Accession Number:

AD0627519

Title:

HIGH TEMPERATURE RESISTANT MATERIALS FOR MISSILE PROPULSION SYSTEMS.

Descriptive Note:

Annual summary rept. 30 Jun 64-30 Jun 65,

Corporate Author:

NAVAL ORDNANCE LAB WHITE OAK MD

Personal Author(s):

Report Date:

1965-11-29

Pagination or Media Count:

35.0

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

Subject Categories:

  • Laminates and Composite Materials
  • Air Conditioning, Heating, Lighting and Ventilating
  • Test Facilities, Equipment and Methods
  • Rocket Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE