SSTO Thermal Protection System Issues

Reusable and maintainable Thermal Protection Systems for SSTOs have been a concern in terms of achieving the combination of low mass, operations in all weather conditions (i.e., not requiring waterproofing between flights), and ease of repair and maintainability. Since the development of the Shuttle's TPS (a combination of ceramic tile and insulation blankets), work has progressed both within NASA and in industry. There are several sources of materials, both composite and metallic, that have been fabricated into SSTO type test panels and tested in expected flight environments by both NASA and in industry test facilities.

SSTO applications are being evaluated for external TPS using advanced composite carbon/carbon-silicon ("C-C/C-Sic"), advanced high temperature metallics, acreage TABI, and carbon fiber blanket insulation ("CFBI"). These materials are selectively applied to the flight vehicle area depending upon expected aeroheating conditions. The challenge is twofold: (1) Achieving an overall aerial density approximating one pound per square foot; and (2) Developing attachment systems for ease of installation and maintenance while ensuring heat and weather protection. Both these issues are being fully addressed in actual hardware.

An alternative to the above approach is a "hot structure TPS" that may be utilized depending upon the type of X-33 SSTO vehicle configuration selected and upon the selected entry/cross range flight profile. This approach is considered achievable with current high temperature materials.

One of the primary objectives of the X-33 SSTO Advanced Technology Demonstrator "X-vehicle" program is to apply the most promising TPS materials and to validate both flight performance and the achievement of operability/maintainability goals.

v. 1 Friday 17 March 1995

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