This program analytically and experimentally investigates the design and thermostructural performance of integrated ablative/radiative thermal protection systems in two phases: CONCEPT DEVELOPMENT AND FULL-SCALE PANEL DEVELOPMENT. In Phase I, the program includes the investigation, analysis, and test of sub-scale specimens and various design concepts to determine design values for the full-scale panels and leading edges. Phase II covers the design and fabrication of large-scale lower surface ablative panels and leading edges for integration on the AFFDL Hypersonic Aerospace Test Structure (HATS). A vehicle configuration, the FDL-5A, is furnished by the Air Force to serve as a basepoint for the analytical and experimental phases of the program. (Author, modified-PL)
Integrated Ablative and Radiative Heat Shield Panels and Leading Edges for High L/D Reentry Vehicles
1973
145 pages
Report
No indication
English
Missile Warheads & Fuses , Composite Materials , Reentry vehicles , Heat shields , Leading edges , Nose cones , Thermal insulation , Ablation , Radiation , Elastomers , Aerodynamic heating , Panels , Composite materials , Interfaces , Compatibility , Fabrication , Atmosphere entry , Simulation , Costs , Low density , Aerodynamic configurations , Carbon , Honeycomb structures , Aluminum alloys , Loads(Forces) , Safety , Silicon dioxide , Phenolic plastics , Carbon fibers , Mechanical properties , Niobium alloys , Nickel alloys , Chromium alloys , Thermophysical properties , FDL-5A reentry vehicle , HATS(Hypersonic aerospace test structure) , Hypersonic aerospace test structure , Carbon carbon composites