99-01 New NASA STI
Nov 22, 2009 -- Additions to the NASA scientific and technical information knowledge base
Title:
Hard X-ray Optics Technology Development for Astronomy at the Marshall Space Flight Center
Document ID:
20090037668
Report #:
None
Available Online:
http://hdl.handle.net/2060/20090037668
Sales Agency:
CASI Hardcopy A01 Copyright
Author(s):
Gubarev, Mikhail (NASA Marshall Space Flight Center) Ramsey, Brian (NASA Marshall Space Flight Center) Kilaru, Kiranmayee (Alabama Univ.)
Published:
20090922
Source:
NASA Marshall Space Flight Center (Huntsville, AL, United States)
Pages:
2
Contract #:
None
Abstract:
Grazing-incidence telescopes based on Wolter 1 geometry have delivered impressive advances in astrophysics at soft-x-ray wavelengths, while the hard xray region remains relatively unexplored at fine angular resolution and high sensitivities. The ability to perform ground-breaking science in the hard-x-ray energy range had been the motivation for technology developments aimed at fabricating low-cost, light-weight, high-quality x-ray mirrors. Grazing-incidence x-ray optics for high-energy astrophysical applications is being developed at MSFC using the electroform-nickel replication process.
Language:
English
Notes:
International Workshop on X-Ray Mirror Design, Fabrication, and Metrology Osaka 22-24 Sep. 2009
Title:
Ares I-X Overview
Document ID:
20090037669
Report #:
M09-0696
Available Online:
http://hdl.handle.net/2060/20090037669
Sales Agency:
CASI Hardcopy A02 No Copyright
Author(s):
Davis, Stephan R. (NASA Marshall Space Flight Center) Askins, Bruce R. (NASA Marshall Space Flight Center)
Published:
20090914
Source:
NASA Marshall Space Flight Center (Huntsville, AL, United States)
Pages:
7
Contract #:
None
Abstract:
The Ares I-X flight test is the first development flight of the Ares I crew launch vehicle. This mission, first conceived in 2006, will be launching later in 2009. Its primary mission objectives will be to demonstrate flight and roll control of a dynamically similar vehicle, perform a separation event and measure its shock effects, stack and recover a first stage booster, and demonstrate ground operations. All of the primary flight test vehicle s hardware is at Kennedy Space Center, and is being stacked in the Vehicle Assembly Building for a liftoff at Launch Complex 39B. Mission hardware specific to Ares I-X also is being installed at Launch Complex 39, which has been supporting Space Shuttle operations. This presentation will provide a status and preview of the upcoming mission.
Language:
English
Notes:
AIAA Space 2009 Conference and Exhibition Pasadena, CA 14-17 Sep. 2009
Title:
Ares Launch Vehicles Overview
Document ID:
20090037670
Report #:
M09-0705
Available Online:
http://hdl.handle.net/2060/20090037670
Sales Agency:
CASI Hardcopy A02 No Copyright
Author(s):
Vanhooser, Teresa (NASA Marshall Space Flight Center)
Published:
20090916
Source:
NASA Marshall Space Flight Center (Huntsville, AL, United States)
Pages:
9
Contract #:
None
Abstract:
Since 2005, the Ares Projects have been building the nation s next generation of crew and cargo launch vehicles. As part of the Constellation Program, the Ares vehicles will enable astronauts in the Orion crew exploration vehicle and Altair lunar lander to reach the Moon and beyond. These vehicles draw upon hardware and experienced developed over 50 years of exploration, while also incorporating technology and management practices from today. Ares is concentrating on building the Ares I crew launch vehicle to ensure America s continued ability to send crews to the International Space Station. Progress has been made on design, fabrication, and testing for the first stage, upper stage, upper stage engine, and integrated vehicle. This presentation will provide an overview of the Ares launch vehicles architecture, milestone progress, and top project risks.
Language:
English
Notes:
AIAA Space 2009 Conference and Exhibition Pasadena, CA 14-17 Sep. 2009
Title:
Testing of NASA LaRC Materials under MISSE 6 and MISSE 7 Missions
Document ID:
20090037671
Report #:
7467-13, LF99-9181
Available Online:
http://hdl.handle.net/2060/20090037671
Sales Agency:
CASI Hardcopy A02 No Copyright
Author(s):
Prasad, Narasimha S. (NASA Langley Research Center)
Published:
20090802
Source:
NASA Langley Research Center (Hampton, VA, United States)
Pages:
6
Contract #:
None
Abstract:
The objective of the Materials International Space Station Experiment (MISSE) is to study the performance of novel materials when subjected to the synergistic effects of the harsh space environment for several months. MISSE missions provide an opportunity for developing space qualifiable materials. Two lasers and a few optical components from NASA Langley Research Center (LaRC) were included in the MISSE 6 mission for long term exposure. MISSE 6 items were characterized and packed inside a ruggedized Passive Experiment Container (PEC) that resembles a suitcase. The PEC was tested for survivability due to launch conditions. MISSE 6 was transported to the international Space Station (ISS) via STS 123 on March 11. 2008. The astronauts successfully attached the PEC to external handrails of the ISS and opened the PEC for long term exposure to the space environment. The current plan is to bring the MISSE 6 PEC back to the Earth via STS 128 mission scheduled for launch in August 2009. Currently, preparations for launching the MISSE 7 mission are progressing. Laser and lidar components assembled on a flight-worthy platform are included from NASA LaRC. MISSE 7 launch is scheduled to be launched on STS 129 mission. This paper will briefly review recent efforts on MISSE 6 and MISSE 7 missions at NASA Langley Research Center (LaRC).
Language:
English
Notes:
SPIE Optics and Photonics San Diego, CA 2-6 Aug. 2009
Title:
Exploring Divisibility and Summability of 'Photon' Wave Packets in Nonlinear Optical Phenomena
Document ID:
20090037673
Report #:
7421-8, LF99-9180
Available Online:
http://hdl.handle.net/2060/20090037673
Sales Agency:
CASI Hardcopy A02 Copyright
Author(s):
Prasad, Narasimha (NASA Langley Research Center) Roychoudhuri, Chandrasekhar (Connecticut Univ.)
Published:
20090802
Source:
NASA Langley Research Center (Hampton, VA, United States)
Pages:
8
Contract #:
None
Abstract:
Formulations for second and higher harmonic frequency up and down conversions, as well as multi photon processes directly assume summability and divisibility of photons. Quantum mechanical (QM) interpretations are completely congruent with these assumptions. However, for linear optical phenomena (interference, diffraction, refraction, material dispersion, spectral dispersion, etc.), we have a profound dichotomy. Most optical engineers innovate and analyze all optical instruments by propagating pure classical electromagnetic (EM) fields using Maxwell s equations and gives only lip-service to the concept "indivisible light quanta". Further, irrespective of linearity or nonlinearity of the phenomena, the final results are always registered through some photo-electric or photo-chemical effects. This is mathematically well modeled by a quadratic action (energy absorption) relation. Since QM does not preclude divisibility or summability of photons in nonlinear & multi-photon effects, it cannot have any foundational reason against these same possibilities in linear optical phenomena. It implies that we must carefully revisit the fundamental roots behind all light-matter interaction processes and understand the common origin of "graininess" and "discreteness" of light energy.
Language:
English
Notes:
SPIE Optics and Photonics San Diego, CA 2-6 Aug. 2009
Title:
Vibration Challenges in the Design of NASA's Ares Launch Vehicles
Document ID:
20090037675
Report #:
M09-0720
Available Online:
http://hdl.handle.net/2060/20090037675
Sales Agency:
CASI Hardcopy A04 No Copyright
Author(s):
Ryan, Stephen G. (NASA Marshall Space Flight Center)
Published:
20090830
Source:
NASA Marshall Space Flight Center (Huntsville, AL, United States)
Pages:
54
Contract #:
None
Abstract:
This paper focuses on the vibration challenges inherent in the design of NASA s Ares launch vehicles. A brief overview of the launch system architecture is provided to establish the context for the discussion. Following this is a general discussion of the design considerations and analytical disciplines that are affected by vibration. The first challenge discussed is that of coupling between the vehicle flight control system and fundamental vibrational modes of the vehicle. The potential destabilizing influence of the vibrational dynamics is described along with discussion of the typical methods employed to overcome this issue. Next is a general discussion of the process for developing the design loads for the primary structure. This includes quasi-steady loads and dynamic loads induced by the structural dynamic response. The two principal parts of this response are the gust induced responses of the lower frequency modes and the buffet induced responses of the higher frequency modes. Structural dynamic model validation will also be addressed. Following this, discussions of three somewhat unique topics of Pogo Instability, Solid Booster Thrust Oscillation, and Liquid Rocket Engine Turbopump Rotordynamic Stability and Response are presented.
Language:
English
Notes:
2009 International Design Engineering Technical Conference: 22nd Biennial Conference on Mechanical Vibration and Noise San Diego, CA 30 Aug. - 2 Sep. 2009
Title:
Ares V: Current Status and Future Capabilities
Document ID:
20090037676
Report #:
M09-0724
Available Online:
http://hdl.handle.net/2060/20090037676
Sales Agency:
CASI Hardcopy A02 No Copyright
Author(s):
Sumrall, Phil (NASA Marshall Space Flight Center)
Published:
20090914
Source:
NASA Marshall Space Flight Center (Huntsville, AL, United States)
Pages:
8
Contract #:
None
Abstract:
This slide presentation reviews the progress made in the design and development of the Ares V launch vehicle. Included in the presentation are views of the elements of the Ares V, the commonality of the Ares I and V, a chart that shows the progress made in the design of the launcher, description of the current activities around the design and preparation for the Ares V, and a slide describing the prospect of large payload volume and the flexibility that this gives to new space sciences.
Language:
English
Notes:
AIAA Space 2009 Pasadena, CA 14-17 Sep. 2009
Title:
Ares First Stage Element Status
Document ID:
20090037677
Report #:
M09-0739
Available Online:
http://hdl.handle.net/2060/20090037677
Sales Agency:
CASI Hardcopy A03 No Copyright
Author(s):
Tiller, Bruce K. (NASA Marshall Space Flight Center)
Published:
20090914
Source:
NASA Marshall Space Flight Center (Huntsville, AL, United States)
Pages:
11
Contract #:
None
Abstract:
This slide presentation summarizes the status of the various elements of the first stage of the Ares I vehicle. It includes views of the first stage in relation to the complete Ares rocket, details of the first stage, upgrades for the Ares, the Avionics system, and the thrust oscillation system. There are also pictures from the testing.
Language:
English
Notes:
AIAA Space 2009 Conference and Exhibition Pasadena, CA 14-17 Sep. 2009
Title:
Advanced Avionics and Processor Systems for Space and Lunar Exploration
Document ID:
20090037678
Report #:
M09-0738, M09-0761
Available Online:
http://hdl.handle.net/2060/20090037678
Sales Agency:
CASI Hardcopy A03 Copyright
Author(s):
Keys, Andrew S. (NASA Marshall Space Flight Center) Adams, James H. (NASA Marshall Space Flight Center) Ray, Robert E. (Jacobs Engineering Group, Inc.) Johnson, Michael A. (NASA Goddard Space Flight Center) Cressler, John D. (Georgia Inst. of Tech.)
