S.P. Schneider, Purdue University. Results of search on NASA RECON for papers on shuttle and tile and impact, keyword. 7 Feb 2003 All papers are publicly available. 20000005892 A [Copyright] Unclassified (Unrestricted - Publicly Available) TI: Orbiter thermal protection system less toxic rewaterproofing agent for faster turnaround capability AU: Cunningham, Suzanne R. (NASA Kennedy Space Center, Cocoa Beach, FL United States) RN: IAF Paper 99-V406 DT: Conference Paper LA: English FS: NASA Kennedy Space Center (Cocoa Beach, FL United States) [NASA] SO: IAF, International Astronautical Congress, 50th, Amsterdam, Netherlands , Oct. 4-8, 1999 PB: International Organization PD: Oct 01, 1999 AV: AIAA Dispatch AVNT: Source Prohibits SC: 16 (Space Transportation and Safety) CTMJ: THERMAL PROTECTION/TOXICITY/SPACE SHUTTLE ORBITERS CTMN: SOLVENTS ID: FTIR SPECTROMETERS AB: The Space Shuttle Orbiter Thermal Protection System (TPS) is one of the Shuttle systems with a high maintenance cycle. The TPS must be rewaterproofed in situ prior to each new launch to avoid serious safety and weight penalties associated with water absorbed into the TPS while on the launch pad. Rewaterproofing is the one TPS maintenance operation that can interfere with the turnaround of all other vehicle systems due to the toxicity of the current agent used, known as dimethylethoxysilane (DMES). DMES performs exceptionally well in preventing water absorption in ceramic, silica-based materials such as the TPS. However, due to toxic vapors produced on application, DMES imposes severe restrictions on personnel access to the Orbiter Processing Facility (OPF), which causes a detrimental impact on other Orbiter processing works in the facility. To reduce costs, minimize schedule impact, and improve safety, NASA sought to reduce the toxicity of this rewaterproofing agent while maintaining acceptable performance. Candidate agents were tested on Orbiter TPS tile for rewaterproofing capability. Agents were also tested for compatibility with other TPS materials. No tested waterproofing agent outperformed DMES. However, five carrier solvents (n-pentane; 2,3-dimethylbutane; 2,3-dimethyl pentane; acetone; perfluorocyclobutane) were downselected to dilute the DMES and reduce its effective toxicity. All solvents performed successfully and were compatible with TPS materials. N-pentane was selected as the solvent of choice due to its low cost, low toxicity, and excellent performance repeatability with DMES. In tiles injected with 20/80 DMES/n-pentane, the acceptable outgassing limit was achieved 44 percent faster than with 100 percent DMES. 19980205365 A [Copyright] Unclassified (Unrestricted - Publicly Available) TI: Penetration equations for thermal protection materials AU: Christiansen, Eric L. (NASA Johnson Space Center, Houston, TX United States)/Friesen, Larry DT: Journal Article LA: English SO: International Journal of Impact Engineering vol: Volume 20 iss: no. 1-5 pt 1 1997 p. 153-164 ISSN: ISSN 0734-743X PB: Oxford, United Kingdom:Elsevier Science Ltd. PD: Jan 01, 1997 MN: 1996 Symposium on Hypervelocity Impact. Part 1 (of 2), Freiburg, Oct. 8-10, 1996 AV: Issuing Activity (12p) AVNT: Source Prohibits SC: 12 (Astronautics (General)) CTMJ: HYPERVELOCITY IMPACT/THERMAL PROTECTION/IMPACT RESISTANCE/MATHEMATICAL MODELS/THERMAL INSULATION/SPACE SHUTTLES/SPACECRAFT CTMN: CERAMICS/CARBON-CARBON COMPOSITES/DEFECTS/SPACE DEBRIS/VELOCITY/DENSITY (MASS/VOLUME)/ALUMINUM AB: NASA has developed a number of penetration equations for a broad range of thermal protection system (TPS) materials used on the Space Shuttle Orbiter and other spacecraft including low-density ceramic tiles, reinforced carbon-carbon, flexible ceramic insulation and multi-layer insulation (MLI). The penetration equations describe the penetration depth or damage extent to be expected from hypervelocity particles as a function of projectile velocity, size, density, and various target parameters including thickness and configuration. 