Accession Number : AD0918032
Title : Integrated Ablative and Radiative Heat Shield Panels and Leading Edges for High L/D Reentry Vehicles.
Descriptive Note : Final technical rept. Jun 70-Aug 73,
Corporate Author : GENERAL DYNAMICS SAN DIEGO CA CONVAIR AEROSPACE DIV
Personal Author(s) : Kiger, Ralph W.
Report Date : SEP 1973
Pagination or Media Count : 145
Abstract : 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)
Descriptors : (*REENTRY VEHICLES, HEAT SHIELDS), (*LEADING EDGES, REENTRY VEHICLES), (*HEAT SHIELDS, 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.
Subject Categories : Laminates and Composite Materials
Guided Missile Reentry Vehicles
Distribution Statement : APPROVED FOR PUBLIC RELEASE