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  • 1
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    Multiwall/RSI concept for local application to space shuttle body flap (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A titanium multiwall/reusable surface insulation (MW/RSI) TPS concept designed to prevent local erosion of the RSI tiles on the upper surface of the Space Shuttle Orbiter body flap was investigated. The concept, which consisted of a combination of a titanium multiwall tile and an RSI tile, was evaluated by thermal analysis and structural and thermal testing of one configuration to assess the attachment scheme and thermal behavior. Results indicate that the MW/RSI concept will remain attached to the vehicle and provide the required thermal protection.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-87589 , NAS 1.15:87589
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Thermal fatigue tests of a radiative heat shield panel for a hypersonic transport (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A pair of corrugation stiffened, beaded skin Rene 41 heat shield panels were exposed to 20,000 thermal cycles between room temperature and 1450 F to evaluate the thermal fatigue response of Rene 41 metallic heat shields for hypersonic cruise aircraft applications. At the conclusion of the tests, the panels retained substantial structural integrity; however, there were cracks and excessive wear in the vicinity of fastener holes and there was an 80-percent loss in ductility of the skin. Shrinkage of the panel which caused the cracks and wear must be considered in design of panels for Thermal Protection Systems (TPS) applications.
    Keywords: METALLIC MATERIALS
    Type: NASA-TM-87583 , NAS 1.15:87583
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Static and aerothermal tests of a superalloy honeycomb prepackaged thermal protection system (1993)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A reusable metallic thermal protection system has been developed for vehicles with maximum surface temperatures of up to 2000 F. An array of two 12- by 12-in. panels was subjected to radiant heating tests that simulated Space Shuttle entry temperature and pressure histories. Results indicate that this thermal protection system, with a mass of 2.201 lbm/ft(exp 2), can successfully prevent typical aluminum primary structure of an entry vehicle like the Space Shuttle from exceeding temperatures greater than 350 F at a location on the vehicle where the maximum surface temperature is 1900 F. A flat array of 20 panels was exposed to aerothermal flow conditions, at a Mach number of 6.75. The panels were installed in a worst-case orientation with the gaps between panels parallel to the flow. Results from the aerothermal tests indicated that convective heating occurred from hot gas flow in the gaps between the panels. Proposed design changes to prevent gap heating occurred from hot gas flow in the gaps between the panels. Proposed design changes to prevent gap heating include orienting panels so that gaps are not parallel to the flow and using a packaged, compressible gap-filler material between panels to block hot gas flow in the gaps.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TP-3257 , L-17084 , NAS 1.60:3257
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    NASA evaluation of Type 2 chemical depositions (1993)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Recent findings from NASA Langley tests to define effects of aircraft Type 2 chemical deicer depositions on aircraft tire friction performance are summarized. The Aircraft Landing Dynamics Facility (ALDF) is described together with the scope of the tire cornering and braking friction tests conducted up to 160 knots ground speed. Some lower speed 32 - 96 km/hr (20 - 60 mph) test run data obtained using an Instrumented Tire Test Vehicle (ITTV) to determine effects of tire bearing pressure and transverse grooving on cornering friction performance are also discussed. Recommendations are made concerning which parameters should be evaluated in future testing.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: SAE PAPER 932582 , SAE, Aerotech ''93; Sep 27, 1993 - Sep 30, 1993; Costa Mesa, CA; United States|(ISSN 0148-7191); 6 p.
    Format: text
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    NASA TECHNICAL REPORTS
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