Published:
20090914
Source:
NASA Marshall Space Flight Center (Huntsville, AL, United States)
Pages:
40
Contract #:
None
Abstract:
NASA's newly named Advanced Avionics and Processor Systems (AAPS) project, formerly known as the Radiation Hardened Electronics for Space Environments (RHESE) project, endeavors to mature and develop the avionic and processor technologies required to fulfill NASA's goals for future space and lunar exploration. Over the past year, multiple advancements have been made within each of the individual AAPS technology development tasks that will facilitate the success of the Constellation program elements. This paper provides a brief review of the project's recent technology advancements, discusses their application to Constellation projects, and addresses the project's plans for the coming year.
Language:
English
Notes:
AIAA SPACE 2009 Conference and Exposition Pasadena, CA 14-17 Sep. 2009
Title:
The Lunar Mapping and Modeling Project
Document ID:
20090037679
Report #:
M09-0751
Available Online:
http://hdl.handle.net/2060/20090037679
Sales Agency:
CASI Hardcopy A01 No Copyright
Author(s):
Noble, Sarah K. (NASA Marshall Space Flight Center) French, R. A. (NASA Marshall Space Flight Center) Nall, M. E. (NASA Marshall Space Flight Center) Muery, K. G. (NASA Marshall Space Flight Center)
Published:
20091116
Source:
NASA Marshall Space Flight Center (Huntsville, AL, United States)
Pages:
1
Contract #:
None
Abstract:
The Lunar Mapping and Modeling Project (LMMP) has been created to manage the development of a suite of lunar mapping and modeling products that support the Constellation Program (CxP) and other lunar exploration activities, including the planning, design, development, test and operations associated with lunar sortie missions, crewed and robotic operations on the surface, and the establishment of a lunar outpost. The information provided through LMMP will assist CxP in: planning tasks in the areas of landing site evaluation and selection, design and placement of landers and other stationary assets, design of rovers and other mobile assets, developing terrain-relative navigation (TRN) capabilities, and assessment and planning of science traverses.
Language:
English
Notes:
Lunar Exploration Analysis Group Meeting Houston, TX 16-19 Nov. 2009
Title:
CRYOTE (Cryogenic Orbital Testbed) Concept
Document ID:
20090037680
Report #:
M09-0747
Available Online:
http://hdl.handle.net/2060/20090037680
Sales Agency:
CASI Hardcopy A03 Copyright
Author(s):
Gravlee, Mari (United Launch Alliance) Kutter, Bernard (United Launch Alliance) Wollen, Mark (Innovative Engineering Solutions) Rhys, Noah (Yetispace, Inc.) Walls, Laurie (NASA Kennedy Space Center)
Published:
20090914
Source:
United Launch Alliance (Denver, CO, United States)
Pages:
15
Contract #:
None
Abstract:
Demonstrating cryo-fluid management (CFM) technologies in space is critical for advances in long duration space missions. Current space-based cryogenic propulsion is viable for hours, not the weeks to years needed by space exploration and space science. CRYogenic Orbital TEstbed (CRYOTE) provides an affordable low-risk environment to demonstrate a broad array of critical CFM technologies that cannot be tested in Earth's gravity. These technologies include system chilldown, transfer, handling, health management, mixing, pressure control, active cooling, and long-term storage. United Launch Alliance is partnering with Innovative Engineering Solutions, the National Aeronautics and Space Administration, and others to develop CRYOTE to fly as an auxiliary payload between the primary payload and the Centaur upper stage on an Atlas V rocket. Because satellites are expensive, the space industry is largely risk averse to incorporating unproven systems or conducting experiments using flight hardware that is supporting a primary mission. To minimize launch risk, the CRYOTE system will only activate after the primary payload is separated from the rocket. Flying the testbed as an auxiliary payload utilizes Evolved Expendable Launch Vehicle performance excess to cost-effectively demonstrate enhanced CFM.
Language:
English
Notes:
AIAA Space 2009 Conference and Exposition Pasadena, CA 14-17 Sep. 2009
Title:
Measurement and Analysis of a Ferroelectric Field-Effect Transistor NAND Gate
Document ID:
20090037681
Report #:
M09-0748
Available Online:
http://hdl.handle.net/2060/20090037681
Sales Agency:
CASI Hardcopy A01 Copyright
Author(s):
Phillips, Thomas A. (NASA Marshall Space Flight Center) MacLeond, Todd C. (NASA Marshall Space Flight Center) Sayyah, Rana (Alabama Univ.) Ho, Fat Duen (Alabama Univ.)
Published:
20090927
Source:
NASA Marshall Space Flight Center (Huntsville, AL, United States)
Pages:
2
Contract #:
None
Abstract:
Previous research investigated expanding the use of Ferroelectric Field-Effect Transistors
electronic devices beyond memory circuits. Ferroelectric based transistors
them interesting and useful properties in digital logic
as it is one of the fundamental building
electronic circuits. In this paper, NAND gate circuits were constructed utilizing
with positive polarization were used for the standard
NAND gate n-channel transistors and n-channel FFETs with negative polarization were
gate p-channel transistors. The voltage transfer curves were
between the actual device data and the
data. These results are compared to standard MOS logic circuits. The circuits
fully operational circuits that would interface with existing logic
into the possibility of using ferroelectric transistors in
devices are presented, and their potential
drawbacks are discussed.
Language:
English
Notes:
Measurement and Analysis of a Ferroelectric Field-Effect Transistor NAND Gate 15th conference Colorado Springs, CO 27-30 Sep. 2009
Title:
EEE Parts Related Issues
Document ID:
20090038173
Report #:
STI 09-170
Available Online:
http://hdl.handle.net/2060/20090038173
Sales Agency:
CASI Hardcopy A02 No Copyright
Author(s):
Hughitt, Brian (NASA)
Published:
20091030
Source:
NASA (Washington, DC, United States)
Pages:
8
Contract #:
None
Abstract:
The contents include: 1) Water Soluble Flux; 2) Non-Hermetic Packages; 3) Counterfeit Parts; and 4) Lead-Free Solder.
Language:
English
Notes:
JAXA/ESA/NASA Trilateral Safety and Mission Assurance Meeting FROM 30 Oct. 2009
Title:
Benefits of Using a Mars Forward Strategy for Lunar Surface Systems
Document ID:
20090038178
Report #:
M09-0735
Available Online:
http://hdl.handle.net/2060/20090038178
Sales Agency:
CASI Hardcopy A02 No Copyright
Author(s):
Mulqueen, Jack (NASA Marshall Space Flight Center) Griffin, Brand (NASA Marshall Space Flight Center) Smitherman, David (NASA Marshall Space Flight Center) Maples, Dauphne (NASA Marshall Space Flight Center)
Published:
20090914
Source:
NASA Marshall Space Flight Center (Huntsville, AL, United States)
Pages:
9
Contract #:
None
Abstract:
This paper identifies potential risk reduction, cost savings and programmatic procurement benefits of a Mars Forward Lunar Surface System architecture that provides commonality or evolutionary development paths for lunar surface system elements applicable to Mars surface systems. The objective of this paper is to identify the potential benefits for incorporating a Mars Forward development strategy into the planned Project Constellation Lunar Surface System Architecture. The benefits include cost savings, technology readiness, and design validation of systems that would be applicable to lunar and Mars surface systems. The paper presents a survey of previous lunar and Mars surface systems design concepts and provides an assessment of previous conclusions concerning those systems in light of the current Project Constellation Exploration Architectures. The operational requirements for current Project Constellation lunar and Mars surface system elements are compared and evaluated to identify the potential risk reduction strategies that build on lunar surface systems to reduce the technical and programmatic risks for Mars exploration. Risk reduction for rapidly evolving technologies is achieved through systematic evolution of technologies and components based on Moore's Law superimposed on the typical NASA systems engineering project development "V-cycle" described in NASA NPR 7120.5. Risk reduction for established or slowly evolving technologies is achieved through a process called the Mars-Ready Platform strategy in which incremental improvements lead from the initial lunar surface system components to Mars-Ready technologies. The potential programmatic benefits of the Mars Forward strategy are provided in terms of the transition from the lunar exploration campaign to the Mars exploration campaign. By utilizing a sequential combined procurement strategy for lunar and Mars exploration surface systems, the overall budget wedges for exploration systems are reduced and the costly technological development gap between the lunar and Mars programs can be eliminated. This provides a sustained level of technological competitiveness as well as maintaining a stable engineering and manufacturing capability throughout the entire duration of Project Constellation.
Language:
English
Notes:
AIAA Space 2009 Pasadena, CA 14-17 Sep. 2009
Title:
Analysis of the Measurement and Modeling of a Digital Inverter Based on a Ferroelectric Transistor
Document ID:
20090038574
Report #:
M09-0793
Available Online:
http://hdl.handle.net/2060/20090038574
Sales Agency:
CASI Hardcopy A01 Copyright
Author(s):
MacLeod, Todd C. (NASA Marshall Space Flight Center) Phillips, Thomas A. (NASA Marshall Space Flight Center) Sayyah, Rana (Alabama Univ.) Ho, Fat D. (Alabama Univ.)
Published:
20090927
Source:
NASA Marshall Space Flight Center (Huntsville, AL, United States)
Pages:
2
Contract #:
None
Abstract:
The use of ferroelectric materials for digital memory devices is widely researched and implemented, but ferroelectric devices also possess unique characteristics that make them have interesting and useful properties in digital circuits. Because ferroelectric transistors possess the properties of hysteresis and nonlinearity, a digital inverter containing a FeFET has very different characteristics than one with a traditional FET. This paper characterizes the properties of the measurement and modeling of a FeFET based digital inverter. The circuit was set up using discrete FeFETs. The purpose of this circuit was not to produce a practical integrated circuit that could be inserted directly into existing digital circuits, but to explore the properties and characteristics of such a device and to look at possible future uses. Input and output characteristics are presented, as well as timing measurements. Comparisons are made between the ferroelectric device and the properties of a standard digital inverter. Potential benefits and possible uses of such a device are presented.
Language:
English
Notes:
International Symposium on Integrated Ferroelectrics and Functionalities Colorado Springs, CO 27-30 Sep. 2009
Title:
A Mathematical Model of a Simple Amplifier Using a Ferroelectric Transistor
Document ID:
20090038575
Report #:
M09-0795
Available Online:
http://hdl.handle.net/2060/20090038575
Sales Agency:
CASI Hardcopy A03 Copyright
Author(s):
Sayyah, Rana (Alabama Univ.) Hunt, Mitchell (Alabama Univ.) MacLeod, Todd C. (NASA Marshall Space Flight Center) Ho, Fat D. (Alabama Univ.)
Published:
20090927
Source:
NASA Marshall Space Flight Center (Huntsville, AL, United States)
Pages:
20
Contract #:
None
Abstract:
This paper presents a mathematical model characterizing the behavior of a simple amplifier using a FeFET. The model is based on empirical data and incorporates several variables that affect the output, including frequency, load resistance, and gate-to-source voltage. Since the amplifier is the basis of many circuit configurations, a mathematical model that describes the behavior of a FeFET-based amplifier will help in the integration of FeFETs into many other circuits.
