SCAN_13-01

13-01 CELESTIAL MECHANICS AND ORBITAL CALCULATIONS
Nov 15, 2009 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

14-01 SPACECRAFT GROUND SUPPORT
Nov 15, 2009 -- Additions to the NASA scientific and technical information knowledge base

Title:
NASA Manned Launch Vehicle Lightning Protection Development
Document ID:
20090037586
Report #:
M09-0744
Available Online:
http://hdl.handle.net/2060/20090037586
Sales Agency:
CASI Hardcopy A02 No Copyright
Author(s):
McCollum, Matthew B. (NASA Marshall Space Flight Center) Jones, Steven R. (NASA Marshall Space Flight Center) Mack, Jonathan D. (NASA Marshall Space Flight Center)
Published:
20090915
Source:
NASA Marshall Space Flight Center (Huntsville, AL, United States)
Pages:
8
Contract #:
None
Abstract:
Historically, the National Aeronautics and Space Administration (NASA) relied heavily on lightning avoidance to protect launch vehicles and crew from lightning effects. As NASA transitions from the Space Shuttle to the new Constellation family of launch vehicles and spacecraft, NASA engineers are imposing design and construction standards on the spacecraft and launch vehicles to withstand both the direct and indirect effects of lightning. A review of current Space Shuttle lightning constraints and protection methodology will be presented, as well as a historical review of Space Shuttle lightning requirements and design. The Space Shuttle lightning requirements document, NSTS 07636, Lightning Protection, Test and Analysis Requirements, (originally published as document number JSC 07636, Lightning Protection Criteria Document) was developed in response to the Apollo 12 lightning event and other experiences with NASA and the Department of Defense launch vehicles. This document defined the lightning environment, vehicle protection requirements, and design guidelines for meeting the requirements. The criteria developed in JSC 07636 were a precursor to the Society of Automotive Engineers (SAE) lightning standards. These SAE standards, along with Radio Technical Commission for Aeronautics (RTCA) DO-160, Environmental Conditions and Test Procedures for Airborne Equipment, are the basis for the current Constellation lightning design requirements. The development and derivation of these requirements will be presented. As budget and schedule constraints hampered lightning protection design and verification efforts, the Space Shuttle elements waived the design requirements and relied on lightning avoidance in the form of launch commit criteria (LCC) constraints and a catenary wire system for lightning protection at the launch pads. A better understanding of the lightning environment has highlighted the vulnerability of the protection schemes and associated risk to the vehicle, which has resulted in lost launch opportunities and increased expenditures in manpower to assess Space Shuttle vehicle health and safety after lightning events at the launch pad. Because of high-percentage launch availability and long-term on-pad requirements, LCC constraints are no longer considered feasible. The Constellation vehicles must be designed to withstand direct and indirect effects of lightning. A review of the vehicle design and potential concerns will be presented as well as the new catenary lightning protection system for the launch pad. This system is required to protect the Constellation vehicles during launch processing when vehicle lightning effects protection might be compromised by such items as umbilical connections and open access hatches.
Language:
English
Notes:
International Conference on Lightning and Static Electricity Pittsfield, MA 15-17 Sep. 2009

14-02 TEST FACILITIES
Nov 15, 2009 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

14-03 SIMULATORS AND SIMULATION
Nov 15, 2009 -- Additions to the NASA scientific and technical information knowledge base

Title:
Intercomparison of model simulations of mixed-phase clouds observed during the ARM Mixed-Phase Arctic Cloud Experiment, Part II: Multi-layered cloud. Quarterly Journal of the Royal Meteorological Society
Document ID:
20090037156
Report #:
PB2009-115293, LLNL-JRNL-401832
Sales Agency:
CASI Hardcopy A04 No Copyright
Author(s):
Morrison, H. McCoy, R. B. Klein, S. A. Xie, S. Luo, Y.
Published:
20080229
Source:
National Center for Atmospheric Research (Boulder, CO United States) California Univ., Lawrence Livermore Lab. (Livermore, CA, United States) Pennsylvania State Univ. (University Park, PA, United States) Colorado State Univ. (Fort Collins, CO, United States)
Pages:
65
Contract #:
None
Abstract:
Results are presented from an intercomparison of single-column and cloud resolving model simulations of a deep, multi-layered, mixed-phase cloud system observed during the ARM Mixed-Phase Arctic Cloud Experiment. This cloud system was associated with strong surface turbulent sensible and latent heat fluxes as cold air flowed over the open Arctic Ocean, combined with a low pressure system that supplied moisture at mid-level. The simulations, performed by 13 single-column and 4 cloud-resolving models, generally overestimate the liquid water path and strongly underestimate the ice water path, although there is a large spread among the models. This finding is in contrast with results for the single-layer, low-level mixed-phase stratocumulus case in Part I of 11 this study, as well as previous studies of shallow mixed-phase Arctic clouds, that showed an underprediction of liquid water path. The overestimate of liquid water path and underestimate of ice water path occur primarily.
Language:
English
Notes:
Prepared in cooperation with California Univ., Berkeley. Lawrence Livermore Lab., Pennsylvania State Univ., University Park., Colorado State Univ., Fort Collins. and State Univ. of New York at Stony Brook.

