-47/07-005-E; L19733; LF99-9286; Copyright; Avail.: CASI: A06, Hardcopy Avail Online: http://hdl.handle.net/2060/20090030615 Severe thunderstorms with associated hail and high winds struck the STS-117 stack on February 26, 2007. Peak winds were recorded at 62 knots with hail sizes ranging from 0.3 inch to 0.8 inch in diameter. As a result of the storm, the North Carolina Foam Institute (NCFI) type 24-124 Thermal Protection System (TPS) foam on the liquid oxygen (LO2) ogive acreage incurred significant impact damage. The NCFI on the ET intertank and the liquid hydrogen (LH2) acreage sustained hail damage. The Polymer Development Laboratory (PDL)-1034 foam of the LO2 ice frost ramps (IFRs) and the Super-Lightweight Ablator (SLA) of the LO2 cable tray also suffered minor damage. NASA Engineering and Safety Center (NESC) was asked to assess the technical feasibility of repairing the ET TPS, the reasonableness of conducting those repairs with the vehicle in a vertical, integrated configuration at the Kennedy Space Center (KSC) Vehicle Assemble Building (VAB), and to address attendant human factors considerations including worker fatigue and the potential for error. The outcome of the assessment is recorded in this document. Author EXTERNAL TANKS; DAMAGE ASSESSMENT; ABLATIVE MATERIALS; HAIL; SPACE TRANSPORTATION SYSTEM; THERMAL PROTECTION; IMPACT DAMAGE Additions to the NASA Aeronautics and Space Database as of 09/14/2009 20090030896 NASA Glenn Research Center, Cleveland, OH, United States Coupled Thermo-Electro-Magneto-Elastic Response of Smart Stiffened Panels Bednarcyk, Brett A.; Yarrington, Phillip W.; July 2009; In English; Original contains color and black and white illustrations Contract(s)/Grant(s): NCC3-878WBS 645846.02.07.03.03.02 Report No.(s): NASA/CR-2009-215269; E-16540; Copyright; Avail.: CASI: A04, Hardcopy Avail Online: http://hdl.handle.net/2060/20090030896 This report documents the procedures developed for incorporating smart laminate and panel analysis capabilities within the HyperSizer aerospace structural sizing software package. HyperSizer analyzes stiffened panels composed of arbitrary composite laminates through stiffener homogenization, or "smearing " techniques. The result is an effective constitutive equation for the stiffened panel that is suitable for use in a full vehicle-scale finite element analysis via MSC/NASTRAN. The existing thermo-elastic capabilities of HyperSizer have herein been extended to include coupled thermo-electro-magneto-elastic analysis capabilities. This represents a significant step toward realization of design tools capable of guiding the development of the next generation of smart aerospace structures. Verification results are presented that compare the developed smart HyperSizer capability with an ABAQUS piezoelectric finite element solution for a facesheet-flange combination. These results show good agreement between HyperSizer and ABAQUS, but highlight a limitation of the HyperSizer formulation in that constant electric field components are assumed. Author SMART STRUCTURES; PIEZOELECTRICITY; LAMINATES; APPLICATIONS PROGRAMS (COMPUTERS); HOMOGENIZING 20090030897 NASA Langley Research Center, Hampton, VA, United States Engine Concept Study for an Advanced Single-Aisle Transport Guynn, Mark D.; Berton, Jeffrey J.; Fisher, Kenneth L.; Haller, William J.; Tong, Michael; Thurman, Douglas R.; August 2009; In English; Original contains color and black and white illustrations Contract(s)/Grant(s): WBS 561581.02.08.07.13.04 Report No.(s): NASA/TM-2009-215784; L-19712; LF-9138; No Copyright; Avail.: CASI: A05, Hardcopy Avail Online: http://hdl.handle.net/2060/20090030897 The desire for higher engine efficiency has resulted in the evolution of aircraft gas turbine engines from turbojets, to low bypass ratio, first generation turbofans, to today's high bypass ratio turbofans. Although increased bypass ratio has clear benefits in terms of propulsion system metrics such as specific fuel consumption, these benefits may not translate into aircraft system level benefits due to integration penalties. In this study, the design trade space for advanced turbofan engines applied to a single aisle transport (737/A320 class aircraft) is explored. The benefits of increased bypass ratio and associated enabling technologies such as geared fan drive are found to depend on the primary metrics of interest. For example, bypass ratios at which mission fuel consumption is minimized may not require geared fan technology. However, geared fan drive does enable higher bypass ratio designs which result in lower noise. The results of this study indicate the potential for the advanced aircraft to realize substantial improvements in fuel efficiency, emissions, and noise compared to the current vehicles in this size class. Author AIRCRAFT DESIGN; GAS TURBINE ENGINES; TURBOJET ENGINES; NOISE REDUCTION; ENGINE DESIGN Additions to the NASA Aeronautics and Space Database as of 09/23/2009 20090032038 NASA Langley Research Center, Hampton, VA, United States Explosion/Blast Dynamics for Constellation Launch Vehicles Assessment Baer, Mel; Crawford, Dave; Hickox, Charles; Kipp, Marlin; Hertel, Gene; Morgan, Hal; Ratzel, Arthur; Cragg, Clinton H.; August 2009; In English; Original contains color illustrations Contract(s)/Grant(s): WBS 869021.06.07.02.99 Report No.(s): NASA/TM-2009-215786; NESC-RP-08-43/07-029-E; L-19734; LF99-9287; Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090032038 An assessment methodology is developed to guide quantitative predictions of adverse physical environments and the subsequent effects on the Ares-1 crew launch vehicle associated with the loss of containment of cryogenic liquid propellants from the upper stage during ascent. Development of the methodology is led by a team at Sandia National Laboratories (SNL) with guidance and support from a number of National Aeronautics and Space Administration (NASA) personnel. The methodology is based on the current Ares-1 design and feasible accident scenarios. These scenarios address containment failure from debris impact or structural response to pressure or blast loading from an external source. Once containment is breached, the envisioned assessment methodology includes predictions for the sequence of physical processes stemming from cryogenic tank failure. The investigative techniques, analysis paths, and numerical simulations that comprise the proposed methodology are summarized and appropriate simulation software is identified in this report. Author ARES 1 LAUNCH VEHICLE; CRYOGENIC ROCKET PROPELLANTS; COMPUTERIZED SIMULATION; CONTAINMENT; SPACECREWS; LIQUID ROCKET PROPELLANTS; EXPLOSIONS; DEBRIS; CRYOGENICS 20090032043 NASA Langley Research Center, Hampton, VA, United States A Future State for NASA Laboratories - Working in the 21st Century Kegelman, Jerome T.; Harris, Charles E.; Antcliff, Richard R.; Bushnell, Dennis M.; Dwoyer, Douglas L.; July 2009; In English; Original contains black and white illustrations Contract(s)/Grant(s): WBS 478076.07.15.05 Report No.(s): NASA/TM-2009-215780; LF99-9167; Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090032043 The name "21 st Century Laboratory" is an emerging concept of how NASA (and the world) will conduct research in the very near future. Our approach is to carefully plan for significant technological changes in products, organization, and society. The NASA mission can be the beneficiary of these changes, provided the Agency prepares for the role of 21st Century laboratories in research and technology development and its deployment in this new age. It has been clear for some time now that the technology revolutions, technology "mega-trends" that we are in the midst of now, all have a common element centered around advanced computational modeling of small scale physics. Whether it is nano technology, bio technology or advanced computational technology, all of these megatrends are converging on science at the very small scale where it is profoundly important to consider the quantum effects at play with physics at that scale. Whether it is the bio-technology creation of "nanites" designed to mimic our immune system or the creation of nanoscale infotechnology devices, allowing an order of magnitude increase in computational capability, all involve quantum physics that serves as the heart of these revolutionary changes. Author RESEARCH AND DEVELOPMENT; TECHNOLOGICAL FORECASTING; LABORATORIES Additions to the NASA Aeronautics and Space Database as of 09/29/2009 20090032603 NASA Goddard Space Flight Center, Greenbelt, MD, United States GSFC Heliophysics Science Division 2008 Science Highlights Gilbert, Holly R.; Strong, Keith T.; Saba, Julia L. R.; Firestone, Elaine R.; March 2009; In English; Original contains color and black and white illustrations Report No.(s): NASA/TM-2009-214178; Copyright; Avail.: CASI: A09, Hardcopy Avail Online: http://hdl.handle.net/2060/20090032603 This report is intended to record and communicate to our colleagues, stakeholders, and the public at large about heliophysics scientific and flight program achievements and milestones for 2008, for which NASA Goddard Space Flight Center's Heliophysics Science Division (HSD) made important contributions. HSD comprises approximately 261 scientists, technologists, and administrative personnel dedicated to the goal of advancing our knowledge and understanding of the Sun and the wide variety of domains that its variability influences. Our activities include Lead science investigations involving flight hardware, theory, and data analysis and modeling that will answer the strategic questions posed in the Heliophysics Roadmap; Lead the development of new solar and space physics mission concepts and support their implementation as Project Scientists; Provide access to measurements from the Heliophysics Great Observatory through our Science Information Systems, and Communicate science results to the public and inspire the next generation of scientists and explorers. Author ATMOSPHERIC PHYSICS; SOLAR PHYSICS; CORONAS; TOPOGRAPHY; MISSION PLANNING 20090032661 NASA Goddard Space Flight Center, Greenbelt, MD, United States Atmospheric Aerosol Properties and Climate Impacts Chin, Mian; Kahn, Ralph A.; Remer, Lorraine A.; Yu, Hongbin; Rind, David; Feingold, Graham; Quinn, Patricia K.; Schwartz, Stephen E.; Streets, David G.; DeCola, Phillip; Halthore, Rangasayi; January 2009; In English; Original contains color and black and white illustrations Report No.(s): NASA/SP-2009-568; Copyright; Avail.: CASI: A07, Hardcopy Avail Online: http://hdl.handle.net/2060/20090032661 This report critically reviews current knowledge about global distributions and properties of atmospheric aerosols, as they relate to aerosol impacts on climate. It assesses possible next steps aimed at substantially reducing uncertainties in aerosol radiative forcing estimates. Current measurement techniques and modeling approaches are summarized, providing context. As a part of the Synthesis and Assessment Product in the Climate Change Science Program, this assessment builds upon recent related assessments, including the Fourth Assessment Report of the Intergovernmental Panel on Climate Change (IPCC AR4, 2007) and other Climate Change Science Program reports. The objectives of this report are (1) to promote a consensus about the knowledge base for climate change decision support, and (2) to provide a synthesis and integration of the current knowledge of the climate-relevant impacts of anthropogenic aerosols for policy makers, policy analysts, and general public, both within and outside the U.S government and worldwide. Derived from text AEROSOLS; CLIMATE; CLIMATE CHANGE; ATMOSPHERIC EFFECTS; CLIMATOLOGY; EARTH ATMOSPHERE Additions to the NASA Aeronautics and Space Database as of 10/01/2009 20090033114 NASA Johnson Space Center, Houston, TX, United States STS-114 Engine Cut-off Sensor Anomaly Technical Consultation Report Wilson, Timmy R.; Kichak, Robert A.; Ungar, Eugene K.; Cherney, Robert; Rickman, Steve L.; April 2009; In English; Original contains color and black and white illustrations Contract(s)/Grant(s): WBS 869021.06.07.02.99 Report No.(s): NASA/TM-2009-215567; NESC-RP-05-125/05-045-E; L-19639; LF99-8395; Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090033114 The NESC consultation team participated in real-time troubleshooting of the Main Propulsion System (MPS) Engine Cutoff (ECO) sensor system failures during STS-114 launch countdown. The team assisted with External Tank (ET) thermal and ECO Point Sensor Box (PSB) circuit analyses, and made real-time inputs to the Space Shuttle Program (SSP) problem resolution teams. Several long-term recommendations resulted. One recommendation was to conduct cryogenic tests of the ECO sensors to validate, or disprove, the theory that variations in circuit impedance due to cryogenic effects on swaged connections within the sensor were the root cause of STS-114 failures. Author ENGINE FAILURE; SPACE TRANSPORTATION SYSTEM; LAUNCHING; CRYOGENICS; EXTERNAL TANKS; MAINTENANCE; NETWORK ANALYSIS; SYSTEM FAILURES 20090033116 NASA Langley Research Center, Hampton, VA, United States Possible Deficiencies in Predicting Transonic Aerodynamics on the X-43A Labbe, Steven G.; Gilbert, Michael G.; Kehoe, Michael W.; April 2009; In English; Original contains color illustrations Contract(s)/Grant(s): WBS 869021.05.07.04.04 Report No.(s): NASA/TM-2009-215711; NESC-RP-04-02/03-002-E; L-19650; LF99-8657; No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090033116 The initial X-43A flight test, June 2, 2001, resulted in a mishap and loss of the vehicle. A mishap investigation board (MIB) report and findings, including the established root cause, were publicly released on July, 23, 2003. The X-43A Flight 1 Hyper-X Launch Vehicle (HXLV) failed because the vehicle control system design was deficient for the trajectory flown due to inaccurate analytical models (Pegasus heritage and HXLV specific), which overestimated the (control) system margin ? X-43A Mishap Investigation Report, Vol. I. ? included as Reference 1. Several specific errors were noted, 1) HXLV aerodynamics ? failure to model changes to wing, fin and rudder airfoil shapes due to addition of thermal protection system (TPS); 2) Fin actuation system (FAS) modeling ? under prediction of the control surface hinge moments and FAS compliance; and 3) Parametric uncertainties ? insufficient variation in the aerodynamic, FAS and control system models. In response to the MIB findings, the X-43A program has been working RTF through an approved Corrective Action Plan (CAP) over the last two years. Author LAUNCH VEHICLES; FLIGHT TESTS; FAILURE; ERRORS; CONTROL SYSTEMS DESIGN; MATHEMATICAL MODELS 20090033142 NASA Langley Research Center, Hampton, VA, United States Tensile Properties and Microstructure of Inconel 718 Fabricated with Electron Beam Freeform Fabrication (EBF(sup 3)) Bird, R. Keith; Hibberd, Joshua; September 2009; In English; Original contains color and black and white illustrations Contract(s)/Grant(s): WBS 561581.02.08.07.15.03 Report No.(s): NASA/TM-2009-215929; L-19731; LF99-9226; Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090033142 Electron beam freeform fabrication (EBF3) direct metal deposition processing was used to fabricate two Inconel 718 single-bead-width wall builds and one multiple-bead-width block build. Specimens were machined to evaluate microstructure and room temperature tensile properties. The tensile strength and yield strength of the as-deposited material from the wall and block builds were greater than those for conventional Inconel 718 castings but were less than those for conventional cold-rolled sheet. Ductility levels for the EBF3 material were similar to those for conventionally-processed sheet and castings. An unexpected result was that the modulus of the EBF3-deposited Inconel 718 was significantly lower than that of the conventional material. This low modulus may be associated with a preferred crystallographic orientation resultant from the deposition and rapid solidification process. A heat treatment with a high solution treatment temperature resulted in a recrystallized microstructure and an increased modulus. However, the modulus was not increased to the level that is expected for Inconel 718. Author INCONEL (TRADEMARK); ELECTRON BEAMS; FABRICATION; DEPOSITION; METALLIZING; RAPID QUENCHING (METALLURGY); HEAT TREATMENT; TENSILE STRENGTH; HEAT OF SOLUTION Additions to the NASA Aeronautics and Space Database as of 10/06/2009 20090033663 NASA Langley Research Center, Hampton, VA, United States NASA Aerosciences Perspective on Proposed De-Scope of Ares I-X Development Flight Instrumentation Schuster, David M.; August 2009; In English; Original contains color and black and white illustrations Contract(s)/Grant(s): WBS 869021.01.07.01.01 Report No.(s): NASA/TM-2009-215909; NESC-RP-08-19/08-00454; L-19744; LF99-9312; No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090033663 This position paper is written as a result of a number of emails and a presentation that have recently been circulated concerning the potential reduction of Development Flight Instrumentation (DFI) to be included on the Ares I-X flight test vehicle. A reduction in instrumentation has been proposed presumably to reduce project costs and relieve project schedule pressures. This proposal has generated a significant amount of discussion on both sides of the issue, primarily from those within the project. The intention here is to provide a perspective on this issue from outside the mainline project. Author AEROSPACE SCIENCES; FLIGHT TEST VEHICLES; FLIGHT INSTRUMENTS 20090033665 NASA Johnson Space Center, Houston, TX, United States Ares I-X Vibroacoustic Environments Larsen, Curtis E.; Schuster, David M.; Kaufman, Daniel S.; August 2009; In English; Original contains black and white illustrations Contract(s)/Grant(s): WBS 869021.03.07.01.05 Report No.(s): NASA/TM-2009-215910; NESC-RP-08-70/08-00456; L-19745; LF99-9313; No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090033665 This paper provides a summary of the NASA Engineering and Safety Center (NESC) team recommendations and observations following participation with the Ares I-X Vibroacoustic (VA) Environments Panel in meetings at the Kennedy Space Center (KSC) and the Marshall Space Flight Center (MSFC) in March and April 2008, respectively. Author VIBRATIONAL STRESS; ACOUSTICS; FLIGHT TESTS; SYSTEMS ENGINEERING; CONFIGURATION MANAGEMENT 20090033666 NASA Langley Research Center, Hampton, VA, United States Review of the Constellation Level II Safety, Reliability, and Quality Assurance (SR&QA) Requirements Documents during Participation in the Constellation Level II SR&QA Forum Cameron, Kenneth D.; Gentz, Steven J.; Beil, Robert J.; Minute, Stephen A.; Currie, Nancy J.; Scott, Steven S.; Thomas, Walter B., III; Smiles, Michael D.; Schafer, Charles F.; Null, Cynthia H.; Bay, P. Michael; August 2009; In English; Original contains black and white illustrations Contract(s)/Grant(s): WBS 869021.07.07.07.99 Report No.(s): NASA/TM-2009-215914; NESC-RP-08-86/08-00476; L-19749; LF99-9326; Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090033666 At the request of the Exploration Systems Mission Directorate (ESMD) and the Constellation Program (CxP) Safety, Reliability; and Quality Assurance (SR&QA) Requirements Director, the NASA Engineering and Safety Center (NESC) participated in the Cx SR&QA Requirements forum. The Requirements Forum was held June 24-26; 2008, at GRC's Plum Brook Facility. The forums purpose was to gather all stakeholders into a focused meeting to help complete the process of refining the CxP to refine its Level II SR&QA requirements or defining project-specific requirements tailoring. Element prime contractors had raised specific questions about the wording and intent of many requirements in areas they felt were driving costs without adding commensurate value. NESC was asked to provide an independent and thorough review of requirements that contractors believed were driving Program costs, by active participation in the forum. This document contains information from the forum. Author CONSTELLATION PROGRAM; QUALITY CONTROL; REQUIREMENTS; RELIABILITY; COSTS; SAFETY 20090033695 NASA Langley Research Center, Hampton, VA, United States Shuttle Ground Support Equipment (GSE) T-0 Umbilical to Space Shuttle Program (SSP) Flight Elements Consultation Wilson, Timmy R.; Kichak, Robert A.; McManamen, John P.; Kramer-White, Julie; Raju, Ivatury S.; Beil, Robert J.; Weeks, John F.; Elliott, Kenny B.; June 2009; In English; Original contains color and black and white illustrations Contract(s)/Grant(s): WBS 869021.05.07.04.99 Report No.