Accession Number : AD0691025

Title :   STRUCTURAL SYNTHESIS OF COMPOSITE MATERIALS FOR ABLATIVE NOZZLE EXTENSIONS,

Corporate Author : AEROSPACE CORP EL SEGUNDO CALIF ENGINEERING SCIENCE OPERATIONS

Personal Author(s) : Au,Norman N. ; Scheyhing,Ernest R. ; Summers,George D.

Report Date : 31 JUL 1969

Pagination or Media Count : 44

Abstract : The ability of certain composite materials to sustain extremely high temperatures has led to their extensive use for the thermal protection of aerospace structures. Frequently, these materials are used in conjunction with metallic or non-metallic substructures to provide optimum combinations of structural and thermal properties. In principle, the substructures are load-carrying structures for strength, which are lined with fiber-reinforced plastics for thermal insulation. However, when insulators become integral with the structure, complexities in design, test, and analysis result. A structural synthesis in this case requires the close coordination of basic materials research, experimental determination of material properties, and results of thermal and structural analyses. In the report, this mode of structural synthesis is applied to obtain an understanding of the structural behavior of an actual composite structure, the Titan III Stage II ablative nozzle extension. The value of the approach is clearly shown by its ability to identify structural failure modes, predict structural failures experienced, and guide a successful modification program. (Author)

Descriptors :   (*LAUNCH VEHICLES, *SECOND-STAGE MOTORS), (*ROCKET NOZZLES, *COMPOSITE MATERIALS), LAMINATES, HONEYCOMB CORES, SANDWICH CONSTRUCTION, GLASS TEXTILES, STRUCTURAL PROPERTIES, SYNTHESIS, THERMAL STRESSES, ABLATION, THERMAL EXPANSION, EXTENDABLE STRUCTURES, THERMAL INSULATION, FAILURE(MECHANICS), OPTIMIZATION

Subject Categories : Laminates and Composite Materials
      Rocket Engines
      Ground Support Sys & Facil For Space Vehicles

Distribution Statement : APPROVED FOR PUBLIC RELEASE