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 Multi-Purpose Crewed Vehicle for beyond Earth orbit exploration (entry, descent, and landing heat shield and backshell), asteroid sample return, and planetary sample return. Earth return can have an entry velocity greater than 11 km/s and a heat flux in the 1500-2500 W/cm2 range. Use of ablatives in rocket nozzles has been extensive, and NASA also stands to benefit in that application. Commercial applications include solid rocket motors for conventional satellite launch, nanosatellite launch systems, launch platform protection, tactical missile solid rocket motors, internal and external motor case insulation, and nosetips.