Title:
Dimits Shift in More Realistic Gyrokinetic Plasma Turbulence Simulations
Document ID:
20090037493
Report #:
DE2009-953703, PPPL-4336
Sales Agency:
National Technical Information Service (NTIS) No Copyright
Author(s):
Mikkelsen, D. R. Dorland, W.
Published:
20080701
Source:
Princeton Univ. (NJ United States)
Pages:
14
Contract #:
DE-AC02-76CH03073
Abstract:
In simulations of turbulent plasma transport due to long wavelength, (k/pi = 1), electrostatic drift-type instabilities we find that a nonlinear upshift of the effective threshold persists. This 'Dimits shift' represents the difference between the linear threshold, at the onset of instability, and the nonlinear threshold, where transport increases suddenly as the driving temperature gradient is increased. As the drive increases, the magnitudes of turbulent eddies and zonal ows grow until the zonal flows become nonlinearly unstable to 'tertiary' modes and their sheared ows no longer grow fast enough to strongly limit eddy size. The tertiary mode threshold sets the effective nonlinear threshold for the heat transport, and the Dimits shift arises when this occurs at a zonal flow magnitude greater than that needed to limit transport near the linear threshold. Next generation tokamaks will likely benefit from the higher effective threshold for turbulent transport, and transport models should incorporate suitable corrections to linear thresholds. These gyrokinetic simulations are more realistic than previous reports of a Dimits shift because they include nonadiabatic electron dynamics, strong collisional damping of zonal flows, and finite electron and ion collisionality together with realistic shaped magnetic geometry. Reversing previously reported results based on idealized adiabatic electrons, we find that increasing collisionality reduces the heat flux because collisionality reduces the nonadiabatic electron drive.
Language:
English
Notes:
Sponsored by Department of Energy, Washington, DC.

Title:
National Institute for Occupational Safety and Health (NIOSH). Hearing Loss Simulator, Instruction and Training Guide
Document ID:
20090037518
Report #:
PB2008-109016, DHHS/PUB/NIOSH-2008-119
Sales Agency:
CASI Hardcopy A03 No Copyright
Author(s):
Randolph, R. F. Reinke, D. C. Unger, R. L.
Published:
20080301
Source:
Michigan State Univ. (East Lansing, MI, United States)
Pages:
12
Contract #:
None
Abstract:
The NIOSH Hearing Loss Simulator is a software training and communication tool for promoting hearing loss prevention. It allows a user or trainer to demonstrate the effects of noise exposure on hearing without experiencing an actual noise-induced hearing loss. Estimates of the effects of different levels of noise exposure are based on the American National Standard Determination of Occupational Noise Exposure and Estimation of Noise-Induced Hearing Impairment, otherwise known as ANSI S3.44. This standard specifies the predicted hearing loss for noise-exposed populations of individuals based on risk factors that include gender, age, sound levels (in A-weighted decibels or dBA), and years of exposure. Algorithms specified in the standard were derived from empirical studies of populations that had no exposure to loud noise and other populations that had experienced various levels and durations of noise exposure. This manual explains the major objectives that can be addressed with the simulator and training scenarios that can be applied to real-life, real worker scenarios. The majority of this guide explains the simulator's functions in detail. Simulator users are encouraged to read this manual while learning how to run the software.
Language:
English
Notes:
Sponsored by National Inst. for Occupational Safety and Health, Washington, DC.

Title:
Advances in Modeling and Simulation of Rotorcraft Noise and Associated Impacts on Survivability
Document ID:
20090037593
Report #:
AD-A505765
Available Online:
http://hdl.handle.net/100.2/ADA505765
Sales Agency:
Defense Technical Information Center (DTIC) No Copyright
Author(s):
Newman, Daniel (Defense Advanced Research Projects Agency) Doligalski, Thomas (Army Research Office) Minniti, Robert (Arion Systems, Inc.)
Journal:
Proceedings of the 26th Army Science Conference
Published:
20081201
Source:
Defense Advanced Research Projects Agency (Arlington, VA United States)
Pages:
9
Contract #:
None
Abstract:
The acoustic signature of a rotorcraft is often the primary means of detection and identification by enemy forces in the modern battlespace. Additionally, this detection is often accomplished without the need for the sophisticated sensing equipment required for other signature components. While this vulnerability has existed for many generations of rotorcraft, the tools for predicting the acoustic signature and understanding its impact on mission survivability have lagged in development. This is partially due the need for development of multidisciplinary knowledge and capability to predict the aerodynamic performance, structural dynamic response, near-field acoustic character, far-field atmospheric propagation and human perception as well as the historical lack of required computational resources. The advent of cheaper and more ubiquitous computational resources at the all levels in the rotorcraft community alleviated the later issue and left the need for a significant investment to address the former. Approximately four years ago, DARPA made this investment and identified teams of researchers guided by an advisory panel made up of industry and government experts aimed at developing the required assets. The DARPA funded Helicopter Quieting Program was initiated to focus on developing a suite of tools appropriate for use by the designer to predict the acoustic signature of rotorcraft. In the last year, the focus was expanded to leverage the signature prediction capabilities and develop tools appropriate for the mission planner and warfighter that enable visual analysis of the impact of signature change on survivability and operational effectiveness. The end product of this effort was three tool suites, verified using experimental data, capable of predicting the aerodynamic performance and acoustic signature of modern main rotors and the tools necessary to show the impact of signature changes on the mission effectiveness of the vehicle.
Language:
English
Notes:
Presented at the Army Science Conference (26th) held in Orlando, Florida on 1-4 December 2008. Published in the Proceedings of the Army Science Conference (26th), December 2008. The original document contains color images 26th Army Science Conference Orlando, FL 1-4 Dec. 2008