'Ballistic limit' equations have also been developed to define projectile conditions causing threshold perforation of more complex targets that combine an outer TPS material with an underlying structural element such as a ceramic tile bonded to an aluminum plate. These equations were developed from hypervelocity impact data collected at the NASA Johnson Space Center (JSC) Hypervelocity Impact Test Facility (HIT-F). 19910025459 A (91A10082) IM [Copyright] Unclassified (Unrestricted - Publicly Available) TI: Hypervelocity impact testing of Shuttle Orbiter thermal protection system tiles AU: Christiansen, Eric L. (NASA Johnson Space Center, Houston, TX, United States)/Ortega, Javier (Lockheed Engineering and Sciences Co., Houston , TX, United States) RN: AIAA PAPER 90-3666 DT: Preprint LA: English OS: NASA Lyndon B. Johnson Space Center (Houston, TX, United States) FS: NASA (United States) [NASA] SO: AIAA, Space Programs and Technologies Conference, Huntsville, AL, Sept. 25-27, 1990. 14 p. PB: United States PD: Sep 01, 1990 AV: Issuing Activity (14p) SC: 18 (SPACECRAFT DESIGN, TESTING AND PERFORMANCE) CTMJ: HYPERVELOCITY IMPACT/IMPACT TESTS/SPACE SHUTTLE ORBITERS/THERMAL PROTECTION/TILES CTMN: HYPERVELOCITY PROJECTILES/PROTECTIVE COATINGS/TEST FACILITIES AB: Results are presented from a series of 22 hypervelocity impact tests carried out on the thermal protection system (TPS) for the Shuttle Orbiter. Both coated and uncoated low-density (0.14 g/cu cm) LI-900 and high-density (0.35 g/cu cm) LI-2200 tiles were tested. The results are used to develop the penetration and damage correlations which can be used in meteoroid and debris hazard analyses for spacecraft with a ceramic tile TPS. It is shown that tile coatings act as a 'bumper' to fragment the impacting projectile, with thicker coating providing increased protection. 19880009180 N (88N18564) IM Unclassified (Unrestricted - Publicly Available) TI: Analysis of shear-layer probe data for holes in hypersonic configurations AU: Bertin, J. J. (Sandia National Labs., Albuquerque, NM, United States) /Tedeschi, W. J. (Sandia National Labs., Albuquerque, NM, United States)/Kelly, D. P. (Sandia National Labs., Albuquerque, NM, United States)/Bustamante, A. C. (Sandia National Labs., Albuquerque, NM, United States)/Reece, E. W. (Sandia National Labs., Albuquerque, NM, United States) RN: DE88-003992/SAND-87-1226C/CONF-880139-2/AIAA PAPER 88-0373 CN: DE-AC04-76DP-00789 DT: Conference Paper LA: English OS: Sandia National Labs. (Albuquerque, NM, United States) FS: Department of Defense (United States) [Other US Government] PB: United States PD: Jan 01, 1988 GRN: Prepared in cooperation with Texas Univ., Austin AV: Hardcopy - A03 CASI A03 (42p)/Microfiche - A01 CASI A01 (42p) SC: 02 (AERODYNAMICS) CTMJ: AERODYNAMIC CONFIGURATIONS/BOUNDARY LAYERS/HYPERSONIC FLOW/NUMERICAL ANALYSIS/SHEAR FLOW/SPACE SHUTTLES/THERMODYNAMICS CTMN: AERODYNAMIC HEAT TRANSFER/HYPERSONIC VEHICLES/REENTRY VEHICLES/TURBULENT FLOW AB: Vehicles entering the Earth's atmosphere are subjected to a severe aerothermodynamic environment. If there is an opening in the surface that allows flow into the interior cavities of the reentry vehicle (RV), the complex viscous/inviscid interactions that are produced can cause increases in the aerodynamic loads and locally severe increases in heating. If a tile or a portion of a surface panel of the Space Shuttle Orbiter were to be inadvertently lost, the increased severity of the aerothermodynamic environment could jeopardize the mission of the Orbiter. In other instances, a foreign object could impact the surface of the reentry vehicle with such force as to damage the surface