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)