(s): NASA/TM-2009-215753; NESC-RP-07-01/05-012-E; LF99-8879; No Copyright; Avail.: CASI: A11, Hardcopy Avail Online: http://hdl.handle.net/2060/20090033695 The NASA Engineering and Safety Center (NESC) was tasked with assessing the validity of an alternate opinion that surfaced during the investigation of recurrent failures at the Space Shuttle T-0 umbilical interface. The most visible problem occurred during the Space Transportation System (STS)-112 launch when pyrotechnics used to separate Solid Rocket Booster (SRB) Hold-Down Post (HDP) frangible nuts failed to fire. Subsequent investigations recommended several improvements to the Ground Support Equipment (GSE) and processing changes were implemented, including replacement of ground-half cables and connectors between flights, along with wiring modifications to make critical circuits quad-redundant across the interface. The alternate opinions maintained that insufficient data existed to exonerate the design, that additional data needed to be gathered under launch conditions, and that the interface should be further modified to ensure additional margin existed to preclude failure. The results of the assessment are contained in this report. Author GROUND SUPPORT EQUIPMENT; SPACE SHUTTLES; CONNECTORS; SPACE SHUTTLE BOOSTERS; SPACE TRANSPORTATION SYSTEM FLIGHTS; LAUNCHING; PYROTECHNICS Additions to the NASA Aeronautics and Space Database as of 10/07/2009 20090033737 NASA Langley Research Center, Hampton, VA, United States Investigation of Helicopter Longeron Cracks Newman, John A.; Baughman, James; Wallace, Terryl A.; September 2009; In English; Original contains color and black and white illustrations Contract(s)/Grant(s): WBS 698259.02.07.07.03.02 Report No.(s): NASA/TP-2009-215791; L-19704; LF99-9060; Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090033737 Four cracked longerons, containing a total of eight cracks, were provided for study. Cracked regions were cut from the longerons. Load was applied to open the cracks, enabling crack surface examination. Examination revealed that crack propagation was driven by fatigue loading in all eight cases. Fatigue crack initiation appears to have occurred on the top edge of the longerons near geometric changes that affect component bending stiffness. Additionally, metallurgical analysis has revealed a local depletion in alloying elements in the crack initiation regions that may be a contributing factor. Fatigue crack propagation appeared to be initially driven by opening-mode loading, but at a crack length of approximately 0.5 inches (12.7 mm), there is evidence of mixed-mode crack loading. For the longest cracks studied, shear-mode displacements destroyed crack-surface features of interest over significant portions of the crack surfaces. Author CRACK INITIATION; LONGERONS; HELICOPTERS; SURFACE CRACKS; CRACK PROPAGATION; FATIGUE (MATERIALS) 20090033738 NASA Glenn Research Center, Cleveland, OH, United States Active Fail-Safe Micro-Array Flow Control for Advanced Embedded Propulsion Systems Anderson, Bernhard H.; Mace, James L.; Mani, Mori; August 2009; In English; 47th Aerospace Sciences Meeting, 5-8 Jan. 2009, Orlando, FL, United States; Original contains color and black and white illustrations Contract(s)/Grant(s): WBS 984754.02.07.03.13.02 Report No.(s): NASA/TM-2009-215596; AIAA Paper 2009-0741; E-16887; Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090033738 The primary objective of this research effort was to develop and analytically demonstrate enhanced first generation active "fail-safe" hybrid flow-control techniques to simultaneously manage the boundary layer on the vehicle fore-body and to control the secondary flow generated within modern serpentine or embedded inlet S-duct configurations. The enhanced first-generation technique focused on both micro-vanes and micro-ramps highly-integrated with micro -jets to provide nonlinear augmentation for the "strength' or effectiveness of highly-integrated flow control systems. The study focused on the micro -jet mass flow ratio (Wjet/Waip) range from 0.10 to 0.30 percent and jet total pressure ratios (Pjet/Po) from 1.0 to 3.0. The engine bleed airflow range under study represents about a 10 fold decrease in micro -jet airflow than previously required. Therefore, by pre-conditioning, or injecting a very small amount of high-pressure jet flow into the vortex generated by the micro-vane and/or micro-ramp, active flow control is achieved and substantial augmentation of the controlling flow is realized. Author FLOW DISTRIBUTION; PROPULSION SYSTEM CONFIGURATIONS; AERODYNAMIC CONFIGURATIONS; SYSTEMS INTEGRATION; BOUNDARY LAYERS; FAIL-SAFE SYSTEMS; JET FLOW; MASS FLOW 20090033743 NASA Langley Research Center, Hampton, VA, United States Shuttle Orbiter-like Cargo Carrier on Crew Launch Vehicle Martinovic, Zoran; September 2009; In English; Original contains color and black and white illustrations Contract(s)/Grant(s): WBS 304029.01.04.02.02 Report No.(s): NASA/TM-2009-215793; L-19711; LF99-9125; No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090033743 The following document summarizes the results of a conceptual design study for which the goal was to investigate the possibility of using a crew launch vehicle to deliver the remaining International Space Station elements should the Space Shuttle orbiter not be available to complete that task. Conceptual designs and structural weight estimates for two designs are presented. A previously developed systematic approach that was based on finite-element analysis and structural sizing was used to estimate growth of structural weight from analytical to "as built" conditions. Author FINITE ELEMENT METHOD; LAUNCH VEHICLES; INTERNATIONAL SPACE STATION; SPACE SHUTTLE ORBITERS; SPACECREWS; CARGO 20090033744 NASA Glenn Research Center, Cleveland, OH, United States A Very Large Eddy Simulation of the Nonreacting Flow in a Single-Element Lean Direct Injection Combustor Using PRNS with a Nonlinear Subscale Model Shih, Tsan-Hsing; Liu, Nan-Suey; August 2009; In English; Original contains color illustrations Contract(s)/Grant(s): WBS 561581.02.08.03.16.02 Report No.(s): NASA/TM-2009-215644; E-16956; Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090033744 Very large eddy simulation (VLES) of the nonreacting turbulent flow in a single-element lean direct injection (LDI) combustor has been successfully performed via the approach known as the partially resolved numerical simulation (PRNS/VLES) using a nonlinear subscale model. The grid is the same as the one used in a previous RANS simulation, which was considered as too coarse for a traditional LES simulation. In this study, we first carry out a steady RANS simulation to provide the initial flow field for the subsequent PRNS/VLES simulation. We have also carried out an unsteady RANS (URANS) simulation for the purpose of comparing its results with that of the PRNS/VLES simulation. In addition, these calculated results are compared with the experimental data. The present effort has demonstrated that the PRNS/VLES approach, while using a RANS type of grid, is able to reveal the dynamically important, unsteady large-scale turbulent structures occurring in the flow field of a single-element LDI combustor. The interactions of these coherent structures play a critical role in the dispersion of the fuel, hence, the mixing between the fuel and the oxidizer in a combustor. Author LARGE EDDY SIMULATION; TURBULENT FLOW; COMPUTATIONAL FLUID DYNAMICS; FLOW DISTRIBUTION; INJECTION 20090033745 NASA Glenn Research Center, Cleveland, OH, United States The Effects of Hot Corrosion Pits on the Fatigue Resistance of a Disk Superalloy Gabb, Timothy P.; Telesman, Jack; Hazel, Brian; Mourer, David P.; August 2009; In English; Original contains color and black and white illustrations Contract(s)/Grant(s): WBS 698259.02.07.03.04.02 Report No.(s): NASA/TM-2009-215629; E-16940; Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090033745 The effects of hot corrosion pits on low cycle fatigue life and failure modes of the disk superalloy ME3 were investigated. Low cycle fatigue specimens were subjected to hot corrosion exposures producing pits, then tested at low and high temperatures. Fatigue lives and failure initiation points were compared to those of specimens without corrosion pits. Several tests were interrupted to estimate the fraction of fatigue life that fatigue cracks initiated at pits. Corrosion pits significantly reduced fatigue life by 60 to 98 percent. Fatigue cracks initiated at a very small fraction of life for high temperature tests, but initiated at higher fractions in tests at low temperature. Critical pit sizes required to promote fatigue cracking were estimated, based on measurements of pits initiating cracks on fracture surfaces. Author HEAT RESISTANT ALLOYS; HOT CORROSION; FATIGUE (MATERIALS); FAILURE MODES; SURFACE CRACKS; HIGH TEMPERATURE TESTS; FRACTURE STRENGTH 20090033749 NASA Glenn Research Center, Cleveland, OH, United States Compressor Study to Meet Large Civil Tilt Rotor Engine Requirements Veres, Joseph P.; August 2009; In English; 65th Annual Forum and Technology Display, 27-29 May 2009, Grapevine, TX, United States; Original contains black and white illustrations Contract(s)/Grant(s): WBS 877868.02.07.03.01.02.02 Report No.(s): NASA/TM-2009-215641; E-16952; No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090033749 A vehicle concept study has been made to meet the requirements of the Large Civil Tilt Rotorcraft vehicle mission. A vehicle concept was determined, and a notional turboshaft engine system study was conducted. The engine study defined requirements for the major engine components, including the compressor. The compressor design-point goal was to deliver a pressure ratio of 31:1 at an inlet weight flow of 28.4 lbm/sec. To perform a conceptual design of two potential compressor configurations to meet the design requirement, a mean-line compressor flow analysis and design code were used. The first configuration is an eight-stage axial compressor. Some challenges of the all-axial compressor are the small blade spans of the rear-block stages being 0.28 in., resulting in the last-stage blade tip clearance-to-span ratio of 2.4 percent. The second configuration is a seven-stage axial compressor, with a centrifugal stage having a 0.28-in. impeller-exit blade span. The compressors conceptual designs helped estimate the flow path dimensions, rotor leading and trailing edge blade angles, flow conditions, and velocity triangles for each stage. Author COMPRESSORS; TURBOCOMPRESSORS; TILT ROTOR AIRCRAFT; LEADING EDGES; ROTARY WING AIRCRAFT; ENGINE DESIGN; FLOW VELOCITY; CENTRIFUGAL FORCE; TRAILING EDGES 20090033760 NASA Glenn Research Center, Cleveland, OH, United States Effects of Thermal Exposure on the Optical Properties of LORD Aeroglaze A276 Ellis, David L.; Jaworske, Donald A.; August 2009; In English; Original contains color illustrations Contract(s)/Grant(s): WBS 463169.04.03.05.01 Report No.(s): NASA/TM-2009-215652; E-16965; No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090033760 A lunar outpost will require electrical energy. One potential source is fission surface power where heat from a reactor is converted into electricity utilizing an energy conversion system, and waste heat will need to be rejected from the system. The Second Generation Radiator Demonstration Unit is a technology demonstration unit leading towards operational radiators. To approximate the infrared emittance of the lunar outpost radiators, a low-cost coating compatible with the test conditions was sought. LORD Aeroglaze A276 has a similar emittance, but its performance in air and vacuum at the desired operating temperatures was unknown. This study determined that the emittance remained above 0.86 for all conditions tested and that LORD Aeroglaze A276 is a suitable surrogate coating for the Second Generation Radiator Demonstration Unit. Author COATING; EMITTANCE; LUNAR BASES; ENERGY CONVERSION; OPERATING TEMPERATURE; OPTICAL PROPERTIES; INFRARED RADIATION; ELECTRICITY 20090033766 NASA Glenn Research Center, Cleveland, OH, United States The NASA In-Space Propulsion Technology Project, Products, and Mission Applicability Anderson, David J.; Pencil, Eric; Liou, Larry; Dankanich, John; Munk, Michelle M.; Kremic, Tibor; August 2009; In English; 2009 Aerospace Conference, 7-14 Mar. 2009, Big Sky, MT, United States; Original contains color illustrations Contract(s)/Grant(s): WBS 346620.01.03.01 Report No.(s): NASA/TM-2009-215649; Paper no. 1176; E-169649; Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090033766 The In-Space Propulsion Technology (ISPT) Project, funded by NASA s Science Mission Directorate (SMD), is continuing to invest in propulsion technologies that will enable or enhance NASA robotic science missions. This overview provides development status, near-term mission benefits, applicability, and availability of in-space propulsion technologies in the areas of aerocapture, electric propulsion, advanced chemical thrusters, and systems analysis tools. Aerocapture investments improved: guidance, navigation, and control models of blunt-body rigid aeroshells; atmospheric models for Earth, Titan, Mars, and Venus; and models for aerothermal effects. Investments in electric propulsion technologies focused on completing NASA s Evolutionary Xenon Thruster (NEXT) ion propulsion system, a 0.6 to 7 kW throttle-able gridded ion system. The project is also concluding its High Voltage Hall Accelerator (HiVHAC) mid-term product specifically designed for a low-cost electric propulsion option. The primary chemical propulsion investment is on the high-temperature Advanced Material Bipropellant Rocket (AMBR) engine providing higher performance for lower cost. The project is also delivering products to assist technology infusion and quantify mission applicability and benefits through mission analysis and tools. In-space propulsion technologies are applicable, and potentially enabling for flagship destinations currently under evaluation, as well as having broad applicability to future Discovery and New Frontiers mission solicitations. Author ELECTRIC PROPULSION; ION PROPULSION; CHEMICAL PROPULSION; AEROCAPTURE; PROPULSION SYSTEM PERFORMANCE; HALL ACCELERATORS; ION ENGINES; LIQUID ROCKET PROPELLANTS; PROPULSION SYSTEM CONFIGURATIONS 20090033769 NASA Glenn Research Center, Cleveland, OH, United States NASA PS400: A New Temperature Solid Lubricant Coating for High Temperature Wear Applications DellaCorte, C.; Edmonds, B. J.; August 2009; In English; Original contains black and white illustrations Contract(s)/Grant(s): WBS 877868.02.07.03.01.01.14 Report No.(s): NASA/TM-2009-215678; E-17044; No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090033769 A new solid lubricant coating, NASA PS400, has been developed for high temperature tribological applications. This plasma sprayed coating is a variant of the patented PS304 coating and has been formulated to provide higher density, smoother surface finish and better dimensional stability than PS304. PS400 is comprised of a nickel-molybdenum binder that provides strength, creep resistance and extreme oxidative and dimensional stability. Chromium oxide, silver and barium-calcium fluoride eutectic are added to the binder to form PS400.Tribological properties were evaluated with a pin-on-disk test rig in sliding contact to 650 C. Coating material samples were exposed to air, argon and vacuum at 760 C followed by cross section microscopic analysis to assess microstructure stability. Oil-Free microturbine engine hot section foil bearing tests were undertaken to assess PS400 s suitability for hot foil gas bearing applications. The preliminary results indicate that PS400 exhibits tribological characteristics comparable to the PS304 coating but with enhanced creep resistance and dimensional stability suitable for demanding, dynamic applications. Author SOLID LUBRICANTS; HIGH TEMPERATURE; FOIL BEARINGS; FRICTION; TRIBOLOGY; CHROMIUM OXIDES; MOLYBDENUM; NICKEL 20090033772 NASA Langley Research Center, Hampton, VA, United States Position Paper External Tank Thermal Protection System (TPS) Manually Sprayed fly-as-is Foam Certification Stadler, John H.; August 2009; In English; Original contains black and white illustrations Contract(s)/Grant(s): WBS 869021.01.07.01.01 Report No.(s): NASA/TM-2009-215917; NESC-PB-04-10; L-19752; LF99-9332; No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090033772 During manufacture of the existing External Tanks (ETs), the Thermal Protection System (TPS) foam manual spray application processes lacked the enhanced controls/procedures to ensure that defects produced were less than the critical size. Therefore the only remaining option to certify the "fly-as-is" foam is to verify ET120 tank hardware meets the new foam debris requirements. The ET project has undertaken a significant effort studying the existing "fly-as-is" TPS foam. This paper contains the findings of the study. Author THERMAL PROTECTION; EXTERNAL TANKS; FOAMS; CERTIFICATION; DEBRIS; DEFECTS 20090033774 NASA Langley Research Center, Hampton, VA, United States Laura Users Manual: 5.1-41601 Mazaheri, Alireza; Gnoffo, Peter A.; Johnston, Christopher O.; Kleb, Bil; August 2009; In English Contract(s)/Grant(s): WBS 37781606030308 Report No.(s): NASA/TM-2009-215783; L-19726; LF99-9183; Copyright; Avail.: CASI: A04, Hardcopy Avail Online: http://hdl.handle.net/2060/20090033774 This users manual provides in-depth information concerning installation and execution of LAURA, version 5. LAURA is a structured, multi-block, computational aerothermodynamic simulation code. Version 5 represents a major refactoring of the original Fortran 77 LAURA code toward a modular structure afforded by Fortran 95. The refactoring improved usability and maintainability by eliminating the requirement for problem-dependent re-compilations, providing more intuitive distribution of functionality, and simplifying interfaces required for multiphysics coupling. As a result, LAURA now shares gas-physics modules, MPI modules, and other low-level modules with the FUN3D unstructured-grid code. In addition to internal refactoring, several new features and capabilities have been added, e.g., a GNU-standard installation process, parallel load balancing, automatic trajectory point sequencing, free-energy minimization, and coupled ablation and flowfield radiation. Author AEROTHERMODYNAMICS; ABLATION; APPLICATIONS PROGRAMS (COMPUTERS); COMPUTER PROGRAMS; COMPUTERIZED SIMULATION; UNSTRUCTURED GRIDS (MATHEMATICS); MAINTAINABILITY 20090033796 NASA Langley Research Center, Hampton, VA, United States Lightning Pin Injection Testing on MOSFETS Ely, Jay J.; Nguyen, Truong X.; Szatkowski, George N.; Koppen, Sandra V.; Mielnik, John J.; Vaughan, Roger K.; Wysocki, Philip F.; Celaya, Jose R.; Saha, Sankalita; September 2009; In English; Original contains color and black and white illustrations Contract(s)/Grant(s): WBS 645846.02.07.07.12.02 Report No.(s): NASA/TM-2009-215794; L-19713; LF99-9139; Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090033796 Lightning transients were pin-injected into metal-oxide-semiconductor field-effect transistors (MOSFETs) to induce fault modes. This report documents the test process and results, and provides a basis for subsequent lightning tests. MOSFETs may be present in DC-DC power supplies and electromechanical actuator circuits that may be used on board aircraft. Results show that unprotected MOSFET Gates are susceptible to failure, even when installed in systems in well-shielded and partial-shielded locations. MOSFET Drains and Sources are significantly less susceptible. Device impedance decreased (current increased) after every failure. Such a failure mode may lead to cascading failures, as the damaged MOSFET may allow excessive current to flow through other circuitry. Preliminary assessments on a MOSFET subjected to 20-stroke pin-injection testing demonstrate that Breakdown Voltage, Leakage Current and Threshold Voltage characteristics show damage, while the device continues to meet manufacturer performance specifications. The purpose of this research is to develop validated tools, technologies, and techniques for automated detection, diagnosis and prognosis that enable mitigation of adverse events during flight, such as from lightning transients; and to understand the interplay between lightning-induced surges and aging (i.e. humidity, vibration thermal stress, etc.) on component degradation. Author DEGRADATION; METAL OXIDE SEMICONDUCTORS; FIELD EFFECT TRANSISTORS; LIGHTNING; THERMAL STRESSES; THRESHOLD VOLTAGE; DIRECT CURRENT; ELECTROMECHANICAL DEVICES Additions to the NASA Aeronautics and Space Database as of 10/09/2009 20090033934 NASA Goddard Space Flight Center, Greenbelt, MD, United States The Astrophysics Science Division Annual Report 2008 Oegerle, William; Reddy, Francis; Tyler, Pat; March 2009; In English; Original contains color and black and white illustrations Contract(s)/Grant(s): NG07EK67C Report No.