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  • 1
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    Status of reusable surface insulation thermal protection system technology programs (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The development of three low-density rigidized insulation materials for the shuttle TPS application is reported. These materials consist of one high purity silica system and two systems based on mullite, an aluminum silicate. Both systems consist of fibers joined together with appropriate binders to obtain a rigidized insulation composite. Both material systems require the application of a glassy coating to provide a wear resistant, high emittance surface and to prevent the absorption of water by the fiber matrix. The technology program has addressed the development of water impervious coatings, methods of assembling the materials in design concepts while minimizing the thermal stress in the insulation, achieving compatibility between the RSI material and the structural system, and test evaluations to demonstrate the feasibility of the surface insulation concept.
    Keywords: SPACE VEHICLES
    Type: NASA Space Shuttle Technol. Conf.; p 435-474
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Development status of reusable nonmetallic thermal protection (1971)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Development of reusable oxidation resistant carbon-carbon laminates and surface insulation materials for thermal protection systems
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA SPACE SHUTTLE TECHNOL. CONF., VOL. 2 APR. 1971; P 1-38
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Orbiter thermal protection system (1985)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The major material and design challenges associated with the orbiter thermal protection system (TPS), the various TPS materials that are used, the different design approaches associated with each of the materials, and the performance during the flight test program are described. The first five flights of the Orbiter Columbia and the initial flight of the Orbiter Challenger provided the data necessary to verify the TPS thermal performance, structural integrity, and reusability. The flight performance characteristics of each TPS material are discussed, based on postflight inspections and postflight interpretation of the flight instrumentation data. Flights to date indicate that the thermal and structural design requirements for the orbiter TPS are met and that the overall performance is outstanding.
    Keywords: SPACE TRANSPORTATION
    Type: Space Shuttle Tech. Conf., Pt. 2; p 1062-1081
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Testing the Shuttle heat-protection armor (1976)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: The article deals with the thermal protection system (TPS) designed to keep Space Shuttle structures at 350 F ratings over a wide range of temperatures encountered in orbit, but also during prelaunch, launch, deorbit and re-entry, landing and turnaround. The structure, function, fabrication, and bonding of various types of reusable surface insulation and composite materials are described. Test programs are developed for insulation, seals, and adhesion bonds; leak tests and acoustic fatigue tests are mentioned. Test facilities include arc jets, radiant heaters, furnaces, and heated tunnels. The certification tests to demonstrate TPS reusability, structural integrity, thermal performance, and endurance will include full-scale assembly tests and initial orbital flight tests.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Astronautics and Aeronautics; 14; Jan. 197
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Reusable surface insulation thermal protection systems test evaluation status (1973)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Changes in coating morphology of mullite, silica, and ceramic mullite fiber at two heating rates are described followed by a discussion of the changes in surface chemistry that occur during convective heating tests. Subsequently, the surface chemistry changes observed are compared to similar data obtained from radiantly heated coatings and the significance of the difference between the results is discussed. Finally, the changes in chemistry of the coatings in cross section before and after convectively heated cyclic testing are discussed and the significance of surface chemistry changes are described. Results indicate that the thermal conductivity of mullite surface insulation is higher than that of silica insulation, based on thermal response data. Acoustic excitation of cracked silica tiles does not lead to catastrophic failure such as spallation or tile loss. Cracks in mullite material after thermal exposure lead to fracturing of the coating and surface insulation material after acoustic excitation.
    Keywords: MATERIALS, NONMETALLIC
    Type: Symp. on Reusable Surface Insulation for Space Shuttle, Vol. 2; p 895-934
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Space shuttle orbiter reusable surface insulation flight results (1983)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The first five flights of the orbiter Columbia provided the initial data required to certify the operational performance of the reusable surface insulation (RSI) thermal protection system (TPS). The flight performance characteristics of the RIS TPS are discussed. The discussion is based primarily on postflight inspections and postflight interpretation of the flight instrumentation. TPS modifications of the future orbiters (OV-099, 103, and subs) are also discussed.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Langley Research Center Shuttle Performance: Lessons Learned, Pt. 2; p 949-966
    Format: application/pdf
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  • 7
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    Thermal performance and radio-frequency transmissivity of candidate ablation materials for S-band antenna window application on manned spacecraft (1970)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A test program was conducted in the MSC 1.5 MW arc-heated facility to evaluate the thermal performance of ablation materials having potential application as radio frequency windows. These tests were conducted for the improvement of omnidirectional antenna operating characteristics during atmospheric reentry. Since a full scale model of the Apollo command service module was available for antenna tests, this mockup was used as a basic for the tests. Test models were subjected to heating conditions simulating the nominal lunar return trajectory (AS-501) and the design trajectories, high heat load and high heating rate. RF measurements were made before and after the arc jet tests to measure attenuation effects due to the thermal degradation of the materials under consideration. The test program demonstrated that additional development is required in materials technology to achieve an ablative system with both good RF transmission characteristics and thermal-structural integrity.
    Keywords: ELECTRONIC EQUIPMENT
    Type: NASA-TM-X-68325 , MSC-01274
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Thermal performance of FRSI/graphite epoxy materials for the Orbiter TPS application (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Radiant tests have been conducted to evaluate the performance of the Flexible Reusable Surface Insulation (FRSI) when bonded to Graphite/Epoxy (G/E) honeycomb sandwich structures. The results from this study indicate reasonable agreement with the baseline FRSI properties that existed prior to this test program. An updated Thermal Math Model (TMM) prediction technique was developed, with the use of the well-defined boundary conditions, which appears to be valid in analyzing the complex heat transfer associated with the honeycomb structure. The updated TM analysis of flight data resulted in good agreement of predicted temperatures with flight data for bondline responses of Orbiter FRSI/GE TPS applications.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 84-1769
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    The Shuttle Orbiter thermal protection system materials, designs, and flight performance overview (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The design requirements for the Orbiter thermal protection system (TPS), the various TPS materials that are used, the different design approaches associated with each of the materials, and the performance experienced during the flight test program are described. The first five flights of the Orbiter Columbia have provided the necessary data to verify the TPS thermal performance, structural integrity, and reusability. The flight performance characteristics of each TPS material are discussed. This discussion is based on postflight inspections and postflight interpretation of the flight instrumentation data. The flights to date indicate that the thermal and structural design requirements for the Orbiter TPS have been met and that the overall performance has been outstanding.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: SAE PAPER 831118
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    Moisture absorption characteristics of the Orbiter thermal protection system and methods used to prevent water ingestion (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The Space Shuttle Orbiter's silica tile Thermal Protection System (TPS) is beset by the moisture absorption problems inherently associated with low density, highly porous insulation systems. Attention is presently given to the comparative success of methods for the minimization and/or prevention of water ingestion by the TPS tiles, covering the development of water-repellent agents and their tile application techniques, flight test program results, and materials improvements. The use of external films for rewaterproofing of the TPS tiles after each mission have demonstrated marginal to unacceptable performance. By contrast, a tile interior waterproofing agent has shown promise.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: SAE PAPER 831117
    Format: text
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