Language:
English
Notes:
International Symposium on Integrated Ferroelectrics and Functionalities Colorado Springs, CO 27-30 Sep. 2009
Title:
Gallium Electromagnetic (GEM) Thruster Performance Measurements
Document ID:
20090038576
Report #:
M09-0810, IEPC-2009-233
Available Online:
http://hdl.handle.net/2060/20090038576
Sales Agency:
CASI Hardcopy A03 Copyright
Author(s):
Thomas, Robert E. (Illinois Univ.) Burton, Rodney L. (Illinois Univ.) Polzin, K. A. (NASA Marshall Space Flight Center)
Published:
20090920
Source:
NASA Marshall Space Flight Center (Huntsville, AL, United States)
Pages:
14
Contract #:
None
Abstract:
Discharge current, terminal voltage, and mass bit measurements are performed on a coaxial gallium electromagnetic thruster at discharge currents in the range of 7-23 kA. It is found that the mass bit varies quadratically with the discharge current which yields a constant exhaust velocity of 20 km/s. Increasing the electrode radius ratio of the thruster from to 2.6 to 3.4 increases the thruster efficiency from 21% to 30%. When operating with a central gallium anode, macroparticles are ejected at all energy levels tested. A central gallium cathode ejects macroparticles when the current density exceeds 3.7 10(exp 8) A/square m . A spatially and temporally broad spectroscopic survey in the 220-520 nm range is used to determine which species are present in the plasma. The spectra show that neutral, singly, and doubly ionized gallium species are present in the discharge, as well as annular electrode species at higher energy levels. Axial Langmuir triple probe measurements yield electron temperatures in the range of 0.8-3.8 eV and electron densities in the range of 8 x 10(exp )20 to 1.6 x 10(exp 21) m(exp -3) . Triple probe measurements suggest an exhaust plume with a divergence angle of 9 , and a completely doubly ionized plasma at the ablating thruster cathode.
Language:
English
Notes:
31st International Electric Propulsion Conference Ann Arbor, MI 20-24 Sep. 2009
Title:
Discharge Oscillations in a Permanent Magnet Cylindrical Hall-Effect Thruster
Document ID:
20090038587
Report #:
M09-0812, IEPC-2009-122
Available Online:
http://hdl.handle.net/2060/20090038587
Sales Agency:
CASI Hardcopy A02 Copyright
Author(s):
Polzin, K. A. (NASA Marshall Space Flight Center) Sooby, E. S. (NASA Marshall Space Flight Center) Raitses, Y. (Princeton Plasma Physics Lab.) Merino, E. (Princeton Plasma Physics Lab.) Fisch, N. J. (Princeton Plasma Physics Lab.)
Published:
20090920
Source:
NASA Marshall Space Flight Center (Huntsville, AL, United States)
Pages:
8
Contract #:
None
Abstract:
Measurements of the discharge current in a cylindrical Hall thruster are presented to quantify plasma oscillations and instabilities without introducing an intrusive probe into the plasma. The time-varying component of the discharge current is measured using a current monitor that possesses a wide frequency bandwidth and the signal is Fourier transformed to yield the frequency spectra present, allowing for the identification of plasma oscillations. The data show that the discharge current oscillations become generally greater in amplitude and complexity as the voltage is increased, and are reduced in severity with increasing flow rate. The breathing mode ionization instability is identified, with frequency as a function of discharge voltage not increasing with discharge voltage as has been observed in some traditional Hall thruster geometries, but instead following a scaling similar to a large-amplitude, nonlinear oscillation mode recently predicted in for annular Hall thrusters. A transition from lower amplitude oscillations to large relative fluctuations in the oscillating discharge current is observed at low flow rates and is suppressed as the mass flow rate is increased. A second set of peaks in the frequency spectra are observed at the highest propellant flow rate tested. Possible mechanisms that might give rise to these peaks include ionization instabilities and interactions between various oscillatory modes.
Language:
English
Notes:
31st International Electric Propulsion Conference Ann Arbor, MI 20-24 Sep. 2009
Title:
Right Ventricular Tissue Doppler in Space Flight
Document ID:
20090038607
Report #:
JSC-CN-19030
Available Online:
http://hdl.handle.net/2060/20090038607
Sales Agency:
CASI Hardcopy A01 Copyright
Author(s):
Hamilton, Douglas R. (Wyle Labs., Inc.) Barratt, Michael R. (NASA Johnson Space Center) Sargsyan, Ashot E. (Wyle Labs., Inc.) Ebert, Douglas (Wyle Labs., Inc.) Garcia, Kathleen M. (Wyle Labs., Inc.) Martin, David S. (Wyle Labs., Inc.) Dulchavsky, Scott A. (Ford (Henry) Hospital) Duncan, J. Michael (NASA Johnson Space Center)
Published:
20090101
Source:
NASA Johnson Space Center (Houston, TX, United States)
Pages:
1
Contract #:
None
Abstract:
Tissue Doppler (TD) registers movement of a given sample of cardiac tissue throughout the cardiac cycle. TD spectra of the right ventricle (RV) were obtained from a long-duration ISS crewmember as a portion of an ongoing experiment ("Braslet" test objective). To our knowledge, this is the first report of RV TD conducted in space flight, and the data represent reproducibility and fidelity of this application in space and serve as the first "space normal" data set. Methods RV TD was performed by astronaut scientists remotely guided by an ultrasound expert from Mission Control Center, Houston, TX. In four of the subjects, RV TD was acquired from the free wall near the tricuspid annulus in two separate sessions 4 to 7 days apart. A fifth subject had only one session. All digital DICOM frames were exported for off-line analysis. Systolic (S ), early diastolic (E ) and late diastolic (A ) velocities were measured. RV Tei-index was calculated using diastolic and systolic time intervals as a combined measure of myocardial performance. Results and Discussion The mean values from the first 4 subjects (8 sessions) were used as the on-orbit reference data, and subject 5 was considered as a hypothetical patient for comparison (see Table). The greatest difference was in the early diastolic A (31 %) yet the standard deviation (a) for A amongst the reference subjects was 2.25 (mean = 16.02). Of interest is the Tei index, a simple and feasible indicator of overall ventricular function; it was similar amongst all the subjects. The late diastolic A seems to compensate for the variance in E . Normal Tei index for the RV is < 0.3, yet our data show all but one subject consistently above this level, notwithstanding their nominal responses to daily exercise in microgravity. These data remind us that the physiology of RV preload in altered gravity environments is still not completely understood.
Language:
English
Notes:
Aerospace Medicine Association Annual Meeting Phoenix, AZ 9-13 May 2010
Title:
Use of DSC and DMA to Study Rubber Crystallization as a Possible Cause for a Tear in a Neoprene Glove Used in a Space Shuttle Pressurized Astronaut Suit
Document ID:
20090038652
Report #:
M09-0749
Available Online:
http://hdl.handle.net/2060/20090038652
Sales Agency:
CASI Hardcopy A03 No Copyright
Author(s):
Wingard, Doug (NASA Marshall Space Flight Center)
Published:
20090921
Source:
NASA Marshall Space Flight Center (Huntsville, AL, United States)
Pages:
24
Contract #:
None
Abstract:
The Advanced Crew Escape Suit (ACES) is a pressurized suit normally worn by astronauts during launch and landing phases of Space Shuttle operations. In 2008, a large tear (0.5 -1 in. long, between the pinky and ring finger) in the ACES left-hand glove made of neoprene latex rubber was found during training for Shuttle flight STS-124. An investigation to help determine the cause(s) of the glove tear was headed by the NASA Johnson Space Center (JSC) in Houston, Texas. Efforts at JSC to reproduce the actual glove tear pattern by cutting/tearing or rupturing were unsuccessful. Chemical and material property data from JSC such as GC-MS, FTIR, DSC and TGA mostly showed little differences between samples from the torn and control gloves. One possible cause for the glove tear could be a wedding ring/band worn by a male astronaut. Even with a smooth edge, such a ring could scratch the material and initiate the tear observed in the left-hand glove. A decision was later made by JSC to not allow the wearing of such a ring during training or actual flight. Another possible cause for the ACES glove tear is crystallinity induced by strain in the neoprene rubber over a long period of time and use. Neoprene is one several elastomeric materials known to be susceptible to crystallization, and such a process is accelerated with exposure of the material to cold temperatures plus strain. When the temperature is lowered below room temperature, researchers have shown that neoprene crystallization may be maintained at temperatures as high as 45-50 F, with a maximum crystallization rate near 20-25 F (1). A convenient conditioning temperature for inducing neoprene crystallization is a typical freezer that is held near 0 F. For work at the NASA Marshall Space Flight Center (MSFC), samples were cut from several areas/locations (pinky/ring finger crotch, index finger and palm) on each of two pairs of unstrained ACES gloves for DSC and DMA thermal analysis testing. The samples were conditioned in a freezer for various times up to about 14 days. Some rectangular conditioned samples were unstrained, while most were subjected to strains up to 250% with the aid of two slotted aluminum blocks and two aluminum clamps per sample. Trends were observed to correlate DSC data (heat of fusion) and DMA data (linear CTE and stress for iso-strain testing) with: (a) sample location on each glove; and (b) level of strain during conditioning. Control samples cut as is from each glove location were also tested by DSC and DMA.
Language:
English
Notes:
2009 North American Thermal Analysis Society (NATAS) Conference Lubbock, TX 21-23 Sept. 2009
Title:
An Investigation of Differential Deposition for Figure Corrections in Full-Shell Grazing-Incidents X-Ray Optics
Document ID:
20090038653
Report #:
M09-0759, M09-0760
Available Online:
http://hdl.handle.net/2060/20090038653
Sales Agency:
CASI Hardcopy A02 Copyright
Author(s):
Gubarev, Mikhail V. (NASA Marshall Space Flight Center) Kilaru, Kirenmayee (Alabama Univ.) Ramsey, Brian D. (NASA Marshall Space Flight Center)
Published:
20090922
Source:
NASA Marshall Space Flight Center (Huntsville, AL, United States)
Pages:
10
Contract #:
None
Abstract:
We are investigating differential deposition as a way of correcting small figure errors inside full-shell grazing-incidence x-ray optics. The optics in our study are fabricated using the electroformed-nickel-replication technique, and the figure errors arise from fabrication errors in the mandrel, from which the shells are replicated, as well as errors induced during the electroforming process. Combined, these give sub-micron-scale figure deviations which limit the angular resolution of the optics to approx. 10 arcsec. Sub-micron figure errors can be corrected by selectively depositing (physical vapor deposition) material inside the shell. The requirements for this filler material are that it must not degrade the ultra-smooth surface finish necessary for efficient x-ray reflection (approx. 5 A rms), and must not be highly stressed. In addition, a technique must be found to produce well controlled and defined beams within highly constrained geometries, as some of our mirror shells are less than 3 cm in diameter.
Language:
English
Notes:
International Workshop on X-ray Mirror Design, Fabrication, and Metrology Suita,Osaka 22-24 Sept. 2009
Title:
NASA Patent Abstracts Bibliography: A Continuing Bibliography
Document ID:
20090038656
Report #:
NASA/SP-2009-7039/SUPPL70
Available Online:
http://hdl.handle.net/2060/20090038656
Sales Agency:
CASI Hardcopy A04 No Copyright
Author(s):
(Author(s) Not Available)
Published:
20091001
Source:
NASA Langley Research Center (Hampton, VA, United States)
Pages:
71
Contract #:
None
Abstract:
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.
