SCAN_32-01

32-01 COMMUNICATION SATELLITES
Jun 28, 2009 -- Additions to the NASA scientific and technical information knowledge base

Title:
GPS Metric Tracking Unit
Document ID:
20090022244
Report #:
None
Sales Agency:
CASI Hardcopy A01 Copyright
Author(s):
(Author(s) Not Available)
Journal:
John F. Kennedy Space Center's Technology Development and Application 2006-2007 Report, Page: 66-67
Published:
20080303
Source:
NASA Kennedy Space Center (Cocoa Beach, FL, United States) ASRC Aerospace Corp. (United States)
Pages:
2
Contract #:
None
Abstract:
As Global Positioning Satellite (GPS) applications become more prevalent for land- and air-based vehicles, GPS applications for space vehicles will also increase. The Applied Technology Directorate of Kennedy Space Center (KSC) has developed a lightweight, low-cost GPS Metric Tracking Unit (GMTU), the first of two steps in developing a lightweight, low-cost Space-Based Tracking and Command Subsystem (STACS) designed to meet Range Safety's link margin and latency requirements for vehicle command and telemetry data. The goals of STACS are to improve Range Safety operations and expand tracking capabilities for space vehicles. STACS will track the vehicle, receive commands, and send telemetry data through the space-based asset, which will dramatically reduce dependence on ground-based assets. The other step was the Low-Cost Tracking and Data Relay Satellite System (TDRSS) Transceiver (LCT2), developed by the Wallops Flight Facility (WFF), which allows the vehicle to communicate with a geosynchronous relay satellite. Although the GMTU and LCT2 were independently implemented and tested, the design collaboration of KSC and WFF engineers allowed GMTU and LCT2 to be integrated into one enclosure, leading to the final STACS. In operation, GMTU needs only a radio frequency (RF) input from a GPS antenna and outputs position and velocity data to the vehicle through a serial or pulse code modulation (PCM) interface. GMTU includes one commercial GPS receiver board and a custom board, the Command and Telemetry Processor (CTP) developed by KSC. The CTP design is based on a field-programmable gate array (FPGA) with embedded processors to support GPS functions.
Language:
English

32-02 COMMUNICATION EQUIPMENT
Jun 28, 2009 -- Additions to the NASA scientific and technical information knowledge base

Title:
T/R Multi-Chip MMIC Modules for 150 GHz
Document ID:
20090022344
Report #:
NPO-46074
Available Online:
http://www.techbriefs.com/component/content/article/5275
Sales Agency:
CASI Hardcopy A01 Copyright
Author(s):
Samoska, Lorene A. (California Inst. of Tech.) Pukala, David M. (California Inst. of Tech.) Soria, Mary M. (California Inst. of Tech.) Sadowy, Gregory A. (California Inst. of Tech.)
Journal:
NASA Tech Briefs, June 2009, Page: 17
Published:
20090601
Source:
California Inst. of Tech. (Pasadena, CA, United States)
Pages:
1
Contract #:
None
Abstract:
Modules containing multiple monolithic microwave integrated-circuit (MMIC) chips have been built as prototypes of transmitting/receiving (T/R) modules for millimeter-wavelength radar systems, including phased-array radar systems to be used for diverse purposes that could include guidance and avoidance of hazards for landing spacecraft, imaging systems for detecting hidden weapons, and hazard-avoidance systems for automobiles. Whereas prior landing radar systems have operated at frequencies around 35 GHz, the integrated circuits in this module operate in a frequency band centered at about 150 GHz. The higher frequency (and, hence, shorter wavelength), is expected to make it possible to obtain finer spatial resolution while also using smaller antennas and thereby reducing the sizes and masses of the affected systems.
Language:
English

32-03 COMMUNICATION SYSTEMS
Jun 28, 2009 -- Additions to the NASA scientific and technical information knowledge base

Title:
Service Management Database for DSN Equipment
Document ID:
20090022349
Report #:
NPO-45013
Available Online:
http://www.techbriefs.com/component/content/article/5290
Sales Agency:
CASI Hardcopy A01 Copyright
Author(s):
Zendejas, Silvino (California Inst. of Tech.) Bui, Tung (California Inst. of Tech.) Bui, Bach (California Inst. of Tech.) Malhotra, Shantanu (California Inst. of Tech.) Chen, Fannie (California Inst. of Tech.) Wolgast, Paul (California Inst. of Tech.) Allen, Christopher (California Inst. of Tech.) Luong, Ivy (California Inst. of Tech.) Chang, George (California Inst. of Tech.) Sadaqathulla, Syed (California Inst. of Tech.)
Journal:
NASA Tech Briefs, June 2009, Page: 25
Published:
20090601
Source:
California Inst. of Tech. (Pasadena, CA, United States)
Pages:
1
Contract #:
None
Abstract:
This data- and event-driven persistent storage system leverages the use of commercial software provided by Oracle for portability, ease of maintenance, scalability, and ease of integration with embedded, client-server, and multi-tiered applications. In this role, the Service Management Database (SMDB) is a key component of the overall end-to-end process involved in the scheduling, preparation, and configuration of the Deep Space Network (DSN) equipment needed to perform the various telecommunication services the DSN provides to its customers worldwide. SMDB makes efficient use of triggers, stored procedures, queuing functions, e-mail capabilities, data management, and Java integration features provided by the Oracle relational database management system. SMDB uses a third normal form schema design that allows for simple data maintenance procedures and thin layers of integration with client applications. The software provides an integrated event logging system with ability to publish events to a JMS messaging system for synchronous and asynchronous delivery to subscribed applications. It provides a structured classification of events and application-level messages stored in database tables that are accessible by monitoring applications for real-time monitoring or for troubleshooting and analysis over historical archives.
Language:
English

32-04 TELEMETRY
Jun 28, 2009 -- Additions to the NASA scientific and technical information knowledge base

Title:
John F. Kennedy Space Center's Technology Development and Application 2006-2007 Report
Document ID:
20090022202
Report #:
NASA/TM-2008-214740, NASA-SP-2008-02-045-KSC
Sales Agency:
CASI CD-ROM C01 Copyright
Author(s):
(Author(s) Not Available)
Published:
20080303
Source:
NASA Kennedy Space Center (Cocoa Beach, FL, United States)
Pages:
152
Contract #:
None
Abstract:
Topics covered include: Reversible Chemochromic Hydrogen Detectors; Determining Trajectory of Triboelectrically Charged Particles, Using Discrete Element Modeling; Using Indium Tin Oxide To Mitigate Dust on Viewing Ports; High-Performance Polyimide Powder Coatings; Controlled-Release Microcapsules for Smart Coatings for Corrosion Applications; Aerocoat 7 Replacement Coatings; Photocatalytic Coatings for Exploration and Spaceport Design; New Materials for the Repair of Polyimide Electrical Wire Insulation; Commodity-Free Calibration; Novel Ice Mitigation Methods; Crack Offset Measurement With the Projected Laser Target Device; New Materials for Structural Composites and Protective Coatings; Fire Chemistry Testing of Spray-On Foam Insulation (SOFI); Using Aerogel-Based Insulation Material To Prevent Foam Loss on the Liquid-Hydrogen Intertank; Particle Ejection and Levitation Technology (PELT); Electrostatic Characterization of Lunar Dust; Numerical Analysis of Rocket Exhaust Cratering; RESOLVE Projects: Lunar Water Resource Demonstration and Regolith Volatile Characterization; Tribocharging Lunar Soil for Electrostatic Beneficiation; Numerically Modeling the Erosion of Lunar Soil by Rocket Exhaust Plumes; Trajectory Model of Lunar Dust Particles; Using Lunar Module Shadows To Scale the Effects of Rocket Exhaust Plumes; Predicting the Acoustic Environment Induced by the Launch of the Ares I Vehicle; Measuring Ultrasonic Acoustic Velocity in a Thin Sheet of Graphite Epoxy Composite; Hail Size Distribution Mapping; Launch Pad 39 Hail Monitor Array System; Autonomous Flight Safety System - Phase III; The Photogrammetry Cube; Bird Vision System; Automating Range Surveillance Through Radio Interferometry and Field Strength Mapping Techniques; Next-Generation Telemetry Workstation; GPS Metric Tracking Unit; and Space-Based Range.
Language:
English

Title:
Next-Generation Telemetry Workstation
Document ID:
20090022243
Report #:
None
Sales Agency:
CASI Hardcopy A01 Copyright
Author(s):
(Author(s) Not Available)
Journal:
John F. Kennedy Space Center's Technology Development and Application 2006-2007 Report, Page: 64-65
Published:
20080303
Source:
NASA Kennedy Space Center (Cocoa Beach, FL, United States) ASRC Aerospace Corp. (United States)
Pages:
2
Contract #:
None
Abstract:
A next-generation telemetry workstation has been developed to replace the one currently used to test and control Range Safety systems. Improving upon the performance of the original system, the new telemetry workstation uses dual-channel telemetry boards for better synchronization of the two uplink telemetry streams. The new workstation also includes an Interrange Instrumentation Group/Global Positioning System (IRIG/GPS) time code receiver board for independent, local time stamping of return-link data. The next-generation system will also record and play back return-link data for postlaunch analysis.
Language:
English

Title:
Distributed Observer Network
Document ID:
20090022245
Report #:
None
Sales Agency:
CASI Hardcopy A01 Copyright
Author(s):
(Author(s) Not Available)
Journal:
John F. Kennedy Space Center's Technology Development and Application 2006-2007 Report, Page: 96-97
Published:
20080303
Source:
NASA Kennedy Space Center (Cocoa Beach, FL, United States) ASRC Aerospace Corp. (United States) Valador, Inc. (Rockville Centre, NY, United States)
Pages:
2
Contract #:
None
Abstract:
NASA s advanced visual simulations are essential for analyses associated with life cycle planning, design, training, testing, operations, and evaluation. Kennedy Space Center, in particular, uses simulations for ground services and space exploration planning in an effort to reduce risk and costs while improving safety and performance. However, it has been difficult to circulate and share the results of simulation tools among the field centers, and distance and travel expenses have made timely collaboration even harder. In response, NASA joined with Valador Inc. to develop the Distributed Observer Network (DON), a collaborative environment that leverages game technology to bring 3-D simulations to conventional desktop and laptop computers. DON enables teams of engineers working on design and operations to view and collaborate on 3-D representations of data generated by authoritative tools. DON takes models and telemetry from these sources and, using commercial game engine technology, displays the simulation results in a 3-D visual environment. Multiple widely dispersed users, working individually or in groups, can view and analyze simulation results on desktop and laptop computers in real time.
Language:
English

Title:
Space-Based Range
Document ID:
20090022246
Report #:
None
Sales Agency:
CASI Hardcopy A01 Copyright
Author(s):
(Author(s) Not Available)
Journal:
John F. Kennedy Space Center's Technology Development and Application 2006-2007 Report, Page: 68-69/70
Published:
20080303
Source:
NASA Kennedy Space Center (Cocoa Beach, FL, United States)
Pages:
2
Contract #:
None
Abstract:
Space-Based Range (SBR), previously known as Space-Based Telemetry and Range Safety (STARS), is a multicenter NASA proof-of-concept project to determine if space-based communications using NASA's Tracking and Data Relay Satellite System (TDRSS) can support the Range Safety functions of acquiring tracking data and generating flight termination signals, while also providing broadband Range User data such as voice, video, and vehicle/payload data. There was a successful test of the Range Safety system at Wallops Flight Facility (WFF) on December 20, 2005, on a two-stage Terrier-Orion spin-stabilized sounding rocket. SBR transmitted GPS tracking data and maintained links with two TDRSS satellites simultaneously during the 10-min flight. The payload section deployed a parachute, landed in the Atlantic Ocean about 90 miles downrange from the launch site, and was successfully recovered. During the Terrier-Orion tests flights, more than 99 percent of all forward commands and more than 95 percent of all return frames were successfully received and processed. The time latency necessary for a command to travel from WFF over landlines to White Sands Complex and then to the vehicle via TDRSS, be processed onboard, and then be sent back to WFF was between 1.0 s and 1.1 s. The forward-link margins for TDRS-10 (TDRS East [TDE]) were 11 dB to 12 dB plus or minus 2 dB, and for TDRS-4 (TDRS Spare [TDS]) were 9 dB to 10 dB plus or minus 1.5 dB. The return-link margins for both TDE and TDS were 6 dB to 8 dB plus or minus 3 dB. There were 11 flights on an F-15B at Dryden Flight Research Center (DFRC) between November 2006 and February 2007. The Range User system tested a 184-element TDRSS Ku-band (15 GHz) phased-array antenna with data rates of 5 Mbps and 10 Mbps. This data was a combination of black-and-white cockpit video, Range Safety tracking and transceiver data, and aircraft and antenna controller data streams. IP data formatting was used.
Language:
English

Title:
Converting CSV Files to RKSML Files
Document ID:
20090022343
Report #:
NPO-45013
Available Online:
http://www.techbriefs.com/component/content/article/5289
Sales Agency:
CASI Hardcopy A01 Copyright
Author(s):
Trebi-Ollennu, Ashitey (Jet Propulsion Lab., California Inst. of Tech.) Liebersbach, Robert (Jet Propulsion Lab., California Inst. of Tech.)
Journal:
NASA Tech Briefs, June 2009, Page: 25
Published:
20090601
Source:
Jet Propulsion Lab., California Inst. of Tech. (Pasadena, CA, United States)
Pages:
1
Contract #:
None
Abstract:
A computer program converts, into a format suitable for processing on Earth, files of downlinked telemetric data pertaining to the operation of the Instrument Deployment Device (IDD), which is a robot arm on either of the Mars Explorer Rovers (MERs). The raw downlinked data files are in comma-separated- value (CSV) format. The present program converts the files into Rover Kinematics State Markup Language (RKSML), which is an Extensible Markup Language (XML) format that facilitates representation of operations of the IDD and enables analysis of the operations by means of the Rover Sequencing Validation Program (RSVP), which is used to build sequences of commanded operations for the MERs. After conversion by means of the present program, the downlinked data can be processed by RSVP, enabling the MER downlink operations team to play back the actual IDD activity represented by the telemetric data against the planned IDD activity. Thus, the present program enhances the diagnosis of anomalies that manifest themselves as differences between actual and planned IDD activities.
Language:
English

32-05 RADIO NOISE
Jun 28, 2009 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

32-06 COMMUNICATION THEORY
Jun 28, 2009 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

33-01 RADAR EQUIPMENT
Jun 28, 2009 -- Additions to the NASA scientific and technical information knowledge base

