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Next Generation Spacecraft, Crew Exploration Vehicle Next Generation Spacecraft, Crew Exploration Vehicle A Special Bibliography From the NASA Scientific and Technical Information Program Includes research on reusable launch vehicles, aerospace planes, shuttle replacement, crew/cargo transfer vehicle, related X-craft, orbital space plane, and next generation launch technology. January 2004 Next Generation Spacecraft, Crew Exploration Vehicle A Special Bibliography from the NASA Scientific and Technical Information Program JANUARY 2004 20040004384 Nebraska Univ., Lincoln, NE, USA Design of Experiments for the Thermal Characterization of Metallic Foam Crittenden, Paul E.; Cole, Kevin D.; Optimal Experiment Design for Thermal Characterization of Functionally Graded Materials; August 18, 2003; In English Contract(s)/Grant(s): NAG1-01087; No Copyright; Avail: CASI; A03, Hardcopy Metallic foams are being investigated for possible use in the thermal protection systems of reusable launch vehicles. As a result, the performance of these materials needs to be characterized over a wide range of temperatures and pressures. In this paper a radiation/conduction model is presented for heat transfer in metallic foams. Candidates for the optimal transient experiment to determine the intrinsic properties of the model are found by two methods. First, an optimality criterion is used to find an experiment to find all of the parameters using one heating event. Second, a pair of heating events is used to determine the parameters in which one heating event is optimal for finding the parameters related to conduction, while the other heating event is optimal for finding the parameters associated with radiation. Simulated data containing random noise was analyzed to determine the parameters using both methods. In all cases the parameter estimates could be improved by analyzing a larger data record than suggested by the optimality criterion. Author Metal Foams; Heat Transfer 20040003713 NASA Langley Research Center, Hampton, VA, USA Development of Structural Health Management Technology for Aerospace Vehicles Prosser, W. H.; [2003]; In English; JANNAF 39th Combustion/27th Airbreathing Propulsion/21st Propulsion Systems Harzards/3rd Modeling and Simulation Joint Subcommittee Meeting, 1-5 Sep. 2003, Colorado Springs, CO, USA; Original contains color illustrations; No Copyright; Avail: CASI; A02, Hardcopy As part of the overall goal of developing Integrated Vehicle Health Management (IVHM) systems for aerospace vehicles, NASA has focused considerable resources on the development of technologies for Structural Health Management (SHM). The motivations for these efforts are to increase the safety and reliability of aerospace structural systems, while at the same time decreasing operating and maintenance costs. Research and development of SHM technologies has been supported under a variety of programs for both aircraft and spacecraft including the Space Launch Initiative, X-33, Next Generation Launch Technology, and Aviation Safety Program. The major focus of much of the research to date has been on the development and testing of sensor technologies. A wide range of sensor technologies are under consideration including fiber-optic sensors, active and passive acoustic sensors, electromagnetic sensors, wireless sensing systems, MEMS, and nanosensors. Because of their numerous advantages for aerospace applications, most notably being extremely light weight, fiber-optic sensors are one of the leading candidates and have received considerable attention. Author Aerospace Vehicles; Systems Health Monitoring; Systems Engineering; Technology Utilization; Remote Sensors 20040001677 Aerospace Corp., USA Liquid Engine Test Facilities Assessment Adams, Michael J.; Emdee, Jeffery L.; George, Daweel J.; Peinemann, Manfred; May 03, 2002; In English Contract(s)/Grant(s): F04701-00-C-0009 Report No.(s): NASA/SE-2002-05-00041-SSC; No Copyright; Avail: CASI; A04, Hardcopy The John C. Stennis Space Center (SSC) requested The Aerospace Corporation to examine the current testing capability of all existing large liquid engine test facilities located in the USA. That information along with projected liquid rocket engine development was used to examine future liquid rocket engine testing facilities needs in the coming decade. Current domestic liquid engine test facilities capabilities, when examined against engine concepts for the coming decade, indicate there are 1 ample facilities offering altitude simulation during test. In addition, it was observed that many contractor facilities have limited ambient test capability of larger thrust engines under current consideration. Finally, it was concluded that diminished contractor participation engine development testing will drive this activity to the government