15-01 LAUNCH VEHICLES
Nov 15, 2009 -- Additions to the NASA scientific and technical information knowledge base

Title:
Propellant Mass Fraction Calculation Methodology for Launch Vehicles
Document ID:
20090037578
Report #:
M09-0261
Sales Agency:
Other Sources Copyright
Author(s):
Holt, James B. (NASA Marshall Space Flight Center) Monk, Timothy S. (Miltec Systems Co.)
Published:
20090914
Source:
NASA Marshall Space Flight Center (Huntsville, AL, United States)
Pages:
1
Contract #:
None
Abstract:
Propellant Mass Fraction (pmf) calculation methods vary throughout the aerospace industry. While typically used as a means of comparison between competing launch vehicle designs, the actual pmf calculation method varies slightly from one entity to another. It is the purpose of this paper to present various methods used to calculate the pmf of a generic launch vehicle. This includes fundamental methods of pmf calculation which consider only the loaded propellant and the inert mass of the vehicle, more involved methods which consider the residuals and any other unusable propellant remaining in the vehicle, and other calculations which exclude large mass quantities such as the installed engine mass. Finally, a historic comparison is made between launch vehicles on the basis of the differing calculation methodologies.
Language:
English
Notes:
American Institute of Aeronautics and Astronautics (AIAA) Space 2009 conference Pasadena, CA 14-17 Sep. 2009

Title:
The Art and Science of Systems Engineering
Document ID:
20090037580
Report #:
M09-0292
Available Online:
http://hdl.handle.net/2060/20090037580
Sales Agency:
CASI Hardcopy A01 No Copyright
Author(s):
Singer, Christopher E. (NASA Marshall Space Flight Center)
Published:
20090914
Source:
NASA Marshall Space Flight Center (Huntsville, AL, United States)
Pages:
5
Contract #:
None
Abstract:
The National Aeronautics and Space Administration (NASA) was established in 1958, and its Marshall Space Flight Center was founded in 1960, as space-related work was transferred from the Army Ballistic Missile Agency at Redstone Arsenal, where Marshall is located. With this heritage, Marshall contributes almost 50 years of systems engineering experience with human-rated launch vehicles and scientific spacecraft to fulfill NASA's mission exploration and discovery. These complex, highly specialized systems have provided vital platforms for expanding the knowledge base about Earth, the solar system, and cosmos; developing new technologies that also benefit life on Earth; and opening new frontiers for America's strategic space goals. From Mercury and Gemini, to Apollo and the Space Shuttle, Marshall's systems engineering expertise is an unsurpassed foundational competency for NASA and the nation. Current assignments comprise managing Space Shuttle Propulsion systems; developing environmental control and life support systems and coordinating science operations on the International Space Station; and a number of exploration-related responsibilities. These include managing and performing science missions, such as the Lunar Crater Observation and Sensing Satellite and the Lunar Reconnaissance Orbiter slated to launch for the Moon in April 2009, to developing the Ares I crew launch vehicle upper stage and integrating the vehicle stack in house, as well as designing the Ares V cargo launch vehicle and contributing to the development of the Altair Lunar Lander and an International Lunar Network with communications nodes and other infrastructure.
Language:
English
Notes:
AIAA Space 2009 conference Pasadena, CA 14-17 Sep. 2009

Title:
Propellant Mass Fraction Calculation Methodology for Launch Vehicles and Application to Ares Vehicles
Document ID:
20090037584
Report #:
M09-0721, M09--0770
Available Online:
http://hdl.handle.net/2060/20090037584
Sales Agency:
CASI Hardcopy A03 Copyright
Author(s):
Holt, James B. (NASA Marshall Space Flight Center) Monk, Timothy S. (NASA Marshall Space Flight Center)
Published:
20090914
Source:
NASA Marshall Space Flight Center (Huntsville, AL, United States)
Pages:
18
Contract #:
None
Abstract:
Propellant Mass Fraction (pmf) calculation methods vary throughout the aerospace industry. While typically used as a means of comparison between candidate launch vehicle designs, the actual pmf calculation method varies slightly from one entity to another. It is the purpose of this paper to present various methods used to calculate the pmf of launch vehicles. This includes fundamental methods of pmf calculation that consider only the total propellant mass and the dry mass of the vehicle; more involved methods that consider the residuals, reserves and any other unusable propellant remaining in the vehicle; and calculations excluding large mass quantities such as the installed engine mass. Finally, a historical comparison is made between launch vehicles on the basis of the differing calculation methodologies, while the unique mission and design requirements of the Ares V Earth Departure Stage (EDS) are examined in terms of impact to pmf.
Language:
English
Notes:
American Institute of Aeronautics and Astronautics (AIAA) Space 2009 conference Pasadena, CA 13-17 Sep. 2009

