Commercial applications for the proposed advanced TPS include conventional satellite launch system solid rocket motors, nanosatellite launch systems, launch platform protection, and tactical solid rocket motors, internal and external motor case insulation, and nosetips. The proposed foam-reinforced hybrid ablator-insulator may meet NASA requirements for increased TPS heat flux capability and reduced mass. NASA applications include the Orion Crew Exploration Vehicle for which entry velocities ranging from 8 km/s for International Space Station missions to as high as 15 km/s for Moon mission return are anticipated, and planetary sample return missions. Use of ablatives in rocket nozzles has been extensive, and NASA also stands to benefit in that application.
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