(s): NASA/TM-2009-214182; 200902507; Copyright; Avail.: CASI: A05, Hardcopy Avail Online: http://hdl.handle.net/2060/20090033934 The Astrophysics Science Division (ASD) at Goddard Space Flight Center (GSFC) is one of the largest and most diverse astrophysical organizations in the world, with activities spanning a broad range of topics in theory, observation, and mission and technology development. Scientific research is carried out over the entire electromagnetic spectrum from gamma rays to radio wavelengths as well as particle physics and gravitational radiation. Members of ASD also provide the scientific operations for three orbiting astrophysics missions WMAP, RXTE, and Swift, as well as the Science Support Center for the Fermi Gamma-ray Space Telescope. A number of key technologies for future missions are also under development in the Division, including X-ray mirrors, and new detectors operating at gamma-ray, X-ray, ultraviolet, infrared, and radio wavelengths. This report includes the Division's activities during 2008. Author ASTROPHYSICS; GAMMA RAY TELESCOPES; X RAY TIMING EXPLORER; COSMOLOGY; AEROSPACE SCIENCES 20090033997 NASA Goddard Space Flight Center, Greenbelt, MD, United States International VLBI Service for Geodesy and Astrometry 2008 Annual Report Behrend, Dirk; Baver, Karen D.; August 2009; In English; Original contains color and black and white illustrations Report No.(s): NASA/TP-2009-214183; Rept-200902253; Copyright; Avail.: CASI: A18, Hardcopy Avail Online: http://hdl.handle.net/2060/20090033997 This volume of reports is the 2008 Annual Report of the International VLBI Service for Geodesy and Astrometry (IVS). The individual reports were contributed by VLBI groups in the international geodetic and astrometric community who constitute the components of IVS. The 2008 Annual Report documents the work of these IVS components over the period January 1, 2008 through December 31, 2008. The reports document changes, activities, and progress of the IVS. The entire contents of this Annual Report also appear on the IVS Web site at http://ivscc.gsfc.nasa.gov/publications/ar2008. Author GEODESY; ASTROMETRY; VERY LONG BASE INTERFEROMETRY; GEOPHYSICS; RADIO ASTRONOMY; GEODYNAMICS; EARTH ORIENTATION 20090033998 Norwegian Defence Research Establishment, Norway FFI Technology Development Center - Software Development Andersen, Per Helge; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 31; In English Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090033998 FFI's contribution to the IVS as a Technology Development Center focuses primarily on the development and validation of the GEOSAT software for a combined analysis at the observation level of data from VLBI, GPS and SLR. This report shortly summarises the latest improvements of the GEOSAT software. FFI is currently an Analysis Center for IVS and ILRS, and a Technology Development Center for IVS Author VERY LONG BASE INTERFEROMETRY; COMPUTER PROGRAMS; SOFTWARE ENGINEERING; PROGRAM VERIFICATION (COMPUTERS); GLOBAL POSITIONING SYSTEM; GEOSAT SATELLITES; COMPUTER PROGRAMMING 20090033999 NASA Goddard Space Flight Center, Greenbelt, MD, United States GSFC Technology Development Center Report Himwich, Ed; Gipson, John; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 318-32; In English Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090033999 This report summarizes the activities of the GSFC Technology Development Center (TDC) for 2008 and forecasts planned activities for 2009. The GSFC TDC develops station software including the Field System, scheduling software (SKED), hardware including tools for station timing and meteorology, scheduling algorithms, and operational procedures. It provides a pool of individuals to assist with station implementation, check-out, upgrades, and training. 1. Technology Center Activities The GSFC IVS Technology Development Center (TDC) develops hardware, software, algorithms, and operational procedures. It provides manpower for station visits for training and upgrades. Other technology development areas at GSFC are covered by other IVS components such as the GSFC Analysis Center. The current staff of the GSFC TDC consists of John Gipson and Ed Himwich, both employed by NVI, Inc. The remainder of this report covers the status of the main areas of development that are currently being pursued. Author SOFTWARE ENGINEERING; COMPUTER PROGRAMS; MANPOWER; EDUCATION; ALGORITHMS 20090034000 Natural Resources Canada, Ottawa, Ontario, Canada Canadian VLBI Technology Development Center Petrachenko, Bill; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 315-31; In English; Original contains color illustrations Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034000 The Canadian VLBI Technology Development Center (TDC) is actively involved in theoretical studies to define recommendations for the VLBI2010 system. In addition, two development programs at the Dominion Radio Astrophysical Observatory (DRAO) are of potential interest to VLBI2010. Composite antennas that are light, stiff, and cost effective are being developed, and a state-of-the-art correlator is being developed for the EVLA. Author VERY LONG BASE INTERFEROMETRY; ASTROPHYSICS; OBSERVATORIES; GEODETIC SURVEYS; CORRELATORS; EARTH RESOURCES 20090034001 Onsala Space Observatory, Sweden Onsala Space Observatory - IVS Network Station Haas, Rudiger; Elgered, Gunnar; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 146-14; In English; Original contains black and white illustrations Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034001 During 2008 the Onsala Space Observatory contributed as an IVS Network Station to 38 VLBI sessions organized by the IVS. Additionally, we performed 27 ultra-rapid dUT1-sessions together with partner telescopes in Japan and Finland. This report briefly summarizes the activities during the year 2008. In 2008 the observatory was involved in the five IVS series EUROPE, R1, T2, RDV, and RD08 plus the CONT08 campaign. In total, Onsala participated and acquired useful observations in 38 experiments, see Table 2. All experiments were recorded on Mark 5 modules. Most of the experiments whose data were correlated at the Bonn correlator were additionally recorded in parallel on the PCEVN computer that is daisy-chained to the Mark 5 computer. The observed data of these experiments were then transferred electronically using the Tsunami protocol, and no Mark 5 modules were actually sent to Bonn. Radio interference due to UMTS mobile telephone signals continued to be a disturbing factor for the S-band observations. Additionally, we suffered from problems with the telescope encoders. Author RADIO FREQUENCY INTERFERENCE; VERY LONG BASE INTERFEROMETRY; SUPERHIGH FREQUENCIES; CORRELATORS; OBSERVATORIES; TSUNAMI WAVES; ULTRAHIGH FREQUENCIES 20090034002 Observatoire de Paris, France Paris Observatory (OPAR) Data Center Barache, Christophe; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 236-23; In English; Original contains color illustrations Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034002 This report summarizes the OPAR Data Center activities in 2008. Included is information about functions, architecture, status, future plans, and staff members of OPAR Data Center. The Paris Observatory (OPAR) has provided a Data Center for the International VLBI Service for Geodesy and Astrometry (IVS) since 1999. The OPAR as well as CDDIS and BKG is one of the three IVS Primary Data Centers. Their activities are done in close collaboration for the purposes of collecting files (data and analysis files), and making them available to the community as soon as they are submitted. The three data centers have a common protocol and each of them: has the same directory structure (with the same control file), has the same script, is able to receive all IVS files (auxiliary, database, products, documents), mirrors the other ones every three hours, gives free FTP access to the files. Author DATA ACQUISITION; VERY LONG BASE INTERFEROMETRY; DATA BASES; GEODESY; LIBRARIES; DIRECTORIES 20090034003 Naval Observatory, Washington, DC, United States U.S. Naval Observatory VLBI Analysis Center Boboltz, David A.; Fey, Alan L.; Bartlett, Jennifer L.; Dugan, Zachary; Kingham, Kerry A.; Hall, David M.; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 305-30; In English; Original contains black and white illustrations Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034003 This report summarizes the activities of the VLBI Analysis Center at the United States Naval Observatory for calendar year 2008. Over the course of the year, Analysis Center personnel analyzed biweekly 24-hour experiments with designations IVS-R1 and IVS-R4 for use in-house and continued timely submission of IVS-R4 databases for distribution to the IVS. During the 2008 calendar year, the USNO Analysis Center produced two periodic global Terrestrial Reference Frame (TRF) solutions with designations usn2008a and usn2008b. Earth orientation parameters (EOP) based on these solutions, updated by the latest 24-hour (IVS-R1 and IVS-R4) experiments, were submitted to the IVS. Other activities in the 2008 calendar year included the continued submission of Sinex files based on new 24-hour experiments to the IVS. For the Celestial Reference Frame (CRF), Analysis Center personnel continued a program designed to increase the sky density of ICRF sources, especially in the Southern Hemisphere. Activities included scheduling, analyzing and submitting databases for IVS-CRF experiments, and the production of global CRF solutions designated crf2008a and crf2008b. In addition, Analysis Center personnel performed research into the next generation ICRF-2 and a future high-frequency reference frame based on the VLBA K/Q-band experiments. Activities planned for the 2009 calendar year include the continued production of EOP/TRF/CRF global solutions and continued research into future reference frames. Author VERY LONG BASE INTERFEROMETRY; CELESTIAL REFERENCE SYSTEMS; EARTH ORIENTATION; EXTREMELY HIGH FREQUENCIES; PLASMA HEATING; STRUCTURAL ANALYSIS; OBSERVATORIES; NAVY 20090034004 Naval Observatory, Washington, DC, United States USNO Analysis Center for Source Structure Report Fey, Alan L.; Boboltz, David A.; Ojha, Roopesh; Gaume, Ralph A.; Kingham, Kerry A.; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 309-31; In English; Original contains color illustrations Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034004 This report summarizes the activities of the United States Naval Observatory Analysis Center for Source Structure for calendar year 2008. VLBA RDV experiments RDV67 and RDV69 were calibrated and imaged. Images from these two experiments, together with images from RDV14, RDV17, RDV19, and RDV22, were added to the USNO Radio Reference Frame Image Database. A Southern Hemisphere imaging and astrometry program for maintenance of the ICRF continued. Activities planned for the year 2009 include continued imaging of ICRF sources at standard and higher frequencies and continued analysis of source structure and its variation. Author VERY LONG BASELINE ARRAY (VLBA); CALIBRATING; RADIO FREQUENCY HEATING; IMAGING TECHNIQUES; ION CYCLOTRON RADIATION; ASTROMETRY; DATA BASES 20090034005 NASA Goddard Space Flight Center, Greenbelt, MD, United States CORE Operation Center Report Thomas, Cynthia C.; MacMillan, Daniel; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 195-19; In English Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034005 This report gives a synopsis of the activities of the Continuous Observations of the Rotation of the Earth (CORE) Operation Center from January 2008 to report forecasts activities planned for 2009. Author EARTH ROTATION; EARTH ORIENTATION 20090034006 Onsala Space Observatory, Sweden Onsala Space Observatory - IVS Analysis Center Haas, Ruediger; Scherneck, Georg; Nilsson, Tobias; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 295-29; In English; Original contains color illustrations Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034006 We briefly summarize the activities of the IVS Analysis Center at the Onsala Space Observatory during 2008 and give examples of results of ongoing work. 1. Introduction We concentrate on a number of research topics that are relevant for space geodesy and geosciences. These research topics are addressed in connection to data observed with geodetic VLBI and complementing techniques. Some topics are briefly presented in the following. Author VERY LONG BASE INTERFEROMETRY; OBSERVATORIES; GEOPHYSICS; GEODESY 20090034007 Italian Space Agency, Matera, Italy Matera CGS VLBI Analysis Center Lanotte, Roberto; Bianco, Giuseppe; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 253-25; In English Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034007 This paper reports the VLBI data analysis activities at the Space Geodesy Center (CGS) at Matera from January 2008 through December 2008 and the contributions that the CGS intends to provide for the future as an IVS Analysis Center. 1. General Information The Matera VLBI station became operational at the Space Geodesy Center (CGS) of the Italian Space Agency (ASI) in May 1990. Since then it has been active in the framework of the most important international programs. VLBI data analysis activities are performed at CGS for a better understanding of the tectonic motions with specific regard for the European area. The CGS, operated by Telespazio on behalf of ASI, provides full scientific and operational support using the main space geodetic techniques: VLBI, SLR and GPS. The main VLBI data analysis activities at the CGS in the year 2008 were directed towards the realization of a global VLBI solution, named asi2008a, using the CALC/SOLVE software (developed at the GSFC). The main characteristics of this solution are: Data span: 1979.08.03 - 2008.11.07 (3510 sessions) Estimated Parameters: Celestial Frame: right ascension and declination as global parameters for 637 sources Terrestrial Frame: Coordinates and velocities for 92 stations as global parameters Earth Orientation: Unconstrained X pole, Y pole, UT1, Xp rate, Yp rate, UT1 rate, dpsi and deps. Author VERY LONG BASE INTERFEROMETRY; GLOBAL POSITIONING SYSTEM; GEODESY; TECTONICS 20090034008 Deutsches Geodaetisches Forschungsinstut, Munich, Germany DGFI Analysis Center Annual Report 2008 Seitz, Manuela; Drewes, Hermann; Tesmer, Volker; Heinkelmann, Robert; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 255-25; In English; Original contains color and black and white illustrations Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034008 This report summarizes the activities of the DGFI Analysis Center in 2008 and outlines the planned activities for 2009. 1. General Information The German Geodetic Research Institute (Deutsches Geod atisches Forschungsinstitut, DGFI) is an autonomous and independent research institution located in Munich. It is run by the German Geodetic Commission (Deutsche Geod atische Kommission, DGK) at the Bavarian Academy of Sciences. The research covers all fields of geodesy and includes participation in national and international projects as well as functions in international bodies (see also http://www.dgfi.badw.de). Homogeneously reprocessed VLBI and GPS height series from 1994 to 2007 were compared. The data analysis used fully adapted state-of-the-art models (such as VMF1 and a priori zenith delays from ECMWF) for the GPS (at GFZ and at TUM with Bernese 5.1) and VLBI (at DGFI with OCCAM 6.1, LSM) processing. The series were compared in terms of long term non-linear behaviour and harmonic and mean annual signals (derived by averaging the positions of all years into one "mean year"). The mean annual signals are quite similar for VLBI and GPS (Figure 1), if the VLBI data is available with an appropriate density. The two almost independent observing techniques show the same mean annual signals at nearly all co-located sites. Therefore we assume that the annual signals can be geophysically interpreted as integral vertical deformations. In order to study regional effects, the stations of one region (with a dimension of some thousand kilometers) with a similar mean annual signal are grouped into a cluster. Accordingly 55 clusters are defined. To illustrate the clusters, and how diverse the signals from clustered sites can be, the results for the European region are displayed in Figure 2. They confirm that the signals reflect regional deformations, not local or technical artifacts. The most important findings from this study are that (1) for most sites, an annual harmonic function is not a sufficent approximation and that (2) the variations of station heights are regional effects and are induced by mass load variations. For each of the 55 clusters, a regional average mean annual signal was computed. They can be used as a tool to validate geophysical models. 2. Atmospheric loading coefficients determined Author VERY LONG BASE INTERFEROMETRY; GEODESY; GLOBAL POSITIONING SYSTEM; HARMONIC FUNCTIONS; WEATHER FORECASTING; POLLUTION TRANSPORT; GEOPHYSICS 20090034009 Massachusetts Inst. of Tech., Westford, MA, United States Haystack Observatory VLBI Correlator Titus, Mike; Cappallo, Roger; Corey, Brian; Dudevoir, Kevin; Niell, Arthur; Whitney, Alan; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 205-20; In English; Original contains color illustrations Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034009 This report summarizes the activities of the Haystack Correlator during 2008. Highlights include correlation of many broadband delay (VLBI2010) experiments and installation at WACO of the correlator run-time software that had been converted to Linux. Problems with bad disks and serial links were investigated. Real-time e-VLBI development for Mark 5B, non-real-time e-VLBI transfers, and engineering support of other correlators continued. Author VERY LONG BASE INTERFEROMETRY; CORRELATORS; BROADBAND; REAL TIME OPERATION; UNIX (OPERATING SYSTEM) 20090034011 Shanghai Astronomical Observatory, China SHAO Analysis Center 2008 Annual Report Li, Jinling; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 302-30; In English Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034011 Our research activities in 2008 are related to astrometric and geodetic VLBI experiments and data analysis, the astrometry of massive star-forming regions and luminous red supergiants, the processing of VLBI tracking data of satellites, and antenna site surveys. These activities will be continued in the next year. We will prepare software for the next Chinese lunar and Martian exploration projects. Author ASTROMETRY; LUNAR EXPLORATION; GEODESY; VERY LONG BASE INTERFEROMETRY; MARS (PLANET); MASSIVE STARS; DIRECTIONAL ANTENNAS 20090034012 NASA Goddard Space Flight Center, Greenbelt, MD, United States CDDIS Data Center Summary for the IVS 2008 Annual Report Noll, Carey; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 227-22; In English Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034012 This report summarizes activities during the year 2008 and future plans of the Crustal Dynamics Data Information System (CDDIS) with respect to the International VLBI Service for Geodesy and Astrometry (IVS). Included in this report are background information about the CDDIS, the computer architecture, staff supporting the system, archive contents, and future plans for the CDDIS within the IVS. 1. Introduction The Crustal Dynamics Data Information System (CDDIS) has supported the archiving and distribution of Very Long Baseline Interferometry (VLBI) data since its inception in 1982. The CDDIS is a central facility providing users access to raw and analyzed data to facilitate scientific investigation. The CDDIS archive of GNSS (GPS and GLONASS), laser ranging, VLBI, and DORIS data is stored on-line for remote access. Information about the system is available via the Web at the URL http://cddis.gsfc.nasa.gov. The current and future plans for the system s support of the IVS are discussed below. Author VERY LONG BASE INTERFEROMETRY; GLOBAL POSITIONING SYSTEM; INFORMATION SYSTEMS; ON-LINE SYSTEMS; DATA SYSTEMS; LASER RANGING; ASTROMETRY 20090034013 Academy of Sciences (Russia), Saint Petersburg, Russian Federation Zelenchukskaya Radio Astronomical Observatory Dyako, Andrei; Smolentsev, Sergey; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 188-19; In English; Original contains black and white illustrations Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034013 This report briefly summarizes the observational activities at the Zelenchukskaya 32-m VLBI station during the year 2008. 