Verification tests of durable thermal protection system concepts
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Shideler, J. L.↗
Engineering topics
Webb, G. L.
Publications and source records attributed to Webb, G. L..
Verification tests of durable TPS concepts
Titanium multiwall, superalloy honeycomb, and Advanced Carbon-carbon (ACC) multipost Thermal Protection System (TPS) concepts are being developed to provide durable protection for surfaces of future space transportation systems. Verification tests including thermal, vibration, acoustic, water absorption, lightning strike, and aerothermal tests are described. Preliminary results indicate that the three TPS concepts are viable up to a surface temperature in excess of 2300 F.
Shideler, J. L.↗
Verification tests of durable TPS concepts
Titanium multiwall, superalloy honeycomb, and Advanced Carbon-Carbon (ACC) multipost Thermal Protection System (TPS) concepts are being developed to provide durable protection for surfaces of future space transportation systems. Verification tests including thermal, vibration, acoustic, water absorption, lightning strike, and aerothermal tests are described. Preliminary results indicate that the three TPS concepts are viable up to a surface temperature in excess of 2300 F.
Shideler, J. L.↗
Assessment of alternate thermal protection systems for the Space Shuttle Orbiter
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.
Kelly, H. N.↗
Assessment of Alternate Thermal Protection Systems for the Space Shuttle Orbiter
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.
Kelly, H. N.↗