Integrated Ablative and Radiative Heat Shield Panels and Leading Edges for High L/D Reentry Vehicles.
Technical rept. Jun 70-May 71,
GENERAL DYNAMICS SAN DIEGO CA CONVAIR AEROSPACE DIV
Pagination or Media Count:
The objective of this program is to provide ablative heat shields and leading edges integrated with radiative heat shields for testing and demonstration in the Air Force Flight Dynamics Laboratory Hypersonic Aerospace Test Structure HATS. The program has included the investigation, analysis, and test of sub-scale specimens and various design concepts to determine design values for the full-scale panels and leading edge. Design, fabrication, test, and post-test analysis of the full-scale surface ablative panels and leading edges integrated on the structure are included. Specific TPS design criteria were established for the basepoint vehicle, and three selected design trajectories were evaluated to determine the aerodynamic heating environments for the leading edges and the lower surface. Complete aeroheating envelopes were established for each selected mission. Conceptual designs of the leading edges, lower surface panels, and interfaces were established and subjected to preliminary thermostructural analyses based on predicted thermal and aerodynamic loading conditions. Candidate materials were selected and evaluated for the leading edges and lower surface panels. Author, modified-PL
- Unmanned Spacecraft
- Spacecraft Trajectories and Reentry