1. General Information Zelenchukskaya Radio Astronomical Observatory was founded by Institute of Applied Astron- omy (IAA) as one of three stations of the Russian VLBI network QUASAR. The sponsoring organization of the project is the Russian Academy of Sciences (RAS). The Zelenchukskaya Radio Astronomical Observatory is situated in Republic Karachaevo-Cherkessiya (Northern Caucasia) about 70 km south of Cherkessk, near to the Zelenchukskaya site (not far from Radiotelescope RATAN-600). The geographic location of the observatory is shown on the IAA RAS Web site: http://www.ipa.nw.ru/PAGE/koi8-r/DEPOBSERV/rus zel.htm. The basic instruments of the ob- servatory are a 32-m radio telescope and technical systems for doing VLBI observations. Author RADIO TELESCOPES; RADIO ASTRONOMY; ASTRONOMICAL OBSERVATORIES; POSITION (LOCATION); VERY LONG BASE INTERFEROMETRY 20090034014 Forschungseinrichtung Satellitengeodaesie (FENG), Wettzell, Germany Fundamentalstation Wettzell - 20m Radiotelescope Neidhardt, Alexander; Kronschnabl, Gerhard; Schatz, Raimund; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 180-18; In English; Original contains color illustrations Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034014 The 20m-radiotelescope at Wettzell, Germany again contributed very successfully and strongly to the IVS observing program in 2008. Technical changes, improvements, and upgrades were made to increase the reliability of the entire VLBI observing system. Author RADIO TELESCOPES; VERY LONG BASE INTERFEROMETRY; GLOBAL POSITIONING SYSTEM; LUNAR RANGEFINDING; METEOROLOGICAL PARAMETERS; SATELLITE LASER RANGING; GEODETIC SURVEYS; GRAVIMETERS 20090034015 Observatorio Astronomico Nacional, Alcala de Henares, Spain Instituto Geografico Nacional of Spain Colomer, Francisco; deVicente, Pablo; Gomez-Gonzalez, Jesus; Lopez-Fernandez, Jose Antonio; Espada, Susana Garcia; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 184-18; In English; Original contains color illustrations Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034015 This report updates the description of the OAN facilities as an IVS network station. The new 40-m radiotelescope performed the first geodetic VLBI observations in September 2008. While commissioning for other frequencies is in progress, the instrument will participate regularly in IVS campaigns in 2009. 1. General Information: the IGN Facilities at OAN-Yebes The Observatorio Astron omico Nacional (OAN) of Spain is a department of the Instituto Geografico Nacional (IGN, Ministerio de Fomento) and operates a new 40-m radiotelescope at Yebes (Guadalajara, Spain). The facility also includes an old 14-m radiotelescope, which was a network station of the IVS and participated regularly in the geodetic VLBI campaigns until 2003. It is being refurbished to become a tracking station for the next space radiotelescope VSOP-2. Yebes is also the reference station for the Spanish GPS network. A building has been finished to hold the IGN gravimeters. Author GLOBAL POSITIONING SYSTEM; GRAVIMETERS; RADIO TELESCOPES; VERY LONG BASE INTERFEROMETRY; TRACKING STATIONS; GEODESY 20090034016 Massachusetts Inst. of Tech., Westford, MA, United States IVS Technology Coordinator Report Whitney, Alan; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 89-9; In English Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034016 In 2008 the Technology Coordinator was active in the following areas: 1) support of work to implement a new geodetic VLBI system as outlined in the IVS Working Group 3 VLBI2010 study, 2) continued development and deployment of e-VLBI, 3) organization of the 7th Annual e-VLBIWorkshop held at Shanghai Observatory in Shanghai, China, and 4) development of the VLBI Data Interchange Format (VDIF) specification. We will briefly describe each of these activities. Author VERY LONG BASE INTERFEROMETRY; GEODESY; DEPLOYMENT 20090034017 Bundesamt fuer Kartographie und Geodaesie, Frankfurt am Main, Germany German Antarctic Receiving Station (GARS) O'Higgins Ploetz, Christian; Wojdziak, Reiner; Kilger, Richard; Neidhardt, Alexander; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 142-14; In English; Original contains color illustrations Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034017 In 2008 the German Antarctic Receiving Station (GARS) in O'Higgins contributed to the IVS observing program with 10 observation sessions. The timing system was enhanced with a rubidium clock, and the cesium clock was reinstated after repair. First VLBI sessions were completely remote-controlled by starting, attending, and finishing them from Wettzell observatory using a remote extension developed for the Field System at Wettzell. Author OBSERVATORIES; VERY LONG BASE INTERFEROMETRY; TIME MEASUREMENT; TIMING DEVICES 20090034018 Norwegian Mapping Authority, Honefoss, Norway Ny-Alesund 20-Meter Antenna Ardal, Ole Bjorn; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 139-14; In English Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034018 For the year 2008, the 20-meter VLBI antenna at the Geodetic Observatory, Ny-Alesund, has participated in VLBI experiments, observing 68 of 78 scheduled 24-hour experiments and 36 of 45 scheduled Intensives. Reasons for the lost experiments were the personnel situation and some problems with the dewar/coldhead during spring. Several experiments also had to be run with a warm receiver due to the latter problem. During fall there was a problem with the X-Band cable and the local oscillator that had to be changed. In 2008, Ny-Alesund was a three-person station until July when Inge Sanden s contract ended and then continued as a two-person station until the CONT08, when Inge Sanden and Svein Rekkedal helped out for some time. After CONT08, until mid-September, the station was only manned by one person followed by a brief period of no observations due to a lack of operators. Ole Bjorn Ardal s contract ended in the end of August, and he agreed on a new one-year contract starting in the end of September. Helge Digre's contract also ended this year. With no renewal, he finished his contract period on 31 October after having worked 11 years for the NMA. In October two new operators were employed and started their training: Carl Petter Nielsen and Geir Mathiassen, both on part-time contracts. Their work schedule is basically three months of work followed by one month off. This caused the station to become a two-person station during December, except for Christmas when only one person manned the station. From July on, except for August, the maintenance and repair were done at a minimum level, given the personnel situation. No responses were made to any alarms, and no errors were corrected during unmanned operation. Ny-Alesund is a Mark 5A station. Author GEODESY; VERY LONG BASE INTERFEROMETRY; ANTENNAS; GRAVIMETRY 20090034019 Bonn Univ., Germany The Bonn Geodetic VLBI Operation Center Nothnagel, A.; Mueskens, A.; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 193-19; In English; Original contains color illustrations Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034019 The IGGB Operation Center has continued to organise and schedule the IVS-T2, IVS-OHIG, IVS-INT3, and EUROPE sessions. 1. Center Activities The IGGB VLBI Operation Center is located at the Institute of Geodesy and Geoinformation of the University of Bonn, Nussallee 17, D-53115 Bonn, Germany. It has been organizing and scheduling VLBI observing sessions for more than twenty years. The observing series organized and scheduled in 2008 are the same as in 2007. Author GEODESY; SCHEDULING; VERY LONG BASE INTERFEROMETRY; SCHEDULES 20090034020 Academy of Sciences of the Ukraine, Kiev, Ukraine IVS Analysis Center at Main Astronomical Observatory of National Academy of Sciences of Ukraine Bolotin, Sergei; Lytvyn, Svitlana; Yatskiv, Yaroslav; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 285-28; In English Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034020 This report summarizes the activities of the VLBI Analysis Center at the Main Astronomical Observatory of the National Academy of Sciences of Ukraine in 2008. 1. Introduction The VLBI Analysis Center was established in 1994 by the Main Astronomical Observatory (MAO) of the National Academy of Sciences of Ukraine (NASU) as a working group of the Department of Space Geodynamics of the MAO. In 1998 the group started its IVS membership as an IVS Analysis Center. The AC MAO is located in the Central office of the observatory in Kiev. Author ASTRONOMICAL OBSERVATORIES; VERY LONG BASE INTERFEROMETRY; GEODYNAMICS; ALTERNATING CURRENT 20090034021 Korea Astronomy and Space Science Inst., Korea, Republic of KASI Combination Center Report Cho, Jungho; Kwak, Younghee; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 283-28; In English; Original contains color illustrations Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034021 This report introduces the Korea Astronomy and Space Science Institute (KASI) and describes the planned activities of the KASI as an IVS Combination Center. 1. General Information The proposal of the Korea Astronomy and Space Science Institute (KASI) for becoming an IVS combination center was accepted on October 21, 2008. KASI is one of the affiliated organizations of IVS. KASI Headquarters is located in the Daeduk research and development complex, Daejeon. The Space Geodesy research of KASI was started in 1992 with GPS. Now the KASI Space Geodesy research division is composed of three groups including the Earth Observing System (EOS) research group. The EOS research areas are based on Space Geodetic techniques such as GNSS, VLBI, SLR and Gravimeter and are focused on the changes of the Earth s shape and its geodynamics. The EOS research group also works on the applications of Space Geodesy such as an early warning system of natural hazards. The EOS group will be in charge of an IVS combination center as an extension of research on the Earth s shape changes Author GLOBAL POSITIONING SYSTEM; EARTH OBSERVING SYSTEM (EOS); EARLY WARNING SYSTEMS; GEODESY; GEODYNAMICS; GRAVIMETERS; VERY LONG BASE INTERFEROMETRY 20090034022 National Inst. of Information and Communications Technology, Ibaraki, Japan Analysis Center at National Institute of Information and Communications Technology Hobiger, Thomas; Takiguchi, Hiroshi; Ichikawa, Ryuichi; Sekido, Mamoru; Koyama, Yasuhiro; Kondo, Tetsuro; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 287-29; In English; Original contains black and white illustrations Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034022 This report summarizes the activities of the Analysis Center at the National Institute of Information and Communications Technology (NICT) for the year 2008. 1. General Information The NICT Analysis Center is located in Kashima, Ibaraki, Japan and is operated by the spacetime standards group of NICT. Analysis of VLBI experiments and related study fields at NICT are mainly concentrated on experimental campaigns for developing new techniques such as e-VLBI for real-time EOP determination, prototyping of a compact VLBI system, time and frequency transfer, atmospheric path delay studies, and improvement of the accuracy of space geodetic techniques. Author SPACE-TIME FUNCTIONS; GEODESY; INFORMATION SYSTEMS; REAL TIME OPERATION; VERY LONG BASE INTERFEROMETRY 20090034023 Istituto di Radioastronomia, Bologna, Italy Noto Station Status Report Tuccari, G.; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 136-13; In English; Original contains color illustrations Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034023 This brief report summarizes the main activities of the Observatory of Noto in 2008. Author OBSERVATORIES; ANTENNAS; DIGITAL TECHNIQUES 20090034024 NASA Goddard Space Flight Center, Greenbelt, MD, United States; Kokee Park Geophysical Observatory, Waimea, HI, United States Kokee Park Geophysical Observatory Kim, Kelly; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 122-12; In English; Original contains color illustrations Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034024 This report summarizes the technical parameters and the staff of the VLBI system at Kokee Park Kauai. Author VERY LONG BASE INTERFEROMETRY; GEODESY 20090034025 Academy of Sciences (Russia), Saint Petersburg, Russian Federation Badary Radio Astronomical Observatory Smolentsev, Sergey; Sergee, Roman; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 95-9; In English; Original contains color and black and white illustrations Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034025 This report provides information about the Badary network station: general information, facilities, staff, present status and outlook. Author RADIO TELESCOPES; VERY LONG BASE INTERFEROMETRY; ASTRONOMICAL OBSERVATORIES; QUASARS 20090034026 Istituto di Radioastronomia, Bologna, Italy The Medicina Station Status Report Orfei, Alessandro; Orlati, Andrea; Maccaferri, Giuseppe; Mantovani, Franco; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 130-13; In English; Original contains color illustrations Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034026 General information about the Medicina Radio Astronomy Station, the 32m antenna status, and the staff in charge of VLBI observations are provided. In 2008 the data from geodetic VLBI observations were acquired using the Mark 5A recording system with good results. Updates of the hardware have been performed and are briefly described. Author GEODETIC SURVEYS; RADIO ASTRONOMY; VERY LONG BASE INTERFEROMETRY; ANTENNAS; GEODESY 20090034027 Italian Space Agency, Matera, Italy Matera CGS VLBI Station Bianco,Giuseppe; Colucci, Giuseppe; Schiavone, Francesco; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 126-12; In English; Original contains color illustrations Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034027 This report describes the status of the Matera VLBI station. Also an overview of the station, some technical characteristics of the system and staff addresses are given. Author VERY LONG BASE INTERFEROMETRY; RADIO ASTRONOMY; RADIO ANTENNAS 20090034028 Jet Propulsion Lab., California Inst. of Tech., Pasadena, CA, United States JPL VLBI Analysis Center Report for 2008 Jacobs, Chris; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 272-28; In English; Original contains color illustrations Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034028 This report describes the activities of the JPL VLBI analysis center for the year 2008. We continue to do celestial reference frame, terrestrial reference frame, earth orientation, and spacecraft navigation work using the VLBI technique. There are several areas of our work that are undergoing active development. An important development was moving our earth orientation and reference frame work completely to Mark 5A recording and software correlation by the end of 2008. Our international collaboration to build celestial frames at K- (24 GHz) and Q-bands (43 GHz) matured to near a part-per-billion accuracy as documented in two submitted papers. Our in-house work to build a reference at X/Ka-bands (8.4/32 GHz) is also close to ppb accuracy. We supported the Phoenix Mars lander and other missions with VLBI navigation measurements. We continue to study ways to improve spacecraft tracking using VLBI techniques. Author VERY LONG BASE INTERFEROMETRY; CELESTIAL REFERENCE SYSTEMS; EARTH ORIENTATION; SPACE NAVIGATION; SUPERHIGH FREQUENCIES 20090034029 Academy of Sciences (Russia), Saint Petersburg, Russian Federation IAA VLBI Analysis Center Report 2008 Skurikhina, Elena; Kurdubov, Sergey; Gubanov, Vadim; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 269-27; In English; Original contains black and white illustrations Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034029 This report presents an overview of IAA VLBI Analysis Center activities during 2008 and the plans for the coming year. 1. General Information The IAA IVS Analysis Center (IAA AC) is located at the Institute of Applied Astronomy of the Russian Academy of Sciences in St. Petersburg, Russia. IAA AC contributes to IVS products, such as daily SINEX files, TRF, CRF, rapid and long-term series of EOP, baseline length, and tropospheric parameters. Source position time series and CRF have been calculated within the scope of the IERS/IVS Working Group on the Second Realization of the ICRF. Several ways of source selection with NNR constraints were proposed and tested. EOP, UT1-UTC, and station positions were estimated from domestic observation programs RU-E and RU-U. AC IAA generates NGS files. Author INFORMATION SYSTEMS; PLASMA HEATING; RADIO FREQUENCY HEATING; TIME SERIES ANALYSIS; VERY LONG BASE INTERFEROMETRY; ION CYCLOTRON RADIATION 20090034030 Natural Resources Canada, Ottawa, Ontario, Canada Design Aspects of the VLBI2010 System - Progress Report of the IVS VLBI2010 Committee Petrachenko, Bill; Niell, Arthur; Behrend, Dirk; Corey, Brian; Bohm, Johannes; Charlot, Patrick; Collioud, Arnaud; Gipson, John; Haas, Rudiger; Hobiger, Thomas; Koyama, Yasuhiro; MacMillan, Dan; Malkin, Zinovy; Nilsson, Tobias; Pany, Andrea; Tuccari, Gino; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 13-6; In English; Original contains color illustrations Copyright; Avail.: CASI: A04, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034030 In September 2005 the IVS Directing Board accepted the final report of its Working Group 3 (WG3) entitled wVLBI2010: Current and Future Requirements for Geodetic VLBI Systems . This bold vision for the future recommended a review of all current VLBI systems and processes from antennas to analysis and outlined a path to a next-generation system with unprecedented new capabilities: h 1-mm position accuracy on global scales, h continuous measurements for time series of station positions and Earth orientation parameters, h turnaround time to initial geodetic results of less than 24 hours. Immediately following the acceptance of the WG3 final report, the IVS established the VLBI2010 Committee (V2C) to carry out a series of studies recommended by WG3 and to encourage the realization of the new vision for geodetic VLBI. Since its inception, the V2C has accomplished much towards this goal. This report summarizes the work of the committee through the end of 2008. Author VERY LONG BASE INTERFEROMETRY; TIME SERIES ANALYSIS; GEODESY; EARTH ORIENTATION; POSITION ERRORS 20090034031 Academia Sinica, Urumqi, China Nanshan VLBI Station Report for 2008 Yusup, Aili; Liu, Xiang; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 173-17; In English Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034031 The Nanshan 25-meter radio telescope is operated by Urumqi Observatory. This report describes the activities and the status of Nanshan VLBI station as an IVS network station in 2008. 1. Introduction The station is located 70 km south of Urumqi, the capital city of Xinjiang Uygur Autonomous Region of China. The station is affiliated with the Urumqi Observatory of the National Astronom- ical Observatories, CAS. We contribute to IVS in geodetic VLBI observations. The Nanshan VLBI station has participated in domestic VLBI experiments and as one of the VLBI ground stations tracking the Chinese Chang E satellite. Urumqi also participated in the Japanese SELENE obser- vations. The telescope participated in real-time experiments among the Chinese VLBI Network. We are grateful for the kind help and support from the VLBI experts within the IVS community. The Urumqi Observatory is willing to continue the collaboration in international VLBI activities. Author REAL TIME OPERATION; RADIO TELESCOPES; GEODETIC SURVEYS; VERY LONG BASE INTERFEROMETRY; AUTONOMY; GROUND STATIONS 20090034032 National Astronomical Observatory, Oshu, Japan VERA Geodetic Activities Jike, Takaaki; Manabe, Seiji; Tamura, Yoshiaki; Shizugami, Makoto; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 132-13; In English; Original contains color and black and white illustrations Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034032 This report describes the status of the VERA network in the context of geodetic VLBI. The main about its technical parameters and a summary of its geodetic VLBI activities Author GEODESY; VERY LONG BASE INTERFEROMETRY; RADIO ASTRONOMY 20090034033 National Inst. of Information and Communications Technology, Japan Kashima 34-m Radio Telescope Kawai, Eiji; Sekido, Mamoru; Ichikawa, Ryuichi; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 114-11; In English; Original contains color and black and white illustrations Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034033 The Kashima 34-m radio telescope is continuously operated and maintained by the National In- stitute of Information and Communications Technology (NICT) as a facility of the Kashima Space Research Center (KSRC) in Japan. This brief report summarizes the status of this telescope, the staff and activities during 2008. The Kashima 34-m radio telescope (Figure 1 left) was constructed as a main station of the "Western Pacific VLBI Network Project" in 1988. After that project s termination, the telescope has been used not only for geodetic purposes but also for astronomy and other purposes. The station is located about 100 km east of Tokyo, Japan and co-located with the 11-m radio telescope and the International GNSS Service station (KSMV) (Figure 1 right). This station is maintained by the Space-Time Measurement Project of the Space-Time Standards Group of KSRC, NICT. Author VERY LONG BASE INTERFEROMETRY; RADIO TELESCOPES; GEODESY; INFORMATION SYSTEMS 20090034034 Istituto di Radioastronomia, Bologna, Italy Italy INAF Data Center Report Neguisini, M.; Sarti, P.; Abbondanza, C.; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 230-23; In English Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034034 This report summarizes the activities of the Italian INAF VLBI Data Center. Our Data Center is located in Bologna, Italy, and belongs to the Institute of Radioastronomy, which is part of the National Institute of Astrophysics. We also report about some changes in the hardware facilities devoted to IVS activities. Author VERY LONG BASE INTERFEROMETRY; GLOBAL POSITIONING SYSTEM; DATA BASES; GEODESY; ASTROPHYSICS 20090034035 Geographical Survey Inst., Tsukuba, Japan Tsukuba 32-m VLBI Station Tanimoto, Daisuke; Kurihara, Shinobu; Kokado, Kensuke; Matsuzaka, Shigeru; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 169-17; In English; Original contains color and black and white illustrations Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034035 The Tsukuba 32-m radio telescope is operated by the Geographical Survey Institute (GSI) VLBI group. This report summarizes the current status and the future plans of the Tsukuba 32-m VLBI station. We participated in a total of 208 domestic and international VLBI sessions in accordance with the IVS 2008 observing plan. The CONT08 campaign in August was the highlight of the year. In experimental sessions in 2008, we achieved an extremely rapid UT1 measurement latency of 3 minutes 45 seconds for an ultra-rapid dUT1 experiment in February. We started 32 Mbps/ch observing using K5/VSSP32 this year. The Tsukuba 32-m VLBI station (TSUKUB32) is located at GSI in Tsukuba Science City, which is about 50 km to the northeast of the capital Tokyo. GSI has four VLBI stations; TSUKUB32, AIRA, CHICHI10, and SINTOTU3. These four stations form our domestic VLBI network named GARNET (GSI Advanced Radio telescope NETwork). We have performed our domestic VLBI observations using GARNET. One series of sessions is named JADE (JApanese Dynamic Earth observation by VLBI). The main purposes of the JADE series are to define the reference frame of Japan and to monitor the plate motions for the advanced study of crustal deformations. The GARNET stations, centered on TSUKUB32, are located to cover the Japanese mainland. The GARNET stations other than TSUKUB32 joined international VLBI sessions this year. Author VERY LONG BASE INTERFEROMETRY; RADIO TELESCOPES; EARTH OBSERVATIONS (FROM SPACE); DYNAMIC TESTS; DEFORMATION; CRUSTS; COORDINATES 20090034036 Massachusetts Inst. of Tech., Westford, MA, United States Westford Antenna Poirier, Mike; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 176-17; In English; Original contains color illustrations Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034036 Technical information is provided about the antenna and VLBI equipment at the Westford site of Haystack Observatory and about changes to the systems since the IVS 2007 Annual Report. 