15-02 SOUNDING ROCKETS
Nov 15, 2009 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

15-03 SPACE PROBES
Nov 15, 2009 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

15-04 SCIENTIFIC SATELLITES
Nov 15, 2009 -- Additions to the NASA scientific and technical information knowledge base

Title:
Monthly Report of the Meteorological Satellite Center: June 2009
Document ID:
20090037169
Report #:
None
Sales Agency:
Other Sources Copyright
Author(s):
(Author(s) Not Available)
Published:
20090601
Source:
Meteorological Satellite Center (Kiyose, Japan)
Pages:
--
Contract #:
None
Abstract:
These CD-ROMs, concerning the March 2009 Monthly Report of the Meteorological Satellite Center (MSC), contains the observation data derived from the Multi-function Transport SATellite (MTSAT-1R) which was operated from 28 June 2005, and the Polar Orbital Meteorological Satellites operated by NOAA. The CD-ROM contains the following observation data: Full Disk Earth's Cloud Image; Cloud Image of Japan and its vicinity; Sea Surface Temperature; Cloud and Water Vapor Motion Wind; Water Vapor Motion Wind; Brightness Temperature Data, Snow and Ice Index, TOVS (TIROS Operational Vertical Sounder) Vertical Profile of Temperature and Precipitable Water; TOVS Total Ozone Amount, Aerosol Optical Thickness, HRIT Image Data Catalog, and Cloud Grid Information.
Language:
English

Title:
Monthly Report of the Meteorological Satellite Center: May 2009
Document ID:
20090037596
Report #:
None
Sales Agency:
Other Sources Copyright
Author(s):
(Author(s) Not Available)
Published:
20090501
Source:
Meteorological Society of Japan (Tokyo, Japan)
Pages:
--
Contract #:
None
Abstract:
The CD-ROM concerning the Meteorological Satellite Center (MSC) May 2009 Monthly Report contains the observation data derived from the Multi-function Transport SATellite(MTSAT-1R) which was operated from 28 June 2005, and the polar orbital meteorological satellites operated by NOAA. The CD-ROM contains the following observation data: Full Disk Earth's Cloud Image; Cloud Image of Japan and its Vicinity; Sea Surface Temperature; Cloud and Water Vapor Motion Wind; Brightness Temperature Data; Snow and Ice Index; TOVS(TIROS Operational Vertical Sounder) Vertical Profile of Temperature and Precipitable Water; TOVS Total Ozone Amount; Aerosol Optical Thickness; HRIT Image Data Catalog; and Cloud Grid Information.
Language:
English

15-05 REENTRY VEHICLES
Nov 15, 2009 -- Additions to the NASA scientific and technical information knowledge base

Title:
Shuttle Gaseous Hydrogen Venting Risk from Flow Control Valve Failure
Document ID:
20090037582
Report #:
NASA/TM-2009-215942, LF99-8616, L-19767
Available Online:
http://hdl.handle.net/2060/20090037582
Sales Agency:
CASI Hardcopy A03 No Copyright
Author(s):
Drummond, J. Philip (NASA Langley Research Center) Baurle, Robert A. (NASA Langley Research Center) Gafney, Richard L. (NASA Langley Research Center) Norris, Andrew T. (NASA Langley Research Center) Pellett, Gerald L. (NASA Langley Research Center) Rock, Kenneth E. (NASA Langley Research Center)
Published:
20091001
Source:
NASA Langley Research Center (Hampton, VA, United States)
Pages:
42
Contract #:
None
Abstract:
This paper describes a series of studies to assess the potential risk associated with the failure of one of three gaseous hydrogen flow control valves in the orbiter's main propulsion system during the launch of Shuttle Endeavour (STS-126) in November 2008. The studies focused on critical issues associated with the possibility of combustion resulting from release of gaseous hydrogen from the external tank into the atmosphere during assent. The Shuttle Program currently assumes hydrogen venting from the external tank will result in a critical failure. The current effort was conducted to increase understanding of the risk associated with venting hydrogen given the flow control valve failure scenarios being considered in the Integrated In-Flight Anomaly Investigation being conducted by NASA.
Language:
English

15-06 U.S.S.R. SPACECRAFT
Nov 15, 2009 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

16-01 SPACE TRANSPORTATION AND MANNED SPACECRAFT
Nov 15, 2009 -- Additions to the NASA scientific and technical information knowledge base