Title:
Hail Size Distribution Mapping
Document ID:
20090022237
Report #:
None
Sales Agency:
CASI Hardcopy A01 Copyright
Author(s):
(Author(s) Not Available)
Journal:
John F. Kennedy Space Center's Technology Development and Application 2006-2007 Report, Page: 52-53
Published:
20080303
Source:
NASA Kennedy Space Center (Cocoa Beach, FL, United States)
Pages:
2
Contract #:
None
Abstract:
A 3-D weather radar visualization software program was developed and implemented as part of an experimental Launch Pad 39 Hail Monitor System. 3DRadPlot, a radar plotting program, is one of several software modules that form building blocks of the hail data processing and analysis system (the complete software processing system under development). The spatial and temporal mapping algorithms were originally developed through research at the University of Central Florida, funded by NASA s Tropical Rainfall Measurement Mission (TRMM), where the goal was to merge National Weather Service (NWS) Next-Generation Weather Radar (NEXRAD) volume reflectivity data with drop size distribution data acquired from a cluster of raindrop disdrometers. In this current work, we adapted these algorithms to process data from a cluster of hail disdrometers positioned around Launch Pads 39A or 39B, along with the corresponding NWS radar data. Radar data from all NWS NEXRAD sites is archived at the National Climatic Data Center (NCDC). That data can be readily accessed at <http://www.ncdc.noaa.gov /nexradin/>. 3DRadPlot plots Level III reflectivity data at four scan elevations (this software is available at Open Channel Software, <http://www.openchannelfoundation.org/projects/3DRadPlot>). By using spatial and temporal interpolation/extrapolation based on hydrometeor fall dynamics, we can merge the hail disdrometer array data coupled with local Weather Surveillance Radar-1988, Doppler (WSR-88D) radial velocity and reflectivity data into a 4-D (3-D space and time) picture of hail size distributions. Hail flux maps can then be generated and used for damage prediction and assessment over specific surfaces corresponding to structures within the disdrometer array volume. Immediately following a hail storm, specific damage areas and degree of damage can be identified for inspection crews.
Language:
English

Title:
Single Longitudinal Mode, High Repetition Rate, Q-switched Ho:YLF Laser for Remote Sensing
Document ID:
20090022381
Report #:
LF99-8155
Sales Agency:
Other Sources Copyright
Author(s):
Bai, Yingxin (Science Systems and Applications, Inc.) Yu, Jirong (NASA Langley Research Center) Petzar, Paul (National Inst. of Aerospace) Petros, M. (Science and Technology Corp.) Chen, Songsheng (Science Systems and Applications, Inc.) Trieu, Bo (NASA Langley Research Center) Lee, Nyung (National Inst. of Aerospace) Singh, U. (NASA Langley Research Center)
Published:
20090531
Source:
NASA Langley Research Center (Hampton, VA, United States)
Pages:
2
Contract #:
None
Abstract:
Ho:YLF/LuLiF lasers have specific applications for remote sensing such as wind-speed measurement and carbon dioxide (CO2) concentration measurement in the atmosphere because the operating wavelength (around 2 m) is located in the eye-safe range and can be tuned to the characteristic lines of CO2 absorption and there is strong backward scattering signal from aerosol (Mie scattering). Experimentally, a diode pumped Ho:Tm:YLF laser has been successfully used as the transmitter of coherent differential absorption lidar for the measurement of with a repetition rate of 5 Hz and pulse energy of 75 mJ [1]. For highly precise CO2 measurements with coherent detection technique, a laser with high repetition rate is required to averaging out the speckle effect [2]. In addition, laser efficiency is critically important for the air/space borne lidar applications, because of the limited power supply. A diode pumped Ho:Tm:YLF laser is difficult to efficiently operate in high repetition rate due to the large heat loading and up-conversion. However, a Tm:fiber laser pumped Ho:YLF laser with low heat loading can be operated at high repetition rates efficiently [3]. No matter whether wind-speed or carbon dioxide (CO2) concentration measurement is the goal, a Ho:YLF/LuLiF laser as the transmitter should operate in a single longitudinal mode. Injection seeding is a valid technique for a Q-switched laser to obtain single longitudinal mode operation. In this paper, we will report the new results for a single longitudinal mode, high repetition rate, Q-switched Ho:YLF laser. In order to avoid spectral hole burning and make injection seeding easier, a four mirror ring cavity is designed for single longitudinal mode, high repetition rate Q-switched Ho:YLF laser. The ramp-fire technique is chosen for injection seeding.
Language:
English
Notes:
Conference on Lasers and Electro-Optics and International Quantum Electronics Conference (CLEO/IQEC 09) Baltimore, MD 31 May - 5 Jun. 2009

Title:
Proton and Gamma Radiation Effects in Undoped, Single-doped and co-doped YLiF4 and LuLiF4
Document ID:
20090022382
Report #:
LF99-8173
Sales Agency:
Other Sources Copyright
Author(s):
Lee, Hyung (National Inst. of Aerospace) Bai, Yingxin (Science Systems and Applications, Inc.) Yu, Kirong (NASA Langley Research Center) Singh, U. (NASA Langley Research Center)
Published:
20090531
Source:
NASA Langley Research Center (Hampton, VA, United States)
Pages:
2
Contract #:
None
Abstract:
Proton and gamma radiation effects in various YLiF4 and LuLiF4 crystals have been investigated. The radiation induced color centers compared with six different kinds of crystal samples in ranges up to 200 krads and 200 MeV. The radiation induced absorption coefficients are strongly dependent on polarization and concentration of rare-earth ions.
Language:
English
Notes:
Conference on Lasers and Electro-Optics and International Quantum Electronics Conference (CLEO/IQEC 09) Baltimore, MD 31 May - 5 Jun. 2009

33-02 SEMICONDUCTORS AND TRANSISTORS
Jun 28, 2009 -- Additions to the NASA scientific and technical information knowledge base

Title:
Improved Starting Materials for Back-Illuminated Imagers
Document ID:
20090022328
Report #:
NPO-41233
Sales Agency:
CASI Hardcopy A01 Copyright
Author(s):
Pain, Bedabrata (California Inst. of Tech.)
Journal:
NASA Tech Briefs, June 2009, Page: 14-15
Published:
20090601
Source:
California Inst. of Tech. (Pasadena, CA, United States)
Pages:
2
Contract #:
None
Abstract:
An improved type of starting materials for the fabrication of silicon-based imaging integrated circuits that include back-illuminated photodetectors has been conceived, and a process for making these starting materials is undergoing development. These materials are intended to enable reductions in dark currents and increases in quantum efficiencies, relative to those of comparable imagers made from prior silicon-on-insulator (SOI) starting materials. Some background information is prerequisite to a meaningful description of the improved starting materials and process. A prior SOI starting material, depicted in the upper part the figure, includes: a) A device layer on the front side, typically between 2 and 20 m thick, made of p-doped silicon (that is, silicon lightly doped with an electron acceptor, which is typically boron); b) A buried oxide (BOX) layer (that is, a buried layer of oxidized silicon) between 0.2 and 0.5 m thick; and c) A silicon handle layer (also known as a handle wafer) on the back side, between about 600 and 650 m thick. After fabrication of the imager circuitry in and on the device layer, the handle wafer is etched away, the BOX layer acting as an etch stop. In subsequent operation of the imager, light enters from the back, through the BOX layer. The advantages of back illumination over front illumination have been discussed in prior NASA Tech Briefs articles.
Language:
English

Title:
Complementary Barrier Infrared Detector
Document ID:
20090022351
Report #:
NPO-46207
Available Online:
http://www.techbriefs.com/component/content/article/5294
Sales Agency:
CASI Hardcopy A01 Copyright
Author(s):
Ting, David Z. (California Inst. of Tech.) Bandara, Sumith V. (California Inst. of Tech.) Hill, Cory J. (California Inst. of Tech.) Gunapala, Sarath D. (California Inst. of Tech.)
Journal:
NASA Tech Briefs, June 2009, Page: 28-29
Published:
20090601
Source:
California Inst. of Tech. (Pasadena, CA, United States)
Pages:
2
Contract #:
None
Abstract:
The complementary barrier infrared detector (CBIRD) is designed to eliminate the major dark current sources in the superlattice infrared detector. The concept can also be applied to bulk semiconductor- based infrared detectors. CBIRD uses two different types of specially designed barriers: an electron barrier that blocks electrons but not holes, and a hole barrier that blocks holes but not electrons. The CBIRD structure consists of an n-contact, a hole barrier, an absorber, an electron barrier, and a p-contact. The barriers are placed at the contact-absorber junctions where, in a conventional p-i-n detector structure, there normally are depletion regions that produce generation-recombination (GR) dark currents due to Shockley-Read- Hall (SRH) processes. The wider-bandgap complementary barriers suppress G-R dark current. The barriers also block diffusion dark currents generated in the diffusion wings in the neutral regions. In addition, the wider gap barriers serve to reduce tunneling dark currents. In the case of a superlattice-based absorber, the superlattice itself can be designed to suppress dark currents due to Auger processes. At the same time, the barriers actually help to enhance the collection of photo-generated carriers by deflecting the photo-carriers that are diffusing in the wrong direction (i.e., away from collectors) and redirecting them toward the collecting contacts. The contact layers are made from materials with narrower bandgaps than the barriers. This allows good ohmic contacts to be made, resulting in lower contact resistances. Previously, THALES Research and Technology (France) demonstrated detectors with bulk InAsSb (specifically InAs0.91Sb0.09) absorber lattice-matched to GaSb substrates. The absorber is surrounded by two wider bandgap layers designed to minimize impedance to photocurrent flow. The wide bandgap materials also serve as contacts. The cutoff wavelength of the InAsSb absorber is fixed. CBIRD may be considered as a modified version of the THALES double heterostructure (DH) p-i-n device, but with even wider bandgap barriers inserted at the contact layer/absorber layer interfaces. It is designed to work with either bulk semiconductors or superlattices as the absorber material. The superlattice bandgap can be adjusted to match the desired absorption cutoff wavelength. This infrared detector has the potential of high-sensitivity operation at higher operating temperatures. This would reduce cooling requirements, thereby reducing the power, mass, and volume of the equipment and allowing an increased mission science return.
Language:
English

33-03 ANTENNAS
Jun 28, 2009 -- Additions to the NASA scientific and technical information knowledge base

Title:
NASA Tech Briefs, June 2009
Document ID:
20090022325
Report #:
None
Sales Agency:
CASI Hardcopy A03 Copyright
Author(s):
(Author(s) Not Available)
Published:
20090601
Source:
NASA (Washington, DC, United States)
Pages:
36
Contract #:
None
Abstract:
Topics covered include: Device for Measuring Low Flow Speed in a Duct, Measuring Thermal Conductivity of a Small Insulation Sample, Alignment Jig for the Precise Measurement of THz Radiation, Autoignition Chamber for Remote Testing of Pyrotechnic Devices, Microwave Power Combiners for Signals of Arbitrary Amplitude, Synthetic Foveal Imaging Technology, Airborne Antenna System for Minimum-Cycle-Slip GPS Reception, Improved Starting Materials for Back-Illuminated Imagers, Multi-Modulator for Bandwidth-Efficient Communication, Some Improvements in Utilization of Flash Memory Devices, GPS/MEMS IMU/Microprocessor Board for Navigation, T/R Multi-Chip MMIC Modules for 150 GHz, Pneumatic Haptic Interfaces, Device Acquires and Retains Rock or Ice Samples, Cryogenic Feedthrough Test Rig, Improved Assembly for Gas Shielding During Welding or Brazing, Two-Step Plasma Process for Cleaning Indium Bonding Bumps, Tool for Crimping Flexible Circuit Leads, Yb14MnSb11 as a High-Efficiency Thermoelectric Material, Polyimide-Foam/Aerogel Composites for Thermal Insulation, Converting CSV Files to RKSML Files, Service Management Database for DSN Equipment, Chemochromic Hydrogen Leak Detectors, Compatibility of Segments of Thermoelectric Generators, Complementary Barrier Infrared Detector, JPL Greenland Moulin Exploration Probe, Ultra-Lightweight Self-Deployable Nanocomposite Structure for Habitat Applications, and Room-Temperature Ionic Liquids for Electrochemical Capacitors.
Language:
English

Title:
Airborne Antenna System for Minimum-Cycle-Slip GPS Reception
Document ID:
20090022327
Report #:
GSC-14436-1
Available Online:
http://www.techbriefs.com/component/content/article/5280
Sales Agency:
CASI Hardcopy A01 Copyright
Author(s):
Wright, C. Wayne (NASA Goddard Space Flight Center)
Journal:
NASA Tech Briefs, June 2009, Page: 13-14
Published:
20090601
Source:
NASA Goddard Space Flight Center (Greenbelt, MD, United States)
Pages:
2
Contract #:
None
Abstract:
A system that includes a Global Positioning System (GPS) antenna and associated apparatus for keeping the antenna aimed upward has been developed for use aboard a remote-sensing-survey airplane. The purpose served by the system is to enable minimum- cycle-slip reception of GPS signals used in precise computation of the trajectory of the airplane, without having to restrict the airplane to maneuvers that increase the flight time needed to perform a survey. Cycle slip signifies loss of continuous track of the phase of a signal. Minimum-cycle-slip reception is desirable because maintaining constant track of the phase of the carrier signal from each available GPS satellite is necessary for surveying to centimeter or subcentimeter precision. Even a loss of signal for as short a time as a nanosecond can cause cycle slip. Cycle slips degrade the quality and precision of survey data acquired during a flight. The two principal causes of cycle slip are weakness of signals and multipath propagation. Heretofore, it has been standard practice to mount a GPS antenna rigidly on top of an airplane, and the radiation pattern of the antenna is typically hemispherical, so that all GPS satellites above the horizon are viewed by the antenna during level flight. When the airplane must be banked for a turn or other maneuver, the reception hemisphere becomes correspondingly tilted; hence, the antenna no longer views satellites that may still be above the Earth horizon but are now below the equatorial plane of the tilted reception hemisphere. Moreover, part of the reception hemisphere (typically, on the inside of a turn) becomes pointed toward ground, with a consequent increase in received noise and, therefore, degradation of GPS measurements. To minimize the likelihood of loss of signal and cycle slip, bank angles of remote-sensing survey airplanes have generally been limited to 10 or less, resulting in skidding or slipping uncoordinated turns. An airplane must be banked in order to make a coordinated turn. For small-radius, short-time coordinated turns, it is necessary to employ banks as steep as 45 , and turns involving such banks are times and for confining airplanes as closely as possible to areas to be surveyed. The idea underlying the design is that if the antenna can be kept properly aimed, then the incidence of cycle slips caused by loss or weakness of signals can be minimized. The system includes an articulating GPS antenna and associated electronic circuitry mounted under a radome atop an airplane. The electronic circuitry includes a microprocessor-based interface-circuit-and-data-translation module. The system receives data on the current attitude of the airplane from the inertial navigation system of the airplane. The microprocessor decodes the attitude data and uses them to compute commands for the GPS-antenna-articulating mechanism to tilt the antenna, relative to the airplane, in opposition to the roll or bank of the airplane to keep the antenna pointed toward the zenith. The system was tested aboard the hurricane- hunting airplane of the National Oceanic and Atmospheric Administration (NOAA) [see figure] during an 11-hour flight to observe the landfall of Hurricane Bret in late summer of 1999. No bank-angle restrictions were imposed during the flight. Post-flight analysis of the GPS trajectory data revealed that no cycle slip had occurred.considered normal maneuvers. These steep banks are highly desirable for minimizing flight
Language:
English

33-04 ELECTRONIC COMPONENTS
Jun 28, 2009 -- Additions to the NASA scientific and technical information knowledge base

