Interface Designs between TPS and Cryogenic Propellant Tank of an RLV Booster Stage

Abstract

The booster of the SpaceLiner 7 was chosen as reference vehicle to investigate the design of an integrated system comprising the cryogenic fuel tank with added thermal insulation and a thermal protection system. One solution is a stack of two layers of cryogenic respectively high-temperature insulation adding up to 130 mm. Another option is a purge gap to reduce thickness. Thermal analyses show that the purge gap is feasible on a cryogenic insulation with reduced thickness. FEM analyses show that requirements can be satisfied. A design suggestion was made for the structural fixation of the TPS to the underlying tank.