Title:
Development of a Portable Oxygen Monitoring System for Operations in the International Space Station Airlock
Document ID:
20090037134
Report #:
JSC-CN-18968
Sales Agency:
Other Sources No Copyright
Author(s):
Graf, John (NASA Johnson Space Center)
Published:
20091020
Source:
NASA Johnson Space Center (Houston, TX, United States)
Pages:
1
Contract #:
None
Abstract:
NASA is currently engaged in an activity to facilitate effective operations on the International Space Station (ISS) after the Space Shuttle retires. Currently, the Space Shuttle delivers crew and cargo to and from ISS. The Space Shuttle provides the only large scale method of hardware return from ISS to the ground. Hardware that needs to be periodically repaired, refurbished, or recalibrated must come back from ISS on the Shuttle. One example of NASA flight hardware that is used on ISS and refurbished on the ground is the Compound Specific Analyzer for Oxygen (CSA-O2). The CSA-O2 is an electrochemical sensor that is used on orbit for about 12 months (depending on Shuttle launch schedules), then returned to the ground for sensor replacement. The shuttle is scheduled to retire in 2010, and the ISS is scheduled to operate until 2016. NASA needs a hand held sensor that measures oxygen in the ISS environment and has a 5-10 year service life. After conducting a survey of oxygen sensor systems, NASA selected a Tunable Diode Laser Absorption Spectrometer (TDLAS) as the method of measurement that best addresses the needs for ISS. These systems are compact, meet ISS accuracy requirements, and because they use spectroscopic techniques, the sensors are not consumed or altered after making a measurement. TDLAS systems have service life ratings of 5-10 years, based on the lifetime of the laser. NASA is engaged in modifying a commercially available sensor, the Vaisala OMT 355, for the ISS application. The Vaisala OMT 355 requires three significant modifications to meet ISS needs. The commercial sensor uses a wall mount power supply, and the ISS sensor needs to use a rechargeable battery as its source of power. The commercial sensor has a pressure correction setpoint: the sensor can be adjusted to operate at reduced pressure conditions, but the sensor does not self correct dynamically and automatically. The ISS sensor needs to operate in the airlock, and make accurate measurements in an environment that can change from 14.7 psia to 10.2 psia in 15 minutes. The commercial sensor needs to be repackaged into a configuration that is more compact, and better suited for ISS airlock operations. NASA has recently completed a prototype of the reconfigured system. The unit has been repackaged in a way that the optical path of the spectrometer is unchanged, but the electronics has been integrated into a case measuring 10.7 X 7.2 X 3.0 inches. Two flight qualified rechargeable batteries have been integrated into system. The batteries can power the sensor for 10 hours on a single charge. A pressure sensor has been added to the system. The modified unit automatically compensates for changes in pressure, and meets 0.2% accuracy requirements for oxygen measurements in an environment with 18 to 32% oxygen across a pressure range of 10.0 to 15.0 psia.
Language:
English
Notes:
SAMAP 2009 (Submarine Air Monitoring and Purification) San Diego, CA 20-21 Oct. 2009

Title:
Science Support Room Operations During Desert RATS 2009
Document ID:
20090037136
Report #:
JSC-CN-19066
Sales Agency:
Other Sources Copyright
Author(s):
Lofgren, Gary E. (NASA Johnson Space Center) Hoerz, F. (NASA Johnson Space Center) Bell, M. S. (D-RATS SSR) Cohen, B. A. (NASA Johnson Space Center) Eppler, D. B. (NASA Johnson Space Center) Evans,C. A. (NASA Johnson Space Center) Hodges, K. V. (NASA Johnson Space Center) Hynek, B. M. (NASA Johnson Space Center) Gruener, J. E. (NASA Johnson Space Center) Kring, D. A. (NASA Johnson Space Center) Hurtado, J. M. (NASA Johnson Space Center) Lee, P. (NASA Johnson Space Center) Ming, D. W. (NASA Johnson Space Center) Rice, J. W. (NASA Johnson Space Center)
Published:
20090101
Source:
NASA Johnson Space Center (Houston, TX, United States)
Pages:
1
Contract #:
None
Abstract:
NASA s Desert Research and Technology Studies (D-RATS) field test is a demonstration that combines operations development, technology advances and science in analog planetary surface conditions. The focus is testing preliminary operational concepts for extravehicular activity (EVA) systems by providing hands-on experience with simulated surface operations and EVA hardware and procedures. The DRATS activities also develop technical skills and experience for the engineers, scientists, technicians, and astronauts responsible for realizing the goals of the Lunar Surface Systems Program. The 2009 test is the twelfth for the D-RATS team.
Language:
English
Notes:
Lunar Exploration Analysis Group Annual Meeting Houston, TX 16-19 Nov. 2009