Title:
Launch Pad 39 Hail Monitor Array System
Document ID:
20090022203
Report #:
None
Sales Agency:
CASI Hardcopy A01 Copyright
Author(s):
(Author(s) Not Available)
Journal:
John F. Kennedy Space Center's Technology Development and Application 2006-2007 Report, Page: 54-55
Published:
20080303
Source:
NASA Kennedy Space Center (Cocoa Beach, FL, United States) CoCoRaHS (Fort Collins, CO, United States) Colorado State Univ. (Fort Collins, CO, United States)
Pages:
2
Contract #:
None
Abstract:
Weather conditions at Kennedy Space Center are extremely dynamic, and they greatly affect the safety of the Space Shuttles sitting on the launch pads. For example, on May 13, 1999, the foam on the External Tank (ET) of STS-96 was significantly damaged by hail at the launch pad, requiring rollback to the Vehicle Assembly Building. The loss of ET foam on STS-114 in 2005 intensified interest in monitoring and measuring damage to ET foam, especially from hail. But hail can be difficult to detect and monitor because it is often localized and obscured by heavy rain. Furthermore, the hot Florida climate usually melts the hail even before the rainfall subsides. In response, the hail monitor array (HMA) system, a joint effort of the Applied Physics Laboratory operated by NASA and ASRC Aerospace at KSC, was deployed for operational testing in the fall of 2006. Volunteers from the Community Collaborative Rain, Hail, and Snow (CoCoRaHS) network, in conjunction with Colorado State University, continue to test duplicate hail monitor systems deployed in the high plains of Colorado.
Language:
English

33-05 CIRCUITRY
Jun 28, 2009 -- Additions to the NASA scientific and technical information knowledge base

Title:
Sixty-four-Channel Inline Cable Tester
Document ID:
20090022205
Report #:
None
Sales Agency:
CASI Hardcopy A01 Copyright
Author(s):
(Author(s) Not Available)
Journal:
John F. Kennedy Space Center's Technology Development and Application 2006-2007 Report, Page: 112-113
Published:
20080303
Source:
NASA Kennedy Space Center (Cocoa Beach, FL, United States) ASRC Aerospace Corp. (United States)
Pages:
2
Contract #:
None
Abstract:
Faults in wiring are a serious concern for the aerospace and aeronautics (commercial, military, and civil) industries. A number of accidents have occurred because faulty wiring created shorts or opens that resulted in the loss of control of the aircraft or because arcing led to fires and explosions. Some of these accidents have resulted in the massive loss of lives (such as in the TWA Flight 800 accident). Circuits on the Space Shuttle have also failed because of faulty insulation on wiring. STS-93 lost power when a primary power circuit in one engine failed and a second engine had a backup power circuit fault. Cables are usually tested on the ground after the crew reports a fault encountered during flight. Often such failures result from vibration and cannot be replicated while the aircraft is stationary. It is therefore important to monitor faults while the aircraft is in operation, when cables are more likely to fail. Work is in progress to develop a cable fault tester capable of monitoring up to 64 individual wires simultaneously. Faults can be monitored either inline or offline. In the inline mode of operation, the monitoring is performed without disturbing the normal operation of the wires under test. That is, the operations are performed unintrusively and are essentially undetectable for the test signal levels are below the noise floor. A cable can be monitored several times per second in the offline mode and once a second in the inline mode. The 64-channel inline cable tester not only detects the occurrence of a fault, but also determines the type of fault (short/open) and the location of the fault. This will enable the detection of intermittent faults that can be repaired before they become serious problems.
Language:
English

Title:
Multi-Modulator for Bandwidth-Efficient Communication
Document ID:
20090022342
Report #:
NPO-40807
Available Online:
http://www.techbriefs.com/component/content/article/5278
Sales Agency:
CASI Hardcopy A01 Copyright
Author(s):
Gray, Andrew (California Inst. of Tech.) Lee, Dennis (California Inst. of Tech.) Lay, Norman (California Inst. of Tech.) Cheetham, Craig (California Inst. of Tech.) Fong, Wai (NASA Goddard Space Flight Center) Yeh, Pen-Shu (NASA Goddard Space Flight Center) King, Robin (NASA Goddard Space Flight Center) Ghuman, Parminder (NASA Goddard Space Flight Center) Hoy, Scott (Lockheed Martin Corp.) Fisher, Dave (Lockheed Martin Corp.)
Journal:
NASA Tech Briefs, June 2009, Page: 15-16
Published:
20090601
Source:
California Inst. of Tech. (Pasadena, CA, United States)
Pages:
2
Contract #:
None
Abstract:
A modulator circuit board has recently been developed to be used in conjunction with a vector modulator to generate any of a large number of modulations for bandwidth-efficient radio transmission of digital data signals at rates than can exceed 100 Mb/s. The modulations include quadrature phaseshift keying (QPSK), offset quadrature phase-shift keying (OQPSK), Gaussian minimum-shift keying (GMSK), and octonary phase-shift keying (8PSK) with square-root raised-cosine pulse shaping. The figure is a greatly simplified block diagram showing the relationship between the modulator board and the rest of the transmitter. The role of the modulator board is to encode the incoming data stream and to shape the resulting pulses, which are fed as inputs to the vector modulator. The combination of encoding and pulse shaping in a given application is chosen to maximize the bandwidth efficiency. The modulator board includes gallium arsenide serial-to-parallel converters at its input end. A complementary metal oxide/semiconductor (CMOS) field-programmable gate array (FPGA) performs the coding and modulation computations and utilizes parallel processing in doing so. The results of the parallel computation are combined and converted to pulse waveforms by use of gallium arsenide parallel-to-serial converters integrated with digital-to-analog converters. Without changing the hardware, one can configure the modulator to produce any of the designed combinations of coding and modulation by loading the appropriate bit configuration file into the FPGA.
Language:
English

Title:
Synthetic Foveal Imaging Technology
Document ID:
20090022352
Report #:
NPO-44209
Sales Agency:
CASI Hardcopy A01 Copyright
Author(s):
Hoenk, Michael (California Inst. of Tech.) Monacos, Steve (California Inst. of Tech.) Nikzad, Shouleh (California Inst. of Tech.)
Journal:
NASA Tech Briefs, June 2009, Page: 12-13
Published:
20090601
Source:
California Inst. of Tech. (Pasadena, CA, United States)
Pages:
2
Contract #:
None
Abstract:
Synthetic Foveal imaging Technology (SyFT) is an emerging discipline of image capture and image-data processing that offers the prospect of greatly increased capabilities for real-time processing of large, high-resolution images (including mosaic images) for such purposes as automated recognition and tracking of moving objects of interest. SyFT offers a solution to the image-data processing problem arising from the proposed development of gigapixel mosaic focal-plane image-detector assemblies for very wide field-of-view imaging with high resolution for detecting and tracking sparse objects or events within narrow subfields of view. In order to identify and track the objects or events without the means of dynamic adaptation to be afforded by SyFT, it would be necessary to post-process data from an image-data space consisting of terabytes of data. Such post-processing would be time-consuming and, as a consequence, could result in missing significant events that could not be observed at all due to the time evolution of such events or could not be observed at required levels of fidelity without such real-time adaptations as adjusting focal-plane operating conditions or aiming of the focal plane in different directions to track such events. The basic concept of foveal imaging is straightforward: In imitation of a natural eye, a foveal-vision image sensor is designed to offer higher resolution in a small region of interest (ROI) within its field of view. Foveal vision reduces the amount of unwanted information that must be transferred from the image sensor to external image-data-processing circuitry. The aforementioned basic concept is not new in itself: indeed, image sensors based on these concepts have been described in several previous NASA Tech Briefs articles. Active-pixel integrated-circuit image sensors that can be programmed in real time to effect foveal artificial vision on demand are one such example. What is new in SyFT is a synergistic combination of recent advances in foveal imaging, computing, and related fields, along with a generalization of the basic foveal-vision concept to admit a synthetic fovea that is not restricted to one contiguous region of an image.
Language:
English

33-06 ELECTRICAL EQUIPMENT
Jun 28, 2009 -- Additions to the NASA scientific and technical information knowledge base

Title:
New Materials for the Repair of Polyimide Electrical Wire Insulation
Document ID:
20090022227
Report #:
None
Sales Agency:
CASI Hardcopy A01 Copyright
Author(s):
(Author(s) Not Available)
Journal:
John F. Kennedy Space Center's Technology Development and Application 2006-2007 Report, Page: 16-17
Published:
20080303
Source:
NASA Kennedy Space Center (Cocoa Beach, FL, United States) ASRC Aerospace Corp. (United States)
Pages:
2
Contract #:
None
Abstract:
Two viable polyimide backbone materials have been identified that will allow the repair of polyimide electrical wire insulation found on the Space Shuttle and other aging aircraft. This identification is the outcome of ongoing efforts to assess the viability of using such polyimides and polyimide precursors (polyamic acids [PAAs]) as repair materials for aging polyimide electrical wire insulation. These repair materials were selected because they match the chemical makeup of the underlying wire insulation as closely as possible. This similarity allows for maximum compatibility, coupled with the outstanding physical properties of polyimides. The two polyimide backbone materials allow the polymer to be extremely flexible and to melt at low temperatures. A polymer chain end capping group that allows the polymer to crosslink into a nonflowable repair upon curing at around 200 C was also identified.
Language:
English

33-07 AMPLIFIERS
Jun 28, 2009 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

33-08 FEEDBACK AND CONTROL THEORY
Jun 28, 2009 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

33-09 ELECTROMAGNETIC RADIATION
Jun 28, 2009 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

33-10 MICROELECTRONICS
Jun 28, 2009 -- Additions to the NASA scientific and technical information knowledge base

33-11 MICROWAVE AND SUBMILLIMETER WAVE TECHNOLOGY
Jun 28, 2009 -- Additions to the NASA scientific and technical information knowledge base

33-12 MAGNETISM
Jun 28, 2009 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

34-01 BOUNDARY LAYER TECHNOLOGY
Jun 28, 2009 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

34-03 FLUIDICS
Jun 28, 2009 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

34-04 FLUID FLOW
Jun 28, 2009 -- Additions to the NASA scientific and technical information knowledge base

Title:
Numerical Analysis of Rocket Exhaust Cratering
Document ID:
20090022209
Report #:
None
Sales Agency:
CASI Hardcopy A01 Copyright
Author(s):
(Author(s) Not Available)
Journal:
John F. Kennedy Space Center's Technology Development and Application 2006-2007 Report, Page: 34-35
Published:
20080303
Source:
NASA Kennedy Space Center (Cocoa Beach, FL, United States) Florida Inst. of Tech. (FL, United States)
Pages:
2
Contract #:
None
Abstract:
Supersonic jet exhaust impinging onto a flat surface is a fundamental flow encountered in space or with a missile launch vehicle system. The flow is important because it can endanger launch operations. The purpose of this study is to evaluate the effect of a landing rocket s exhaust on soils. From numerical simulations and analysis, we developed characteristic expressions and curves, which we can use, along with rocket nozzle performance, to predict cratering effects during a soft-soil landing. We conducted a series of multiphase flow simulations with two phases: exhaust gas and sand particles. The main objective of the simulation was to obtain the numerical results as close to the experimental results as possible. After several simulating test runs, the results showed that packing limit and the angle of internal friction are the two critical and dominant factors in the simulations.
Language:
English

Title:
Modeling of Slosh Dynamics in Cryogenic Propellant Tanks in Microgravity Environments
Document ID:
20090022217
Report #:
None
Sales Agency:
CASI Hardcopy A01 Copyright
Author(s):
(Author(s) Not Available)
Journal:
John F. Kennedy Space Center's Technology Development and Application 2006-2007 Report, Page: 86-87/88
Published:
20080303
Source:
NASA Kennedy Space Center (Cocoa Beach, FL, United States) Florida Inst. of Tech. (FL, United States) Sierra Lobo, Inc. (OH, United States)
Pages:
2
Contract #:
None
Abstract:
The slosh dynamics in cryogenic fuel tanks under microgravity is a pressing problem that severely affects the reliability of launching spacecraft. After reaching low Earth orbit, the propellant in a multistage rocket experiences large and cyclic changes in temperature as a result of solar heating. Tank wall heating can induce thermal stratification and propellant boiloff, particularly during slosh-inducing vehicle maneuvers. Precise understanding of the dynamic and thermodynamic effects of propellant slosh caused by these maneuvers is critical to mission performance and success. Computational fluid dynamics (CFD) analysis is used extensively within the space vehicle industry in an attempt to characterize the behavior of liquids in microgravity, yet experimental data to quantify these predictions is very limited and reduces confidence in the analytical predictions. A novel approach designed to produce high-fidelity data for correlation to CFD model predictions is being developed with the assistance of Florida Institute of Technology (FIT) and Sierra Lobo, Inc. With few exceptions, previous work in slosh dynamics was theoretical or treated the mass of fuel as a variable of inertia only; such models did not consider the viscosity, surface tension, or other important fluid effects. The challenges in this research are in the development of instrumentation able to measure the required parameters, the computational ability to quantify the fluid behaviors, and the means to assess both the measurements and predictions. The design of this experiment bridges the understanding of slosh dynamics in microgravity by a comprehensive approach that combines CFD tools, dynamic simulation tools, semianalytical models of the predominant fluid effects, and an experimental framework that includes measurement and characterization of liquid slosh in one-degree-of-freedom (DOF) and two-DOF experiments, and ultimately experiments in a NASA low-gravity aircraft.
Language:
English

Title:
HART-II Acoustic Predictions using a Coupled CFD/CSD Method
Document ID:
20090022380
Report #:
LF99-7866
Available Online:
http://hdl.handle.net/2060/20090022380
Sales Agency:
CASI Hardcopy A03 No Copyright
Author(s):
Boyd, D. Douglas, Jr. (NASA Langley Research Center)
Published:
20090527
Source:
NASA Langley Research Center (Hampton, VA, United States)
Pages:
19
Contract #:
None
Abstract:
This paper documents results to date from the Rotorcraft Acoustic Characterization and Mitigation activity under the NASA Subsonic Rotary Wing Project. The primary goal of this activity is to develop a NASA rotorcraft impulsive noise prediction capability which uses first principles fluid dynamics and structural dynamics. During this effort, elastic blade motion and co-processing capabilities have been included in a recent version of the computational fluid dynamics code (CFD). The CFD code is loosely coupled to computational structural dynamics (CSD) code using new interface codes. The CFD/CSD coupled solution is then used to compute impulsive noise on a plane under the rotor using the Ffowcs Williams-Hawkings solver. This code system is then applied to a range of cases from the Higher Harmonic Aeroacoustic Rotor Test II (HART-II) experiment. For all cases presented, the full experimental configuration (i.e., rotor and wind tunnel sting mount) are used in the coupled CFD/CSD solutions. Results show good correlation between measured and predicted loading and loading time derivative at the only measured radial station. A contributing factor for a typically seen loading mean-value offset between measured data and predictions data is examined. Impulsive noise predictions on the measured microphone plane under the rotor compare favorably with measured mid-frequency noise for all cases. Flow visualization of the BL and MN cases shows that vortex structures generated in the prediction method are consist with measurements. Future application of the prediction method is discussed.
Language:
English
Notes:
AHS International 65th Forum and Technology Display Grapevine, TX 27-29 May 2009

