A survey of the general problem of aerothermal reentry is made, showing the complexity of the problem for HERMES as well as for future ASTS.
The present status of the TPS solution choosen for HERMES is given. Under consideration are ceramic composites or carbon carbon for hot structures, insulation using for hot zones either ceramic composite shingles plus internal multiscreen insulation or ceramic tiles, and for lower temperature zones flexible external insulation.
The difference between HERMES and other potential Space Transportation Systems are studied. A comparaison is made between HERMES solutions and other possible TPS systems.
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