sector. Only three facilities are seen as key contributors to engine testing in the coming decade, namely John C. Stennis Space Center (SSC), Marshall Space Flight Center (MSFC), and Air Force Research Laboratory (AFRL). Past rocket engine test experience was evaluated as a possible resource for projecting future engine test needs. A database comprised of various engine models and the level of testing performed to flight qualify those systems for their first flight was constructed. For comparison purposes in this study, development and qualification efforts were totaled and treated as one test program. Based on experience with past Air Force programs, the time on the test stand accounts for typically 50% or more of the total program time. Historical data show that the time to design and develop new engines has increased over the last 40 years, most likely due to scarcer resources in today’s funding environment. Derived from text Engine Tests; Liquid Propellant Rocket Engines; Test Facilities; Aerospace Systems 20040001153 NASA Langley Research Center, Hampton, VA, USA Cryopumping in Cryogenic Insulations for a Reusable Launch Vehicle Johnson, Theodore F.; Weiser, Erik S.; Grimsley, Brian W.; Jensen, Brian J.; [2003]; In English; No Copyright; Avail: CASI; A03, Hardcopy Testing at cryogenic temperatures was performed to verify the material characteristics and manufacturing processes of reusable propellant tank cryogenic insulations for a Reusable Launch Vehicle (RLV). The unique test apparatus and test methods developed for the investigation of cryopumping in cryogenic insulations are described. Panel level test specimens with various types of cryogenic insulations were subjected to a specific thermal profile where the temperature varied from -262 C to 21 C. Cryopumping occurred if the interior temperature of the specimen exhibited abnormal temperature fluctuations, such as a sudden decrease in temperature during the heating phase. Author Cryogenic Temperature; Cryopumping; Insulation; Reusable Launch Vehicles; Manufacturing 20040000905 NASA Stennis Space Center, Bay Saint Louis, MS, USA Improved Testing Capability and Adaptability Through the Use of Wireless Sensors Solano, Wanda M.; April 14, 2003; In English; 2003 Propulsion Measurement Sensor Development Workshop, 13-15 May 2003, Huntsville, AL, USA; Original contains color illustrations Report No.(s): SE-2003-04-00020-SSC; No Copyright; Avail: CASI; A02, Hardcopy From the first Saturn V rocket booster (S-II-T) testing in 1966 and the routine Space Shuttle Main Engine (SSME) testing beginning in 1975, to more recent test programs such as the X-33 Aerospike Engine, the Integrated Powerhead Development (IPD) program, and the Hybrid Sounding Rocket (HYSR), Stennis Space Center (SSC) continues to be a premier location for conducting large-scale testing. Central to each test program is the capability for sensor systems to deliver reliable measurements and high quality data, while also providing a means to monitor the test stand area to the highest degree of safety and sustainability. Sensor wiring is routed along piping and through cable trenches, making its way from the engine test area, through the test stand area and to the signal conditioning building before final transfer to the test control center. When sensor requirements lie outside the reach of the routine sensor cable routing, the use of wireless sensor networks becomes particularly attractive due to their versatility and ease of installation. As part of an on-going effort to enhance the testing capabilities of Stennis Space Center, the Test Technology and Development group has found numerous applications for its sensor-adaptable wireless sensor suite. While not intended for critical engine measurements or control loops, in-house hardware and software development of the sensor suite can provide improved testing capability for a range of applications including the safety monitoring of propellant storage barrels and as an experimental test-bed for embedded health monitoring paradigms. Author Engine Tests; Engine Monitoring Instruments; Instrument Packages 20040000874 Lockheed Martin Space Operations, Bay Saint Louis, MS, USA NASA Stennis Space Center V and V Capabilities Overview Ryan, Robert; October 22, 2001; In English; MAPPS-ASPRS Conference: Measuring the Earth-Digital Elevation Technologies and Applications, 31 Oct. - 2 Nov. 2001, Saint Petersburg, FL, USA Contract(s)/Grant(s): NAS13-650 Report No.(s): SE-2001-10-00062-SSC; No Copyright; Avail: CASI; A03, Hardcopy 2 The objective are provide independent field measurement ground capability for satellite and aircraft mounted in-flight sensor validation. NASA Stennis is considering expanding its Verification and Validation (V&V) range to support LIDAR and digital camera characterization.
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