Title:
Adjoint-Based Design of Rotors using the Navier-Stokes Equations in a Noninertial Reference Frame
Document ID:
20090022383
Report #:
LF99-8473
Available Online:
http://hdl.handle.net/2060/20090022383
Sales Agency:
CASI Hardcopy A03 No Copyright
Author(s):
Nielsen, Eric J. (NASA Langley Research Center) Lee-Rausch, Elizabeth M. (NASA Langley Research Center) Jones, William T. (NASA Langley Research Center)
Published:
20090527
Source:
NASA Langley Research Center (Hampton, VA, United States)
Pages:
11
Contract #:
None
Abstract:
Optimization of rotorcraft flowfields using an adjoint method generally requires a time-dependent implementation of the equations. The current study examines an intermediate approach in which a subset of rotor flowfields are cast as steady problems in a noninertial reference frame. This technique permits the use of an existing steady-state adjoint formulation with minor modifications to perform sensitivity analyses. The formulation is valid for isolated rigid rotors in hover or where the freestream velocity is aligned with the axis of rotation. Discrete consistency of the implementation is demonstrated using comparisons with a complex-variable technique, and a number of single- and multi-point optimizations for the rotorcraft figure of merit function are shown for varying blade collective angles. Design trends are shown to remain consistent as the grid is refined.
Language:
English
Notes:
AHS International 65th Forum and Technology Display Grapevine, TX 27-29 May 2009

34-05 COMBUSTION PHYSICS
Jun 28, 2009 -- Additions to the NASA scientific and technical information knowledge base

Title:
Autoignition Chamber for Remote Testing of Pyrotechnic Devices
Document ID:
20090022346
Report #:
MSC-24433-1
Available Online:
http://www.techbriefs.com/component/content/article/5274
Sales Agency:
CASI Hardcopy A01 Copyright
Author(s):
Harrington, Maureen L. (NASA Johnson Space Center) Steward, Gerald R. (NASA Johnson Space Center) Dartez, Toby W. (Jacobs Sverdrup Technology, Inc.)
Journal:
NASA Tech Briefs, June 2009, Page: 8-9
Published:
20090601
Source:
NASA Johnson Space Center (Houston, TX, United States)
Pages:
2
Contract #:
None
Abstract:
The autoignition chamber (AIC) performs by remotely heating pyrotechnic devices that can fit the inner diameter of the tube furnace. Two methods, a cold start or a hot start, can be used with this device in autoignition testing of pyrotechnics. A cold start means extending a pyrotechnic device into the cold autoignition chamber and then heating the device until autoignition occurs. A hot start means heating the autoignition chamber to a specified temperature, and then extending the device into a hot autoignition chamber until autoignition occurs. Personnel are remote from the chamber during the extension into the hot chamber. The autoignition chamber, a commercially produced tubular furnace, has a 230-V, single-phase, 60-Hz electrical supply, with a total power output of 2,400 W. It has a 6-in. (15.2-cm) inner diameter, a 12-in. (30.4-cm) outer diameter and a 12-in.- long (30.4-cm), single-zone, solid tubular furnace (element) capable of heating to temperatures up to 2,012 F (1,100 C) in air.
Language:
English

34-06 HEAT TRANSFER, BASIC
Jun 28, 2009 -- Additions to the NASA scientific and technical information knowledge base

Title:
Compatibility of Segments of Thermoelectric Generators
Document ID:
20090022338
Report #:
NPO-30798
Available Online:
http://www.techbriefs.com/component/content/article/5292
Sales Agency:
CASI Hardcopy A01 Copyright
Author(s):
Snyder, G. Jeffrey (California Inst. of Tech.) Ursell, Tristan (California Inst. of Tech.)
Journal:
NASA Tech Briefs, June 2009, Page: 27-28
Published:
20090601
Source:
California Inst. of Tech. (Pasadena, CA, United States)
Pages:
2
Contract #:
None
Abstract:
A method of calculating (usually for the purpose of maximizing) the power-conversion efficiency of a segmented thermoelectric generator is based on equations derived from the fundamental equations of thermoelectricity. Because it is directly traceable to first principles, the method provides physical explanations in addition to predictions of phenomena involved in segmentation. In comparison with the finite-element method used heretofore to predict (without being able to explain) the behavior of a segmented thermoelectric generator, this method is much simpler to implement in practice: in particular, the efficiency of a segmented thermoelectric generator can be estimated by evaluating equations using only hand-held calculator with this method. In addition, the method provides for determination of cascading ratios. The concept of cascading is illustrated in the figure and the definition of the cascading ratio is defined in the figure caption. An important aspect of the method is its approach to the issue of compatibility among segments, in combination with introduction of the concept of compatibility within a segment. Prior approaches involved the use of only averaged material properties. Two materials in direct contact could be examined for compatibility with each other, but there was no general framework for analysis of compatibility. The present method establishes such a framework. The mathematical derivation of the method begins with the definition of reduced efficiency of a thermoelectric generator as the ratio between (1) its thermal-to-electric power-conversion efficiency and (2) its Carnot efficiency (the maximum efficiency theoretically attainable, given its hot- and cold-side temperatures). The derivation involves calculation of the reduced efficiency of a model thermoelectric generator for which the hot-side temperature is only infinitesimally greater than the cold-side temperature. The derivation includes consideration of the ratio (u) between the electric current and heat-conduction power and leads to the concept of compatibility factor (s) for a given thermoelectric material, defined as the value of u that maximizes the reduced efficiency of the aforementioned model thermoelectric generator.
Language:
English

Title:
Cryogenic Feedthrough Test Rig
Document ID:
20090022339
Report #:
SSC-00299-1
Available Online:
http://www.techbriefs.com/component/content/article/5283
Sales Agency:
CASI Hardcopy A01 Copyright
Author(s):
Skaff, Antony (Sierra Lobo, Inc.)
Journal:
NASA Tech Briefs, June 2009, Page: 20
Published:
20090601
Source:
Sierra Lobo, Inc. (Milan, OH, United States)
Pages:
1
Contract #:
None
Abstract:
The cryogenic feedthrough test rig (CFTR) allows testing of instrumentation feedthroughs at liquid oxygen and liquid hydrogen temperature and pressure extremes (dangerous process fluid) without actually exposing the feedthrough to a combustible or explosive process fluid. In addition, the helium used (inert gas), with cryogenic heat exchangers, exposes the feedthrough to that environment that allows definitive leak rates of feedthrough by typical industry-standard helium mass spectrometers.
Language:
English

34-07 REENTRY HEAT TRANSFER
Jun 28, 2009 -- Additions to the NASA scientific and technical information knowledge base

Title:
NDE for Characterizing Oxidation Damage in Reinforced Carbon-Carbon
Document ID:
20090022154
Report #:
E-17014
Sales Agency:
CASI Hardcopy A03 Copyright
Author(s):
Roth, Don J. (NASA Glenn Research Center) Rauser, Richard W. (Toledo Univ.) Jacobson, nathan S. (NASA Glenn Research Center) Wincheski, Russell A. (NASA Langley Research Center) Walker, James L. (NASA Marshall Space Flight Center) Cosgriff, Laura A. (Cleveland State Univ.)
Published:
20090531
Source:
NASA Glenn Research Center (Cleveland, OH, United States)
Pages:
14
Contract #:
None
Abstract:
In this study, coated reinforced carbon-carbon (RCC) samples of similar structure and composition as that from the NASA space shuttle orbiter s thermal protection system were fabricated with slots in their coating simulating craze cracks. These specimens were used to study oxidation damage detection and characterization using NDE methods. These specimens were heat treated in air at 1143 and 1200 C to create cavities in the carbon substrate underneath the coating as oxygen reacted with the carbon and resulted in its consumption. The cavities varied in diameter from approximately 1 to 3 mm. Single-sided NDE methods were used since they might be practical for on-wing inspection, while x-ray micro-computed tomography (CT) was used to measure cavity sizes in order to validate oxidation models under development for carbon-carbon materials. An RCC sample having a naturally-cracked coating and subsequent oxidation damage was also studied with x-ray micro-CT. This effort is a follow-on study to one that characterized NDE methods for assessing oxidation damage in an RCC sample with drilled holes in the coating. The results of that study are briefly reviewed in this article as well. Additionally, a short discussion on the future role of simulation to aid in these studies is provided.
Language:
English
Notes:
PacRim8 British Columbia 31 May - 5 Jun. 2009

34-08 THERMAL PROTECTION
Jun 28, 2009 -- Additions to the NASA scientific and technical information knowledge base

Title:
Cassini/Huygens Probe Entry, Descent, and Landing (EDL) at Titan Independent Technical Assessment
Document ID:
20090022173
Report #:
NASA/TM-2009-215732, NESC-RP-05-67/04-069-I, L-19670, LF99-8787
Sales Agency:
CASI Hardcopy A06 Copyright
Author(s):
Powell, Richard W. (NASA Langley Research Center) Lockwood, Mary Kae (NASA Langley Research Center) Cruz, Juan R. (NASA Langley Research Center) Striepe, Scott A. (NASA Langley Research Center) Sutton, Kenneth (NASA Langley Research Center) Fisher, Jody (NASA Langley Research Center) Takashima, Naruhisa T. (NASA Langley Research Center) Justus, Jere (Morgan Research Corp.) Keller, Vernon W. (NASA Marshall Space Flight Center) Bose, Deepak (Eloret Corp.) Prabhu, Dinesh (Eloret Corp.) Chen, Y. K. (NASA Ames Research Center) Olejniczak, Joe (NASA Ames Research Center) Cruz, Juan R (NASA Ames Research Center) Duvall, Aleta (Morgan Research Corp.)
Published:
20090501
Source:
NASA Langley Research Center (Hampton, VA, United States)
Pages:
121
Contract #:
None
Abstract:
Starting in January 2004, the NESC has received several communications from knowledgeable technical experts at NASA expressing shared concerns (mainly at the Langley Research Center (LaRC) and Ames Research Center (ARC)) about Huygens mission success. It was suggested that NASA become more technically involved directly in the analysis of Huygens' entry, descent and landing (EDL) focusing on the parachute deployment trigger performance and the resultant effects on the operation of the parachute system, and the determination of the radiative heating environment at Titan by ESA and the corresponding thermal protection system (TPS) response. A NESC Team was formed and tasked to provide an independent assessment of these concerns. The results of that assessment are documented in this report.
Language:
English

Title:
Fire Chemistry Testing of Spray-On Foam Insulation (SOFI)
Document ID:
20090022214
Report #:
None
Sales Agency:
CASI Hardcopy A01 Copyright
Author(s):
(Author(s) Not Available)
Journal:
John F. Kennedy Space Center's Technology Development and Application 2006-2007 Report, Page: 26-27
Published:
20080303
Source:
NASA Kennedy Space Center (Cocoa Beach, FL, United States) ASRC Aerospace Corp. (United States)
Pages:
2
Contract #:
None
Abstract:
An experimental study was initiated that included the long-term testing of the following SOFI materials, which make up the majority of the Thermal Protection System of the Shuttle External Tank: NCFI 24-124 (acreage foam) and BX-265 (close-out foam, including the intertank flange and bipod areas). A potential alternate material, NCFI 27-68 (acreage foam with flame retardant removed), was also tested. Fire chemistry testing was completed on samples that were retrieved after aging/weathering at intervals of 3, 6, and 12 months. The testing included three standard test methods: limiting oxygen index (ASTM G125), radiant panel (ASTM E162), and cone calorimeter (ASTM E1354).
Language:
English

Title:
Thermal Performance of Aged and Weathered Spray-On Foam Insulation (SOFI) Materials Under Cryogenic Vacuum Conditions (Cryostat-4)
Document ID:
20090022220
Report #:
None
Sales Agency:
CASI Hardcopy A01 Copyright
Author(s):
(Author(s) Not Available)
Journal:
John F. Kennedy Space Center's Technology Development and Application 2006-2007 Report, Page: 80-81
Published:
20080303
Source:
NASA Kennedy Space Center (Cocoa Beach, FL, United States) ASRC Aerospace Corp. (United States)
Pages:
2
Contract #:
None
Abstract:
The NASA Cryogenics Test Laboratory at Kennedy Space Center conducted long-term testing of SOFI materials under actual-use cryogenic conditions with Cryostat-4. The materials included in the testing were NCFI 24-124 (acreage foam), BX-265 (close-out foam, including intertank flange and bipod areas), and a potential alternate material, NCFI 27-68, (acreage foam with the flame retardant removed). Specimens of these materials were placed at two locations: a site that simulated aging (the Vehicle Assembly Building [VAB]) and a site that simulated weathering (the Atmospheric Exposure Test Site [beach site]). After aging/weathering intervals of 3, 6, and 12 months, the samples were retrieved and tested for their thermal performance under cryogenic vacuum conditions with test apparatus Cryostat-4.
Language:
English

Title:
Cryogenic Moisture Analysis of Spray-On Foam Insulation (SOFI)
Document ID:
20090022223
Report #:
None
Sales Agency:
CASI Hardcopy A01 Copyright
Author(s):
(Author(s) Not Available)
Journal:
John F. Kennedy Space Center's Technology Development and Application 2006-2007 Report, Page: 78-79
Published:
20080303
Source:
NASA Kennedy Space Center (Cocoa Beach, FL, United States) ASRC Aerospace Corp. (United States)
Pages:
2
Contract #:
None
Abstract:
The NASA Cryogenics Test Laboratory at Kennedy Space Center conducted long-term testing of SOFI materials under actual-use cryogenic conditions. The lab tested NCFI 24-124 (acreage foam), BX-265 (close-out foam, including intertank flange and bipod areas), and a potential alternate material, NCFI 27-68 (acreage foam with the flame retardant removed). Specimens of all three materials were placed at a site that simulated aging (the Vehicle Assembly Building [VAB]) and a site that simulated weathering (Atmospheric Exposure Test Site [beach site]). After aging/ weathering intervals of 3, 6, and 12 months, the samples were retrieved and tested for their ability to absorb moisture under conditions similar to those experienced by the Space Shuttle External Tank (ET) during the loading of cryogenic propellants.
Language:
English

Title:
Using Aerogel-Based Insulation Material To Prevent Foam Loss on the Liquid-Hydrogen Intertank
Document ID:
20090022235
Report #:
None
Sales Agency:
CASI Hardcopy A01 Copyright
Author(s):
(Author(s) Not Available)
Journal:
John F. Kennedy Space Center's Technology Development and Application 2006-2007 Report, Page: 28-29
Published:
20080303
Source:
NASA Kennedy Space Center (Cocoa Beach, FL, United States) ASRC Aerospace Corp. (United States)
Pages:
2
Contract #:
None
Abstract:
Uninsulated areas on cryogenic propellant tanks and feedlines cause moisture in the air to condense or ice to form. Flange joints, bracket supports, expansion bellows, and other cavities are uninsulated by design. These areas cannot be sealed because conventional thermal insulation materials would restrict mechanical articulations. Aerogel-based thermal insulation systems are able to seal critical locations such as the liquid-oxygen (LO2) feedline bellows. A new thermal insulation system was also necessary between the intertank wall, flange, and the liquid-hydrogen (LH2) tank dome, where there is a cavity (or crevice) with an exposed 20-K surface. When nitrogen gas is used for purging within the intertank volume, it condenses on this cold surface. Some solid nitrogen may also form on the colder side of the crevice. Voids or discontinuities within the foam can pressurize and cause areas of foam to weaken and break off, reducing thermal efficiency and creating potentially dangerous debris. To prevent this foam loss, we developed a thermal insulation system using bulk-fill aerogel material and demonstrated it with a one-tenth-scale model of the LH2 intertank flange area
Language:
English

