STRUCTURAL SYNTHESIS OF COMPOSITE MATERIALS FOR ABLATIVE NOZZLE EXTENSIONS,
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)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 31, 1969
- Accession Number
- AD0691025
Entities
People
- Ernest R. Scheyhing
- George D. Summers
- Norman N. Au
Organizations
- The Aerospace Corporation