Analytical studies had found the employment of an aerobraking trajectory for return of a reusable Space Tug from geosynchronous missions to be feasible and practical. To establish the minimum-weight ablative dome heat shield, trajectories involving 2 and 30 perigee passes were investigated both analytically and by plasma arc testing. Silicone-base ablators with densities of 15, 30, and 50 lb/cu ft were selected for evaluation. All models withstood the multipass exposures without deleterius surface recession or char erosion. Dome heat shield weights based on optimum ablative compositions indicated that ablators are a highly efficient thermal protection system for these missions.
Ablative thermal protection for space tug multipass, aerobraking entry
Structures, Structural Dynamics and Materials Conference ; 1974 ; Las Vegas, NV, US
1974-04-01
Conference paper
No indication
English
Ablative thermal protection for space tug multipass, aerobraking entry
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