Title:
Polyimide-Foam/Aerogel Composites for Thermal Insulation
Document ID:
20090022326
Report #:
KSC-12894
Available Online:
http://www.techbriefs.com/component/content/article/5287
Sales Agency:
CASI Hardcopy A01 Copyright
Author(s):
Williams, Martha (NASA Kennedy Space Center) Fesmire, James (NASA Kennedy Space Center) Sass, Jared (NASA Kennedy Space Center) Smith, Trent (NASA Kennedy Space Center) Weoser. Erol (NASA Langley Research Center)
Journal:
NASA Tech Briefs, June 2009, Page: 24
Published:
20090601
Source:
NASA Kennedy Space Center (Cocoa Beach, FL, United States)
Pages:
1
Contract #:
None
Abstract:
Composites of specific types of polymer foams and aerogel particles or blankets have been proposed to obtain thermal insulation performance superior to those of the neat polyimide foams. These composites have potential to also provide enhanced properties for vibration dampening or acoustic attenuation. The specific type of polymer foam is denoted "TEEK-H", signifying a series, denoted H, within a family of polyimide foams that were developed at NASA s Langley Research Center and are collectively denoted TEEK (an acronym of the inventors names). The specific types of aerogels include Nanogel aerogel particles from Cabot Corporation in Billerica, MA. and of Spaceloft aerogel blanket from Aspen Aerogels in Northborough, MA. The composites are inherently flame-retardant and exceptionally thermally stable. There are numerous potential uses for these composites, at temperatures from cryogenic to high temperatures, in diverse applications that include aerospace vehicles, aircraft, ocean vessels, buildings, and industrial process equipment. Some low-temperature applications, for example, include cryogenic storage and transfer or the transport of foods, medicines, and chemicals. Because of thermal cycling, aging, and weathering most polymer foams do not perform well at cryogenic temperatures and will undergo further cracking over time. The TEEK polyimides are among the few exceptions to this pattern, and the proposed composites are intended to have all the desirable properties of TEEK-H foams, plus improved thermal performance along with enhanced vibration or acoustic-attenuation performance. A composite panel as proposed would be fabricated by adding an appropriate amount of TEEK friable balloons into a mold to form a bottom layer. A piece of flexible aerogel blanket material, cut to the desired size and shape, would then be placed on the bottom TEEK layer and sandwiched between another top layer of polyimide friable balloons so that the aerogel blanket would become completely encased in an outer layer of TEEK friable balloons. Optionally, the process could be further repeated to produce multiple aerogel-blanket layers interspersed with and encased by TEEK friable balloons.
Language:
English

Title:
Pneumatic Haptic Interfaces
Document ID:
20090022340
Report #:
NPO-43010
Available Online:
http://www.techbriefs.com/component/content/article/5282
Sales Agency:
CASI Hardcopy A01 Copyright
Author(s):
Bae, Sam Y. (California Inst. of Tech.) White, Victor (California Inst. of Tech.) Manohara, Harish (California Inst. of Tech.)
Journal:
NASA Tech Briefs, June 2009, Page: 19
Published:
20090601
Source:
California Inst. of Tech. (Pasadena, CA, United States)
Pages:
1
Contract #:
None
Abstract:
An instrumentation system for direct measurement of the thermal conductivity of a small sample of a highly insulating material has been devised. As used here, (1) "small" signifies having dimensions of the order of two centimeters - significantly less than the sizes of specimens for which prior devices for direct measurement of thermal conductivity have been designed; and (2) "highly insulating" signifies having thermal conductivity of the order of that of air. The heart of the system is an assembly that includes two copper disks - one electrically heated, the other cooled with chilled water. The disks are separated by a guard ring made of strong, thermally insulating polymethacrylamide foam. The sample fits between the copper disks and within the ring (see figure). Matched thermocouples are used to measure the temperatures of the heated and cooled disks. The heated and cooled disks are affixed to larger foam disks, and the essentially still air in the gap between the larger disks insulates the sides of the specimen. This air gap region can be further divided by extending the foam ring into the gap region. The entire assembly as described thus far is lightly clamped together by means of nylon threaded rods and is placed inside a cylindrical chamber wherein the temperature is maintained at a set value (typically, 25 C).
Language:
English

34-09 ABLATION
Jun 28, 2009 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

34-10 CRYOGENICS
Jun 28, 2009 -- Additions to the NASA scientific and technical information knowledge base

Title:
Composite Materials for Low-Temperature Applications
Document ID:
20090022212
Report #:
None
Sales Agency:
CASI Hardcopy A01 Copyright
Author(s):
(Author(s) Not Available)
Journal:
John F. Kennedy Space Center's Technology Development and Application 2006-2007 Report, Page: 74-75
Published:
20080303
Source:
NASA Kennedy Space Center (Cocoa Beach, FL, United States) ASRC Aerospace Corp. (United States)
Pages:
2
Contract #:
None
Abstract:
Composite materials with improved thermal conductivity and good mechanical strength properties should allow for the design and construction of more thermally efficient components (such as pipes and valves) for use in fluid-processing systems. These materials should have wide application in any number of systems, including ground support equipment (GSE), lunar systems, and flight hardware that need reduced heat transfer. Researchers from the Polymer Science and Technology Laboratory and the Cryogenics Laboratory at Kennedy Space Center were able to develop a new series of composite materials that can meet NASA's needs for lightweight materials/composites for use in fluid systems and also expand the plastic-additive markets. With respect to thermal conductivity and physical properties, these materials are excellent alternatives to prior composite materials and can be used in the aerospace, automotive, military, electronics, food-packaging, and textile markets. One specific application of the polymeric composition is for use in tanks, pipes, valves, structural supports, and components for hot or cold fluid-processing systems where heat flow through materials is a problem to be avoided. These materials can also substitute for metals in cryogenic and other low-temperature applications. These organic/inorganic polymeric composite materials were invented with significant reduction in heat transfer properties. Decreases of 20 to 50 percent in thermal conductivity versus that of the unmodified polymer matrix were measured. These novel composite materials also maintain mechanical properties of the unmodified polymer matrix. These composite materials consist of an inorganic additive combined with a thermoplastic polymer material. The intrinsic, low thermal conductivity of the additive is imparted into the thermoplastic, resulting in a significant reduction in heat transfer over that of the base polymer itself, yet maintaining most of the polymer's original properties. Normal polymer processing techniques can turn these composite materials into unique, custom parts for ground support, Shuttle, and Constellation needs. We fabricated test specimens of the composite and base materials for thermal and mechanical characterization and found that the strength of the composite material at nominal-percentage loading remained relatively unchanged from the base material.
Language:
English

Title:
Calibrating the Helium Pressurization System for the Space Shuttle Liquid-Hydrogen Tank
Document ID:
20090022247
Report #:
None
Sales Agency:
CASI Hardcopy A01 Copyright
Author(s):
(Author(s) Not Available)
Journal:
John F. Kennedy Space Center's Technology Development and Application 2006-2007 Report, Page: 72-73
Published:
20080303
Source:
NASA Kennedy Space Center (Cocoa Beach, FL, United States) United Space Alliance (United States)
Pages:
2
Contract #:
None
Abstract:
Analysis of the results from the STS-114 tanking tests and subsequent launch called into question existing thermal and mass models of helium pressurization of the liquid hydrogen tank. This hydrogen tank, which makes up the bottom two-thirds of the External Tank, is pressurized prior to launch to avoid cavitation in the Shuttle Main Engine pumps. At about 2 minutes prior to launch, the main vent valve is closed, and pressurized helium flows into the tank ullage space to achieve set point pressure. As the helium gas cools, its pressure drops, calling for additional helium. Subsequent helium flows are provided in short, timed pulses. The number of pulses is taken as a rough leak indicator. An analysis of thermal models by Marshall Space Flight Center showed considerable uncertainty in the pressure-versus-time behavior of the helium ullage space and the ability to predict the number of pulses normally expected. Kennedy Space Center proposed to calibrate the dime-sized orifice, which together with valves, controls the helium flow quantity (Figure 1). Pressure and temperature sensors were installed to provide upstream and downstream measurements necessary to compute flow rate based on the orifice discharge coefficient. An assessment of flow testing with helium indicated an extremely costly use of this critical resource. In order to reduce costs, we proposed removing the orifices from each Mobile Launcher Platform (MLP) and asking Colorado Engineering Experiment Station Inc. (CEESI) to calibrate the flow. CEESI has a high-pressure air flow system with traceable flow meters capable of handling the large flow rates. However, literature research indicated that square-edged orifices of small diameters often exhibit significant hysteresis and nonrepeatability in the vicinity of choked or sonic flow. Fortunately, the MLP orifices behaved relatively well in testing (Figure 2). Using curve fitting of the air-flow data, in conjunction with ASME orifice modeling equations, a method of relating the helium mass flow to measured air flow data was obtained. This analysis showed that the highest uncertainty in flow occurred in the vicinity of the choking pressure ratio, as would be expected. In addition, analysis of typical flow pulses showed that most of the helium flow occurred either well below or well above this uncertain area. The final result is the ability to provide postlaunch estimates of helium mass flows that are within 1.5 percent of the actual value.
Language:
English

Title:
External Tank Liquid Hydrogen (LH2) Prepress Regression Analysis Independent Review Technical Consultation Report
Document ID:
20090022321
Report #:
NASA/TM-2009-215745, NESC-RP-06-01/05-171-E, L-19680, LF99-8837
Available Online:
http://hdl.handle.net/2060/20090022321
Sales Agency:
CASI Hardcopy A03 No Copyright
Author(s):
Parsons, Vickie s. (NASA Langley Research Center)
Published:
20090501
Source:
NASA Langley Research Center (Hampton, VA, United States)
Pages:
39
Contract #:
None
Abstract:
The request to conduct an independent review of regression models, developed for determining the expected Launch Commit Criteria (LCC) External Tank (ET)-04 cycle count for the Space Shuttle ET tanking process, was submitted to the NASA Engineering and Safety Center NESC on September 20, 2005. The NESC team performed an independent review of regression models documented in Prepress Regression Analysis, Tom Clark and Angela Krenn, 10/27/05. This consultation consisted of a peer review by statistical experts of the proposed regression models provided in the Prepress Regression Analysis. This document is the consultation's final report.
Language:
English

Title:
Chemochromic Hydrogen Leak Detectors
Document ID:
20090022337
Report #:
KSC-13088
Available Online:
http://www.techbriefs.com/component/content/article/5291
Sales Agency:
CASI Hardcopy A01 Copyright
Author(s):
Roberson, Luke (NASA Kennedy Space Center) Captain, Janine (NASA Kennedy Space Center) Williams, Martha (NASA Kennedy Space Center) Smith, Trent (NASA Kennedy Space Center) Tate, LaNetra (NASA Kennedy Space Center) Raissi, Ali (Florida Solar Energy Center) Mohajeri, Nahid (Florida Solar Energy Center) Muradov, Nazim (Florida Solar Energy Center) Bokerman, Gary (Florida Solar Energy Center)
Journal:
NASA Tech Briefs, June 2009, Page: 27
Published:
20090601
Source:
NASA Kennedy Space Center (Cocoa Beach, FL, United States)
Pages:
1
Contract #:
None
Abstract:
At NASA, hydrogen safety is a key concern for space shuttle processing. Leaks of any level must be quickly recognized and addressed due to hydrogen s lower explosion limit. Chemo - chromic devices have been developed to detect hydrogen gas in several embodiments. Because hydrogen is odorless and colorless and poses an explosion hazard, there is an emerging need for sensors to quickly and accurately detect low levels of leaking hydrogen in fuel cells and other advanced energy- generating systems in which hydrogen is used as fuel. The device incorporates a chemo - chromic pigment into a base polymer. The article can reversibly or irreversibly change color upon exposure to hydrogen. The irreversible pigment changes color from a light beige to a dark gray. The sensitivity of the pigment can be tailored to its application by altering its exposure to gas through the incorporation of one or more additives or polymer matrix. Furthermore, through the incorporation of insulating additives, the chemochromic sensor can operate at cryogenic temperatures as low as 78 K. A chemochromic detector of this type can be manufactured into any feasible polymer part including injection molded plastic parts, fiber-spun textiles, or extruded tapes. The detectors are simple, inexpensive, portable, and do not require an external power source. The chemochromic detectors were installed and removed easily at the KSC launch pad without need for special expertise. These detectors may require an external monitor such as the human eye, camera, or electronic detector; however, they could be left in place, unmonitored, and examined later for color change to determine whether there had been exposure to hydrogen. In one type of envisioned application, chemochromic detectors would be fabricated as outer layers (e.g., casings or coatings) on high-pressure hydrogen storage tanks and other components of hydrogen-handling systems to provide visible indications of hydrogen leaks caused by fatigue failures or other failures in those systems. In another type of envisioned application, chemochromic detectors of this type could be optoelectronically instrumented for monitoring to provide measured digital indications of color changes indicative of the presence of hydrogen.
Language:
English

Title:
Development Status of the Carbon Dioxide and Moisture Removal Amine Swing-Bed System (CAMRAS)
Document ID:
20090022370
Report #:
09ICES-0212, JSC-CN-18290
Sales Agency:
Other Sources Copyright
Author(s):
Papale, William (Hamilton Sundstrand Corp.) Nalette Tim (Hamilton Sundstrand Corp.) Sweterlitsch, Jeffrey (NASA Johnson Space Center)
Published:
20090101
Source:
NASA Johnson Space Center (Houston, TX, United States)
Pages:
5
Contract #:
None
Abstract:
Under a cooperative agreement with NASA, Hamilton Sundstrand has successfully designed, fabricated, tested and delivered three, state-of-the-art, solid amine prototype systems capable of continuous CO2 and humidity removal from a closed, habitable atmosphere. Two prototype systems (CAMRAS #1 and #2) incorporated a linear spool valve design for process flow control through the sorbent beds, with the third system (CAMRAS #3) employing a rotary valve assembly that improves system fluid interfaces and regeneration capabilities. The operational performance of CAMRAS #1 and #2 has been validated in a relevant environment, through both simulated human metabolic loads in a closed chamber and through human subject testing in a closed environment. Performance testing at Hamilton Sundstrand on CAMRAS #3, which incorporates a new valve and modified canister design, showed similar CO2 and humidity removal performance as CAMRAS #1 and #2, demonstrating that the system form can be modified within certain bounds with little to no effect in system function or performance. Demonstration of solid amine based CO2 and humidity control is an important milestone in developing this technology for human spaceflight. The systems have low power requirements; with power for air flow and periodic valve actuation and indication the sole requirements. Each system occupies the same space as roughly four shuttle non-regenerative LiOH canisters, but have essentially indefinite CO2 removal endurance provided a regeneration pathway is available. Using the solid amine based systems to control cabin humidity also eliminates the latent heat burden on cabin thermal control systems and the need for gas/liquid phase separation in a low gravity environment, resulting in additional simplification of vehicle environmental control and life support system process requirements.
Language:
English
Notes:
39th International Conference on Environmental Systems Savannah, GA 12-16 Jul. 2009

35-01 PHOTOGRAPHY
Jun 28, 2009 -- Additions to the NASA scientific and technical information knowledge base