1. Westford Antenna at Haystack Observatory Since 1981 the Westford antenna has been one of the primary geodetic VLBI sites in the world. Located 70 km northwest of Boston, Massachusetts, the antenna is part of the MIT Haystack Observatory complex. The Westford antenna was constructed in 1961 as part of the Lincoln Laboratory Project West Ford that demonstrated the feasibility of long-distance communication by bouncing radio signals off a spacecraft-deployed belt of copper dipoles at an altitude of 3,600 km. In 1981 the antenna was converted to geodetic use as one of the first two VLBI stations in the National Geodetic Survey Project POLARIS. Westford has continued to perform geodetic VLBI observations on a regular basis since 1981. Westford has also served as a test bed in the development of new equipment and techniques now employed in geodetic VLBI worldwide. Primary funding for geodetic VLBI at Westford is provided by the NASA Space Geodesy Program. Author RADIO SIGNALS; VERY LONG BASE INTERFEROMETRY; ANTENNAS; GEODETIC SURVEYS; GEODESY; OBSERVATORIES; RADOMES 20090034037 Deutsches Geodaetisches Forschungsinstut, Munich, Germany; Bundesamt fuer Kartographie und Geodaesie, Frankfurt am Main, Germany BKG/DGFI Combination Center Annual Report 2008 Scwegmann, Wolfgang; Gerstl, Michael; Heinkelmann, Robert; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 250-25; In English Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034037 This report summarizes the activities of the BKG/DGFI Combination Center in 2008 and outlines the planned activities for the year 2009. 1. General Information The BKG/DGFI Combination Center has been established jointly by the Federal Agency for Cartography and Geodesy (Bundesamt f ur Kartographie und Geod asie, BKG) and the German Geodetic Research Institute (Deutsches Geod atisches Forschungsinstitut, DGFI). BKG is a German federal authority assigned to the Federal Ministry of the Interior. Its tasks include, among others, the provision of geodetic reference data and basic spatial data for the needs of the Federal Government-the administrative, economic, and scientific sectors-as well as for the citizens. DGFI is an autonomous and independent research institution located in Munich. It is run by the German Geodetic Commission (Deutsche Geod atische Kommission, DGK) at the Bavarian Academy of Sciences. The research covers all fields of geodesy and includes the participation in national and international projects as well as functions in international bodies. The joint BKG/DGFI Combination Center was inaugurated by the IVS Directing Board in October 2008. The tasks of this IVS Combination Center include quality control and a timely combination of the session-based intermediate results of the IVS Analysis Centers into a final combination product (e.g., Earth Orientation Parameters, EOP). After consultation with the IVS Analysis Coordinator, the combination results will be released as official IVS products. The Combination Center is also expected to contribute to the generation of the official IVS input to any ITRF activities. These tasks should be performed on an operational basis. Author EARTH ORIENTATION; QUALITY CONTROL; ECONOMICS; GEODESY; AUTONOMY 20090034038 Wien Univ., Austria Vienna IGG Special Analysis Center Annual Report 2008 Schuh, Harald; Boehm, Johannes; Englich, Sigrid; Heinkelmann, Robert; MendesCerveira, Paulo Jorge; Pany, Andrea; Plank, Lucia; Spicakova, Hana; Teke, Kamil; Wresnik, Joerg; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 273-27; In English; Original contains color illustrations Contract(s)/Grant(s): Proj. P16992-N10; Proj. P18404-N10; Proj. 22353; SCHU 1103/301 Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034038 The main activities of the Institute of Geodesy and Geophysics (IGG) at the Vienna University of Technology in 2008 have been the contribution to the VLBI2010 simulations and the development of new VLBI software based on Matlab. Furthermore, studies about Earth rotation and reference frames have been continued. 1. General Information The Institute of Geodesy and Geophysics (IGG) is part of the Faculty of Mathematics and Geoinformation of the Vienna University of Technology. It is divided into three research units, one of them focusing on advanced geodesy (mathematical and physical geodesy, space geodesy). Within this research unit, one group (out of four) is dealing with geodetic VLBI. Author GEOPHYSICS; VERY LONG BASE INTERFEROMETRY; COMPUTER PROGRAMMING; GEODESY 20090034039 Istituto di Radioastronomia, Bologna, Italy Italy INAF Analysis Center Report Negusini, M.; Sarti, P.; Abbondanza, C.; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 277-27; In English Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034039 This report summarizes the activity of the Italian INAF VLBI Analysis Center. Our Analysis Center is located in Bologna, Italy and belongs to the Institute of Radioastronomy, which is part of the National Institute of Astrophysics. IRA runs the observatories of Medicina and Noto, where two 32 m VLBI AZ-EL telescopes are situated. This report contains the AC s VLBI data analysis activities and shortly outlines the investigations carried out at Medicina and Noto concerning gravitational deformations of the VLBI telescopes. 1. Current Status and Activity Data analysis of terrestrial surveys carried out during 2008 focused on the investigation of deformation under the effects of gravity and, in particular, on the possibility of inferring a general model for gravitational deformations of large VLBI telescopes. The strategy used relies on the combination of different metrological approaches applied to the antennas: on one hand, classical terrestrial surveys executed via forward intersections on some specific targets located on the tele- scope s primary reflector and on the quadrupod; on the other, laser scanning surveys which allow analysts to infer a more continuous representation of the parabolic mirror deformation. A third kind of information was derived from Finite Element Modelling (FEM) which provides a scenario of feasible deformations of the antenna structure at its peculiar nodes under the influence of its own weight. The joint usage of these data types permitted us to identify, quantify and detach the effects of gravitational deformations: according to [1], these latter can be decomposed into a (i) paraboloid s vertex displacement, (ii) relative motion of the S/X receivers placed in the primary focus with respect to the antenna primary reflector, (iii) a focal length variation induced by deformations of the VLBI reflector. This combination approach might offer valuable help for estimating a signal path variation model induced by gravity to be applied within VLBI data processing. Concerning the laser scanning measurement analysis, a specific focal length variation model, valid for the Medicina and Noto antennas, was derived with the aim of supplying a model which can account for the relative change in focal length as the VLBI antenna is steered in elevation; results of these considerations can be found in [2], which has been reviewed and is in the course of publication Author RADIO ASTRONOMY; VERY LONG BASE INTERFEROMETRY; GRAVITATIONAL EFFECTS; ASTROPHYSICS; METROLOGY; LASER APPLICATIONS; FINITE ELEMENT METHOD; ALTERNATING CURRENT 20090034040 Bonn Univ., Germany Analysis Coordinator Report Nothnagel, A.; Boeckmann, S.; Artz, T.; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 80-8; In English; Original contains black and white illustrations Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034040 IVS analysis coordination issues in 2008 are reported here. Routine EOP combinations on the basis of datum-free normal equations have been continued. For this, it was necessary to compute a new realization of a terrestrial reference frame. Investigations have been carried out on certain quality aspects of the IVS EOP series. 1. General Issues The "Ninth IVS Analysis Workshop" was held at the Institute of Applied Astronomy, St. Petersburg, Russia, on March 7, 2008, in connection with the Fifth IVS General Meeting. The workshop was attended by more than 40 participants who enjoyed being hosted by the IAA with an impressive look onto the still winterly Neva. More details on the workshop can be found in Nothnagel (2008a). Author TIME SERIES ANALYSIS; COORDINATES; LOGISTICS; MATRICES (MATHEMATICS); VARIANCE (STATISTICS); UNIVERSAL TIME; DERIVATION 20090034041 TIGO, Chile Geodetic Observatory TIGO in Concepcion Sobarzo, Sergio; Onate, Eric; Jara, Cristobal; Herrera, Cristian; Zaror, Pedro; Duguet, Cristian; Soto, Miguel; Hase, Hayo; Boeer, Armin; Sierk, Bernd; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 165-16; In English; Original contains color and black and white illustrations Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034041 During the seventh year of operation in Chile, TIGO carried out 110 successful VLBI observations. Activities of the VLBI group at TIGO during 2008 and an outlook for 2009 are given. Author VERY LONG BASE INTERFEROMETRY; OBSERVATORIES; GEODESY; LATITUDE; LONGITUDE 20090034042 NVI, Inc., Greenbelt, MD, United States Network Coordinator Report Himwich, Ed; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 83-8; In English Copyright; Avail.: CASI: A02, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034042 This report includes an assessment of the network performance in terms of lost observing time for the 2008 calendar year. Overall, the observing time loss was about 15.1%, an increase of about 3.7% from the previous year. A table of relative incidence of problems with various subsystems is presented. The most significant identified causes of loss were antenna reliability (accounting for about 19.2%), RFI (14.8%), and receiver problems (13.8%), Unidentified problems accounted for about 17.7% of the loss. There are prospects for Korea, India, and New Zealand to start contributing to IVS. New antennas are being purchased by Australia and New Zealand. Author COMPUTER NETWORKS; VERY LONG BASELINE ARRAY (VLBA); INFORMATION SYSTEMS; CORRELATORS; LIBRARIES 20090034043 Auckland Univ., New Zealand New Zealand 12-m VLBI Station for Geodesy and Astronomy Gulyaev, Sergei; Natusch, Tim; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 68-7; In English; Original contains color and black and white illustrations Copyright; Avail.: CASI: A02, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034043 This report summarizes the radio astronomical and VLBI activities recently started in New Zealand. It provides geographical and technical details of a new 12-m geodetic VLBI antenna being operated by Auckland University of Technology. Details of the VLBI system to be installed in the station are outlined. A co-located GNSS station and specialized surveying equipment are also described. 1. Introduction The IVS report [1] proposes a number of strategies to improve the long-term accuracy of geodetic VLBI with an eye to achieving 1 mm long-term accuracy on baselines. Among these strategies are: "to increase the number of antennas and improve their geographic distribution" and "to increase the number of observations per unit of time". These IVS strategies can best be addressed through construction of new small (10-12 m), fast moving antennas in areas that are under-represented (Australia) or lack geodetic VLBI stations (New Zealand). Author ASTRONOMY; VERY LONG BASE INTERFEROMETRY; CONSTRUCTION; SURVEYS; GEODESY 20090034044 NVI, Inc., Greenbelt, MD, United States Coordinating Center Report Behrend, Dirk; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 77-7; In English; Original contains color illustrations Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034044 This report summarizes the activities of the IVS Coordinating Center during the year 2008 and forecasts activities planned for the year 2009. 1. Coordinating Center Operation The IVS Coordinating Center is based at the Goddard Space Flight Center and is operated by NEOS (National Earth Orientation Service), a joint effort for VLBI by the U.S. Naval Observatory and the NASA Goddard Space Flight Center. The mission of the Coordinating Center is to provide communications and information for the IVS community and the greater scientific community and to coordinate the day-to-day and long-term activities of IVS. The Web server for the Coordinating Center is provided by Goddard. Author COMMUNICATION; EARTH ORIENTATION; VERY LONG BASE INTERFEROMETRY; FORECASTING 20090034045 Geographical Survey Inst., Tsukuba, Japan Tsukuba VLBI Correlator Shigematsu, Hiromi; Kurihara, Shinobu; Kokado, Kensuke; Nozawa, Kentarou; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 216-21; In English; Original contains black and white illustrations Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034045 This is a report of the activities at the Tsukuba VLBI Correlator in 2008. The Tsukuba VLBI Correlator processed 99 intensive sessions (IVS-INT2), nine JADE sessions and two geodetic sessions for JAXA. Additionally, we processed ultra-rapid dUT1 e-VLBI experiments and obtained UT1-TAI only 3 minutes 45 seconds after the end of the observing sessions. 1. General Information The Tsukuba VLBI Correlator is situated at the Geographical Survey Institute (GSI) in Tsukuba, Japan. It is a part of the VLBI components operated by GSI, together with the Tsukuba 32-m VLBI station (TSUKUB32). There are two K5/VSSP correlator units. Intensive sessions (IVS-INT2), performed on Saturdays and Sundays on the TSUKUB32-WETTZELL baseline for monitoring UT1-UTC, have been correlated at the Tsukuba VLBI Correlator. The processing of the JADE series (geodetic sessions with domestic VLBI network of GSI) is also a major task of the Tsukuba VLBI Correlator. Author UNIVERSAL TIME; GEODESY; SURVEYS; VERY LONG BASE INTERFEROMETRY 20090034046 Hartebeesthoek Radio Astronomy Observatory, South Africa Hartebeesthoek Radio Astronomy Observatory (HartRAO) International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 107-11; In English; Original contains color and black and white illustrations Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034046 HartRAO, the only fiducial geodetic site in Africa, participates in VLBI, GNSS, and SLR global networks, among others. This report provides an overview of our geodetic VLBI activities during 2008. On the 3rd of October 2008, a critical failure of the 26-m radio telescope put a halt to VLBI observations. 1. Geodetic VLBI at HartRAO Hartebeesthoek is located 65 kilometers northwest of Johannesburg within the World Heritage Site known as the Cradle of Humankind, just inside the provincial boundary of Gauteng, South Africa. The nearest town, Krugersdorp, is 32 km distant. The telescope is situated in an isolated valley which affords protection from terrestrial interference. HartRAO uses a 26-metre equatorially mounted Cassegrain radio telescope built by Blaw Knox in 1961. The telescope was part of the NASA deep space tracking network until 1975 when the facility was converted to an astronomical observatory. The telescope is co-located with an SLR station (MOBLAS-6) and an IGS GNSS station (HRAO). HartRAO joined the EVN as an associate member during 2001. Geodetic VLBI has been allocated 18% of the available telescope time. The allocation for geodetic VLBI was increased from 58 24-hour experiments in 2007 to 65 in 2008 to include the CONT08 campaign. Author ASTRONOMICAL OBSERVATORIES; GEODESY; VERY LONG BASE INTERFEROMETRY; TRACKING NETWORKS; SATELLITE LASER RANGING; RADIO TELESCOPES; RADIO ASTRONOMY 20090034047 Universidade Presbiteriana Mackenzie, Sao Paulo, Brazil Fortaleza Station Report for 2008 Kaufmann, Pierre; PereiradeLucena, A. Macilio; SombradaSilva, Adeildo; Tateyama, Claudio E.; Filho, Avicena; Moreira, Carlos Fabiano B.; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 99-10; In English; Original contains color illustrations Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034047 This is a brief report about the activities carried out at the Fortaleza geodetic VLBI station (ROEN: Radio Observatorio Espacial do Nordeste), located in Eus ebio, CE, Brazil, in 2008. The observing activities consisted of 79 VLBI sessions and continuous GPS monitoring recordings. The installation of optical fiber was completed, and the station switched to a 1 Gbit/s high speed network, to be used in e-VLBI operations. Regular GPS observations were carried out at the same site. Author VERY LONG BASE INTERFEROMETRY; OPTICAL FIBERS; HIGH SPEED; SWITCHING; GLOBAL POSITIONING SYSTEM; GEODESY 20090034048 Bundesamt fuer Kartographie und Geodaesie, Frankfurt am Main, Germany BKG Data Center Thorandt, Volkmar; Wojdziak, Reiner; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 225-22; In English; Original contains color illustrations Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034048 This report summarizes the activities of the Washington Correlator for the year 2008. The Washington Correlator provides up to 80 hours of processing per week, primarily supporting Earth Orientation and astrometric observations. An additional 40 hours per week of unattended processing is also provided routinely. In 2008 the major programs supported include the IVS-R4, IVS-INT, IVS-R1, CONT08, APSG, and CRF (CRF, CRMS, CRDS, and CRFS) observing sessions. 