The problems posed for temperature control of Hermes by the wide operating range are reviewed. The design is based around a delta body and has airbrakes to assist landing. Thermal control poses special problems because of the size of the craft. The STS approach of a cold structure protected by heat shielding is not possible. The fuselage and wings are cold structures, with protection, while the nose, leading edges, winglets, and control surfaces are hot, i.e., made from heat resistant materials. The aerothermodynamic development and test program is mentioned.
Hermes Aerothermodynamic Concept
1988
2 pages
Report
No indication
English
Computational Simulation of the Aerothermodynamic Characteristics for the Reentry of HERMES
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