of the RV. Other surface openings (or ports) may be designed into reentry vehicles and proper account must be taken of the internal heating within these cavities. The effect of surface openings on the aerothermodynamic environment has been the subject of numerous investigations. A series of test programs have been conducted in Tunnel B of the Arnold Engineering Development Center (AEDC) in which wedges were exposed to the Mach 8 stream. The model design was such that one of several external surface ports, or ESPs, could be located in the wedge surface, exposing an internal cavity to the external flow. This report describes the test methods, code development and numerical analysis, and provides the experimental data obtained. 19820048361 A (82A31896) IM Unclassified (Unrestricted - Publicly Available) TI: Assessment of alternate thermal protection systems for the Space Shuttle Orbiter AU: Kelly, H. N. (NASA Langley Research Center, Hampton, VA, United States) /Webb, G. L. (NASA Langley Research Center, Loads and Aeroelasticity Div., Hampton, VA, United States) RN: AIAA PAPER 82-0899 DT: Conference Paper LA: English OS: NASA Langley Research Center (Hampton, VA, United States) FS: NASA (United States) [NASA] SO: American Institute of Aeronautics and Astronautics and American Society of Mechanical Engineers, Joint Thermophysics, Fluids, Plasma and Heat Transfer Conference, 3rd, St. Louis, MO, June 7-11, 1982, AIAA 12 p. PB: United States PD: Jun 01, 1982 MN: Joint Thermophysics, Fluids, Plasma and Heat Transfer Conference, 3rd. St. Louis, MO, June 7-11, 1982 MS: American Institute of Aeronautics and Astronautics and American Society of Mechanical Engineers AV: Issuing Activity (12p) SC: 16 (SPACE TRANSPORTATION) CTMJ: REUSABLE HEAT SHIELDING/SPACE SHUTTLE ORBITERS/SPACECRAFT SHIELDING/TECHNOLOGY ASSESSMENT/THERMAL PROTECTION CTMN: CARBON-CARBON COMPOSITES/CERAMICS/LIFE CYCLE COSTS/TILES AB: Technical aspects of the alternate thermal protection system (TPS) study for the Shuttle Orbiter are reviewed, and a status report on alternate TPS technology developments is presented. Mission impact, life cycle costs and risks, and selected candidate concepts are identified. The best system would consist of mechanically attached metallic and carbon-carbon TPS concepts employing a titanium multiwall prepackaged concept at temperatures below 1000 F, a superalloy honeycomb prepackaged concept at temperatures between 1000-1800 F, and an advanced carbon-carbon multipost standoff concept above 1800 F. Alternative concepts offer significant improvements in durability and are mass competitive with current ceramic tile reusable surface insulation. 19820030374 A (82A13909) IM Unclassified (Unrestricted - Publicly Available) TI: OEX - Use of the Shuttle Orbiter as a research vehicle AU: Jones, J. J. (NASA Langley Research Center, Space Systems Div., Hampton , VA, United States) RN: AIAA PAPER 81-2512 DT: Conference Paper LA: English OS: NASA Langley Research Center (Hampton, VA, United States) FS: NASA (United States) [NASA] SO: AIAA, SETP, SFTE, SAE, ITEA, and IEEE, Flight Testing Conference, 1st, Las Vegas, NV, Nov. 11-13, 1981, AIAA 8 p. PB: United States PD: Nov 01, 1981 MN: Flight Testing Conference, 1st. Las Vegas, NV, Nov. 11-13, 1981 AV: Issuing Activity (8p) SC: 16 (SPACE TRANSPORTATION) CTMJ: AERODYNAMIC CHARACTERISTICS/AEROTHERMODYNAMICS/HEAT SHIELDING/RESEARCH VEHICLES/SPACE SHUTTLE ORBITERS/SPACE SHUTTLE PAYLOADS CTMN: HEAT TRANSFER/INFRARED IMAGERY/MASS SPECTROMETERS/REENTRY SHIELDING/SPACECRAFT DESIGN AB: The Orbiter Experiments Program to provide research instrumentation on the Shuttle Orbiter is discussed. Flight aerodynamic problems such as ground-based data limitations, rarefied flow effects, body flap and control surface effectiveness, and windward surface heat transfer are reviewed. Experiments currently under development are described, including experiments on tile gaps and wall catalytic effects which provide the opportunity to obtain data not available in ground facilities and apply the results to improvements in the Orbiter's thermal protection system. Such experiments combined with other instrumentation on the Orbiter should provide benchmark flight data which can make a significant impact on the design of future space transportation systems. 