1. Introduction The Washington Correlator (WACO) is located at and staffed by the U. S. Naval Observatory (USNO) in Washington, DC, USA. The correlator is sponsored and funded by the National Earth Orientation Service (NEOS) which is a joint effort of the USNO and NASA. Dedicated to processing geodetic and astrometric VLBI observations, the facility spent 100 percent of its time on these experiments. All of the weekly IVS-R4 sessions, all of the daily Intensives, several IVS-R1 sessions, and the entire CONT08 were processed at WACO. The remaining time was spent on terrestrial reference frame and astrometry sessions. The facility houses a Mark IV Correlator. Author EARTH ORIENTATION; CORRELATORS; ASTROMETRY; VERY LONG BASE INTERFEROMETRY 20090034049 Naval Observatory, Washington, DC, United States NEOS Operation Center Kingham, Kerry; Carter, M. S.; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 19; In English Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034049 This report covers the activities of the National Earth Orientation Service (NEOS) Operation Center at US Naval Observatory (USNO) for 2008. The Operation Center schedules IVS-R4 and the INT1 Intensive experiments. Author EARTH ORIENTATION; GEODESY 20090034050 Bonn Univ., Germany The Bonn Astro/Geo Mark IV Correlator Bernhart, Simone; Bertarini, Alexxandra; Mueskens, Arno; Alef, Walter; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 201-20; In English; Original contains color illustrations Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034050 The Bonn Mark IV VLBI correlator is operated jointly by the Max-Planck-Institut fur Radioastronomie (MPIfR) and the IGG in Bonn and the BKG in Frankfurt. Since 2007, e-VLBI transfers have become routine for geodetic experiments, and, thanks to that, a new Intensive series (INT3) was introduced and is correlated in Bonn. Three Mark 5B units have been installed and are in regular use for stream correlation. In late December 2007, the first phase of a Linux cluster dedicated for the software correlator, which will become the long-term future replacement of the hardware correlator, was installed. Towards the end of 2008 the cluster was extended to 60 nodes with nearly 500 compute-cores and 40 TB of disk storage. Author CORRELATORS; GEODESY 20090034051 Crimean Astrophysical Observatory, Russian Federation Simeiz VLBI Station - H-maser and Mark 5B+ Upgrade Volvach, A. E.; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 154-15; In English; Original contains color and black and white illustrations Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034051 We summarize briefly the status of the 22-m radio telescope as an IVS Network Station. In 2008 RT-22 was equipped with a modern Mark 5B+ VLBI recording system and a new H-maser. That gives the possibility to continue astrophysical and fundamental geodetic VLBI observations. Author VERY LONG BASE INTERFEROMETRY; RADIO ASTRONOMY; RADIO TELESCOPES; GEODETIC SURVEYS; ASTROPHYSICS; GEODESY 20090034052 Naval Observatory, Washington, DC, United States Washington Correlator Kingham, Kerry A.; Hall, David M.; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 220-22; In English; Original contains color illustrations Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034052 This report summarizes the activities of the Washington Correlator for the year 2008. The Washington Correlator provides up to 80 hours of processing per week, primarily supporting Earth Orientation and astrometric observations. An additional 40 hours per week of unattended processing is also provided routinely. In 2008 the major programs supported include the IVS-R4, IVS-INT, IVS-R1, CONT08, APSG, and CRF (CRF, CRMS, CRDS, and CRFS) observing sessions. 1. Introduction The Washington Correlator (WACO) is located at and staffed by the U. S. Naval Observatory (USNO) in Washington, DC, USA. The correlator is sponsored and funded by the National Earth Orientation Service (NEOS) which is a joint effort of the USNO and NASA. Dedicated to processing geodetic and astrometric VLBI observations, the facility spent 100 percent of its time on these experiments. All of the weekly IVS-R4 sessions, all of the daily Intensives, several IVS-R1 sessions, and the entire CONT08 were processed at WACO. The remaining time was spent on terrestrial reference frame and astrometry sessions. The facility houses a Mark IV Correlator. Author VERY LONG BASE INTERFEROMETRY; ASTROMETRY; EARTH ORIENTATION; GEODETIC SURVEYS; CORRELATORS 20090034053 National Inst. of Information and Communications Technology, Japan Kashima and Koganei 11-m VLBI Stations Koyama, Yasuhiro; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 118-12; In English; Original contains color illustrations Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034053 Two 11-m VLBI antennas at Kashima and Koganei used to be stations of the Key Stone Project VLBI Network. The network consisted of four VLBI stations at Kashima, Koganei, Miura, and Tateyama. Since the Miura and Tateyama stations have been transported to Tomakomai and Gifu, the Kashima and Koganei 11-m stations remain as IVS Network Stations. After the regular VLBI sessions with the Key Stone Project VLBI Network terminated in 2001, these stations have been mainly used for the purposes of technical developments and miscellaneous observations. In 2008, a series of geodetic VLBI experiments were performed between the Kashima and Koganei 11-m VLBI stations to evaluate the capability of the VLBI technique for precise time transfer between Time and Frequency laboratories to construct Coordinated Universal Time. Other series of experiments were also carried out for the development of e-VLBI by using the high speed network connection between the sites. Author GEODESY; VERY LONG BASE INTERFEROMETRY 20090034054 Tasmania Univ., Hobart, Australia Hobart, Mt. Pleasant, Station Report for 2008 Lovell, Jim; Dickey, John M.; Reid, Brett; Ellingsen, Simon; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 111-11; In English; Original contains color and black and white illustrations Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034054 This is a brief report on the activities carried out at the Mt. Pleasant Radio Astronomy Observatory at Hobart, Tasmania. During 2008, the observatory participated in 59 IVS VLBI 24-hour observing sessions, and significant progress was made on the AuScope VLBI array which will see three new antennas installed across Australia for geodesy. Author VERY LONG BASE INTERFEROMETRY; RADIO ASTRONOMY; GEODESY; OBSERVATORIES 20090034055 Geoscience Australia, Canberra, Australia Geoscience Australia Analysis Center Titov, Oleg; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 243-24; In English; Original contains color illustrations Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034055 This report gives an overview about the activities of the Geoscience Australia IVS Analysis Center during 2008. Author GEODESY; VERY LONG BASE INTERFEROMETRY; CELESTIAL REFERENCE SYSTEMS 20090034056 Massachusetts Inst. of Tech., Westford, MA, United States Haystack Observatory Technology Development Center Niell, Arthur; Whitney, Alan; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 321-32; In English; Original contains color illustrations Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034056 Work at the MIT Haystack Observatory is currently focusing on three areas of technology development: Mark 5C/DBE2 VLBI data system VLBI2010 prototype antenna systems e-VLBI Considerable progress has been made in each of these areas. 1. Mark 5C VLBI Data System The Mark 5C is being designed as the next-generation Mark 5 high rate data recording system. It will have the capability of recording at sustained rates up to 4096 Mbps. An important feature is that the same disk modules will be used as for the Mark 5A and Mark 5B, thus preserving the existing investments in storage media. The Mark 5C data interface for both recording and playback will be 10 Gigabit Ethernet, which is rapidly becoming a widely supported standard. Changing from the hardware-defined VSI-H linkage for the Mark 5B to the network-based interface for the Mark 5C offers both advantages and limitations. For example, data playback through the 10GigE interface is expected to be the natural interface to the large-scale software correlators coming into use. On the other hand, implementing the 10GigE interface requires that the data source must be designed to encapsulate data streams in a format compatible with the Mark 5C requirements. However, in the interest of backward compatibility, the Mark 5C will also support writing the disk modules in Mark 5B format to enable correlation on the existing Mark 4 hardware correlators, although only at 2048 Mbps. Author VERY LONG BASE INTERFEROMETRY; ANTENNA DESIGN; DATA SYSTEMS; DATA RECORDING; DATA FLOW ANALYSIS; CORRELATORS; COMPUTER SYSTEMS PROGRAMS 20090034057 Observatoire de Paris, France Paris Observatory Analysis Center OPAR: Report on Activities, January - December 2008 Gontier, Anne-Marie; Lambert, Sebastien B.; Barache, Christophe; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 291-29; In English; Original contains black and white illustrations Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034057 We report on activities of the Paris Observatory VLBI analysis center (OPAR) for calendar year 2008. Among the main issues is the inclusion of OPAR solutions in the IVS rapid solution. We also summarize various scientific results concerning the stabilization of the celestial reference frame, the determination of the dissipative factor associated with the Earth s fluid core by the use of VLBI and superconducting gravimeters, improvements in the theory of nutation and precession, and the determination of the relativistic parameter gamma from VLBI delays. Author VERY LONG BASE INTERFEROMETRY; CELESTIAL REFERENCE SYSTEMS; OBSERVATORIES; GRAVIMETERS; EARTH CORE; SUPERCONDUCTIVITY 20090034058 Central Astronomical Observatory, Pulkovo, Russian Federation Pulkovo IVS Analysis Center (PUL) 2008 Report Malkin, Zinovy; Miller, Natalia; Sokolova, Julia; Popova, Elena; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 299-30; In English Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034058 This report briefly presents the PUL IVS Analysis Center activities during 2008 and plans for the coming year. The main topics of investigations in that period were comparison and combination of catalogs of radio source positions, analysis of VLBI Earth Orientation Parameters (EOP) series, analysis of radio source position and zenith troposphere delay time series. Author EARTH ORIENTATION; VERY LONG BASE INTERFEROMETRY; GEODESY; TIME SERIES ANALYSIS 20090034059 National Inst. of Information and Communications Technology, Japan Technology Development Center at NICT Takefuji, Kazuhiro; Ichikawa, Ryuichi; Sekido, Mamoru; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 325-32; In English; Original contains color and black and white illustrations Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034059 National Institute of Information and Communications Technology (NICT) has led the development of the VLBI technique and has been maintaining a high level of activity in both observations and technical developments. This report gives a review of the Technology Development Center (TDC) at NICT and summarizes its recent activities. Author VERY LONG BASE INTERFEROMETRY; DATA ACQUISITION; INFORMATION SYSTEMS; DISTRIBUTED PROCESSING; AUTOCORRELATION; DATA BASES 20090034060 Onsala Space Observatory, Sweden Onsala Space Observatory - IVS Technology Development Center Haas, Ruediger; Helldner, Leif; Pantaleev, Miroslav; Loefgren, Johan; Elgered, Gunnar; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 329-33; In English; Original contains color illustrations Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034060 This report summarizes the technical development related to the geodetic VLBI activities that were performed at the Onsala Space Observatory during 2008. Most of the tasks planned for the year were addressed, and some new tasks were initiated. The focus was on: (1) tests of an analog fiber link for the transfer of VLBI IF-signals, (2) a contribution to the project to develop a dual-polarized broadband Eleven feed for VLBI2010, (3) the superconducting gravimeter, and (4) the development of a GNSS-based tide gauge. Author VERY LONG BASE INTERFEROMETRY; SUPERCONDUCTIVITY; MEASURING INSTRUMENTS; AEROSPACE ENGINEERING; BROADBAND; GRAVIMETERS; GEODESY 20090034061 Bordeaux Univ., France Bordeaux Observatory Analysis Center Report Charlot, Patrick; Bellanger, Antoine; Bourda, Geraldine; Colioud, Arnaud; Zhang, Ming; Baudry, Alain; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 246-24; In English; Original contains black and white illustrations Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034061 This report summarizes the activities of the Bordeaux Observatory Analysis Center in 2008. During this period, we continued our VLBI imaging activity and produced a total of 581 VLBI maps by processing three RDV sessions. Structure indices and source compactness were derived from these images to assess the astrometric source quality. A pipeline is also being developed to model-fit the VLBI structures in an automatic way and extract relevant physical information for astrophysics. Other activities focused on regular analysis of the IVS-R1 and IVS-R4 sessions and simulations to study the imaging capabilities of the next generation VLBI system. On the observational side, we further pursued our project to identify new reference frame sources for the link with the future Gaia frame, and we imaged 105 weak candidate sources for this link. Plans for 2009 follow the same analysis and research lines. Author VERY LONG BASE INTERFEROMETRY; ASTROMETRY; EXTRACTION; OBSERVATORIES; ASTROPHYSICS 20090034062 Academia Sinica, Shanghai, China Sheshan VLBI Station Report for 2008 Hong, Xiaoyu; Fan, Qingyuan; An, Tao; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 150-15; In English; Original contains color illustrations Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034062 This report summarizes the observing activities at the Sheshan station (SESHAN25) in 2008. The Sheshan radio telescope participated in nineteen 24-hour VLBI sessions organized by the IVS and in thirty-seven traditional VLBI experiments, as well as in a number of e-VLBI sessions and formatter tests organized by the EVN. Apart from the international VLBI activities, the telescope was involved in 125 monitoring experiments of the Chinese Chang E-1 lunar satellite, and in nine observations of the Japanese SELENE lunar satellite. We also report on updates to and development of the facilities at the station. Author VERY LONG BASE INTERFEROMETRY; LUNAR SATELLITES; RADIO TELESCOPES; SATELLITE OBSERVATION 20090034063 Norwegian Defence Research Establishment, Kjeller, Norway FFI Analysis Center Andersen, Per Helge; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 259-26; In English Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034063 FFI s contribution to the IVS as an analysis center focuses primarily on a combined analysis at the observation level of data from VLBI, GPS and SLR using the GEOSAT software. This report shortly summarises the current status of analyses performed with the GEOSAT software. FFI is currently an Analysis Center for IVS and ILRS, a Technology Development Center for IVS, and a Combination Research Center for IERS. Author VERY LONG BASE INTERFEROMETRY; GLOBAL POSITIONING SYSTEM; GEOSAT SATELLITES; MATHEMATICAL MODELS; PARAMETER IDENTIFICATION; METEOROLOGICAL PARAMETERS; CORRELATION; EARTH ORIENTATION; GEODESY; GEOPHYSICS 20090034064 NASA Goddard Space Flight Center, Greenbelt, MD, United States GSFC VLBI Analysis Center Gordon, David; Ma, Chopo; MacMillan, Dan; Gipson, John; Baver, Karen; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 265-26; In English Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034064 This report presents the activities of the GSFC VLBI Analysis Center during 2008. The GSFC Analysis Center analyzes all IVS sessions, makes regular IVS submissions of data and analysis products, and performs research and software development aimed at improving the VLBI technique. 1. Introduction The GSFC VLBI Analysis Center is located at NASA s Goddard Space Flight Center in Green- belt, Maryland. It is part of a larger VLBI group which also includes the IVS Coordinating Center, the CORE Operation Center, a Technology Development Center, and a Network Station. The Analysis Center participates in all phases of geodetic and astrometric VLBI analysis, software development, and research aimed at improving the VLBI technique. Author VERY LONG BASE INTERFEROMETRY; SOFTWARE ENGINEERING; GEODESY; ASTROMETRY 20090034065 NASA Goddard Space Flight Center, Greenbelt, MD, United States Goddard Geophysical and Astronomical Observatory Rdmond, Jay; Diegel, Irv; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 103-10; In English; Original contains color and black and white illustrations Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034065 This report summarizes the technical parameters and the technical staff of the VLBI system at the fundamental station GGAO. It also gives an overview about the VLBI activities during the previous year. The outlook lists the outstanding tasks to improve the performance of GGAO. 1. GGAO at Goddard The Goddard Geophysical and Astronomical Observatory (GGAO) consists of a radio telescope for VLBI, an SLR site to include MOBLAS-7, SLR-2000 (development system), a 48" telescope for developmental two color Satellite Ranging, a GPS timing and development lab, meteorological sensors, and an H-maser. In addition, we are a fiducial IGS site with several IGS/IGSX receivers. Author TIME MEASUREMENT; RADIO TELESCOPES; METEOROLOGICAL INSTRUMENTS; GLOBAL POSITIONING SYSTEM; GEOPHYSICAL OBSERVATORIES; ASTRONOMICAL OBSERVATORIES; VERY LONG BASE INTERFEROMETRY 20090034066 Saint Petersburg Univ., Saint Petersburg, Russian Federation Analysis Center of Saint Petersburg University Vityazev, Veniamin; Trofimov, Dmitriy; Kudryashova, Maria; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 241-24; In English Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034066 This report briefly summarizes the activities of the Analysis Center of Saint Petersburg University during 2008. Changes which happened in our solutions and staff, as well as our future plans, are described. 1. Introduction The Sobolev Astronomical Institute is located in Petrodvorets, near Saint Petersburg. It is a research institute of the Saint Petersburg State University. In 1998 the Analysis Center of Saint Petersburg University was established in the Institute. Due to the staff changes in 2007 we had a gap in our submissions for IVS that year. The main activity of the SPU AC for the International VLBI Service before 2007 consisted of routine processing of 24-hour and 1-hour observational sessions for obtaining Earth Orientation Parameters (EOP) and rapid UT1-UTC values respectively. In 2008 we resumed submitting results of 24-hour session processing. During 2008 the activities of the SPU AC were supported by the Ministry of Education and Science of the Russian Federation (grant 2.1.1.5077). Author ASTRONOMY; VERY LONG BASE INTERFEROMETRY; ALTERNATING CURRENT; EARTH ORIENTATION 20090034067 Academy of Sciences (Russia), Saint Petersburg, Russian Federation Svetloe Radio Astronomical Observatory Smolentsev, Sergey; Rahimov, Ismail; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 158-16; In English; Original contains black and white illustrations Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034067 This report summarizes information on recent activities at the Svetloe Radio Astronomical Observatory (SvRAO). During the previous year a number of changes were carried out at the observatory to improve some technical parameters and upgrade some units to required status. The report provides also an overview of current geodetic VLBI activities and gives an outlook for the next year. Author VERY LONG BASE INTERFEROMETRY; GEODESY; ASTRONOMICAL OBSERVATORIES 20090034068 National Inst. of Polar Research, Tokyo, Japan JARE Syowa Station 11-m Antenna, Antarctica Doi, Koichiro; Shibuya, Kazuo; Aoyama, Yuichi; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 161-16; In English; Original contains color illustrations Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034068 The operation of the 11-m S/X-band antenna at Syowa Station (69.0.S, 39.6.E) by the Japanese Antarctic Research Expeditions (JAREs) started in February 1998 and continues until today (January 2009). A cumulative total of 83 quasi-regular geodetic VLBI experiments were observed by the end of 2008. Syowa Station will participate in six OHIG sessions in 2009. The data from six OHIG sessions in 2008 were recorded on hard disks through the K5 terminal. They will be brought back from Syowa Station to Japan in April 2009. The data from the OHIG51 through the OHIG57 sessions observed by JARE48 and JARE49 have been transferred to the Bonn Correlator directly by way of one of NICT's servers. Analysis results obtained from the data until the OHIG56 session indicate that the length of the Syowa-Hobart baseline is increasing with a rate of 54.7 +/-0.4 mm/yr and that the length of the Syowa-HartRAO baseline is increasing with a rate of 11.7+/- 0.3 mm/yr. The length of the Syowa-O'Higgins baseline is slightly increasing with a rate of 1.7+/-0.9 mm/yr. Author MICROWAVE ANTENNAS; SUPERHIGH FREQUENCIES; VERY LONG BASE INTERFEROMETRY; ULTRAHIGH FREQUENCIES; GEODESY; CORRELATORS 20090034069 National Inst. of Information and Communications Technology, Ibaraki, Japan Data Center at NICT Koyama, Yasuhiro; Sekido, Mamoru; Takiguchi, Hiroshi; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 232-23; In English; Original contains color illustrations Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034069 The Data Center at National Institute of Information and Communications Technology (NICT) archives and releases the databases and analysis results processed at the Correlation Center and the Analysis Center at NICT. Regular VLBI sessions with the Key Stone Project VLBI Network were the primary objective of the Data Center. These regular sessions continued until the end of November 2001. In addition to the Key Stone Project VLBI sessions, NICT has been conducting geodetic VLBI sessions for various purposes, and these data are also archived and released by the Data Center. Author VERY LONG BASE INTERFEROMETRY; CORRELATION; GEODESY 20090034070 National Inst. of Information and Communications Technology, Ibaraki, Japan VLBI Correlators in Kashima Sekido, Mamoru; Kimura, Moritaka; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 212-21; In English; Original contains black and white illustrations Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034070 Software correlator systems developed at Kashima Space Research Center are used for data processing of R&D VLBI experiments. Major correlation tasks processed in 2008 were the following three: e-VLBI project for rapid UT1 measurement, CARAVAN2400 project for reference baseline determination with small diameter antennas, and a project for time standards comparison with VLBI. An automatic data processing scheme, which distributes correlation tasks to a cluster of PCs for parallel processing, has been extensively used for this geodetic VLBI processing. Author DATA PROCESSING; GEODESY; PARALLEL PROCESSING (COMPUTERS); SOFTWARE ENGINEERING; VERY LONG BASE INTERFEROMETRY; CORRELATORS 20090034071 Academy of Sciences (Russia), Saint Petersburg, Russian Federation IAA Correlator Center Surkis, Igor; Fateev, Artemy; Melnikov, Alexey; Mishin, Vladimir; Shantyr, Violet; Zimovsky, Vladimir; International VLBI Service for Geodesy and Astrometry 2008 Annual Report; August 2009; pp. 209-21; In English; Original contains color illustrations Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034071 The prototype correlator of ARC was produced. It is a 2-station VSI-H XF-type hardware VLBI correlator connected to two Mark 5B terminals. The fullscale 6-station VLBI correlator ARC is scheduled next and will be constructed soon. The VLBI data of the 3-station sessions of the Russian national network Quasar was processed using the MicroPARSEC correlator. The IAA Correlator Center is located and staffed by the Institute of Applied Astronomy in St.