Title:
Effectiveness of Needles Vial Adaptors and Blunt Cannulas for Drug Administration in a Microgravity Environment
Document ID:
20090037374
Report #:
JSC-CN-19031
Sales Agency:
Other Sources Copyright
Author(s):
Hailey, Melinda (NASA Johnson Space Center) Bayuse, Tina (Wyle Integrated Science and Engineering Group)
Published:
20090101
Source:
NASA Johnson Space Center (Houston, TX, United States)
Pages:
1
Contract #:
None
Abstract:
The need for a new system of injectable medications aboard the International Space Station (ISS) was identified. It is desired that this system fly medications in their original manufacturer's packaging, allowing the system to comply with United States Pharmacopeia (USP) guidelines while minimizing the resupply frequency due to medication expiration. Pre-filled syringes are desired, however, the evolving nature of the healthcare marketplace requires flexibility in the redesign. If medications must be supplied in a vial, a system is required that allows for the safe withdrawal of medication from the vial into a syringe for administration in microgravity. During two reduced gravity flights, the effectiveness of two versions of a blunt cannula and needleless vial adaptors was evaluated to facilitate the withdrawal of liquid medication from a vial into a syringe for injection. Other parameters assessed included the ability to withdraw the required amount of medication and whether this is dependent on vial size, liquid, or the total volume of fluid within the vial. Injectable medications proposed for flight on ISS were used for this evaluation. Due to differing sizes of vials and the fluid properties of the medications, the needleless vial adaptors proved to be too cumbersome to recommend for use on the ISS. The blunt cannula, specifically the plastic version, proved to be more effective at removing medication from the various sizes of vials and are the recommended hardware for ISS. Fluid isolation within the vials and syringes is an important step in preparing medication for injection regardless of the hardware used. Although isolation is a challenge in the relatively short parabolas during flight, it is not an obstacle for sustained microgravity. This presentation will provide an overview of the products tested as well as the challenges identified during the microgravity flights.
Language:
English
Notes:
Aerospace Medical Association Annual Meeting Phoenix, AZ 9-13 May 2010

Title:
Strategies For Human Exploration Leading To Human Colonization of Space
Document ID:
20090037579
Report #:
M09-0209
Available Online:
http://hdl.handle.net/2060/20090037579
Sales Agency:
CASI Hardcopy A01 Copyright
Author(s):
Smitherman, David (NASA Marshall Space Flight Center) Everett, Harmon (Houston Univ.)
Published:
20090914
Source:
NASA Marshall Space Flight Center (Huntsville, AL, United States)
Pages:
2
Contract #:
None
Abstract:
Enabling the commercial development of space is key to the future colonization of space and key to a viable space exploration program. Without commercial development following in the footsteps of exploration it is difficult to justify and maintain public interest in the efforts. NASA's exploration program has suffered from the lack of a good commercial economic strategy for decades. Only small advances in commercial space have moved forward, and only up to Earth orbit with the commercial satellite industry. A way to move beyond this phase is to begin the establishment of human commercial activities in space in partnership with the human exploration program. In 2007 and 2008, the authors researched scenarios to make space exploration and commercial space development more feasible as part of their graduate work in the Space Architecture Program at the Sasakawa International Center for Space Architecture at the University of Houston, Houston, Texas. Through this research it became apparent that the problems facing future colonization are much larger than the technology being developed or the international missions that our space agencies are pursuing. These issues are addressed in this paper with recommendations for space exploration, commercial development, and space policy that are needed to form a strategic plan for human expansion into space. In conclusion, the authors found that the current direction in space as carried out by our space agencies around the world is definitely needed, but is inadequate and incapable of resolving all of the issues that inhibit commercial space development. A bolder vision with strategic planning designed to grow infrastructures and set up a legal framework for commercial markets will go a long way toward enabling the future colonization of space.
Language:
English
Notes:
AIAA Space 2009 Conference and Exposition Pasadena, CA 14-17 Spe. 2009

Title:
Measurement and Characterization of Space Shuttle Solid Rocket Motor Plume Acoustics
Document ID:
20090037585
Report #:
M09-0740
Available Online:
http://hdl.handle.net/2060/20090037585
Sales Agency:
CASI Hardcopy A01 No Copyright
Author(s):
Kenny, Robert Jeremy (NASA Marshall Space Flight Center)
Published:
20090101
Source:
NASA Marshall Space Flight Center (Huntsville, AL, United States)
Pages:
2
Contract #:
None
Abstract:
NASA's current models to predict lift-off acoustics for launch vehicles are currently being updated using several numerical and empirical inputs. One empirical input comes from free-field acoustic data measured at three Space Shuttle Reusable Solid Rocket Motor (RSRM) static firings. The measurements were collected by a joint collaboration between NASA - Marshall Space Flight Center, Wyle Labs, and ATK Launch Systems. For the first time NASA measured large-thrust solid rocket motor plume acoustics for evaluation of both noise sources and acoustic radiation properties. Over sixty acoustic free-field measurements were taken over the three static firings to support evaluation of acoustic radiation near the rocket plume, far-field acoustic radiation patterns, plume acoustic power efficiencies, and apparent noise source locations within the plume. At approximately 67 m off nozzle centerline and 70 m downstream of the nozzle exit plan, the measured overall sound pressure level of the RSRM was 155 dB. Peak overall levels in the far field were over 140 dB at 300 m and 50-deg off of the RSRM thrust centerline. The successful collaboration has yielded valuable data that are being implemented into NASA's lift-off acoustic models, which will then be used to update predictions for Ares I and Ares V liftoff acoustic environments.
Language:
English
Notes:
Year-in-Review Article

17-01 SPACE COMMUNICATIONS
Nov 15, 2009 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

17-02 NAVIGATION SYSTEMS
Nov 15, 2009 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

17-03 GUIDANCE SYSTEMS
Nov 15, 2009 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

17-04 TRACKING
Nov 15, 2009 -- Additions to the NASA scientific and technical information knowledge base