Title:
The Photogrammetry Cube
Document ID:
20090022216
Report #:
None
Sales Agency:
CASI Hardcopy A01 Copyright
Author(s):
(Author(s) Not Available)
Journal:
John F. Kennedy Space Center's Technology Development and Application 2006-2007 Report, Page: 58-59
Published:
20080303
Source:
NASA Kennedy Space Center (Cocoa Beach, FL, United States) ASRC Aerospace Corp. (United States)
Pages:
2
Contract #:
None
Abstract:
We can determine distances between objects and points of interest in 3-D space to a useful degree of accuracy from a set of camera images by using multiple camera views and reference targets in the camera s field of view (FOV). The core of the software processing is based on the previously developed foreign-object debris vision trajectory software (see KSC Research and Technology 2004 Annual Report, pp. 2 5). The current version of this photogrammetry software includes the ability to calculate distances between any specified point pairs, the ability to process any number of reference targets and any number of camera images, user-friendly editing features, including zoom in/out, translate, and load/unload, routines to help mark reference points with a Find function, while comparing them with the reference point database file, and a comprehensive output report in HTML format. In this system, scene reference targets are replaced by a photogrammetry cube whose exterior surface contains multiple predetermined precision 2-D targets. Precise measurement of the cube s 2-D targets during the fabrication phase eliminates the need for measuring 3-D coordinates of reference target positions in the camera's FOV, using for example a survey theodolite or a Faroarm. Placing the 2-D targets on the cube s surface required the development of precise machining methods. In response, 2-D targets were embedded into the surface of the cube and then painted black for high contrast. A 12-inch collapsible cube was developed for room-size scenes. A 3-inch, solid, stainless-steel photogrammetry cube was also fabricated for photogrammetry analysis of small objects.
Language:
English

35-02 INFRARED TECHNOLOGY
Jun 28, 2009 -- Additions to the NASA scientific and technical information knowledge base

35-03 INSTRUMENT STANDARDS AND CALIBRATION TECHNIQUES
Jun 28, 2009 -- Additions to the NASA scientific and technical information knowledge base

Title:
Wireless Inclinometer Calibration System
Document ID:
20090022230
Report #:
None
Sales Agency:
CASI Hardcopy A01 Copyright
Author(s):
(Author(s) Not Available)
Journal:
John F. Kennedy Space Center's Technology Development and Application 2006-2007 Report, Page: 114-115
Published:
20080303
Source:
NASA Kennedy Space Center (Cocoa Beach, FL, United States) ASRC Aerospace Corp. (United States)
Pages:
2
Contract #:
None
Abstract:
A special system was fabricated to properly calibrate the wireless inclinometer, a new device that will measure the Orbiter s hang angle. The wireless inclinometer has a unique design and method of attachment to the Orbiter that will improve the accuracy of the measurements, as well as the safety and ease of the operation. The system properly calibrates the four attached inclinometers, in both the horizontal and vertical axes, without needing to remove any of the component parts. The Wireless Inclinometer Calibration System combines (1) a calibration fixture that emulates the point of attachment to the Orbiter in both the horizontal and vertical axes and the measurement surfaces, (2) an application-specific software program that accepts calibration data such as dates, zero functions, or offsets and tables, and (3) a wireless interface module that enables the wireless inclinometer to communicate with a calibration PC.
Language:
English

35-04 TEMPERATURE MEASUREMENT
Jun 28, 2009 -- Additions to the NASA scientific and technical information knowledge base

35-05 PRESSURE MEASUREMENT
Jun 28, 2009 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

35-06 DISPLAY SYSTEMS
Jun 28, 2009 -- Additions to the NASA scientific and technical information knowledge base

35-07 DATA RECORDING
Jun 28, 2009 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

35-08 GAS FLOW MEASUREMENT
Jun 28, 2009 -- Additions to the NASA scientific and technical information knowledge base

Title:
Measuring Thermal Conductivity of a Small Insulation Sample
Document ID:
20090022348
Report #:
LEW-18356-1
Available Online:
http://www.techbriefs.com/component/content/article/5272
Sales Agency:
CASI Hardcopy A01 Copyright
Author(s):
Miller, Robert A. (NASA Glenn Research Center) Kuczmarski, Maria A. (NASA Glenn Research Center)
Journal:
NASA Tech Briefs, June 2009, Page: 6-7
Published:
20090601
Source:
NASA Glenn Research Center (Cleveland, OH, United States)
Pages:
2
Contract #:
None
Abstract:
A multiple-throat venturi system has been invented for measuring laminar flow of air or other gas at low speed (1 to 30 cm/s) in a duct while preserving the laminar nature of the flow and keeping the velocity profile across the duct as nearly flat as possible. While means for measuring flows at higher speeds are well established, heretofore, there have been no reliable means for making consistent, accurate measurements in this speed range. In the original application for which this system was invented, the duct leads into the test section of a low-speed wind tunnel wherein uniform, low-speed, laminar flow is required for scientific experiments. The system could also be used to monitor a slow flow of gas in an industrial process like chemical vapor deposition. In the original application, the multiple- throat venturi system is mounted at the inlet end of the duct having a rectangular cross section of 19 by 14 cm, just upstream of an assembly of inlet screens and flow straighteners that help to suppress undesired flow fluctuations (see Figure 1). The basic venturi measurement principle is well established: One measures the difference in pressure between (1) a point just outside the inlet, where the pressure is highest and the kinetic energy lowest; and (2) the narrowest part (the throat) of the venturi passage, where the kinetic energy is highest and the pressure is lowest. Then by use of Bernoulli s equation for the relationship between pressure and kinetic energy, the volumetric flow speed in the duct can be calculated from the pressure difference and the inlet and throat widths. The design of this system represents a compromise among length, pressure recovery, uniformity of flow, and complexity of assembly. Traditionally, venturis are used to measure faster flows in narrower cross sections, with longer upstream and downstream passages to maintain accuracy. The dimensions of the passages of the present venturi system are sized to provide a readily measurable pressure drop. Multiple throats are used to minimize the length needed to recover internal energy and enable the velocity profile to recover to near flatness.
Language:
English

36-01 LASERS AND MASERS
Jun 28, 2009 -- Additions to the NASA scientific and technical information knowledge base

36-02 LASER APPLICATIONS
Jun 28, 2009 -- Additions to the NASA scientific and technical information knowledge base

Title:
Crack Offset Measurement With the Projected Laser Target Device
Document ID:
20090022253
Report #:
None
Sales Agency:
CASI Hardcopy A01 Copyright
Author(s):
(Author(s) Not Available)
Journal:
John F. Kennedy Space Center's Technology Development and Application 2006-2007 Report, Page: 22-23
Published:
20080303
Source:
NASA Kennedy Space Center (Cocoa Beach, FL, United States) ASRC Aerospace Corp. (United States)
Pages:
2
Contract #:
None
Abstract:
The device and associated analysis methodology summarized in this report were developed for the purpose of estimating the size of discontinuities in the surface of the foam that covers the Space Shuttle External Tank. These surface offsets are thought to be due to subsurface cracks in the foam insulation. The mathematical analysis and procedure described here provide a method to quantity the dimensions of the crack offset in a direction perpendicular to the surface, making use of the projected laser target device (PLTD) tool and a laser line projector. The keys to the construction and use of the PLTD are the following geometrical design requirements: Laser dots are on a square grid: length on a side. Laser beams are perpendicular to projected surface. Beams are parallel out to the distance being projected. The PLTD can be used to (1) calibrate fixed cameras of unknown magnification and orientation (far-field solution); (2) provide equivalent calibration to multiple cameras, previously achieved only by the use of known target points, for example, in 3.D foreign-object debris tracking on a fixed launch platform; (3) compute scaling for conventional 2.D images, and depth of field for 3.D images (near-field solution); and (4) in conjunction with a laser line projector, achieve accurate measurements of surface discontinuity (cracks) in a direction perpendicular to the surface.
Language:
English

37-01 BEARINGS AND GEARS
Jun 28, 2009 -- Additions to the NASA scientific and technical information knowledge base

Title:
Performance and Analysis of Perfluorinated Grease used on Space Shuttle Actuators
Document ID:
20090022125
Report #:
NASA/TM-2009-215605, E-16522-1
Available Online:
http://hdl.handle.net/2060/20090022125
Sales Agency:
CASI Hardcopy A03 No Copyright
Author(s):
Morales, Wilfredo (NASA Glenn Research Center) Street, Kenneth W. (NASA Glenn Research Center) Zaretsky, Erwin V. (NASA Glenn Research Center)
Published:
20090401
Source:
NASA Glenn Research Center (Cleveland, OH, United States)
Pages:
16
Contract #:
None
Abstract:
Actuators used on the United States space shuttle fleet are lubricated with grease consisting of a perfluoropolyalkyl ether (PFPE) base oil thickened with a polytetrafluoroethylene (PTFE) filler. The actuators were designed to operate for life without periodic relubrication and some have been in use for over 20 years. Visible inspection of a partially dissembled actuator, however, raised concerns over possible grease degradation due to discoloration of the grease on several places on the surfaces of the gears. Whereas new grease is beige in appearance, the discolored grease consisted of both grey and reddish colors. A number of grease samples were taken from various locations in the actuators and subjected to a variety of physical and chemical analytical tests. Gravimetric tests show that base oil separation from the actuator PFPE grease was not significant after two decades within the sealed actuators. The gray color of grease samples taken from the actuators was due to metallic iron. The red color was due to oxidation of the metallic wear particles from the gears and the bearings comprising the actuators. Both infrared spectroscopy and size exclusion chromatography analyses show no chemical differences between the used and unused grease samples. Little or no degradation of the PFPE grease had occurred in the actuators over the decades of operation.
Language:
English

Title:
Lubricated Bearing Lifetimes of a Multiply Alkylated Cyclopentane and a Linear Perfluoropolyether Fluid in Oscillatory Motion at Elevated Temperatures in Ultrahigh Vacuum
Document ID:
20090022128
Report #:
NASA/CR-2009-215637, E-16946
Sales Agency:
CASI Hardcopy A03 Copyright
Author(s):
Braza, Joseph (Nye Lubricants, Inc.) Jansen, Mark J. (Toledo Univ.) Jones, William R. (Sest, Inc.)
Published:
20090501
Source:
Nye Lubricants, Inc. (New Bedford, MA, United States)
Pages:
12
Contract #:
None
Abstract:
Bearing life tests in vacuum with three space liquid lubricants, two multiply alkylated cyclopentanes (MACs) and a linear perfluoropolyether (PFPE) were performed. Test conditions included: an 89 N axial load (mean Hertzian stress 0.66 GPa), vacuum level below 7x10(exp -4) Pa, and a +/-30deg dither angle. Dither rate was 75 cycles per minute. Higher (110 to 122 C) and lower temperature tests (75 C) were performed. For the higher temperature tests, the PFPE, Fomblin (Ausimont SpA) Z25 outperformed Pennzane (Shell Global Solutions) X-2000 by more than an order of magnitude. Lubricant evaporation played a key role in these high temperature results. At 75 C, the order was reversed with both Pennzane X-1000 and X-2000 outperforming Fomblin Z25 by more than an order of magnitude. Most Pennzane tests were suspended without failure. The primary failure mechanism in these lower temperature tests was lubricant consumption in the tribocontacts.
Language:
English
Notes:
12th European Space Mechanisms and Tribology Symposium England 19 - 21 Sep. 2007

Title:
Redox Interactions between Iron and Carbon in Planetary Mantles: Implications for Degassing and Melting Processes
Document ID:
20090022169
Report #:
JSC-CN-18433
Available Online:
http://hdl.handle.net/2060/20090022169
Sales Agency:
CASI Hardcopy A01 No Copyright
Author(s):
Martin, A. (NASA Johnson Space Center) Righter, K. (NASA Johnson Space Center)
Published:
20090101
Source:
NASA Johnson Space Center (Houston, TX, United States)
Pages:
1
Contract #:
None
Abstract:
Carbon stability in planetary mantles has been studied by numerous authors because it is thought to be the source of C-bearing atmospheres and of C-rich lavas observed at the planetary surface. In the Earth, carbonaceous peridotites and eclogites compositions have been experimentally studied at mantle conditions [1] [2] [3]. [4] showed that the fO2 variations observed in martian meteorites can be explained by polybaric graphite-CO-CO2 equilibria in the Martian mantle. Based on thermodynamic calculations [4] and [5] inferred that the stable form of carbon in the source regions of the Martian basalts should be graphite (and/or diamond), and equilibrium with melts would be a source of CO2 for the martian atmosphere. Considering the high content of iron in the Martian mantle (approx.18.0 wt% FeO; [6]), compared to Earth s mantle (8.0 wt% FeO; [7]) Fe/C redox interactions should be studied in more detail.
Language:
English
Notes:
72nd Annual Meeting of the Meteoritical Society Nancy 13 - 18 Jul. 2009

37-02 LUBRICATION AND LUBRICANTS
Jun 28, 2009 -- Additions to the NASA scientific and technical information knowledge base

37-03 MACHINING
Jun 28, 2009 -- Additions to the NASA scientific and technical information knowledge base

Title:
GPS/MEMS IMU/Microprocessor Board for Navigation
Document ID:
20090022335
Report #:
MSC-23098-1
Sales Agency:
CASI Hardcopy A01 Copyright
Author(s):
Gender, Thomas K. (GNC Corp.) Chow, James (GNC Corp.) Ott, William E. (GNC Corp.)
Journal:
NASA Tech Briefs, June 2009, Page: 16
Published:
20090601
Source:
GNC Corp. (United States)
Pages:
1
Contract #:
None
Abstract:
A miniaturized instrumentation package comprising a (1) Global Positioning System (GPS) receiver, (2) an inertial measurement unit (IMU) consisting largely of surface-micromachined sensors of the microelectromechanical systems (MEMS) type, and (3) a microprocessor, all residing on a single circuit board, is part of the navigation system of a compact robotic spacecraft intended to be released from a larger spacecraft [e.g., the International Space Station (ISS)] for exterior visual inspection of the larger spacecraft. Variants of the package may also be useful in terrestrial collision-detection and -avoidance applications. The navigation solution obtained by integrating the IMU outputs is fed back to a correlator in the GPS receiver to aid in tracking GPS signals. The raw GPS and IMU data are blended in a Kalman filter to obtain an optimal navigation solution, which can be supplemented by range and velocity data obtained by use of (l) a stereoscopic pair of electronic cameras aboard the robotic spacecraft and/or (2) a laser dynamic range imager aboard the ISS. The novelty of the package lies mostly in those aspects of the design of the MEMS IMU that pertain to controlling mechanical resonances and stabilizing scale factors and biases.
Language:
English

Title:
Device Acquires and Retains Rock or Ice Samples
Document ID:
20090022336
Report #:
NPO-46293
Available Online:
http://www.techbriefs.com/component/content/article/5281
Sales Agency:
CASI Hardcopy A01 Copyright
Author(s):
Giersch, Louis R. (California Inst. of Tech.) Backes, Paul G. (California Inst. of Tech.)
Journal:
NASA Tech Briefs, June 2009, Page: 19-20
Published:
20090601
Source:
California Inst. of Tech. (Pasadena, CA, United States)
Pages:
2
Contract #:
None
Abstract:
The Rock Baller is a sample acquisition tool that improves sample retention. The basic elements of the Rock Baller are the tool rotation axis, the hub, the two jaws, and the cutting blades, which are located on each of the jaws. The entire device rotates about the tool rotation axis, which is aligned parallel to the nominal normal direction of the parent rock surface. Both jaws also rotate about the jaw axis, which is perpendicular to the tool rotation axis, at a rate much slower than the rotation about the tool rotation axis. This movement gradually closes the jaws into a nearly continuous hemispherical shell that encloses the sample as it is cut from the parent rock. When required the jaws are opened to release the sample. The hemispherical cutting method eliminates the sample retention problems associated with existing sample acquisition methods that employ conventional cylindrical cutting. The resulting samples are hemispherical, or nearly hemispherical, and as a result the aspect ratio (sample depth relative to sample radius) is essentially fixed. This fixed sample aspect ratio may be considered a drawback of the Rock Baller method, as samples with a higher aspect ratio (more depth, less width) may be considered more scientifically valuable because such samples would allow for a broader inspection of the geological record. This aspect ratio issue can be ameliorated if the Rock Baller is paired with a device similar to the Rock Abrasion Tool (RAT) used on the Mars Exploration Rovers. The RAT could be used to first grind into the surface of the parent rock, after which the Rock Baller would extract a sample from a depth inside the rock that would not have been possible without first using the RAT. Other potential applications for this technology include medical applications such as the removal of tissue samples or tumors from the body, particularly during endoscopic, laparoscopic, or thoracoscopic surgeries.
Language:
English