-Petersburg, Russia. The IAA Correlator Center is devoted to processing geodetic, astrometric, and astrophysical observations made with the Russian national VLBI network Quasar. Author ASTROMETRY; GEODETIC SURVEYS; QUASARS; VERY LONG BASE INTERFEROMETRY; ASTROPHYSICS; CORRELATORS Additions to the NASA Aeronautics and Space Database as of 10/12/2009 20090034082 Commonwealth Scientific and Industrial Research Organization, Linfield, Australia Development and Evaluation of Sensor Concepts for Ageless Aerospace Vehicles: Report 5 - Phase 2 Implementation of the Concept Demonstrator Batten, Adam; Dunlop, John; Edwards, Graeme; Farmer, Tony; Gaffney, Bruce; Hedley, Mark; Hoschke, Nigel; Isaacs, Peter; Johnson, Mark; Lewis, Chris; Murdoch, Alex; Poulton, Geoff; Price, Don; Prokopenko, Mikhail; Sharp, Ian; Scott, Andrew; Valencia, Philip; Wang, Peter; Whitnall, Denis; September 2009; In English; Original contains color and black and white illustrations Contract(s)/Grant(s): WBS 939904.05.07 Report No.(s): NASA/CR-2009-215931; LF99-7916; L-71308D; TIPP 2056; Copyright; Avail.: CASI: A04, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034082 This report describes the second phase of the implementation of the Concept Demonstrator experimental test-bed system containing sensors and processing hardware distributed throughout the structure, which uses multi-agent algorithms to characterize impacts and determine a suitable response to these impacts. This report expands and adds to the report of the first phase implementation. The current status of the system hardware is that all 192 physical cells (32 on each of the 6 hexagonal prism faces) have been constructed, although only four of these presently contain data-acquisition sub-modules to allow them to acquire sensor data. Impact detection.. location and severity have been successfully demonstrated. The software modules for simulating cells and controlling the test-bed are fully operational. although additional functionality will be added over time. The visualization workstation displays additional diagnostic information about the array of cells (both real and simulated) and additional damage information. Local agent algorithms have been developed that demonstrate emergent behavior of the complex multi-agent system, through the formation of impact damage boundaries and impact networks. The system has been shown to operate well for multiple impacts. and to demonstrate robust reconfiguration in the presence of damage to numbers of cells. Author ALGORITHMS; DATA ACQUISITION; TEST STANDS; MODULES; IMPACT DAMAGE; DISPLAY DEVICES; COMPUTER PROGRAMS; COMPLEX SYSTEMS; PROVING 20090034086 NASA Dryden Flight Research Center, Edwards, CA, United States Further Development of Ko Displacement Theory for Deformed Shape Predictions of Nonuniform Aerospace Structures Ko, William L.; Fleischer, Van Tran; September 2009; In English; Original contains black and white illustrations Report No.(s): NASA/TP-2009-214643; H-2889; DFRC-781; No Copyright; Avail.: CASI: A05, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034086 The Ko displacement theory previously formulated for deformed shape predictions of nonuniform beam structures is further developed mathematically. The further-developed displacement equations are expressed explicitly in terms of geometrical parameters of the beam and bending strains at equally spaced strain-sensing stations along the multiplexed fiber-optic sensor line installed on the bottom surface of the beam. The bending strain data can then be input into the displacement equations for calculations of local slopes, deflections, and cross-sectional twist angles for generating the overall deformed shapes of the nonuniform beam. The further-developed displacement theory can also be applied to the deformed shape predictions of nonuniform two-point supported beams, nonuniform panels, nonuniform aircraft wings and fuselages, and so forth. The high degree of accuracy of the further-developed displacement theory for nonuniform beams is validated by finite-element analysis of various nonuniform beam structures. Such structures include tapered tubular beams, depth-tapered unswept and swept wing boxes, width-tapered wing boxes, and double-tapered wing boxes, all under combined bending and torsional loads. The Ko displacement theory, combined with the fiber-optic strain-sensing system, provide a powerful tool for in-flight deformed shape monitoring of unmanned aerospace vehicles by ground-based pilots to maintain safe flights. Author SLOPES; DISPLACEMENT; DEFORMATION; BEAMS (SUPPORTS); STRUCTURAL ENGINEERING; IN-FLIGHT MONITORING; FINITE ELEMENT METHOD 20090034167 Boeing Co., Huntington Beach, CA, United States Damage Arresting Composites for Shaped Vehicles Velicki, Alex; September 2009; In English; Original contains color and black and white illustrations Contract(s)/Grant(s): NNL07AA48CWBS 561581.02.08.07.15.03; 4200208122 Report No.(s): NASA/CR-2009-215932; LF99-8391; Copyright; Avail.: CASI: A05, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034167 This report describes the development of a novel structural solution that addresses the demanding fuselage loading requirements for the Hybrid Wing or Blended Wing Body configurations that are described in NASA NRA subtopic A2A.3, "Materials and Structures for Wing Components and Non-Circular Fuselage." The phase I portion of this task includes a comprehensive finite element model-based structural sizing exercise performed using the BWB airplane configuration to generate internal loads and fuselage panel weights for an advanced Pultruded Rod Stitched Efficient Unitized Structure (PRSEUS) structural concept. An accompanying element-level test program is also described which substantiates the analytical results and calculation methods used in the trade study. The phase II plan for the continuation of this research is also included herein. Author BLENDED-WING-BODY CONFIGURATIONS; AERODYNAMIC CONFIGURATIONS; FUSELAGES; PULTRUSION; LOADS (FORCES); DAMAGE 20090034177 NASA Goddard Space Flight Center, Greenbelt, MD, United States Design Aspects of the VLBI2010 System - Progress Report of the IVS VLBI2010 Committee Petrachenko, Bill; Niell, Arthur; Behrend, Dirk; Corey, Brian; Boehm, Johannes; Chralot, Patrick; Collioud, Arnaud; Gipson, John; Haas, Ruediger; Hobiger, Thomas; Koyama, Yasuhiro; MacMillan, Dan; Malkin, Zinvoy; Nilsson, Tobias; Pany, Andrea; Tuccari, Gino; Whitney, Alan; Wresnik, Joerg; June 2009; In English; Original contains color and black and white illustrations Contract(s)/Grant(s): NNG05HY04CP18404-N10 Report No.(s): NASA/TM-2009-214180; 200901964; Copyright; Avail.: CASI: A04, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034177 This report summarizes the progress made in developing the next generation VLBI system, dubbed the VLBI2010 system. The VLBI2010 Committee of the International VLBI Service for Geodesy and Astrometry (IVS) worked on the design aspects of the new system. The report covers Monte Carlo simulations showing the impact of the new operating modes on the final products. A section on system considerations describes the implications for the VLBI2010 system parameters by considering the new modes and system-related issues such as sensitivity, antenna slew rate, delay measurement error. RF1, frequency requirements, antenna deformation, and source structure corrections_ This is followed by a description of all major subsystems and recommendations for the network, station. and antenna. Then aspects of the feed, polarization processing. calibration, digital back end, and correlator subsystems are covered. A section is dedicated to the NASA. proof-of-concept demonstration. Finally, sections tm operational considerations, on risks and fallback options, and on the next steps complete the report. Author VERY LONG BASE INTERFEROMETRY; GEODESY; ASTROMETRY; DIGITAL SYSTEMS; CALIBRATING; FREQUENCIES; PROVING; CORRELATORS Additions to the NASA Aeronautics and Space Database as of 10/13/2009 20090034255 NASA Dryden Flight Research Center, Edwards, CA, United States Stability and Control Analysis of the F-15B Quiet SpikeTM Aircraft McWherter, Shaun C.; Moua, Cheng M.; Gera, Joseph; Cox, Timothy H.; August 2009; In English; Original contains color illustrations Contract(s)/Grant(s): NAS4-02021 Report No.(s): NASA/TM-2009-214651; H-2956; DFRC-654; Copyright; Avail.: CASI: A04, Hardcopy Avail Online: http://hdl.handle.net/2060/20090034255 The primary purpose of the Quiet Spike(TradeMark) flight research program was to analyze the aerodynamic, structural, and mechanical proof-of-concept of a large multi-stage telescoping nose spike installed on the National Aeronautics and Space Administration Dryden Flight Research Center (Edwards, California) F-15B airplane. This report describes the preflight stability and control analysis performed to assess the effect of the spike on the stability, controllability, and handling qualities of the airplane; and to develop an envelope expansion approach to maintain safety of flight. The overall flight test objective was to collect flight data to validate the spike structural dynamics and loads model up to Mach 1.8. Other objectives included validating the mechanical feasibility of a morphing fuselage at operational conditions and determining the near-field shock wave characterization. The two main issues relevant to the stability and control objectives were the effects of the spike-influenced aerodynamics on the F-15B airplane flight dynamics, and the air data and angle-of-attack sensors. The analysis covered the sensitivity of the stability margins, and the handling qualities due to aerodynamic variation and the maneuvering limitations of the F-15B Quiet Spike configuration. The results of the analysis and the implications for the flight test program are also presented. Author STABILITY TESTS; AERODYNAMICS; DYNAMIC STRUCTURAL ANALYSIS; FLIGHT TESTS; ANGLE OF ATTACK; SPIKES (AERODYNAMIC CONFIGURATIONS); AEROMANEUVERING Additions to the NASA Aeronautics and Space Database as of 11/05/2009 20090036992 NASA Ames Research Center, Moffett Field, CA, United States On Organization of Information: Approach and Early Work Degani, Asaf; Jorgensen, Charles C.; Iverson, David; Shafto, Michael; Olson, Leonard; May 2009; In English; Original contains color and black and white illustrations Contract(s)/Grant(s): WBS 292487.01.01.02 Report No.(s): NASA/TM-2009-215368; ARC-E-DAA-TN585; No Copyright; Avail.: CASI: A06, Hardcopy Avail Online: http://hdl.handle.net/2060/20090036992 In this report we describe an approach for organizing information for presentation and display. "e approach stems from the observation that there is a stepwise progression in the way signals (from the environment and the system under consideration) are extracted and transformed into data, and then analyzed and abstracted to form representations (e.g., indications and icons) on the user interface. In physical environments such as aerospace and process control, many system components and their corresponding data and information are interrelated (e.g., an increase in a chamber s temperature results in an increase in its pressure). "ese interrelationships, when presented clearly, allow users to understand linkages among system components and how they may affect one another. Organization of these interrelationships by means of an orderly structure provides for the so-called "big picture" that pilots, astronauts, and operators strive for. Author AEROSPACE SYSTEMS; INFORMATION SYSTEMS; LINKAGES 20090037028 NASA Glenn Research Center, Cleveland, OH, United States A Theoretical Investigation of Composite Overwrapped Pressure Vessel (COPV) Mechanics Applied to NASA Full Scale Tests Thesken, John C.; Murthy, Pappu L. N.; Phoenix, S. L.; Greene, N.; Palko, Joseph L.; Eldridge, Jeffrey; Sutter, James; Saulsberry, R.; Beeson, H.; September 2009; In English; Original contains color and black and white illustrations Contract(s)/Grant(s): WBS 869021.03.03.02.01 Report No.(s): NASA/TM-2009-215684; E-17056; Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090037028 A theoretical investigation of the factors controlling the stress rupture life of the National Aeronautics and Space Administration's (NASA) composite overwrapped pressure vessels (COPVs) continues. Kevlar (DuPont) fiber overwrapped tanks are of particular concern due to their long usage and the poorly understood stress rupture process in Kevlar filaments. Existing long term data show that the rupture process is a function of stress, temperature and time. However due to the presence of a load sharing liner, the manufacturing induced residual stresses and the complex mechanical response, the state of actual fiber stress in flight hardware and test articles is not clearly known. This paper is a companion to a previously reported experimental investigation and develops a theoretical framework necessary to design full-scale pathfinder experiments and accurately interpret the experimentally observed deformation and failure mechanisms leading up to static burst in COPVs. The fundamental mechanical response of COPVs is described using linear elasticity and thin shell theory and discussed in comparison to existing experimental observations. These comparisons reveal discrepancies between physical data and the current analytical results and suggest that the vessel s residual stress state and the spatial stress distribution as a function of pressure may be completely different from predictions based upon existing linear elastic analyses. The 3D elasticity of transversely isotropic spherical shells demonstrates that an overly compliant transverse stiffness relative to membrane stiffness can account for some of this by shifting a thin shell problem well into the realm of thick shell response. The use of calibration procedures are demonstrated as calibrated thin shell model results and finite element results are shown to be in good agreement with the experimental results. The successes reported here have lead to continuing work with full scale testing of larger NASA COPV hardware. Author PRESSURE VESSELS; COMPOSITE WRAPPING; ELASTIC PROPERTIES; FULL SCALE TESTS; RESIDUAL STRESS; SHELL THEORY; DEFORMATION 20090037048 NASA Glenn Research Center, Cleveland, OH, United States An Overview of Prognosis Health Management Research at Glenn Research Center for Gas Turbine Engine Structures With Special Emphasis on Deformation and Damage Modeling Arnold, Steven M.; Goldberg, Robert K.; Lerch, Bradley A.; Saleeb, Atef F.; September 2009; In English; Annual Conference of the Prognostics and Health Management Society 2009, 27 Sep. -1 Oct. 2009, San Diego, CA, United States; Original contains color and black and white illustrations Contract(s)/Grant(s): WBS 645846.02.02.03.03 Report No.(s): NASA/TM-2009-215827; E-17089; Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090037048 Herein a general, multimechanism, physics-based viscoelastoplastic model is presented in the context of an integrated diagnosis and prognosis methodology which is proposed for structural health monitoring, with particular applicability to gas turbine engine structures. In this methodology, diagnostics and prognostics will be linked through state awareness variable(s). Key technologies which comprise the proposed integrated approach include (1) diagnostic/detection methodology, (2) prognosis/lifing methodology, (3) diagnostic/prognosis linkage, (4) experimental validation, and (5) material data information management system. A specific prognosis lifing methodology, experimental characterization and validation and data information management are the focal point of current activities being pursued within this integrated approach. The prognostic lifing methodology is based on an advanced multimechanism viscoelastoplastic model which accounts for both stiffness and/or strength reduction damage variables. Methods to characterize both the reversible and irreversible portions of the model are discussed. Once the multiscale model is validated the intent is to link it to appropriate diagnostic methods to provide a full-featured structural health monitoring system. Author GAS TURBINE ENGINES; MULTISCALE MODELS; PROGNOSIS; VISCOELASTICITY; ELASTOPLASTICITY; DAMAGE; DEFORMATION; DIAGNOSIS Additions to the NASA Aeronautics and Space Database as of 11/06/2009 20090037083 NASA Glenn Research Center, Cleveland, OH, United States COMPASS Final Report: Near Earth Asteroids Rendezvous and Sample Earth Returns (NEARER) Oleson, Steven R.; McGuire, Melissa L.; September 2009; In English; (NEARER) Near Earth Asteroids Rendezvous and Sample Earth Returns (NEARER)/ 31st IEPC, 20-24 Sep. 2009, Ann Arbor, MI, United States; Original contains color illustrations Contract(s)/Grant(s): WBS 346620.02.01.01.03.02 Report No.(s): NASA/TM-2009-215825; CD-2008-28; E-17087; No Copyright; Avail.: CASI: A05, Hardcopy Avail Online: http://hdl.handle.net/2060/20090037083 In this study, the Collaborative Modeling for Parametric Assessment of Space Systems (COMPASS) team completed a design for a multi-asteroid (Nereus and 1996 FG3) sample return capable spacecraft for the NASA In-Space Propulsion Office. The objective of the study was to support technology development and assess the relative benefits of different electric propulsion systems on asteroid sample return design. The design uses a single, heritage Orion solar array (SA) (approx.6.5 kW at 1 AU) to power a single NASA Evolutionary Xenon Thruster ((NEXT) a spare NEXT is carried) to propel a lander to two near Earth asteroids. After landing and gathering science samples, the Solar Electric Propulsion (SEP) vehicle spirals back to Earth where it drops off the first sample s return capsule and performs an Earth flyby to assist the craft in rendezvousing with a second asteroid, which is then sampled. The second sample is returned in a similar fashion. The vehicle, dubbed Near Earth Asteroids Rendezvous and Sample Earth Returns (NEARER), easily fits in an Atlas 401 launcher and its cost estimates put the mission in the New Frontier s (NF's) class mission. Author ASTEROIDS; SOLAR ELECTRIC PROPULSION; SAMPLE RETURN MISSIONS; PROPULSION SYSTEM CONFIGURATIONS; SYSTEMS ENGINEERING; FLYBY MISSIONS; PROPULSION SYSTEM PERFORMANCE; ELECTRIC PROPULSION Additions to the NASA Aeronautics and Space Database as of 11/10/2009 20090037329 NASA Langley Research Center, Hampton, VA, United States From Verified Models to Verifiable Code Lensink, Leonard; Munoz, Cesar A.; Goodloe, Alwyn E.; October 2009; In English; Original contains color illustrations Contract(s)/Grant(s): NCC1-02043NNX08AE37AWBS 645846.02.07.07.15.03 Report No.