Title:
Ocean, Land and Meteorology Studies Using Space-Based Lidar Measurements
Document ID:
20090037431
Report #:
LF99-9425, Paper-626-301
Available Online:
http://hdl.handle.net/2060/20090037431
Sales Agency:
CASI Hardcopy A01 No Copyright
Author(s):
Hu,Yongxiang (NASA Langley Research Center)
Published:
20091017
Source:
NASA Langley Research Center (Hampton, VA, United States)
Pages:
4
Contract #:
None
Abstract:
CALIPSO's main mission objective is studying the climate impact of clouds and aerosols in the atmosphere. CALIPSO also collects information about other components of the Earth's ecosystem, such as oceans and land. This paper introduces the physics concepts and presents preliminary results for the valueadded CALIPSO Earth system science products. These include ocean surface wind speeds, column atmospheric optical depths, ocean subsurface backscatter, land surface elevations, atmospheric temperature profiles, and A-train data fusion products.
Language:
English
Notes:
5th WSEAS International Conference on Remote Sensing (REMOTE'09) Genova 17-19 Oct. 2009

18-01 SPACECRAFT ATTITUDE CONTROL AND STABILIZATION
Nov 15, 2009 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

18-02 RENDEZVOUS AND DOCKING
Nov 15, 2009 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

18-03 SPACE STATIONS
Nov 15, 2009 -- Additions to the NASA scientific and technical information knowledge base

19-01 SPACECRAFT INSTRUMENTATION
Nov 15, 2009 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

19-02 SENSORS AND TRANSDUCERS
Nov 15, 2009 -- Additions to the NASA scientific and technical information knowledge base

Title:
Detection, Identification, Location, and Remote Sensing Using SAW RFID Sensor Tags
Document ID:
20090037326
Report #:
JSC-CN-19047
Available Online:
http://hdl.handle.net/2060/20090037326
Sales Agency:
CASI Hardcopy A03 Copyright
Author(s):
Barton, Richard J. (NASA Johnson Space Center) Kennedy, Timothy F. (NASA Johnson Space Center) Williams, Robert M. (NASA Johnson Space Center) Fink, Patrick W. (NASA Johnson Space Center) Ngo, Phong H. (NASA Johnson Space Center)
Published:
20090101
Source:
NASA Johnson Space Center (Houston, TX, United States)
Pages:
36
Contract #:
None
Abstract:
The Electromagnetic Systems Branch (EV4) of the Avionic Systems Division at NASA Johnson Space Center in Houston, TX is studying the utility of surface acoustic wave (SAW) radiofrequency identification (RFID) tags for multiple wireless applications including detection, identification, tracking, and remote sensing of objects on the lunar surface, monitoring of environmental test facilities, structural shape and health monitoring, and nondestructive test and evaluation of assets. For all of these applications, it is anticipated that the system utilized to interrogate the SAW RFID tags may need to operate at fairly long range and in the presence of considerable multipath and multiple-access interference. Towards that end, EV4 is developing a prototype SAW RFID wireless interrogation system for use in such environments called the Passive Adaptive RFID Sensor Equipment (PARSED) system. The system utilizes a digitally beam-formed planar receiving antenna array to extend range and provide direction-of-arrival information coupled with an approximate maximum-likelihood signal processing algorithm to provide near-optimal estimation of both range and temperature. The system is capable of forming a large number of beams within the field of view and resolving the information from several tags within each beam. The combination of both spatial and waveform discrimination provides the capability to track and monitor telemetry from a large number of objects appearing simultaneously within the field of view of the receiving array. In this paper, we will consider the application of the PARSEQ system to the problem of simultaneous detection, identification, localization, and temperature estimation for multiple objects. We will summarize the overall design of the PARSEQ system and present a detailed description of the design and performance of the signal detection and estimation algorithms incorporated in the system. The system is currently configured only to measure temperature (jointly with range and tag ID), but future versions will be revised to measure parameters other than temperature as SAW tags capable of interfacing with external sensors become available. It is anticipated that the estimation of arbitrary parameters measured using SAW-based sensors will be based on techniques very similar to the joint range and temperature estimation techniques described in this paper.
Language:
English
Notes:
2010 IEEE Aerospace Conference Big Sky, MT 6-13 Mar. 2010

Title:
Technology of the LSST Focal Plane. ch Reactor
Document ID:
20090037506
Report #:
DE2008-924404, SLAC-PUB-13138
Sales Agency:
Department of Energy Information Bridge No Copyright
Author(s):
O'Connor, P. Geary, J. Gilmore, K. Oliver, J. Takacs, P.
Published:
20080227
Source:
Stanford Linear Accelerator Center (CA, United States) Harvard Univ. (Cambridge, MA, United States) Harvard-Smithsonian Center for Astrophysics (Cambridge, MA, United States) Brookhaven National Lab. (Upton, NY United States)
Pages:
6
Contract #:
AC02-76SF00515
Abstract:
The Large Synoptic Survey Telescope, now in the research and development phase, will undertake a wide angle, deep survey of the entire southern sky starting in 2014. The survey database will support a wide variety of astrophysical investigations, with particular emphasis on elucidating the nature of dark energy. To achieve its science goals, LSST will incorporate a silicon-based focal plane with unprecedented size (3 Gpixel), speed (2 s readout), and sensitivity (high QE over 350--1000 nm wavelength). The technologies to be used in the LSST camera are described, with an emphasis on the silicon sensors and readout electronics.
Language:
English
Notes:
Prepared in cooperation with Harvard Univ., Cambridge, MA., Harvard-Smithsonian Center for Astrophysics, Cambridge, MA., Brookhaven National Lab., Upton, NY. and Harvard Univ., Cambridge, MA. Sponsored by Department of Energy, Washington, DC.