Language:
English
Title:
Multi-Core Processor Memory Contention Benchmark Analysis Case Study
Document ID:
20090038666
Report #:
None
Available Online:
http://hdl.handle.net/2060/20090038666
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CASI Hardcopy A03 Copyright
Author(s):
Simon, Tyler (Computer Sciences Corp.) McGalliard, James (General Services Administration)
Published:
20090101
Source:
Computer Sciences Corp. (Greenbelt, MD, United States)
Pages:
12
Contract #:
NNG08HZ01I
Abstract:
Multi-core processors dominate current mainframe, server, and high performance computing (HPC) systems. This paper provides synthetic kernel and natural benchmark results from an HPC system at the NASA Goddard Space Flight Center that illustrate the performance impacts of multi-core (dual- and quad-core) vs. single core processor systems. Analysis of processor design, application source code, and synthetic and natural test results all indicate that multi-core processors can suffer from significant memory subsystem contention compared to similar single-core processors.
Language:
English
Notes:
35th International Computer Measurement Group Conference - CMG'09 Dallas, TX 6-11 Dec. 2009
Title:
Towards Behavioral Reflexion Models
Document ID:
20090038668
Report #:
None
Available Online:
http://hdl.handle.net/2060/20090038668
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CASI Hardcopy A02 Copyright
Author(s):
Ackermann, Christopher (Fraunhofer USA, Inc.) Lindvall, Mikael (Fraunhofer USA, Inc.) Cleaveland, Rance (Fraunhofer USA, Inc.)
Published:
20090101
Source:
Fraunhofer USA, Inc. (College Park, MD, United States)
Pages:
10
Contract #:
None
Abstract:
Software architecture has become essential in the struggle to manage today s increasingly large and complex systems. Software architecture views are created to capture important system characteristics on an abstract and, thus, comprehensible level. As the system is implemented and later maintained, it often deviates from the original design specification. Such deviations can have implication for the quality of the system, such as reliability, security, and maintainability. Software architecture compliance checking approaches, such as the reflexion model technique, have been proposed to address this issue by comparing the implementation to a model of the systems architecture design. However, architecture compliance checking approaches focus solely on structural characteristics and ignore behavioral conformance. This is especially an issue in Systems-of- Systems. Systems-of-Systems (SoS) are decompositions of large systems, into smaller systems for the sake of flexibility. Deviations of the implementation to its behavioral design often reduce the reliability of the entire SoS. An approach is needed that supports the reasoning about behavioral conformance on architecture level. In order to address this issue, we have developed an approach for comparing the implementation of a SoS to an architecture model of its behavioral design. The approach follows the idea of reflexion models and adopts it to support the compliance checking of behaviors. In this paper, we focus on sequencing properties as they play an important role in many SoS. Sequencing deviations potentially have a severe impact on the SoS correctness and qualities. The desired behavioral specification is defined in UML sequence diagram notation and behaviors are extracted from the SoS implementation. The behaviors are then mapped to the model of the desired behavior and the two are compared. Finally, a reflexion model is constructed that shows the deviations between behavioral design and implementation. This paper discusses the approach and shows how it can be applied to investigate reliability issues in SoS.
Language:
English
Notes:
20th annual International Symposium on Software Reliability Engineering (ISSRE 2009) Bangalore 16-19 Nov. 2009
Title:
J-2X Upper Stage Engine: Hardware and Testing 2009
Document ID:
20090038671
Report #:
M09-0725
Available Online:
http://hdl.handle.net/2060/20090038671
Sales Agency:
CASI Hardcopy A02 No Copyright
Author(s):
Buzzell, James C. (NASA Marshall Space Flight Center)
Published:
20090914
Source:
NASA Marshall Space Flight Center (Huntsville, AL, United States)
Pages:
8
Contract #:
None
Abstract:
Mission: Common upper stage engine for Ares I and Ares V. Challenge: Use proven technology from Saturn X-33, RS-68 to develop the highest Isp GG cycle engine in history for 2 missions in record time . Key Features: LOX/LH2 GG cycle, series turbines (2), HIP-bonded MCC, pneumatic ball-sector valves, on-board engine controller, tube-wall regen nozzle/large passively-cooled nozzle extension, TEG boost/cooling . Development Philosophy: proven hardware, aggressive schedule, early risk reduction, requirements-driven.
Language:
English
Notes:
AIAA SPACE 2009 Conference and Exposition Pasadena, CA 14-17 Sep. 2009
Title:
Use of Cumulative Degradation Factor Prediction and Life Test Result of the Thruster Gimbal Assembly Actuator for the Dawn Flight Project
Document ID:
20090038672
Report #:
NASA/CR-2009-215681, E-17052
Available Online:
http://hdl.handle.net/2060/20090038672
Sales Agency:
CASI Hardcopy A03 Copyright
Author(s):
Lo, C. John (Northrop Grumman Corp.) Brophy, John R. (Jet Propulsion Lab., California Inst. of Tech.) Etters, M. Andy (Jet Propulsion Lab., California Inst. of Tech.) Ramesham, Rajeshuni (Jet Propulsion Lab., California Inst. of Tech.) Jones, William R., Jr. (Sest, Inc.) Jansen, Mark J. (Toledo Univ.)
Published:
20091001
Source:
Northrop Grumman Corp. (Redondo Beach, CA, United States)
Pages:
16
Contract #:
NNC07JF14T
Abstract:
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.
Language:
English
Title:
Lunar Neutral Exposphere Properties from Pickup Ion Analysis
Document ID:
20090038677
Report #:
None
Available Online:
http://hdl.handle.net/2060/20090038677
Sales Agency:
CASI Hardcopy A01 Copyright
Author(s):
Hartle, R. E. (NASA Goddard Space Flight Center) Sarantos, M. (NASA Goddard Space Flight Center) Killen, R. (California Univ.) Sittler, E. C. Jr. (California Univ.) Halekas, J. (California Univ.) Yokota, S. (Japan Aerospace Exploration Agency) Saito, Y. (NASA Ames Research Center)
Published:
20090101
Source:
NASA Goddard Space Flight Center (Greenbelt, MD, United States)
Pages:
1
Contract #:
None
Abstract:
Composition and structure of neutral constituents in the lunar exosphere can be determined through measurements of phase space distributions of pickup ions borne from the exosphere [1]. An essential point made in an early study [ 1 ] and inferred by recent pickup ion measurements [2, 3] is that much lower neutral exosphere densities can be derived from ion mass spectrometer measurements of pickup ions than can be determined by conventional neutral mass spectrometers or remote sensing instruments. One approach for deriving properties of neutral exospheric source gasses is to first compare observed ion spectra with pickup ion model phase space distributions. Neutral exosphere properties are then inferred by adjusting exosphere model parameters to obtain the best fit between the resulting model pickup ion distributions and the observed ion spectra. Adopting this path, we obtain ion distributions from a new general pickup ion model, an extension of a simpler analytic description obtained from the Vlasov equation with an ion source [4]. In turn, the ion source is formed from a three-dimensional exospheric density distribution, which can range from the classical Chamberlain type distribution to one with variable exobase temperatures and nonthermal constituents as well as those empirically derived. The initial stage of this approach uses the Moon's known neutral He and Na exospheres to deriv e He+ and Na+ pickup ion exospheres, including their phase space distributions, densities and fluxes. The neutral exospheres used are those based on existing models and remote sensing studies. As mentioned, future ion measurements can be used to constrain the pickup ion model and subsequently improve the neutral exosphere descriptions. The pickup ion model is also used to estimate the exosphere sources of recently observed pickup ions on KAGUYA [3]. Future missions carrying ion spectrometers (e.g., ARTEMIS) will be able to study the lunar neutral exosphere with great sensitivity, yielding the necessary ion velocity spectra needed to further analysis of parent neutral exosphere properties.
Language:
English
Notes:
2009 AGU Fall Meeting San Francisco, CA 14-18 Dec. 2009
Title:
Technology Infusion of CodeSonar into the Space Network Ground Segment
Document ID:
20090038682
Report #:
None
Available Online:
http://hdl.handle.net/2060/20090038682
Sales Agency:
CASI Hardcopy A03 No Copyright
Author(s):
Benson, Markland J. (NASA Goddard Space Flight Center)
Published:
20090922
Source:
NASA Goddard Space Flight Center (Greenbelt, MD, United States)
Pages:
31
Contract #:
None
Abstract:
This slide presentation reviews the applicability of CodeSonar to the Space Network software. CodeSonar is a commercial off the shelf system that analyzes programs written in C, C++ or Ada for defects in the code. Software engineers use CodeSonar results as an input to the existing source code inspection process. The study is focused on large scale software developed using formal processes. The systems studied are mission critical in nature but some use commodity computer systems.
Language:
English
Notes:
Software Assurance Symposium (SAS) '09/NASA Software Assurance Research Program (SARP) Fairmont, WV 22-23 Sep. 2009
Title:
Computing Challenges in Coded Mask Imaging
Document ID:
20090038683
Report #:
None
Available Online:
http://hdl.handle.net/2060/20090038683
Sales Agency:
CASI Hardcopy A03 No Copyright
Author(s):
Skinner, Gerald (NASA Goddard Space Flight Center)
Published:
20091012
Source:
NASA Goddard Space Flight Center (Greenbelt, MD, United States)
Pages:
14
Contract #:
None
Abstract:
This slide presaentation reviews the complications and challenges in developing computer systems for Coded Mask Imaging telescopes. The coded mask technique is used when there is no other way to create the telescope, (i.e., when there are wide fields of view, high energies for focusing or low energies for the Compton/Tracker Techniques and very good angular resolution.) The coded mask telescope is described, and the mask is reviewed. The coded Masks for the INTErnational Gamma-Ray Astrophysics Laboratory (INTEGRAL) instruments are shown, and a chart showing the types of position sensitive detectors used for the coded mask telescopes is also reviewed. Slides describe the mechanism of recovering an image from the masked pattern. The correlation with the mask pattern is described. The Matrix approach is reviewed, and other approaches to image reconstruction are described. Included in the presentation is a review of the Energetic X-ray Imaging Survey Telescope (EXIST) / High Energy Telescope (HET), with information about the mission, the operation of the telescope, comparison of the EXIST/HET with the SWIFT/BAT and details of the design of the EXIST/HET.
