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  • 1
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    Thermal protection system trade studies on ablators and reuseable surface insulation (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Analytical trade studies are presented that consider passive TPS configurations using the following material categories: (1) reuseable surface insulation - surface-coated rigidized ceramic fiber; (2) low density charring ablators; and (3) carbon-carbon and high density ablators for leading edge areas. Emphasized are effects on TPS weight by variations in entry trajectories and material thermal characteristics.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA Space Shuttle Technol. Conf.; p 303-334
    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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    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
  • 4
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    Early development of ceramic fiber insulation for the Space Shuttle (1981)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: The evolution of reusable surface insulation is described, with attention to the mullite and other aluminosilicates, zirconia, and silicon carbide-coated carbon compositions experimented with in the late 1960s and early 1970s. Evaluation and development concentrated in this period on such aspects of design and material properties as cold soak performance, attachment, shock impingement, surface coating cracks, and tile gap design and heating. In addressing the central problem of heat-shield thermal conductivity, it was found that for a given density, silica fibers had a lower conductivity than those of mullite. This was due to the one-micron, as opposed to 4.7-micron, diameter of the silica fibers, which resulted in smaller pores and therefore less convective and radiative heat transfer. Attention is also given to tile coating materials and the high-temperature processes by which they were applied.
    Keywords: NONMETALLIC MATERIALS
    Type: American Ceramic Society Bulletin; 60; Nov. 198
    Format: text
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  • 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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    Thermal protection system performance of the Apollo command module. (1966)
    In:  Other Sources
    Details
    Publication Date: 2018-12-01
    Description: Thermal protection system for Apollo command module
    Keywords: SPACE VEHICLES
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    The effect of gas phase chemical reactions on heat transfer to a charring ablator (1970)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: Gas phase chemical reactions effect on heat transfer to charring ablator, deriving numerical solution for multicomponent stagnation point flow
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: AIAA PAPER 70-869
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Coated-felt thermal insulation (1979)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Thin coated-felt insulation tile is lighter and easier-to-install replacement for silica tiles for temperatures below 700 F.
    Keywords: MATERIALS
    Type: MSC-12737 , NASA Tech Briefs (ISSN 0145-319X); 3; 4; P. 535
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Thermal insulation protection means (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A system for providing thermal insulation for portions of a spacecraft which do not exceed 900 F during ascent or reentry relative to the earth's atmosphere is described. The thermal insulation is formed of relatively large flexible sheets of needled Nomex felt having a flexible waterproof coating. The thickness of the felt is sized to protect against projected temperatures and is attached to the structure by a resin adhesive. Vent holes in the sheets allow ventilation while maintaining waterproofing. The system is heat treated to provide thermal stability.
    Keywords: COMPOSITE MATERIALS
    Format: application/pdf
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  • 10
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    Definition of entry corridor thermal limits for Apollo spacecraft. (1968)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Entry corridor thermal entry limits for Apollo spacecraft defined for design of thermal protection system
    Keywords: SPACE VEHICLES
    Type: AIAA PAPER 68-1144 , AMERICAN INST. OF AERONAUTICS AND ASTRONAUTICS, ENTRY VEHICLE SYSTEMS AND TECHNOLOGY MEETING; Dec 03, 1968 - Dec 05, 1968; WILLIAMSBURG, VA
    Format: text
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