(s): NASA/TM-2009-215943; L-19766; LF99-9439; Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090037329 Declarative specifications of digital systems often contain parts that can be automatically translated into executable code. Automated code generation may reduce or eliminate the kinds of errors typically introduced through manual code writing. For this approach to be effective, the generated code should be reasonably efficient and, more importantly, verifiable. This paper presents a prototype code generator for the Prototype Verification System (PVS) that translates a subset of PVS functional specifications into an intermediate language and subsequently to multiple target programming languages. Several case studies are presented to illustrate the tool's functionality. The generated code can be analyzed by software verification tools such as verification condition generators, static analyzers, and software model-checkers to increase the confidence that the generated code is correct. Author PROGRAMMING LANGUAGES; FUNCTIONAL DESIGN SPECIFICATIONS; DIGITAL SYSTEMS; PROGRAM VERIFICATION (COMPUTERS); ERRORS Additions to the NASA Aeronautics and Space Database as of 11/11/2009 20090037432 NASA Langley Research Center, Hampton, VA, United States Coupled Neutron Transport for HZETRN Slaba, Tony C.; Blattnig, Steve R.; October 2009; In English; Original contains black and white illustrations Contract(s)/Grant(s): WBS 65149.02.07.01 Report No.(s): NASA/TP-2009-215941; L-19769; LF99-9539; Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090037432 Exposure estimates inside space vehicles, surface habitats, and high altitude aircrafts exposed to space radiation are highly influenced by secondary neutron production. The deterministic transport code HZETRN has been identified as a reliable and efficient tool for such studies, but improvements to the underlying transport models and numerical methods are still necessary. In this paper, the forward-backward (FB) and directionally coupled forward-backward (DC) neutron transport models are derived, numerical methods for the FB model are reviewed, and a computationally efficient numerical solution is presented for the DC model. Both models are compared to the Monte Carlo codes HETC-HEDS, FLUKA, and MCNPX, and the DC model is shown to agree closely with the Monte Carlo results. Finally, it is found in the development of either model that the decoupling of low energy neutrons from the light particle transport procedure adversely affects low energy light ion fluence spectra and exposure quantities. A first order correction is presented to resolve the problem, and it is shown to be both accurate and efficient. Author NEUTRONS; ENERGY TRANSFER; EXTRATERRESTRIAL RADIATION; EXPOSURE; DECOUPLING; ENERGY SPECTRA; LIGHT IONS Additions to the NASA Aeronautics and Space Database as of 11/13/2009 20090037582 NASA Langley Research Center, Hampton, VA, United States Shuttle Gaseous Hydrogen Venting Risk from Flow Control Valve Failure Drummond, J. Philip; Baurle, Robert A.; Gafney, Richard L.; Norris, Andrew T.; Pellett, Gerald L.; Rock, Kenneth E.; October 2009; In English; Original contains color and black and white illustrations Contract(s)/Grant(s): WBS 378343.10.01.05.08 Report No.(s): NASA/TM-2009-215942; LF99-8616; L-19767; No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090037582 This paper describes a series of studies to assess the potential risk associated with the failure of one of three gaseous hydrogen flow control valves in the orbiter's main propulsion system during the launch of Shuttle Endeavour (STS-126) in November 2008. The studies focused on critical issues associated with the possibility of combustion resulting from release of gaseous hydrogen from the external tank into the atmosphere during assent. The Shuttle Program currently assumes hydrogen venting from the external tank will result in a critical failure. The current effort was conducted to increase understanding of the risk associated with venting hydrogen given the flow control valve failure scenarios being considered in the Integrated In-Flight Anomaly Investigation being conducted by NASA. Author CONTROL VALVES; HYDROGEN; VENTING; AEROSPACE SAFETY; ENDEAVOUR (ORBITER); RISK MANAGEMENT; FAILURE ANALYSIS Additions to the NASA Aeronautics and Space Database as of 11/19/2009 20090038656 NASA Langley Research Center, Hampton, VA, United States NASA Patent Abstracts Bibliography: A Continuing Bibliography Supplement 70 October 2009; In English; Original contains black and white illustrations Report No.(s): NASA/SP-2009-7039/SUPPL70; No Copyright; Avail.: CASI: A04, Hardcopy Avail Online: http://hdl.handle.net/2060/20090038656 Several thousand inventions result each year from research supported by the National Aeronautics and Space Administration. NASA seeks patent protection on inventions to which it has title if the invention has important use in government programs or significant commercial potential. These inventions cover a broad range of technologies and include many that have useful and valuable commercial application. NASA inventions best serve the interests of the United States when their benefits are available to the public. In many instances, the granting of nonexclusive or exclusive licenses for the practice of these inventions may assist in the accomplishment of this objective. This bibliography is published as a service to companies, firms, and individuals seeking new, licensable products for the commercial market. The NASA Patent Abstracts Bibliography is an annual NASA publication containing comprehensive abstracts of NASA-owned inventions covered by U.S. patents. The citations included were originally published in NASA s Scientific and Technical Aerospace Reports (STAR). The citations published in this issue cover the period October 2008 through September 2009. The subjects covered include the NASA Scope and Subject Category Guide s 10 broad subject divisions separated further into 76 specific categories. However, not all categories contain citations during the date range of this issue; therefore, the Table of Contents does not include all divisions and categories. Each citation includes an abstract and, when available, a key illustration taken from the patent or application for patent. Also when available, citations include a link to the full-text document online. Author INVENTIONS; ABSTRACTS; TECHNOLOGY UTILIZATION; PATENT APPLICATIONS 20090038672 Northrop Grumman Corp., Redondo Beach, CA, United States Use of Cumulative Degradation Factor Prediction and Life Test Result of the Thruster Gimbal Assembly Actuator for the Dawn Flight Project Lo, C. John; Brophy, John R.; Etters, M. Andy; Ramesham, Rajeshuni; Jones, William R., Jr.; Jansen, Mark J.; October 2009; In English; Original contains color and black and white illustrations Contract(s)/Grant(s): NNC07JF14TWBS 431731.04.01.03 Report No.(s): NASA/CR-2009-215681; E-17052; Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090038672 The Dawn Ion Propulsion System is the ninth project in NASA s Discovery Program. The Dawn spacecraft is being developed to enable the scientific investigation of the two heaviest main-belt asteroids, Vesta and Ceres. Dawn is the first mission to orbit two extraterrestrial bodies, and the first to orbit a main-belt asteroid. The mission is enabled by the onboard Ion Propulsion System (IPS) to provide the post-launch delta-V. The three Ion Engines of the IPS are mounted on Thruster Gimbal Assembly (TGA), with only one engine operating at a time for this 10-year mission. The three TGAs weigh 14.6 kg. Author VESTA ASTEROID; ION PROPULSION; ACTUATORS; THERMOGRAVIMETRY; ION ENGINES 20090038700 NASA Glenn Research Center, Cleveland, OH, United States Large Eddy Simulation of Transonic Flow Field in NASA Rotor 37 Hah, Chunill; September 2009; In English; 47th Aerospace Sciences Meeting, 5-8 Jan. 2009, Orlando, FL, United States; Original contains color and black and white illustrations Contract(s)/Grant(s): WBS 561581.02.08.03.21.02 Report No.(s): NASA/TM-2009-215627; E-16939; No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090038700 The current paper reports on numerical investigations on the flow characteristics in a transonic axial compressor, NASA Rotor 37. The flow field was used previously as a CFD blind test case conducted by American Society of Mechanical Engineers in 1994. Since the CFD blind-test exercise, many numerical studies on the flow field in the NASA Rotor 37 have been reported. Although steady improvements have been reported in both numerical procedure and turbulence closure, it is believed that all the important aspects of the flow field have not been fully explained with numerical studies based on the Reynolds Averaged Navier-Stokes (RANS) solution. Experimental data show large dip in total pressure distribution near the hub at downstream of the rotor at 100% rotor speed. Most original numerical solutions from the blind test exercise did not predict this total pressure deficit correctly. This total pressure deficit at the rotor exit was attributed to a hub corner flow separation by the author. Several subsequent numerical studies with different turbulence closure model also calculated this dip in total pressure rise. Also, several studies attributed this total pressure deficit to a small leakage flow coming from the hub in the test article. As the experimental study cannot be repeated, either explanation cannot be validated. The primary purpose of the current investigation is to investigate the transonic flow field with both RANS and a Large Eddy Simulation (LES). The RANS approach gives similar results presented at the original blind test exercise. Although the RANS calculates higher overall total pressure rise, the total pressure deficit near the hub is calculated correctly. The numerical solution shows that the total pressure deficit is due to a hub corner flow separation. The calculated pressure rise from the LES agrees better with the measured total pressure rise especially near the casing area where the passage shock interacts with the tip clearance vortex and flow becomes unsteady due to this interaction. The LES simulation also calculates the total pressure rise deficit near the hub and it agrees well with the measured data. Author TRANSONIC COMPRESSORS; PRESSURE DISTRIBUTION; LARGE EDDY SIMULATION; NAVIER-STOKES EQUATION; COMPUTATIONAL FLUID DYNAMICS; FLOW CHARACTERISTICS; REYNOLDS AVERAGING; SEPARATED FLOW; TURBULENT FLOW; BOUNDARY LAYER SEPARATION 20090038701 NASA Glenn Research Center, Cleveland, OH, United States Attenuation of FJ44 Turbofan Engine Noise with a Foam-Metal Liner Installed Over-the-Rotor Sutliff, Daniel L.; Elliott, Dave M.; Jones, Michael G.; Hartley, Thomas C.; September 2009; In English; 30th Aeroacoustics Conference, 11-13 May 2009, Miami, Fl, United States; Original contains color and black and white illustrations Contract(s)/Grant(s): WBS 685676.01.03.08.0 Report No.(s): NASA/TM-2009-215666; AIAA Paper 2009-3141; E-17008; Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090038701 A Williams International FJ44-3A 3000-lb thrust class turbofan engine was used as a demonstrator for a Foam-Metal Liner (FML) installed in close proximity to the fan. Two FML designs were tested and compared to the hardwall baseline. Traditional single degree-of-freedom liner designs were also evaluated to provide a comparison. Farfield acoustic levels and limited engine performance results are presented in this paper. The results show that the FML achieved up to 5 dB Acoustic Power Level (PWL) overall attenuation in the forward quadrant, equivalent to the traditional liner design. An earlier report presented the test set-up and conditions. Author ENGINE NOISE; TURBOFAN ENGINES; SOUND PRESSURE; ACOUSTIC MEASUREMENT; DEGREES OF FREEDOM; LININGS 20090038702 NASA Glenn Research Center, Cleveland, OH, United States Health Monitoring of a Rotating Disk Using a Combined Analytical-Experimental Approach Abdul-Aziz, Ali; Woike, Mark R.; Lekki, John D.; Baaklini, George Y.; September 2009; In English; Original contains color and black and white illustrations Contract(s)/Grant(s): WBS 645846.02.07.03.11.03 Report No.(s): NASA/TM-2009-215675; E-17038; No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090038702 Rotating disks undergo rigorous mechanical loading conditions that make them subject to a variety of failure mechanisms leading to structural deformities and cracking. During operation, periodic loading fluctuations and other related factors cause fractures and hidden internal cracks that can only be detected via noninvasive types of health monitoring and/or nondestructive evaluation. These evaluations go further to inspect material discontinuities and other irregularities that have grown to become critical defects that can lead to failure. Hence, the objectives of this work is to conduct a collective analytical and experimental study to present a well-rounded structural assessment of a rotating disk by means of a health monitoring approach and to appraise the capabilities of an in-house rotor spin system. The analyses utilized the finite element method to analyze the disk with and without an induced crack at different loading levels, such as rotational speeds starting at 3000 up to 10 000 rpm. A parallel experiment was conducted to spin the disk at the desired speeds in an attempt to correlate the experimental findings with the analytical results. The testing involved conducting spin experiments which, covered the rotor in both damaged and undamaged (i.e., notched and unnotched) states. Damaged disks had artificially induced through-thickness flaws represented in the web region ranging from 2.54 to 5.08 cm (1 to 2 in.) in length. This study aims to identify defects that are greater than 1.27 cm (0.5 in.), applying available means of structural health monitoring and nondestructive evaluation, and documenting failure mechanisms experienced by the rotor system under typical turbine engine operating conditions. Author TURBINE ENGINES; NONDESTRUCTIVE TESTS; CRACKS; STRUCTURAL FAILURE; FRACTURES (MATERIALS); ROTATING DISKS; ROTORS Additions to the NASA Aeronautics and Space Database as of 11/20/2009 20090038706 Sest, Inc., Middleburgh Heights, OH, United States; Jet Propulsion Lab., California Inst. of Tech., Pasadena, CA, United States Effect of Ceramic Ball and Hybrid Stainless Steel Bearing/Wheel Combinations on the Lifetime of a Precision Translation Stage for the SIM Flight Project Lo, C. John; Klein, Kerry; Jones, William R., Jr.; Jansen, Mark J.; Wemhoner, Jens; October 2009; In English; Original contains color and black and white illustrations Contract(s)/Grant(s): NNC07JF14T; NAS7-03001WBS 431731.04.01.03 Report No.(s): NASA/CR-2009-215682; E-17053; Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090038706 A study of hybrid material couples using the Spiral Orbit Tribometer (SOT) was initiated to investigate both lubricated (Pennzane X2000 and Brayco 815Z) and unlubricated Si3N4, 440C SS, Rex 20, Cronidur X30 and X40 plates with Cerbec SN-101-C (Si3N4) and 440C balls. The hybrid wheel/bearing assembly will be used on the Linear Optical Delay Line (LODL) stage as an element of the NASA Space Interferometry Mission (SIM). SIM is an orbiting interferometer linking a pair of telescopes within the spacecraft and, by using an interferometry technique and several precision optical stages, is able to measure the motions of known stars much better than current ground or space based systems. This measurement will provide the data to "infer" the existence of any plants, undetectable by other methods, orbiting these known stars. Author BALL BEARINGS; TRIBOMETERS; DELAY LINES; SPACE MISSIONS; INTERFEROMETERS 20090038710 NASA Glenn Research Center, Cleveland, OH, United States The Case for Distributed Engine Control in Turbo-Shaft Engine Systems Culley, Dennis E.; Paluszewski, Paul J.; Storey, William; Smith, Bert J.; September 2009; In English; Original contains color and black and white illustrations Contract(s)/Grant(s): WBS 561581.02.08.03.17.03 Report No.(s): NASA/TM-2009-215654; AHS 2009 080366; E-16966; Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090038710 The turbo-shaft engine is an important propulsion system used to power vehicles on land, sea, and in the air. As the power plant for many high performance helicopters, the characteristics of the engine and control are critical to proper vehicle operation as well as being the main determinant to overall vehicle performance. When applied to vertical flight, important distinctions exist in the turbo-shaft engine control system due to the high degree of dynamic coupling between the engine and airframe and the affect on vehicle handling characteristics. In this study, the impact of engine control system architecture is explored relative to engine performance, weight, reliability, safety, and overall cost. Comparison of the impact of architecture on these metrics is investigated as the control system is modified from a legacy centralized structure to a more distributed configuration. A composite strawman system which is typical of turbo-shaft engines in the 1000 to 2000 hp class is described and used for comparison. The overall benefits of these changes to control system architecture are assessed. The availability of supporting technologies to achieve this evolution is also discussed. Author SHAFTS (MACHINE ELEMENTS); ACTIVE CONTROL; TURBINE ENGINES; HELICOPTERS; ENGINE CONTROL; CONTROL SYSTEMS DESIGN; DISTRIBUTED PARAMETER SYSTEMS 20090038711 NASA Glenn Research Center, Cleveland, OH, United States High Efficiency Nuclear Power Plants Using Liquid Fluoride Thorium Reactor Technology Juhasz, Albert J.; Rarick, Richard A.; Rangarajan, Rajmohan; October 2009; In English; Original contains color and black and white illustrations Contract(s)/Grant(s): WBS 138494.01.04.01 Report No.(s): NASA/TM-2009-215829; AIAA Paper 2009-4565; E-17030-1; Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090038711 An overall system analysis approach is used to propose potential conceptual designs of advanced terrestrial nuclear power plants based on Oak Ridge National Laboratory (ORNL) Molten Salt Reactor (MSR) experience and utilizing Closed Cycle Gas Turbine (CCGT) thermal-to-electric energy conversion technology. In particular conceptual designs for an advanced 1 GWe power plant with turbine reheat and compressor intercooling at a 950 K turbine inlet temperature (TIT), as well as near term 100 MWe demonstration plants with TITs of 950 and 1200 K are presented. Power plant performance data were obtained for TITs ranging from 650 to 1300 K by use of a Closed Brayton Cycle (CBC) systems code which considered the interaction between major sub-systems, including the Liquid Fluoride Thorium Reactor (LFTR), heat source and heat sink heat exchangers, turbo-generator machinery, and an electric power generation and transmission system. Optional off-shore submarine installation of the power plant is a major consideration. Author FLUORIDES; GAS TURBINES; NUCLEAR POWER PLANTS; REACTOR TECHNOLOGY; SYSTEMS ANALYSIS; THORIUM 20090038726 NASA Langley Research Center, Hampton, VA, United States LAURA Users Manual: 5.2-43231 Mazaheri, Alireza; Gnoffo, Peter A.; Johnston, Christopher O.; Kleb, Bil; November 2009; In English; Original contains color and black and white illustrations Contract(s)/Grant(s): WBS 736466.11.01.07.43.05.01 Report No.(s): NASA/TM-2009-215944; LF99-9703; L-19783; Copyright; Avail.: CASI: A05, Hardcopy Avail Online: http://hdl.handle.net/2060/20090038726 This users manual provides in-depth information concerning installation and execution of LAURA, version 5. LAURA is a structured, multi-block, computational aerothermodynamic simulation code. Version 5 represents a major refactoring of the original Fortran 77 LAURA code toward a modular structure afforded by Fortran 95. The refactoring improved usability and maintainability by eliminating the requirement for problem-dependent re-compilations, providing more intuitive distribution of functionality, and simplifying interfaces required for multiphysics coupling. As a result, LAURA now shares gas-physics modules, MPI modules, and other low-level modules with the FUN3D unstructured-grid code. In addition to internal refactoring, several new features and capabilities have been added, e.g., a GNU-standard installation process, parallel load balancing, automatic trajectory point sequencing, free-energy minimization, and coupled ablation and flowfield radiation. Author AEROTHERMODYNAMICS; ABLATION; FLOW DISTRIBUTION; COMPUTERIZED SIMULATION; UNSTRUCTURED GRIDS (MATHEMATICS); USER MANUALS (COMPUTER PROGRAMS); FREE ENERGY; COMPUTER PROGRAMS
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