Language:
English
Notes:
High Performance Computing in Observational Astronomy: Requirements and Challenges Conference/Dell; Intel Pune 12-16 Oct. 2009
Title:
Connecting Research and Practice: An Experience Report on Research Infusion with SAVE
Document ID:
20090038684
Report #:
None
Available Online:
http://hdl.handle.net/2060/20090038684
Sales Agency:
CASI Hardcopy A03 Copyright
Author(s):
Lindvall, Mikael (Maryland Univ.) Stratton, William C. (Johns Hopkins Univ.) Sibol, Deane E. (Johns Hopkins Univ.) Ackermann, Christopher (Maryland Univ.) Reid, W. Mark (Johns Hopkins Univ.) Ganesan, Dharmalingam (Maryland Univ.) McComas, David (NASA Goddard Space Flight Center) Bartholomew, Maureen (NASA Goddard Space Flight Center) Godfrey, Sally (NASA Goddard Space Flight Center)
Published:
20090101
Source:
Maryland Univ. (College Park, MD, United States)
Pages:
36
Contract #:
None
Abstract:
NASA systems need to be highly dependable to avoid catastrophic mission failures. This calls for rigorous engineering processes including meticulous validation and verification. However, NASA systems are often highly distributed and overwhelmingly complex, making the software portion of these systems challenging to understand, maintain, change, reuse, and test. NASA's systems are long-lived and the software maintenance process typically constitutes 60-80% of the total cost of the entire lifecycle. Thus, in addition to the technical challenges of ensuring high life-time quality of NASA's systems, the post-development phase also presents a significant financial burden. Some of NASA's software-related challenges could potentially be addressed by some of the many powerful technologies that are being developed in software research laboratories. Many of these research technologies seek to facilitate maintenance and evolution by for example architecting, designing and modeling for quality, flexibility, and reuse. Other technologies attempt to detect and remove defects and other quality issues by various forms of automated defect detection, architecture analysis, and various forms of sophisticated simulation and testing. However promising, most such research technologies nevertheless do not make the transition from the research lab to the software lab. One reason the transition from research to practice seldom occurs is that research infusion and technology transfer is difficult. For example, factors related to the technology are sometimes overshadowed by other types of factors such as reluctance to change and therefore prohibits the technology from sticking. Successful infusion might also take very long time. One famous study showed that the discrepancy between the conception of the idea and its practical use was 18 years plus or minus three. Nevertheless, infusing new technology is possible. We have found that it takes special circumstances for such research infusion to succeed: 1) there must be evidence that the technology works in the practitioner's particular domain, 2) there must be a potential for great improvements and enhanced competitive edge for the practitioner, 3) the practitioner has to have strong individual curiosity and continuous interest in trying out new technologies, 4) the practitioner has to have support on multiple levels (i.e. from the researchers, from management, from sponsors etc), and 5) to remain infused, the new technology has to be integrated into the practitioner's processes so that it becomes a natural part of the daily work. NASA IV&V's Research Infusion initiative sponsored by NASA's Office of Safety & Mission Assurance (OSMA) through the Software Assurance Research Program (SARP), strives to overcome some of the problems related to research infusion.
Language:
English
Notes:
To be submitted to Innovations in Systems and Software Engineering a NASA Journal
Title:
Fully Employing Software Inspections Data
Document ID:
20090038685
Report #:
None
Available Online:
http://hdl.handle.net/2060/20090038685
Sales Agency:
CASI Hardcopy A03 Copyright
Author(s):
Shull, Forrest (Maryland Univ.) Feldmann, Raimund L. (Maryland Univ.) Seaman, Carolyn (Maryland Univ.) Regardie, Myrna (Maryland Univ.) Godfrey, Sally (NASA Goddard Space Flight Center)
Published:
20090101
Source:
Maryland Univ. (College Park, MD, United States)
Pages:
19
Contract #:
None
Abstract:
Software inspections provide a proven approach to quality assurance for software products of all kinds, including requirements, design, code, test plans, among others. Common to all inspections is the aim of finding and fixing defects as early as possible, and thereby providing cost savings by minimizing the amount of rework necessary later in the lifecycle. Measurement data, such as the number and type of found defects and the effort spent by the inspection team, provide not only direct feedback about the software product to the project team but are also valuable for process improvement activities. In this paper, we discuss NASA's use of software inspections and the rich set of data that has resulted. In particular, we present results from analysis of inspection data that illustrate the benefits of fully utilizing that data for process improvement at several levels. Examining such data across multiple inspections or projects allows team members to monitor and trigger cross project improvements. Such improvements may focus on the software development processes of the whole organization as well as improvements to the applied inspection process itself.
Language:
English
Notes:
To be submitted to Innovations in Systems and Software Engineering a NASA Journal
Title:
The Influence of the 2006 Indonesian Biomass Burning Aerosols on Tropical Dynamics Studied with the GEOS-5 AGCM
Document ID:
20090038688
Report #:
None
Available Online:
http://hdl.handle.net/2060/20090038688
Sales Agency:
CASI Hardcopy A03 No Copyright
Author(s):
Ott, Lesley (NASA Goddard Space Flight Center) Duncan, Bryan (NASA Goddard Space Flight Center) Pawson, Steven (NASA Goddard Space Flight Center) Colarco, Peter (NASA Goddard Space Flight Center) Chin, Mian (NASA Goddard Space Flight Center) Randles, Cynthia (NASA Goddard Space Flight Center) Diehl, Thomas (NASA Goddard Space Flight Center) Nielsen, Eric (Science Systems and Applications, Inc.)
Published:
20090101
Source:
NASA Goddard Space Flight Center (Greenbelt, MD, United States)
Pages:
46
Contract #:
None
Abstract:
The direct and semi-direct effects of aerosols produced by Indonesian biomass burning (BB) during August November 2006 on tropical dynamics have been examined using NASA's Goddard Earth Observing System, Version 5 (GEOS-5) atmospheric general circulation model (AGCM). The AGCM includes CO, which is transported by resolved and sub-grid processes and subject to a linearized chemical loss rate. Simulations were driven by two sets of aerosol forcing fields calculated offline, one that included Indonesian BB aerosol emissions and one that did not. In order to separate the influence of the aerosols from internal model variability, the means of two ten-member ensembles were compared. Diabatic heating from BB aerosols increased temperatures over Indonesia between 150 and 400 hPa. The higher temperatures resulted in strong increases in upward grid-scale vertical motion, which increased water vapor and CO over Indonesia. In October, the largest increases in water vapor were found in the mid-troposphere (~25%) while the largest increases in CO occurred just below the tropopause (80 ppbv or ~50%). Diabatic heating from the Indonesian BB aerosols caused CO to increase by 9% throughout the tropical tropopause layer in November and 5% in the lower stratosphere in December. The results demonstrate that aerosol heating plays an important role in the transport of BB pollution and troposphere-to-stratosphere transport. Changes in vertical motion and cloudiness induced by aerosol heating can also alter the transport and phase of water vapor in the upper troposphere/lower stratosphere.
Language:
English
Notes:
Submitted tothe Journal of Geophysical Research, Atmospheres, Sep. 2009
Title:
Testing the Reliability of Cluster Mass Indicators with a Systematics Limited Dataset
Document ID:
20090038690
Report #:
None
Available Online:
http://hdl.handle.net/2060/20090038690
Sales Agency:
CASI Hardcopy A03 Copyright
Author(s):
Juett, Adrienne M. (NASA Goddard Space Flight Center) Davis, David S. (Maryland Univ. Baltimore County) Mushotzky, Richard (NASA Goddard Space Flight Center)
Published:
20090101
Source:
NASA Goddard Space Flight Center (Greenbelt, MD, United States)
Pages:
14
Contract #:
None
Abstract:
We present the mass X-ray observable scaling relationships for clusters of galaxies using the XMM-Newton cluster catalog of Snowden et al. Our results are roughly consistent with previous observational and theoretical work, with one major exception. We find 2-3 times the scatter around the best fit mass scaling relationships as expected from cluster simulations or seen in other observational studies. We suggest that this is a consequence of using hydrostatic mass, as opposed to virial mass, and is due to the explicit dependence of the hydrostatic mass on the gradients of the temperature and gas density profiles. We find a larger range of slope in the cluster temperature profiles at radii 500 than previous observational studies. Additionally, we find only a weak dependence of the gas mass fraction on cluster mass, consistent with a constant. Our average gas mass fraction results also argue for a closer study of the systematic errors due to instrumental calibration and modeling method variations between analyses. We suggest that a more careful study of the differences between various observational results and with cluster simulations is needed to understand sources of bias and scatter in cosmological studies of galaxy clusters.
Language:
English
Notes:
To be published in The Astrophysical Journal
Title:
An Fe XXVI Absorption Line in the Persistent Spectrum of the Dipping Low Mass X-ray Binary 1A 1744-361
Document ID:
20090038691
Report #:
None
Available Online:
http://hdl.handle.net/2060/20090038691
Sales Agency:
CASI Hardcopy A02 Copyright
Author(s):
Gavriil, Fotis P. (NASA Goddard Space Flight Center) Strohmayer, Tod E. (NASA Goddard Space Flight Center) Bhattacharyya, Sudip (Tata Inst. of Fundamental Research)
Published:
20090101
Source:
NASA Goddard Space Flight Center (Greenbelt, MD, United States)
Pages:
8
Contract #:
None
Abstract:
We report on Chandra X-ray Observatory (CXO) High-Energy Transmission Grating (HETG) spectra of the dipping Low Mass X-ray Binary (LMXB) 1A 1744-361 during its July 2008 outburst. We find that its persistent emission is well modeled by a blackbody (kT approx. 1.0 keV) plus power-law (Gamma approx. 1.7) with an absorption edge at 7.6 keV. In the residuals of the combined spectrum we find a significant absorption line at 6.961+/-0.002 keV, consistent with the Fe XXVI (hydrogen-like Fe) 2 - 1 transition. We place an upper limit on the velocity of a redshifted flow of v < 221 km/s. We find an equivalent width for the line of 27+2/-3 eV, from which we determine a column density of 7+/-1 x 10(exp 17)/sq cm via a curve-of-growth analysis. Using XSTAR simulations, we place a lower limit on the ionization parameter of > 10(exp 3.6) erg cm/s. The properties of this line are consistent with those observed in other dipping LMXBs. Using Rossi X-ray Timing Explorer (RXTE) data accumulated during this latest outburst we present an updated color-color diagram which clearly shows that IA 1744-361 is an "atoll" source. Finally, using additional dips found in the RXTE and CXO data we provide an updated orbital period estimate of 52+/-5 minutes.
Language:
English
Notes:
To be published in The Astrophysical Journal
Title:
Timing Behavior of the Magnetically Active Rotation-Powered Pulsar in the Supernova Remnant Kesteven 75
Document ID:
20090038692
Report #:
None
Available Online:
http://hdl.handle.net/2060/20090038692
Sales Agency:
CASI Hardcopy A03 Copyright
Author(s):
Livingstone, Margaret A. (McGill Univ.) Gavriil, Fotis P. (NASA Goddard Space Flight Center) Kaspi, Victoria M. (McGill Univ.)
Published:
20090101
Source:
NASA Goddard Space Flight Center (Greenbelt, MD, United States)
Pages:
13
Contract #:
None
Abstract:
We report a large spin-up glitch in PSR J1846-0258 which coincided with the onset of magnetar-like behavior on 2006 May 31. We show that the pulsar experienced an unusually large glitch recovery, with a recovery fraction of Q = 5.9+/-0.3, resulting in a net decrease of the pulse frequency. Such a glitch recovery has never before been observed in a rotation-powered pulsar, however, similar but smaller glitch over-recovery has been recently reported in the magnetar AXP 4U 0142+61 and may have occurred in the SGR 1900+14. We discuss the implications of the unusual timing behavior in PSR J1846-0258 on its status as the first identified magnetically active rotation-powered pulsar.