19820019358 N (82N27234) IM Unclassified (Unrestricted - Publicly Available) TI: Assessment of alternate thermal protection systems for the Space Shuttle Orbiter AU: Kelly, H. N. (NASA Langley Research Center, Hampton, VA, United States) /Webb, G. L. (NASA Langley Research Center, Hampton, VA, United States) RN: NASA-TM-84491/NAS 1.15:84491 PJN: RTOP 506-53-33-04 DT: Conference Paper LA: English OS: NASA Langley Research Center (Hampton, VA, United States) FS: NASA (United States) [NASA] PB: United States PD: May 01, 1982 AV: Hardcopy - A03 CASI A03 (13p)/Microfiche - A01 CASI A01 (13p) SC: 03 (AIR TRANSPORTATION AND SAFETY) CTMJ: REUSABLE HEAT SHIELDING/SPACE SHUTTLE ORBITERS/THERMAL PROTECTION CTMN: ABLATIVE MATERIALS/CARBON-CARBON COMPOSITES/SPACE TRANSPORTATION SYSTEM AB: Candidate concepts are identified. The impact on the Shuttle Orbiter performance life cycle cost, and risk was assessed and technology advances required to bring the selected TPS to operational readiness are defined. The best system is shown to be a hybrid blend of metallic and carbon-carbon TPS concepts. These alternate concepts offer significant improvements in reusability and are mass competitive with the current ceramic tile reusable surface insulation. Programmatic analysis indicates approximately five years are required to bring the concepts to operational readiness. 19800050587 A (80A34757) [Copyright] Unclassified (Unrestricted - Publicly Available) TI: Studies for improved high temperature coatings for Space Shuttle application AU: Creedon, J. (Lockheed Missiles and Space Co., Sunnyvale, CA, United States)/Banas, R. (Lockheed Missiles and Space Co., Sunnyvale, CA, United States)/Garofalini, S. H. (Lockheed Missiles and Space Co., Inc., Space Systems Div., Sunnyvale, Calif., United States) CN: NAS2-9809 DT: Conference Proceedings LA: English OS: Lockheed Missiles and Space Co. (Sunnyvale, CA, United States) FS: NASA (United States) [NASA] SO: In: New horizons - Materials and processes for the eighties; Proceedings of the Eleventh National Conference, Boston, Mass., November 13-15, 1979. (A80-34751 14-23) Azusa, Calif., Society for the Advancement of Material and Process Engineering, 1979, p. 82-93. PB: United States PD: Jan 01, 1979 MN: New horizons - Materials and processes for the eighties, 11th. Boston, MA, November 13-15, 1979 AV: Issuing Activity (12p) SC: 27 (NONMETALLIC MATERIALS) CTMJ: HIGH TEMPERATURE TESTS/PROTECTIVE COATINGS/SPACE SHUTTLE ORBITERS/SPACECRAFT CONSTRUCTION MATERIALS/THERMAL PROTECTION CTMN: RESIDUAL STRESS/SHRINKAGE/SPACE COMMERCIALIZATION/SPACECRAFT DESIGN/THERMAL EXPANSION/YIELD STRENGTH AB: Improvement of the current Class 2 Space Shuttle Orbiter RCG coating was experimentally investigated.Coatings, which are applied to LI-900 or LI-2200 tiles, were prepared to provide increased performance in thermal expansion, impact, residual strain and increased viscosity. Turbulent duct arc-plasma tests at NASA/Ames Research Center are continuing on two candidates that show improved low residual strain and increased high temperature viscosity. A coating system with lower fusion-temperature (1950 F) was identified which has the potential of improving tile yield through reduced LI-900 shrinkage and distortion since it can be fused at 250 F lower than the present Class 2 coating. See Also: A80-34751 14-23 (A80-34751 14-23)