Title:
Improvements to a Major Digital Archive of Seismic Waveforms from Nuclear Explosions: The Borovoye Seismogram Archive
Document ID:
20090037588
Report #:
AD-A505432, AFRL-RV-HA-TR-2009-1068
Available Online:
http://hdl.handle.net/100.2/ADA505432
Sales Agency:
Defense Technical Information Center (DTIC) No Copyright
Author(s):
Baker, Diane (Los Alamos National Lab.) Kim, Won-Young (Lamont-Doherty Geological Observatory) Patton, Howard (Los Alamos National Lab.) Randall, George (Los Alamos National Lab.) Richards, Paul (Lamont-Doherty Geological Observatory)
Journal:
Proceedings of the 2009 Monitoring Research Review (MRR) on Ground-Based Nuclear Explosion Monitoring Technologies, Volume: Volume 1 , Page: 12-21
Published:
20090930
Source:
Los Alamos National Lab. (Albuquerque, NM, United States)
Pages:
11
Contract #:
FA8718-07-C-0004
Abstract:
We are in the final year of a three-year project to generate in modern form an easily usable archive of digital seismograms derived from regional waveforms recorded at the Borovoye Observatory (BRV), northern Kazakhstan, over a thirty-year period going back to 1966 and forward to the time when state-of-the-art sensors and dataloggers were introduced at this site by several different western groups. The BRV seismograms, which include multi-channel regional signals from 350 underground nuclear test explosions carried out in Eurasia, were made generally available to western scientists in 2001, but only as copies of the bits in the original digital waveforms. Those copies contain large numbers of glitches and did not include instrument responses for approximately two-thirds of the events. Our project is a joint effort by scientists at Lamont-Doherty Earth Observatory of Columbia University (LDEO) and at Los Alamos National Laboratory (LANL). The work of deglitching all the Borovoye digital seismograms has now been completed (at LANL). The initial work of determining instrument responses for the many different channels of the three different digital systems used at Borovoye over the thirty-year period has also been completed (at LDEO). Three different sets of Soviet-style instruments and recording systems were used at BRV from 1966 to 1996. LANL scientists had processed the BRV regional signals for 210 nuclear tests (1355 traces) before the present project started, mainly those for which instrument responses were available (the TSG system). In this project LANL processed the waveforms of the so-called SS system for 148 nuclear tests (1679 traces), some of which were also recorded on the TSG system, and these have now been processed too (281 traces). The remaining main block of events was recorded on the oldest, so-called KOD, system, which was used in operations beginning in 1966 and which operated continuously from 1967 to 1973.
Language:
English
Notes:
2009 Monitoring Research Review (MRR) on Ground-Based Nuclear Explosion Monitoring Technologies Tucson, AZ 21-23 Sep. 2009

20-01 ROCKET ENGINES, NOZZLES AND THRUST CHAMBERS
Nov 15, 2009 -- Additions to the NASA scientific and technical information knowledge base

20-02 AUXILIARY PROPULSION
Nov 15, 2009 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

20-03 ELECTRIC PROPULSION
Nov 15, 2009 -- Additions to the NASA scientific and technical information knowledge base

Title:
An Overview of the NASA FAP Hypersonics Project Airbreathing Propulsion Research
Document ID:
20090037583
Report #:
LF99-9121
Available Online:
http://hdl.handle.net/2060/20090037583
Sales Agency:
CASI Hardcopy A02 No Copyright
Author(s):
Auslender, A. H. (NASA Langley Research Center) Suder, Kenneth L. (NASA Glenn Research Center) Thomas, Scott R. (NASA Glenn Research Center)
Published:
20091019
Source:
NASA Glenn Research Center (Cleveland, OH, United States)
Pages:
7
Contract #:
None
Abstract:
The propulsion research portfolio of the National Aeronautics and Space Administration Fundamental Aeronautics Program Hypersonics Project encompasses a significant number of technical tasks that are aligned to achieve mastery and intellectual stewardship of the core competencies in the hypersonic-flight regime. An overall coordinated programmatic and technical effort has been structured to advance the state-of-the-art, via both experimental and analytical efforts. A subset of the entire hypersonics propulsion research portfolio is presented in this overview paper. To this end, two programmatic research disciplines are discussed; namely, (1) the Propulsion Discipline, including three associated research elements: the X-51A partnership, the HIFiRE-2 partnership, and the Durable Combustor Rig, and (2) the Turbine-Based Combine Cycle Discipline, including three associated research elements: the Combined Cycle Engine Large Scale Inlet Mode Transition Experiment, the small-scale Inlet Mode Transition Experiment, and the High-Mach Fan Rig.
Language:
English
Notes:
16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference Bremen 19-23 Oct. 2009