37-04 FRICTION AND WEAR
Jun 28, 2009 -- Additions to the NASA scientific and technical information knowledge base

Title:
NEXT Long-Duration Test Plume and Wear Characteristics after 16,550 h of Operation and 337 kg of Xenon Processed
Document ID:
20090022127
Report #:
NASA/TM-2009-215613, AIAA Paper 2008-4919, E-16929
Sales Agency:
CASI Hardcopy A03 Copyright
Author(s):
Herman, Daniel A. (ASRC Aerospace Corp.) Soulas, George C. (NASA Glenn Research Center) Patterson, Michael J. (NASA Glenn Research Center)
Published:
20090501
Source:
ASRC Aerospace Corp. (Cleveland, OH, United States)
Pages:
39
Contract #:
GESS-2
Abstract:
The NASA s Evolutionary Xenon Thruster (NEXT) program is developing the next-generation ion propulsion system with significant enhancements beyond the state-of-the-art. The NEXT ion propulsion system provides improved mission capabilities for future NASA science missions to enhance and enable Discovery, New Frontiers, and Flagship-type NASA missions. As part of a comprehensive thruster service life assessment utilizing both testing and analyses, a Long-Duration Test (LDT) was initiated to validate and qualify the NEXT propellant throughput capability to a qualification-level of 450 kg, 1.5 times the mission-derived throughput requirement of 300 kg. This wear test is being conducted with a modified, flight-representative NEXT engineering model ion thruster, designated EM3. As of June 25, 2008, the thruster has accumulated 16,550 h of operation: the first 13,042 h at the thruster full-input-power of 6.9 kW with 3.52 A beam current and 1800 V beam power supply voltage. Operation since 13,042 h, i.e., the most recent 3,508 h, has been at an input power of 4.7 kW with 3.52 A beam current and 1180 V beam power supply voltage. The thruster has processed 337 kg of xenon (Xe) surpassing the NSTAR propellant throughput demonstrated during the extended life testing of the Deep Space 1 flight spare. The NEXT LDT has demonstrated a total impulse of 13.3 106 N s; the highest total impulse ever demonstrated by an ion thruster. Thruster plume diagnostics and erosion measurements are obtained periodically over the entire NEXT throttle table with input power ranging 0.5 to 6.9 kW. Observed thruster component erosion rates are consistent with predictions and the thruster service life assessment. There have not been any observed anomalous erosion and all erosion estimates indicate a thruster throughput capability that exceeds ~750 kg of Xe, an equivalent of 36,500 h of continuous operation at the full-power operating condition. This paper presents the erosion measurements and plume diagnostic results for the NEXT LDT to date with emphasis on the change in thruster operating condition and resulting impact on wear characteristics. Ion optics grid-gap data, both cold and operating, are presented. Performance and wear predictions for the LDT throttle profile are presented.
Language:
English
Notes:
44th Joint Propulsion Conference and Exhibit Connecticut 21 - 23 Jul. 2008

37-05 SEALS
Jun 28, 2009 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

37-06 WELDING
Jun 28, 2009 -- Additions to the NASA scientific and technical information knowledge base

Title:
Tool for Crimping Flexible Circuit Leads
Document ID:
20090022332
Report #:
MSC-23461-1
Available Online:
http://www.techbriefs.com/component/content/article/5285
Sales Agency:
CASI Hardcopy A01 Copyright
Author(s):
Hulse, Aaron (Lockheed Martin Corp.) Diftler, Myron A. (Lockheed Martin Corp.)
Journal:
NASA Tech Briefs, June 2009, Page: 22
Published:
20090601
Source:
Lockheed Martin Corp. (United States)
Pages:
1
Contract #:
None
Abstract:
A hand tool has been developed for crimping leads in flexible tails that are parts of some electronic circuits -- especially some sensor circuits. The tool is used to cut the tails to desired lengths and attach solder tabs to the leads. For tailoring small numbers of circuits for special applications, this hand tool is a less expensive alternative to a commercially available automated crimping tool. The crimping tool consists of an off-the-shelf hand crimping tool plus a specialized crimping insert designed specifically for the intended application.
Language:
English

Title:
Improved Assembly for Gas Shielding During Welding or Brazing
Document ID:
20090022333
Report #:
MFS-32644-1
Available Online:
http://www.techbriefs.com/component/content/article/5286
Sales Agency:
CASI Hardcopy A01 Copyright
Author(s):
Gradl, Paul (NASA Marshall Space Flight Center) Baker, Kevin (NASA Marshall Space Flight Center) Weeks, Jack (Pratt and Whitney Aircraft)
Journal:
NASA Tech Briefs, June 2009, Page: 21
Published:
20090601
Source:
NASA Marshall Space Flight Center (Huntsville, AL, United States)
Pages:
1
Contract #:
None
Abstract:
An improved assembly for inert-gas shielding of a metallic joint is designed to be useable during any of a variety of both laser-based and traditional welding and brazing processes. The basic purpose of this assembly or of a typical prior related assembly is to channel the flow of a chemically inert gas to a joint to prevent environmental contamination of the joint during the welding or brazing process and, if required, to accelerate cooling upon completion of the process.
Language:
English

37-07 METAL FORMING
Jun 28, 2009 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

37-08 PUMPS
Jun 28, 2009 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

37-09 VACUUM TECHNOLOGY
Jun 28, 2009 -- Additions to the NASA scientific and technical information knowledge base

Title:
Particle Ejection and Levitation Technology (PELT)
Document ID:
20090022233
Report #:
None
Sales Agency:
CASI Hardcopy A01 Copyright
Author(s):
(Author(s) Not Available)
Journal:
John F. Kennedy Space Center's Technology Development and Application 2006-2007 Report, Page: 30-31
Published:
20080303
Source:
NASA Kennedy Space Center (Cocoa Beach, FL, United States) ASRC Aerospace Corp. (United States) University of Central Florida (Orlando, FL, United States)
Pages:
2
Contract #:
None
Abstract:
Each of the six Apollo landers touched down at unique sites on the lunar surface. Aside from the Apollo 12 landing site located 180 meters from the Surveyor III lander, plume impingement effects on ground hardware during the landings were not a problem. The planned return to the Moon requires numerous landings at the same site. Since the top few centimeters of lunar soil are loosely packed regolith, plume impingement from the lander will eject the granular material at high velocities. A picture shows what the astronauts viewed from the window of the Apollo 14 lander. There was tremendous dust excavation beneath the vehicle. With high-vacuum conditions on the Moon (10 (exp -14) to 10 (exp -12) torr), motion of all particles is completely ballistic. Estimates derived from damage to Surveyor III caused by the Apollo 12 lander show that the speed of the ejected regolith particles varies from 100 m/s to 2,000 m/s. It is imperative to understand the physics of plume impingement to safely design landing sites for future Moon missions. Aerospace scientists and engineers have examined and analyzed images from Apollo video extensively in an effort to determine the theoretical effects of rocket exhaust impingement. KSC has joined the University of Central Florida (UCF) to develop an instrument that will measure the 3-D vector of dust flow caused by plume impingement during descent of landers. The data collected from the instrument will augment the theoretical studies and analysis of the Apollo videos.
Language:
English

Title:
New Materials for Structural Composites and Protective Coatings
Document ID:
20090022255
Report #:
None
Sales Agency:
CASI Hardcopy A01 Copyright
Author(s):
(Author(s) Not Available)
Journal:
John F. Kennedy Space Center's Technology Development and Application 2006-2007 Report, Page: 24-25
Published:
20080303
Source:
NASA Kennedy Space Center (Cocoa Beach, FL, United States) Georgia Inst. of Tech. (United States) Nanocomp Technologies, Inc. (Concord, NH, United States) ASRC Aerospace Corp. (United States)
Pages:
2
Contract #:
None
Abstract:
The objective of this Phase I project was to create novel conductive materials that are lightweight and strong enough for multiple ground support equipment and Exploration applications. The long-term goal is to combine these materials within specially designed devices to create composites or coatings with diagnostic capabilities, increased strength, and tunable properties such as transparency, electroluminescence, and fire resistance. One such technology application is a smart windows system. In such a system, the transmission of light through a window is controlled by electrical power. In the future, these materials may also be able to absorb sunlight and convert it into electrical energy to produce light, thereby creating a self-sufficient lighting system. This experiment, conducted in collaboration with the Georgia Institute of Technology, demonstrated enhancements in fabricating fiber materials from carbon nanotubes (CNT). These nanotubes were grown as forests in an ultra-high-purity chemical vapor deposition (CVD) furnace and then drawn, using novel processing techniques, into fibers and yarns that would be turned into filaments. This work was submitted to the Journal of Advanced Functional Materials. The CNT fibers were initially tested as filament materials at atmospheric pressure; however, even under high current loads, the filaments produced only random sparking. The CNT fibers were also converted into transparent, hydrophobic, and conductive sheets. Filament testing at low vacuum pressures is in progress, and the technology will be enhanced in 2008. As initial proof of the smart-windows application concept, the use of CNT sheets as composites/ protective coatings was demonstrated in collaboration with Nanocomp Technologies of Concord, New Hampshire.
Language:
English

37-10 NONDESTRUCTIVE TESTING
Jun 28, 2009 -- Additions to the NASA scientific and technical information knowledge base

37-11 TURBOMACHINERY
Jun 28, 2009 -- Additions to the NASA scientific and technical information knowledge base

Title:
FJ44 Turbofan Engine Test at NASA Glenn Research Center's Aero-Acoustic Propulsion Laboratory
Document ID:
20090022124
Report #:
NASA/TM-2009-215594, AIAA Paper 2009-0620, E-16885
Sales Agency:
CASI Hardcopy A03 Copyright
Author(s):
Lauer, Joel T. (Sierra Lobo, Inc.) McAllister, Joseph (Sierra Lobo, Inc.) Loew, Raymond A. (Sierra Lobo, Inc.) Sutliff, Daniel L. (NASA Glenn Research Center) Harley, Thomas C. (Williams International)
Published:
20090501
Source:
Sierra Lobo, Inc. (OH, United States)
Pages:
21
Contract #:
None
Abstract:
A Williams International FJ44-3A 3000-lb thrust class turbofan engine was tested in the NASA Glenn Research Center s Aero-Acoustic Propulsion Laboratory. This report presents the test set-up and documents the test conditions. Farfield directivity, in-duct unsteady pressures, duct mode data, and phased-array data were taken and are reported separately.
Language:
English
Notes:
47th Aerospace Sciences Meeting Florida 5 - 8 Jan. 2009

Title:
Preliminary Axial Flow Turbine Design and Off-Design Performance Analysis Methods for Rotary Wing Aircraft Engines
Document ID:
20090022130
Report #:
NASA/TM-2009-215651/PART1, E-16964-1
Available Online:
http://hdl.handle.net/2060/20090022130
Sales Agency:
CASI Hardcopy A03 No Copyright
Author(s):
Chen, Shu-cheng, S. (NASA Glenn Research Center)
Published:
20090501
Source:
NASA Glenn Research Center (Cleveland, OH, United States)
Pages:
26
Contract #:
None
Abstract:
For the preliminary design and the off-design performance analysis of axial flow turbines, a pair of intermediate level-of-fidelity computer codes, TD2-2 (design; reference 1) and AXOD (off-design; reference 2), are being evaluated for use in turbine design and performance prediction of the modern high performance aircraft engines. TD2-2 employs a streamline curvature method for design, while AXOD approaches the flow analysis with an equal radius-height domain decomposition strategy. Both methods resolve only the flows in the annulus region while modeling the impact introduced by the blade rows. The mathematical formulations and derivations involved in both methods are documented in references 3, 4 for TD2-2) and in reference 5 (for AXOD). The focus of this paper is to discuss the fundamental issues of applicability and compatibility of the two codes as a pair of companion pieces, to perform preliminary design and off-design analysis for modern aircraft engine turbines. Two validation cases for the design and the off-design prediction using TD2-2 and AXOD conducted on two existing high efficiency turbines, developed and tested in the NASA/GE Energy Efficient Engine (GE-E3) Program, the High Pressure Turbine (HPT; two stages, air cooled) and the Low Pressure Turbine (LPT; five stages, un-cooled), are provided in support of the analysis and discussion presented in this paper.
Language:
English
Notes:
65th Annual Forum and Technology Display Grapevine, TX 27-29 May 2009

Title:
Preliminary Axial Flow Turbine Design and Off-Design Performance Analysis Methods for Rotary Wing Aircraft Engines
Document ID:
20090022142
Report #:
NASA/TM-2009-215651/PART2, E-16964-2
Available Online:
http://hdl.handle.net/2060/20090022142
Sales Agency:
CASI Hardcopy A03 No Copyright
Author(s):
Chen, Shu-cheng, S. (NASA Glenn Research Center)
Published:
20090501
Source:
NASA Glenn Research Center (Cleveland, OH, United States)
Pages:
24
Contract #:
None
Abstract:
In this paper, preliminary studies on two turbine engine applications relevant to the tilt-rotor rotary wing aircraft are performed. The first case-study is the application of variable pitch turbine for the turbine performance improvement when operating at a substantially lower shaft speed. The calculations are made on the 75 percent speed and the 50 percent speed of operations. Our results indicate that with the use of the variable pitch turbines, a nominal (3 percent (probable) to 5 percent (hypothetical)) efficiency improvement at the 75 percent speed, and a notable (6 percent (probable) to 12 percent (hypothetical)) efficiency improvement at the 50 percent speed, without sacrificing the turbine power productions, are achievable if the technical difficulty of turning the turbine vanes and blades can be circumvented. The second casestudy is the contingency turbine power generation for the tilt-rotor aircraft in the One Engine Inoperative (OEI) scenario. For this study, calculations are performed on two promising methods: throttle push and steam injection. By isolating the power turbine and limiting its air mass flow rate to be no more than the air flow intake of the take-off operation, while increasing the turbine inlet total temperature (simulating the throttle push) or increasing the air-steam mixture flow rate (simulating the steam injection condition), our results show that an amount of 30 to 45 percent extra power, to the nominal take-off power, can be generated by either of the two methods. The methods of approach, the results, and discussions of these studies are presented in this paper.
Language:
English
Notes:
65th Annual Forum and Technology Display Grapevine, TX 27-29 May 2009

