HIGH TEMPERATURE RESISTANT MATERIALS FOR MISSILE PROPULSION SYSTEMS.
Abstract
Parametric studies were completed on methods for computing thickness of heat shield needed for a given set of conditions. For two very different materials, the studies showed that total insulation thickness needed is not sensitive to the exact value of the front-face temperature. Furthermore, whereas an average value of effective thermal diffusivity is sufficiently accurate for these calculations, the actual variation of heat flux with time must be used. One preliminary check of the above method against experimental data gave satisfactory agreement within 7%. A total of seven typical ablation materials was tested in the oxyacetylene burner using the alpha -rod technique. The results are in general agreement with previous arc image furnace data but are more precise, primarily due to the accuracy of the automatic feed device as compared with manual operation. Design work on the hi-pressure gas stabilized hi-intensity plasma arc head was almost completed. Most of the extensive auxiliary equipment has been obtained or requested. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Nov 29, 1965
- Accession Number
- AD0627519
Entities
People
- B. T. Hartmann
- D. M. Caum
- F. J. Koubek
Organizations
- Naval Ordnance Laboratory