Language:
English
Notes:
Sponsored in part by FQRNT, CIFAR and CFI
Title:
Estimation of Sea Ice Thickness Distributions through the Combination of Snow Depth and Satellite Laser Altimetry Data
Document ID:
20090038693
Report #:
None
Available Online:
http://hdl.handle.net/2060/20090038693
Sales Agency:
CASI Hardcopy A04 Copyright
Author(s):
Kurtz, Nathan T. (Maryland Univ. Baltimore County) Markus, Thorsten (NASA Goddard Space Flight Center) Cavalieri, Donald J. (NASA Goddard Space Flight Center) Sparling, Lynn C. (Maryland Univ. Baltimore County) Krabill, William B. (NASA Goddard Space Flight Center) Gasiewski, Albin J. (Colorado Univ.) Sonntag, John G. (EG and G Technical Services, Inc.)
Published:
20090724
Source:
NASA Goddard Space Flight Center (Greenbelt, MD, United States)
Pages:
53
Contract #:
None
Abstract:
Combinations of sea ice freeboard and snow depth measurements from satellite data have the potential to provide a means to derive global sea ice thickness values. However, large differences in spatial coverage and resolution between the measurements lead to uncertainties when combining the data. High resolution airborne laser altimeter retrievals of snow-ice freeboard and passive microwave retrievals of snow depth taken in March 2006 provide insight into the spatial variability of these quantities as well as optimal methods for combining high resolution satellite altimeter measurements with low resolution snow depth data. The aircraft measurements show a relationship between freeboard and snow depth for thin ice allowing the development of a method for estimating sea ice thickness from satellite laser altimetry data at their full spatial resolution. This method is used to estimate snow and ice thicknesses for the Arctic basin through the combination of freeboard data from ICESat, snow depth data over first-year ice from AMSR-E, and snow depth over multiyear ice from climatological data. Due to the non-linear dependence of heat flux on ice thickness, the impact on heat flux calculations when maintaining the full resolution of the ICESat data for ice thickness estimates is explored for typical winter conditions. Calculations of the basin-wide mean heat flux and ice growth rate using snow and ice thickness values at the 70 m spatial resolution of ICESat are found to be approximately one-third higher than those calculated from 25 km mean ice thickness values.
Language:
English
Notes:
To be published in Journal of Geophysical Research: Oceans
Title:
Eta Carinae in the Context of the Most Massive Stars
Document ID:
20090038698
Report #:
None
Available Online:
http://hdl.handle.net/2060/20090038698
Sales Agency:
CASI Hardcopy A03 Copyright
Author(s):
Gull, Theodore R. (NASA Goddard Space Flight Center) Damineli, Augusto (Sao Paulo Univ.)
Published:
20090101
Source:
NASA Goddard Space Flight Center (Greenbelt, MD, United States)
Pages:
26
Contract #:
None
Abstract:
Eta Car, with its historical outbursts, visible ejecta and massive, variable winds, continues to challenge both observers and modelers. In just the past five years over 100 papers have been published on this fascinating object. We now know it to be a massive binary system with a 5.54-year period. In January 2009, Car underwent one of its periodic low-states, associated with periastron passage of the two massive stars. This event was monitored by an intensive multi-wavelength campaign ranging from -rays to radio. A large amount of data was collected to test a number of evolving models including 3-D models of the massive interacting winds. August 2009 was an excellent time for observers and theorists to come together and review the accumulated studies, as have occurred in four meetings since 1998 devoted to Eta Car. Indeed, Car behaved both predictably and unpredictably during this most recent periastron, spurring timely discussions. Coincidently, WR140 also passed through periastron in early 2009. It, too, is a intensively studied massive interacting binary. Comparison of its properties, as well as the properties of other massive stars, with those of Eta Car is very instructive. These well-known examples of evolved massive binary systems provide many clues as to the fate of the most massive stars. What are the effects of the interacting winds, of individual stellar rotation, and of the circumstellar material on what we see as hypernovae/supernovae? We hope to learn. Topics discussed in this 1.5 day Joint Discussion were: Car: the 2009.0 event: Monitoring campaigns in X-rays, optical, radio, interferometry WR140 and HD5980: similarities and differences to Car LBVs and Eta Carinae: What is the relationship? Massive binary systems, wind interactions and 3-D modeling Shapes of the Homunculus & Little Homunculus: what do we learn about mass ejection? Massive stars: the connection to supernovae, hypernovae and gamma ray bursters Where do we go from here? (future directions) The Science Organizing Committee: Co-chairs: Augusto Damineli (Brazil) & Theodore R. Gull (USA). Members: D. John Hillier (USA), Gloria Koenigsberger (Mexico), Georges Meynet (Switzerland), Nidia Morrell (Chile), Atsuo T. Okazaki (Japan), Stanley P. Owocki (USA), Andy M.T. Pol- lock (Spain), Nathan Smith (USA), Christiaan L. Sterken (Belgium), Nicole St Louis (Canada), Karel A. van der Hucht (Netherlands), Roberto Viotti (Italy) and GerdWeigelt (Germany)
Language:
English
Notes:
To be published in Highlights of Atronomy, Volume 14, 26th General Assembly of International Astronomical Union (IAU) Proceedings
Title:
Longitudinal Proximity Effects in Superconducting Transition-Edge Sensors
Document ID:
20090038699
Report #:
None
Available Online:
http://hdl.handle.net/2060/20090038699
Sales Agency:
CASI Hardcopy A01 Copyright
Author(s):
Sadleir, John E. (NASA Goddard Space Flight Center) Smith, Stephen J. (NASA Goddard Space Flight Center) Bandler, SImon R. (NASA Goddard Space Flight Center) Chervenak, James A. (NASA Goddard Space Flight Center) Clem, John R. (Iowa State Univ.)
Published:
20090101
Source:
NASA Goddard Space Flight Center (Greenbelt, MD, United States)
Pages:
4
Contract #:
DE-AC02-07CH11358
Abstract:
We have found experimentally that the critical current of a square superconducting transition-edge sensor (TES) depends exponentially upon the side length L and the square root of the temperature T. As a consequence, the effective transition temperature T(sub c) of the TES is current-dependent and at fixed current scales as 1/L(sup 2). We also have found that the critical current can show clear Fraunhofer-like oscillations in an applied magnetic field, similar to those found in Josephson junctions. The observed behavior has a natural theoretical explanation in terms of longitudinal proximity effects if the TES is regarded as a weak link between superconducting leads. We have observed the proximity effect in these devices over extraordinarily long lengths exceeding 100 microns.
Language:
English
Notes:
To be published in Proceedings, Physical Review Letters/American Physical Society
Title:
Large Eddy Simulation of Transonic Flow Field in NASA Rotor 37
Document ID:
20090038700
Report #:
NASA/TM-2009-215627, E-16939
Available Online:
http://hdl.handle.net/2060/20090038700
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CASI Hardcopy A03 No Copyright
Author(s):
Hah, Chunill (NASA Glenn Research Center)
Published:
20090901
Source:
NASA Glenn Research Center (Cleveland, OH, United States)
Pages:
25
Contract #:
None
Abstract:
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.
Language:
English
Notes:
47th Aerospace Sciences Meeting Orlando, FL 5-8 Jan. 2009
Title:
Attenuation of FJ44 Turbofan Engine Noise with a Foam-Metal Liner Installed Over-the-Rotor
Document ID:
20090038701
Report #:
NASA/TM-2009-215666, AIAA Paper 2009-3141, E-17008
Available Online:
http://hdl.handle.net/2060/20090038701
Sales Agency:
CASI Hardcopy A03 Copyright
Author(s):
Sutliff, Daniel L. (NASA Glenn Research Center) Elliott, Dave M. (NASA Glenn Research Center) Jones, Michael G. (NASA Langley Research Center) Hartley, Thomas C. (Williams International)
Published:
20090901
Source:
NASA Glenn Research Center (Cleveland, OH, United States)
Pages:
20
Contract #:
None
Abstract:
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.
Language:
English
Notes:
30th Aeroacoustics Conference Miami, Fl 11-13 May 2009
Title:
Health Monitoring of a Rotating Disk Using a Combined Analytical-Experimental Approach
Document ID:
20090038702
Report #:
NASA/TM-2009-215675, E-17038
Available Online:
http://hdl.handle.net/2060/20090038702
Sales Agency:
CASI Hardcopy A03 No Copyright
Author(s):
Abdul-Aziz, Ali (NASA Glenn Research Center) Woike, Mark R. (NASA Glenn Research Center) Lekki, John D. (NASA Glenn Research Center) Baaklini, George Y. (NASA Glenn Research Center)
Published:
20090901
Source:
NASA Glenn Research Center (Cleveland, OH, United States)
Pages:
21
Contract #:
None
Abstract:
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.
Language:
English
Title:
NASA Johnson Space Center Medical Licensing Opportunities
Document ID:
20090038703
Report #:
JSC-CN-19163
Available Online:
http://hdl.handle.net/2060/20090038703
Sales Agency:
CASI Hardcopy A03 No Copyright
Author(s):
Hernandez-Moya, Sonia (NASA Johnson Space Center)
Published:
20090101
Source:
NASA Johnson Space Center (Houston, TX, United States)
Pages:
33
Contract #:
None
Abstract:
This presentation reviews patented medical items that are available for licensing in the areas of Laboratory Technologies, Medical Devices, Medical Equipment and other technologies that are of interest to the medical community.
Language:
English
Notes:
MicroMed Presentation FROM 9 Nov. 2009
Title:
Effect of Ceramic Ball and Hybrid Stainless Steel Bearing/Wheel Combinations on the Lifetime of a Precision Translation Stage for the SIM Flight Project
Document ID:
20090038706
Report #:
NASA/CR-2009-215682, E-17053
Available Online:
http://hdl.handle.net/2060/20090038706
Sales Agency:
CASI Hardcopy A03 Copyright
Author(s):
Lo, C. John (Jet Propulsion Lab., California Inst. of Tech.) Klein, Kerry (Jet Propulsion Lab., California Inst. of Tech.) Jones, William R., Jr. (Sest, Inc.) Jansen, Mark J. (Toledo Univ.) Wemhoner, Jens (Cerobear G.m.b.H.)
Published:
20091001
Source:
Sest, Inc. (Middleburgh Heights, OH, United States) Jet Propulsion Lab., California Inst. of Tech. (Pasadena, CA, United States)
Pages:
13
Contract #:
NNC07JF14T NAS7-03001
Abstract:
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.
Language:
English
Title:
Five-Year (2004-2009)Observations of Upper Tropospheric Water Vapor and Cloud Ice from MLS and Comparisons with GEOS-5 Analyses
Document ID:
20090038709
Report #:
None
Available Online:
http://hdl.handle.net/2060/20090038709
Sales Agency:
CASI Hardcopy A03 Copyright
Author(s):
Jiang, Jonathan H. (Jet Propulsion Lab., California Inst. of Tech.) Su, Hui (Jet Propulsion Lab., California Inst. of Tech.) Pawson, Steven (NASA Goddard Space Flight Center) Liu, Hui-Chun (NASA Goddard Space Flight Center) Read, William (Jet Propulsion Lab., California Inst. of Tech.) Waters, Joe W. (Jet Propulsion Lab., California Inst. of Tech.) Santee, Michelle (Jet Propulsion Lab., California Inst. of Tech.) Wu, Dong L. (Jet Propulsion Lab., California Inst. of Tech.) Schwartz, Michael (Jet Propulsion Lab., California Inst. of Tech.) Lambert, Alyn (Jet Propulsion Lab., California Inst. of Tech.) Fuller, Ryan (Jet Propulsion Lab., California Inst. of Tech.) Lee, Jae N. (Jet Propulsion Lab., California Inst. of Tech.) Livesey, Nathaniel (Jet Propulsion Lab., California Inst. of Tech.)
