Reusable Launch Vehicle Technology Development and Test Program (1995) / Chapter Skim
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4 THERMAL PROTECTION SYSTEM
4 THERMAL PROTECTION SYSTEM
Pages 43-54
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From page 43... ...
The space shuttle orbiter TPS, the only demonstrated reusable TPS, provides valuable lessons for development of the REV TPS. The aluminum orbiter structure has successfully remained within temperature limits, and the primary bonded attachment method has prevented heat lealcs directly into the structure.
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From page 44... ...
Advanced Flexible Coating loss, embrittlement, fabric frays, tears, Can be repaired Reusable Surface broken threads, blanket debonds Insulation (AFRSI) Felt Reusable Surface Coating overheating, coating tears, joint seal Least frequent Insulation damage, edge member damage Reinforced Carbon- Chips or cracks in SiC coating, flaking or loss Refurbished by vendor, less Carbon of sealant' pin holes, exposure of underlying frequent than tile or AFRSI carbon substrate Gap fillers and thermal Lost coatings, frays, fabric breaking, tears, Two of the major items that barrier coatings charring, protruding or lost gap fillers require reworking Filler Bars Overheating caused by out-of-tolerance steps, gaps, or heating environments TABLE 4-2 100 Mission Maximum Operating Temperature for Space Shuttle Orbiters Material System 100 Mission Max.
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From page 45... ...
Cryogenic insulation on the orbiter is limited to areas adjacent to feedlines because the cryopropellants are carried in the disposable external tank. The REV TPS mounted on the cryogenic insulation which is attached directly to the cryotanks, either internally or externally, form the surface of the vehicle.
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From page 46... ...
All appropriate element testing required to achieve this goal will be completed and documented. All appropriate attachment mechanisms will have been analyzed and preferred technologies included in the test article.
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From page 47... ...
The TPS based on these designs will be fabricated to REV requirements and tested against weather exposure and thermal vacuum conditions, rain erosion, low speed and hypenrelocity particle impacts, aerothermal effects in wind tunnel and arc jets, thermal acoustic environments, and, finally, an oxidation environment. Tests are planned both at the individual TPS tile or panel level and at the large, integrated cryotank wall/cryoinsulation/TPS/attachments scale.
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From page 48... ...
of the vehicle, which is exposed to higher temperatures than the upper surface. The materials are: AETB Alumina enhanced thermal barrier is a high-temperature tile incorporating alumina fibers; can withstand temperatures up to 2,600°F.
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From page 49... ...
In addition to developing the candidate TPSs, ARC provides direct support to the prime contractors, as requested, including performing aerothermal environment studies for specific configurations and TPS materials. These include studies on the use of ARC's advanced computational fluid dynamics codes, TPS requirements, design and trade support, blanket coating evaluations, advanced waterproofing techniques, and integrated health monitoring systems (including the development of sensors)
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From page 50... ...
; others were investigated under the NASP program (C/SiC; SiC/SiC) ; and the metallic panels have been evaluated and refined over the past 25 years, since the inception of the space shuttle program.
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From page 51... ...
Better Requires waterproofing. Coating performance data insulator than TABI.
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From page 52... ...
Development, primarily at two NASA centers, has proceeded along two distinct, but complementary lines. One approach takes advantage of the long heritage of the shuttle TPS while significantly improving the robustness of reusable blankets and ceramic tiles against damage known to require excessive manpower for vehicle turnaround.
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From page 53... ...
Use of metallic panels will require mechanical attachments that are still under refinement. Cryogenic foam insulation has been used on expendable vehicles (including the shuttle's external tank)
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From page 54... ...
1995. Space Shuttle Orbiter Thermal Protection System Processing Assessment: Final Report.
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