Ablative thermal protection for space tug multipass, aerobraking entryAnalytical 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.
Document ID
19740043949
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Strauss, E. L. (Martin Marietta Aerospace Denver, Colo., United States)
Date Acquired
August 7, 2013
Publication Date
April 1, 1974
Subject Category
Thermodynamics And Combustion
Report/Patent Number
AIAA PAPER 74-400
Meeting Information
Meeting: Structures, Structural Dynamics and Materials Conference