Published:
20090101
Source:
Jet Propulsion Lab., California Inst. of Tech. (Pasadena, CA, United States)
Pages:
38
Contract #:
None
Abstract:
This paper gives an overview of August 2004 through July 2009 upper tropospheric (UT) water vapor (H2O) and ice water content (IWC) from the Aura Microwave Limb Sounder (MLS) and comparisons with outputs from the NASA Goddard Earth Observing System Version 5 (GEOS-5) data assimilation system. Both MLS and GEOS-5 show that high values of H2O and IWC at 215 to 147 hPa are associated with areas of deep convection. They exhibit good (within approximately 15%) agreement in IWC at these altitudes, but GEOS-5 H2O is approximately 50% (215 hPa) to approximately 30% (147 hPa) larger than MLS, possibility due to its higher temperatures at these altitudes. GOES-5 produces a weaker intertropical convergence zone than MLS, while a seasonally-migrating band of tropical deep convection is clearly evident in both the MLS and GEOS-5 UT H2O and IWC. MLS and GEOS-5 both show spatial anti-correlation between IWC and H2O at 100 hPa, where less H2O is associated with low temperatures in regions of tropical convection. At 100 hPa, GEOS-5 produces 50% less IWC and 15% less H2O in the tropics, and approximately 20% more H2O in the extra-tropics, than does MLS. Behavior of the 100 hPa H2O, which exhibits a quasi-biennial oscillation, appears consistent with it being controlled by temperature. The seasonal cycle in the vertical transport of tropical mean H2O from approximately 147 hPa to approximately 10 hPa appears much stronger in MLS than in GEOS-5. The UT IWC and H2O interannual variations, from both MLS and GEOS-5, show clear imprints of the El Nino-Southern Oscillation.
Language:
English
Notes:
To be published in Journal of Geophysical Research, Atmospheres
Title:
The Case for Distributed Engine Control in Turbo-Shaft Engine Systems
Document ID:
20090038710
Report #:
NASA/TM-2009-215654, AHS 2009 080366, E-16966
Available Online:
http://hdl.handle.net/2060/20090038710
Sales Agency:
CASI Hardcopy A03 Copyright
Author(s):
Culley, Dennis E. (NASA Glenn Research Center) Paluszewski, Paul J. (Goodrich Engine Control Systems, North America) Storey, William (Goodrich Engine Control Systems, North America) Smith, Bert J. (Aviation Applied Technology Directorate)
Published:
20090901
Source:
NASA Glenn Research Center (Cleveland, OH, United States)
Pages:
21
Contract #:
None
Abstract:
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.
Language:
English
Title:
High Efficiency Nuclear Power Plants Using Liquid Fluoride Thorium Reactor Technology
Document ID:
20090038711
Report #:
NASA/TM-2009-215829, AIAA Paper 2009-4565, E-17030-1
Available Online:
http://hdl.handle.net/2060/20090038711
Sales Agency:
CASI Hardcopy A03 Copyright
Author(s):
Juhasz, Albert J. (NASA Glenn Research Center) Rarick, Richard A. (Cleveland State Univ.) Rangarajan, Rajmohan (Cleveland State Univ.)
Published:
20091001
Source:
NASA Glenn Research Center (Cleveland, OH, United States)
Pages:
19
Contract #:
None
Abstract:
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.
Language:
English
Title:
The Soil Moisture Active and Passive (SMAP) Mission
Document ID:
20090038719
Report #:
None
Available Online:
http://hdl.handle.net/2060/20090038719
Sales Agency:
CASI Hardcopy A03 Copyright
Author(s):
Entekhabi, Dara (Massachusetts Inst. of Tech.) Nijoku, Eni G. (Jet Propulsion Lab., California Inst. of Tech.) ONeill, Peggy E. (NASA Goddard Space Flight Center) Kellogg, Kent H. (Jet Propulsion Lab., California Inst. of Tech.) Crow, Wade T. (Universities Space Research Association) Edelstein, Wendy N. (Jet Propulsion Lab., California Inst. of Tech.) Entin, Jared K. (NASA) Goodman, Shawn D. (Jet Propulsion Lab., California Inst. of Tech.) Jackson, Thomas J. (Universities Space Research Association) Johnson, Joel (Ohio State Univ.) Kimball, John (Montana Univ.) Piepmeier, Jeffrey R. (NASA Goddard Space Flight Center) Koster, Randal D. (NASA Goddard Space Flight Center) McDonald, Kyle C. (Jet Propulsion Lab., California Inst. of Tech.) Moghaddam, Mahta (Michigan Univ.) Moran, Susan (Universities Space Research Association) Reichle, Rolf (NASA Goddard Space Flight Center) Shi, J. C. (California Univ.) Spencer, Michael W. (Jet Propulsion Lab., California Inst. of Tech.) Thurman, Samuel W. (Jet Propulsion Lab., California Inst. of Tech.) Tsang, Leung (Washington Univ.) VanZyl, Jakob (Jet Propulsion Lab., California Inst. of Tech.)
Published:
20090101
Source:
NASA Goddard Space Flight Center (Greenbelt, MD, United States)
Pages:
21
Contract #:
None
Abstract:
The Soil Moisture Active and Passive (SMAP) Mission is one of the first Earth observation satellites being developed by NASA in response to the National Research Council s Decadal Survey. SMAP will make global measurements of the moisture present at Earth's land surface and will distinguish frozen from thawed land surfaces. Direct observations of soil moisture and freeze/thaw state from space will allow significantly improved estimates of water, energy and carbon transfers between land and atmosphere. Soil moisture measurements are also of great importance in assessing flooding and monitoring drought. SMAP observations can help mitigate these natural hazards, resulting in potentially great economic and social benefits. SMAP soil moisture and freeze/thaw timing observations will also reduce a major uncertainty in quantifying the global carbon balance by helping to resolve an apparent missing carbon sink on land over the boreal latitudes. The SMAP mission concept would utilize an L-band radar and radiometer. These instruments will share a rotating 6-meter mesh reflector antenna to provide high-resolution and high-accuracy global maps of soil moisture and freeze/thaw state every two to three days. The SMAP instruments provide direct measurements of surface conditions. In addition, the SMAP project will use these observations with advanced modeling and data assimilation to provide deeper root-zone soil moisture and estimates of land surface-atmosphere exchanges of water, energy and carbon. SMAP is scheduled for a 2014 launch date
Language:
English
Notes:
Submitted to Proceedings of the IEEE
Title:
Microwave Treatment for Cardiac Arrhythmias
Document ID:
20090038725
Report #:
JSC-CN-19165
Available Online:
http://hdl.handle.net/2060/20090038725
Sales Agency:
CASI Hardcopy A01 No Copyright
Author(s):
Hernandez-Moya, Sonia (NASA Johnson Space Center)
Published:
20090101
Source:
NASA Johnson Space Center (Houston, TX, United States)
Pages:
5
Contract #:
None
Abstract:
NASA seeks to transfer the NASA developed microwave ablation technology, designed for the treatment of ventricular tachycardia (irregular heart beat), to industry. After a heart attack, many cells surrounding the resulting scar continue to live but are abnormal electrically; they may conduct impulses unusually slowly or fire when they would typically be silent. These diseased areas might disturb smooth signaling by forming a reentrant circuit in the muscle. The objective of microwave ablation is to heat and kill these diseased cells to restore appropriate electrical activity in the heart. This technology is a method and apparatus that provides for propagating microwave energy into heart tissues to produce a desired temperature profile therein at tissue depths sufficient for thermally ablating arrhythmogenic cardiac tissue while preventing excessive heating of surrounding tissues, organs, and blood. A wide bandwidth double-disk antenna is effective for this purpose over a bandwidth of about six gigahertz. A computer simulation provides initial screening capabilities for an antenna such as antenna, frequency, power level, and power application duration. The simulation also allows optimization of techniques for specific patients or conditions. In comparison with other methods that involve direct-current pulses or radio frequencies below 1 GHz, this method may prove more effective in treating ventricular tachycardia. This is because the present method provides for greater control of the location, cross-sectional area, and depth of a lesion via selection of the location and design of the antenna and the choice of microwave power and frequency.
Language:
English
Notes:
Texas Life Science Conference Houston, TX 12-13 Nov. 2009
Title:
LAURA Users Manual: 5.2-43231
Document ID:
20090038726
Report #:
NASA/TM-2009-215944, LF99-9703, L-19783
Available Online:
http://hdl.handle.net/2060/20090038726
Sales Agency:
CASI Hardcopy A05 Copyright
Author(s):
Mazaheri, Alireza (Analytical Mechanics Associates, Inc.) Gnoffo, Peter A. (NASA Langley Research Center) Johnston, Christopher O. (NASA Langley Research Center) Kleb, Bil (NASA Langley Research Center)
Published:
20091101
Source:
NASA Langley Research Center (Hampton, VA, United States)
Pages:
86
Contract #:
None
Abstract:
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.
Language:
English
Title:
Frequency Agile Transceiver for Advanced Vehicle Data Links
Document ID:
20090038727
Report #:
DFRC-964, DFRC-1075
Available Online:
http://hdl.handle.net/2060/20090038727
Sales Agency:
CASI Hardcopy A03 No Copyright
Author(s):
Freudinger, Lawrence C. (NASA Dryden Flight Research Center) Macias, Filiberto (White Sands Missile Range) Cornelius, Harold (Hi-Vac-U Consulting)
Published:
20091026
Source:
NASA Dryden Flight Research Center (Edwards, CA, United States)
Pages:
29
Contract #:
None
Abstract:
Emerging and next-generation test instrumentation increasingly relies on network communication to manage complex and dynamic test scenarios, particularly for uninhabited autonomous systems. Adapting wireless communication infrastructure to accommodate challenging testing needs can benefit from reconfigurable radio technology. Frequency agility is one characteristic of reconfigurable radios that to date has seen only limited progress toward programmability. This paper overviews an ongoing project to validate a promising chipset that performs conversion of RF signals directly into digital data for the wireless receiver and, for the transmitter, converts digital data into RF signals. The Software Configurable Multichannel Transceiver (SCMT) enables four transmitters and four receivers in a single unit, programmable for any frequency band between 1 MHz and 6 GHz.
Language:
English
Notes:
International Telemetering Conference (ITC) 2009 Las Vegas, NV 26-29 Oct. 2009
Title:
XPS Protocol for the Characterization of Pristine and Functionalized Single Wall Carbon Nanotubes
Document ID:
20090038728
Report #:
JSC-CN-16923
Available Online:
http://hdl.handle.net/2060/20090038728
Sales Agency:
CASI Hardcopy A03 Copyright
Author(s):
Sosa, E. D. (Engineering Research and Consulting, Inc.) Allada, R. (Engineering Research and Consulting, Inc.) Huffman, C. B. (Marshall Univ.) Arepalli, S. (Engineering Research and Consulting, Inc.)