Title:
Design and Testing of Braided Composite Fan Case Materials and Components
Document ID:
20090022155
Report #:
ISABE-2009-1201, E-17015
Sales Agency:
Other Sources Copyright
Author(s):
Roberts, Gary D. (NASA Glenn Research Center) Pereira, J. Michael (NASA Glenn Research Center) Braley, Michael S. (A and P Technology, Inc.) Arnold, William A. (Akron Univ.) Dorer, James D. (Williams International) Watson, William R. (Honeywell Aerospace)
Published:
20090101
Source:
NASA Glenn Research Center (Cleveland, OH, United States)
Pages:
12
Contract #:
None
Abstract:
Triaxial braid composite materials are beginning to be used in fan cases for commercial gas turbine engines. The primary benefit for the use of composite materials is reduced weight and the associated reduction in fuel consumption. However, there are also cost benefits in some applications. This paper presents a description of the braided composite materials and discusses aspects of the braiding process that can be utilized for efficient fabrication of composite cases. The paper also presents an approach that was developed for evaluating the braided composite materials and composite fan cases in a ballistic impact laboratory. Impact of composite panels with a soft projectile is used for materials evaluation. Impact of composite fan cases with fan blades or blade-like projectiles is used to evaluate containment capability. A post-impact structural load test is used to evaluate the capability of the impacted fan case to survive dynamic loads during engine spool down. Validation of these new test methods is demonstrated by comparison with results of engine blade-out tests.
Language:
English

38-01 QUALITY CONTROL AND RELIABILITY
Jun 28, 2009 -- Additions to the NASA scientific and technical information knowledge base

Title:
Probabilistic Methods for Structural Reliability and Risk
Document ID:
20090022153
Report #:
Paper No. 2413, E-16477
Available Online:
http://hdl.handle.net/2060/20090022153
Sales Agency:
CASI Hardcopy A02 No Copyright
Author(s):
Chamis, Christos C. (NASA Glenn Research Center)
Published:
20080602
Source:
NASA Glenn Research Center (Cleveland, OH, United States)
Pages:
10
Contract #:
None
Abstract:
A probabilistic method is used to evaluate the structural reliability and risk of select metallic and composite structures. The method is a multiscale, multifunctional and it is based on the most elemental level. A multi-factor interaction model is used to describe the material properties which are subsequently evaluated probabilistically. The metallic structure is a two rotor aircraft engine, while the composite structures consist of laminated plies (multiscale) and the properties of each ply are the multifunctional representation. The structural component is modeled by finite element. The solution method for structural responses is obtained by an updated simulation scheme. The results show that the risk for the two rotor engine is about 0.0001 and the composite built-up structure is also 0.0001.
Language:
English
Notes:
ECCM13 European Conference on Composite Materials Stockholm 2-5 Jun. 2008

39-01 SHELLS
Jun 28, 2009 -- Additions to the NASA scientific and technical information knowledge base

Title:
Controlled-Release Microcapsules for Smart Coatings for Corrosion Applications
Document ID:
20090022207
Report #:
None
Sales Agency:
CASI Hardcopy A01 Copyright
Author(s):
(Author(s) Not Available)
Journal:
John F. Kennedy Space Center's Technology Development and Application 2006-2007 Report, Page: 10-11
Published:
20080303
Source:
NASA Kennedy Space Center (Cocoa Beach, FL, United States)
Pages:
2
Contract #:
None
Abstract:
Corrosion is a serious problem that has enormous costs and serious safety implications. Localized corrosion, such as pitting, is very dangerous and can cause catastrophic failures. The NASA Corrosion Technology Laboratory at Kennedy Space Center is developing a smart coating based on pH-sensitive microcapsules for corrosion applications. These versatile microcapsules are designed to be incorporated into a smart coating and deliver their core content when corrosion starts. Corrosion indication was the first function incorporated into the microcapsules. Current efforts are focused on incorporating the corrosion inhibition function through the encapsulation of corrosion inhibitors into water core and oil core microcapsules. Scanning electron microscopy (SEM) images of encapsulated corrosion inhibitors are shown.
Language:
English

39-02 STRESSES AND LOADS
Jun 28, 2009 -- Additions to the NASA scientific and technical information knowledge base

Title:
Capability Description for NASA's F/A-18 TN 853 as a Testbed for the Integrated Resilient Aircraft Control Project
Document ID:
20090022324
Report #:
DFRC-IRAC-CAP-002, DFRC-972
Available Online:
http://hdl.handle.net/2060/20090022324
Sales Agency:
CASI Hardcopy A03 No Copyright
Author(s):
Hanson, Curt (NASA Dryden Flight Research Center)
Published:
20090128
Source:
NASA Dryden Flight Research Center (Edwards, CA, United States)
Pages:
17
Contract #:
None
Abstract:
The NASA F/A-18 tail number (TN) 853 full-scale Integrated Resilient Aircraft Control (IRAC) testbed has been designed with a full array of capabilities in support of the Aviation Safety Program. Highlights of the system's capabilities include: 1) a quad-redundant research flight control system for safely interfacing controls experiments to the aircraft's control surfaces; 2) a dual-redundant airborne research test system for hosting multi-disciplinary state-of-the-art adaptive control experiments; 3) a robust reversionary configuration for recovery from unusual attitudes and configurations; 4) significant research instrumentation, particularly in the area of static loads; 5) extensive facilities for experiment simulation, data logging, real-time monitoring and post-flight analysis capabilities; and 6) significant growth capability in terms of interfaces and processing power.
Language:
English

39-03 STRUCTURE VIBRATION AND DAMPING
Jun 28, 2009 -- Additions to the NASA scientific and technical information knowledge base

Title:
Concept of Operations Visualization in Support of Ares I Production
Document ID:
20090022312
Report #:
MSFC-2103-2
Sales Agency:
CASI Hardcopy A03 Copyright
Author(s):
Chilton, James H. (Boeing Aerospace Co.) Smith, Daid Alan (Boeing Aerospace Co.)
Published:
20081003
Source:
Boeing Aerospace Co. (Huntsville, AL, United States)
Pages:
11
Contract #:
NNM07AB03C
Abstract:
Boeing was selected in 2007 to manufacture Ares I Upper Stage and Instrument Unit according to NASA's design which would require the use of the latest manufacturing and integration processes to meet NASA budget and schedule targets. Past production experience has established that the majority of the life cycle cost is established during the initial design process. Concept of Operations (CONOPs) visualizations/simulations help to reduce life cycle cost during the early design stage. Production and operation visualizations can reduce tooling, factory capacity, safety, and build process risks while spreading program support across government, academic, media and public constituencies. The NASA/Boeing production visualization (DELMIA; Digital Enterprise Lean Manufacturing Interactive Application) promotes timely, concurrent and collaborative producibility analysis (Boeing)while supporting Upper Stage Design Cycles (NASA). The DELMIA CONOPs visualization reduced overall Upper Stage production flow time at the manufacturing facility by over 100 man-days to 312.5 man-days and helped to identify technical access issues. The NASA/Boeing Interactive Concept of Operations (ICON) provides interactive access to Ares using real mission parameters, allows users to configure the mission which encourages ownership and identifies areas for improvement, allows mission operations or spacecraft detail to be added as needed, and provides an effective, low coast advocacy, outreach and education tool.
Language:
English
Notes:
59th International Astronautical Conference/International Astronautical Federation Glasgow, Scotland 29 Sep. - 4 Oct. 2008

Title:
Developing Soil Models for Dynamic Impact Simulations
Document ID:
20090022374
Report #:
LF99-7733
Available Online:
http://hdl.handle.net/2060/20090022374
Sales Agency:
CASI Hardcopy A03 No Copyright
Author(s):
Fasanella, Edwin L. (NASA Langley Research Center) Lyle, Karen H. (NASA Langley Research Center) Jackson, Karen E. (NASA Langley Research Center)
Published:
20090527
Source:
NASA Langley Research Center (Hampton, VA, United States)
Pages:
21
Contract #:
None
Abstract:
This paper describes fundamental soils characterization work performed at NASA Langley Research Center in support of the Subsonic Rotary Wing (SRW) Aeronautics Program and the Orion Landing System (LS) Advanced Development Program (ADP). LS-DYNA(Registered TradeMark)1 soil impact model development and test-analysis correlation results are presented for: (1) a 38-ft/s vertical drop test of a composite fuselage section, outfitted with four blocks of deployable energy absorbers (DEA), onto sand, and (2) a series of impact tests of a 1/2-scale geometric boilerplate Orion capsule onto soil. In addition, the paper will discuss LS-DYNA contact analysis at the soil/structure interface, methods used to estimate frictional forces, and the sensitivity of the model to density, moisture, and compaction.
Language:
English
Notes:
AHS International 65th Forum and Technology Display Grapevine, TX 27-29 May 2009

39-04 IMPACT PHENOMENA
Jun 28, 2009 -- Additions to the NASA scientific and technical information knowledge base

Title:
Evaluation of Material Models within LS-DYNA(Registered TradeMark) for a Kevlar/Epoxy Composite Honeycomb
Document ID:
20090022372
Report #:
LF99-7613
Sales Agency:
CASI Hardcopy A03 Copyright
Author(s):
Polanco, Michael A. (ATK Space) Kellas, Sotiris (NASA Langley Research Center) Jackson, Karen (NASA Langley Research Center)
Published:
20090527
Source:
NASA Langley Research Center (Hampton, VA, United States)
Pages:
16
Contract #:
None
Abstract:
The performance of material models to simulate a novel composite honeycomb Deployable Energy Absorber (DEA) was evaluated using the nonlinear explicit dynamic finite element code LS-DYNA(Registered TradeMark). Prototypes of the DEA concept were manufactured using a Kevlar/Epoxy composite material in which the fibers are oriented at +/-45 degrees with respect to the loading axis. The development of the DEA has included laboratory tests at subcomponent and component levels such as three-point bend testing of single hexagonal cells, dynamic crush testing of single multi-cell components, and impact testing of a full-scale fuselage section fitted with a system of DEA components onto multi-terrain environments. Due to the thin nature of the cell walls, the DEA was modeled using shell elements. In an attempt to simulate the dynamic response of the DEA, it was first represented using *MAT_LAMINATED_COMPOSITE_FABRIC, or *MAT_58, in LS-DYNA. Values for each parameter within the material model were generated such that an in-plane isotropic configuration for the DEA material was assumed. Analytical predictions showed that the load-deflection behavior of a single-cell during three-point bending was within the range of test data, but predicted the DEA crush response to be very stiff. In addition, a *MAT_PIECEWISE_LINEAR_PLASTICITY, or *MAT_24, material model in LS-DYNA was developed, which represented the Kevlar/Epoxy composite as an isotropic elastic-plastic material with input from +/-45 degrees tensile coupon data. The predicted crush response matched that of the test and localized folding patterns of the DEA were captured under compression, but the model failed to predict the single-cell three-point bending response.
Language:
English
Notes:
AHS International 65th Forum and Technology Display Grapevine, TX 27-29 May 2009

39-05 STRUCTURAL FATIGUE
Jun 28, 2009 -- Additions to the NASA scientific and technical information knowledge base

39-06 SANDWICH CONSTRUCTION
Jun 28, 2009 -- Additions to the NASA scientific and technical information knowledge base

Title:
Ultra-Lightweight Self-Deployable Nanocomposite Structure for Habitat Applications
Document ID:
20090022329
Report #:
MSC-24290-1
Available Online:
http://www.techbriefs.com/component/content/article/5296
Sales Agency:
CASI Hardcopy A01 Copyright
Author(s):
Tan, Seng C. (Wright Materials Research Co.)
Journal:
NASA Tech Briefs, June 2009, Page: 31
Published:
20090601
Source:
Wright Materials Research Co. (Beavercreek, OH, United States)
Pages:
1
Contract #:
None
Abstract:
A document discusses self-deployable, rigidized structures that are ultra-lightweight and have gas barrier properties, space durability, and high impact resistance. Developed here are microcellular-foamed sandwich structures made from nanocomposite shape memory polymers (SMPs) with Cold-Hibernated Elastic Memory (CHEM) deployed technique for space structural components including space habitats. This type of foam sandwich also does not suffer from the toxicity problems of conventional foams, and has higher mechanical properties than those processed with conventional techniques. This design can be compacted into a very small volume for launch. Once deployed, the microcellular structure can use the heat from the Sun to recover 98 to 100 percent of its shape.
Language:
English

39-07 STRESS ANALYSIS
Jun 28, 2009 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

39-08 STRUCTURAL TESTS AND RELIABILITY
Jun 28, 2009 -- Additions to the NASA scientific and technical information knowledge base

Title:
Automated Method for Estimating Nutation Time Constant Model Parameters for Spacecraft Spinning on Axis
Document ID:
20090022204
Report #:
None
Sales Agency:
CASI Hardcopy A01 Copyright
Author(s):
(Author(s) Not Available)
Journal:
John F. Kennedy Space Center's Technology Development and Application 2006-2007 Report, Page: 82-83
Published:
20080303
Source:
NASA Kennedy Space Center (Cocoa Beach, FL, United States) Southwest Research Inst. (United States)
Pages:
2
Contract #:
None
Abstract:
Calculating an accurate nutation time constant (NTC), or nutation rate of growth, for a spinning upper stage is important for ensuring mission success. Spacecraft nutation, or wobble, is caused by energy dissipation anywhere in the system. Propellant slosh in the spacecraft fuel tanks is the primary source for this dissipation and, if it is in a state of resonance, the NTC can become short enough to violate mission constraints. The Spinning Slosh Test Rig (SSTR) is a forced-motion spin table where fluid dynamic effects in full-scale fuel tanks can be tested in order to obtain key parameters used to calculate the NTC. We accomplish this by independently varying nutation frequency versus the spin rate and measuring force and torque responses on the tank. This method was used to predict parameters for the Genesis, Contour, and Stereo missions, whose tanks were mounted outboard from the spin axis. These parameters are incorporated into a mathematical model that uses mechanical analogs, such as pendulums and rotors, to simulate the force and torque resonances associated with fluid slosh.
Language:
English

Title:
Parameter Estimation of Lateral Spacecraft Fuel Slosh
Document ID:
20090022238
Report #:
None
Sales Agency:
CASI Hardcopy A01 Copyright
Author(s):
Sudermann, James E. (NASA Kennedy Space Center) Schlee, Keith L. (Analex Corp.)
Journal:
John F. Kennedy Space Center's Technology Development and Application 2006-2007 Report, Page: 84-85
Published:
20080303
Source:
NASA Kennedy Space Center (Cocoa Beach, FL, United States)
Pages:
2
Contract #:
None
Abstract:
Predicting the effect of fuel slosh on the attitude control system of a spacecraft or launch vehicle is a very important and challenging task. Whether the spacecraft is spinning or moving laterally, the dynamic effect of the fuel slosh helps determine whether the spacecraft will remain on its intended trajectory. Three categories of slosh can be caused by launch vehicle or spacecraft maneuvers when the fuel is in the presence of an acceleration field. These are bulk-fluid motion, subsurface wave motion (currents), and free-surface slosh. Each of these slosh types has a periodic component defined by either a spinning or a lateral motion. For spinning spacecraft, all three types of slosh can greatly affect stability. Bulk-fluid motion and free-surface slosh can affect the lateral-slosh characteristics. For either condition, an unpredicted coupled resonance between the spacecraft and its onboard fuel could threaten a mission. This ongoing research effort seeks to improve the accuracy and efficiency of modeling techniques used to predict these types of fluid motions for lateral motion. Particular efforts focus on analyzing the effects of viscoelastic diaphragms on slosh dynamics.
Language:
English