Published:
20090101
Source:
NASA Johnson Space Center (Houston, TX, United States)
Pages:
31
Contract #:
NNJ05HI05C
Abstract:
Recent interest in developing new applications for carbon nanotubes (CNT) has fueled the need to use accurate macroscopic and nanoscopic techniques to characterize and understand their chemistry. X-ray photoelectron spectroscopy (XPS) has proved to be a useful analytical tool for nanoscale surface characterization of materials including carbon nanotubes. Recent nanotechnology research at NASA Johnson Space Center (NASA-JSC) helped to establish a characterization protocol for quality assessment for single wall carbon nanotubes (SWCNTs). Here, a review of some of the major factors of the XPS technique that can influence the quality of analytical data, suggestions for methods to maximize the quality of data obtained by XPS, and the development of a protocol for XPS characterization as a complementary technique for analyzing the purity and surface characteristics of SWCNTs is presented. The XPS protocol is then applied to a number of experiments including impurity analysis and the study of chemical modifications for SWCNTs.
Language:
English
Notes:
Sponsored in part from the National Research Council Research Associateship Program. To be published in Journal of Nanoscience and Nanotecnology, September 2008
Title:
Background: Preflight Screening, In-flight Capabilities, and Postflight Testing
Document ID:
20090038729
Report #:
JSC-CN-18652
Available Online:
http://hdl.handle.net/2060/20090038729
Sales Agency:
CASI Hardcopy A03 Copyright
Author(s):
Gibson, Charles Robert (NASA Johnson Space Center) Duncan, James (Wyle Labs., Inc.)
Published:
20090727
Source:
NASA Johnson Space Center (Houston, TX, United States)
Pages:
43
Contract #:
None
Abstract:
Recommendations for minimal in-flight capabilities: Retinal Imaging - provide in-flight capability for the visual monitoring of ocular health (specifically, imaging of the retina and optic nerve head) with the capability of downlinking video/still images. Tonometry - provide more accurate and reliable in-flight capability for measuring intraocular pressure. Ultrasound - explore capabilities of current on-board system for monitoring ocular health. We currently have limited in-flight capabilities on board the International Space Station for performing an internal ocular health assessment. Visual Acuity, Direct Ophthalmoscope, Ultrasound, Tonometry(Tonopen):
Language:
English
Notes:
NASA Papilledema Summit Houston, TX 27-28 Jul. 2009
Title:
International Space Station USOS Potable Water Dispenser On-Orbit Functionality vs Design
Document ID:
20090038742
Report #:
JSC-CN-19125
Available Online:
http://hdl.handle.net/2060/20090038742
Sales Agency:
CASI Hardcopy A01 Copyright
Author(s):
Toon, Katherine P. (NASA Johnson Space Center) Lovell, Randal W. (Jacobs Technologies Engineering Science Contract Group)
Published:
20090101
Source:
NASA Johnson Space Center (Houston, TX, United States)
Pages:
2
Contract #:
None
Abstract:
The International Space Station (ISS) currently provides potable water dispensing for rehydrating crewmembers food and drinking packages with one system located in the United States On-orbit Segment (USOS) and one system in the Russian Segment. The USOS Potable Water Dispenser (PWD) was delivered to ISS on ULF2, Shuttle Mission STS-126, and was subsequently activated in November 2008. The PWD activation on ISS is capable of supporting an ISS crew of six but nominally supplies only half the crew. The PWD is designed to provide incremental quantities of hot and ambient temperature potable water to US style food packages. PWD receives iodinated water from the US Laboratory Fuel Cell Water Bus, which is fed from the Water Processing Assembly (WPA). The PWD removes the biocidal iodine to make the water potable prior to dispensing. A heater assembly contained within the unit supplies up to 2.0 liters of hot water (65 to 93oC) every thirty minutes. This quantity supports three to four crewmembers to rehydrate their food and beverages from this location during a single meal. The unit is designed to remain functional for up to ten years with replacement of limited life items such as filters. To date, the PWD on-orbit performance has been acceptable. Since activation of the PWD, there have been several differences between on-orbit functionality and expected performance of hardware design. The comparison of on-orbit functionality to performance of hardware design is outlined for the following key areas: microbiology, PWD to food package water leakage, no-dispense scenarios, under-dispense scenarios, and crewmember feedback on actual on-orbit use.
Language:
English
Notes:
International Conference on Environmental Systems Barcelona 11-15 Jul. 2010
99-02 New NASA STI Report Series
Nov 22, 2009 -- Additions to the NASA scientific and technical information knowledge base
Title:
NASA Patent Abstracts Bibliography: A Continuing Bibliography
Document ID:
20090038656
Report #:
NASA/SP-2009-7039/SUPPL70
Available Online:
http://hdl.handle.net/2060/20090038656
Sales Agency:
CASI Hardcopy A04 No Copyright
Author(s):
(Author(s) Not Available)
Published:
20091001
Source:
NASA Langley Research Center (Hampton, VA, United States)
Pages:
71
Contract #:
None
Abstract:
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.
Language:
English
Title:
Use of Cumulative Degradation Factor Prediction and Life Test Result of the Thruster Gimbal Assembly Actuator for the Dawn Flight Project
Document ID:
20090038672
Report #:
NASA/CR-2009-215681, E-17052
Available Online:
http://hdl.handle.net/2060/20090038672
Sales Agency:
CASI Hardcopy A03 Copyright
Author(s):
Lo, C. John (Northrop Grumman Corp.) Brophy, John R. (Jet Propulsion Lab., California Inst. of Tech.) Etters, M. Andy (Jet Propulsion Lab., California Inst. of Tech.) Ramesham, Rajeshuni (Jet Propulsion Lab., California Inst. of Tech.) Jones, William R., Jr. (Sest, Inc.) Jansen, Mark J. (Toledo Univ.)
Published:
20091001
Source:
Northrop Grumman Corp. (Redondo Beach, CA, United States)
Pages:
16
Contract #:
NNC07JF14T
Abstract:
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.
Language:
English
Title:
Large Eddy Simulation of Transonic Flow Field in NASA Rotor 37
Document ID:
20090038700
Report #:
NASA/TM-2009-215627, E-16939
Available Online:
http://hdl.handle.net/2060/20090038700
Sales Agency:
CASI Hardcopy A03 No Copyright
Author(s):
Hah, Chunill (NASA Glenn Research Center)
Published:
20090901
Source:
NASA Glenn Research Center (Cleveland, OH, United States)
Pages:
25
Contract #:
None
Abstract:
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.
Language:
English
Notes:
47th Aerospace Sciences Meeting Orlando, FL 5-8 Jan. 2009
Title:
Attenuation of FJ44 Turbofan Engine Noise with a Foam-Metal Liner Installed Over-the-Rotor
Document ID:
20090038701
Report #:
NASA/TM-2009-215666, AIAA Paper 2009-3141, E-17008
Available Online:
http://hdl.handle.net/2060/20090038701
Sales Agency:
CASI Hardcopy A03 Copyright
Author(s):
Sutliff, Daniel L. (NASA Glenn Research Center) Elliott, Dave M. (NASA Glenn Research Center) Jones, Michael G. (NASA Langley Research Center) Hartley, Thomas C. (Williams International)
Published:
20090901
Source:
NASA Glenn Research Center (Cleveland, OH, United States)
Pages:
20
Contract #:
None
Abstract:
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.
Language:
English
Notes:
30th Aeroacoustics Conference Miami, Fl 11-13 May 2009
Title:
Health Monitoring of a Rotating Disk Using a Combined Analytical-Experimental Approach
Document ID:
20090038702
Report #:
NASA/TM-2009-215675, E-17038
Available Online:
http://hdl.handle.net/2060/20090038702
Sales Agency:
CASI Hardcopy A03 No Copyright
Author(s):
Abdul-Aziz, Ali (NASA Glenn Research Center) Woike, Mark R. (NASA Glenn Research Center) Lekki, John D. (NASA Glenn Research Center) Baaklini, George Y. (NASA Glenn Research Center)
Published:
20090901
Source:
NASA Glenn Research Center (Cleveland, OH, United States)
Pages:
21
Contract #:
None
Abstract:
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.
Language:
English
Title:
Effect of Ceramic Ball and Hybrid Stainless Steel Bearing/Wheel Combinations on the Lifetime of a Precision Translation Stage for the SIM Flight Project
Document ID:
20090038706
Report #:
NASA/CR-2009-215682, E-17053
Available Online:
http://hdl.handle.net/2060/20090038706
Sales Agency:
CASI Hardcopy A03 Copyright
Author(s):
Lo, C. John (Jet Propulsion Lab., California Inst. of Tech.) Klein, Kerry (Jet Propulsion Lab., California Inst. of Tech.) Jones, William R., Jr. (Sest, Inc.) Jansen, Mark J. (Toledo Univ.) Wemhoner, Jens (Cerobear G.m.b.H.)
Published:
20091001
Source:
Sest, Inc. (Middleburgh Heights, OH, United States) Jet Propulsion Lab., California Inst. of Tech. (Pasadena, CA, United States)
Pages:
13
Contract #:
NNC07JF14T NAS7-03001
Abstract:
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.
Language:
English
Title:
The Case for Distributed Engine Control in Turbo-Shaft Engine Systems
Document ID:
20090038710
Report #:
NASA/TM-2009-215654, AHS 2009 080366, E-16966
Available Online:
http://hdl.handle.net/2060/20090038710
Sales Agency:
CASI Hardcopy A03 Copyright
Author(s):
Culley, Dennis E. (NASA Glenn Research Center) Paluszewski, Paul J. (Goodrich Engine Control Systems, North America) Storey, William (Goodrich Engine Control Systems, North America) Smith, Bert J. (Aviation Applied Technology Directorate)
Published:
20090901
Source:
NASA Glenn Research Center (Cleveland, OH, United States)
Pages:
21
Contract #:
None
Abstract:
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.
Language:
English
Title:
High Efficiency Nuclear Power Plants Using Liquid Fluoride Thorium Reactor Technology
Document ID:
20090038711
Report #:
NASA/TM-2009-215829, AIAA Paper 2009-4565, E-17030-1
Available Online:
http://hdl.handle.net/2060/20090038711
Sales Agency:
CASI Hardcopy A03 Copyright
Author(s):
Juhasz, Albert J. (NASA Glenn Research Center) Rarick, Richard A. (Cleveland State Univ.) Rangarajan, Rajmohan (Cleveland State Univ.)
Published:
20091001
Source:
NASA Glenn Research Center (Cleveland, OH, United States)
Pages:
19
Contract #:
None
Abstract:
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.
Language:
English
Title:
LAURA Users Manual: 5.2-43231
Document ID:
20090038726
Report #:
NASA/TM-2009-215944, LF99-9703, L-19783
Available Online:
http://hdl.handle.net/2060/20090038726
Sales Agency:
CASI Hardcopy A05 Copyright
Author(s):
Mazaheri, Alireza (Analytical Mechanics Associates, Inc.) Gnoffo, Peter A. (NASA Langley Research Center) Johnston, Christopher O. (NASA Langley Research Center) Kleb, Bil (NASA Langley Research Center)
Published:
20091101
Source:
NASA Langley Research Center (Hampton, VA, United States)
Pages:
86
Contract #:
None
Abstract:
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.
Language:
English