Accession Number:

AD0647309

Title:

HIGH TEMPERATURE RESISTANT MATERIALS FOR MISSILE PROPULSION SYSTEMS.

Descriptive Note:

Summary rept., 30 Jun 65-30 Jun 66,

Corporate Author:

NAVAL ORDNANCE LAB WHITE OAK MD

Personal Author(s):

• Caum,D. M.
• Hartmann,B. T.
• Koubek,F. J.

Report Date:

1966-12-27

Pagination or Media Count:

51.0

Abstract:

A temperature prediction program showed agreement to within 10 to 25 of experimental internal temperature for three ablators tested in the oxy-acetylene burner. However, if alpha effective thermal diffusivity is not obtained under steady-state ablation conditions, the agreement could be several hundred per cent in error. The alpha-rod test technique was found to be useful for ablators with widely varying properties. The NOL oxy-acetylene panel test was accepted and published as a tentative ASTM method. Author

Descriptors:

• (*COMPOSITE MATERIALS
• ABLATION)
• (*HEAT SHIELDS
• COMPOSITE MATERIALS)
• (*HIGH TEMPERATURE
• MATERIALS)
• (*ROCKET ENGINES
• HEAT RESISTANT MATERIALS)
• HEAT RESISTANT PLASTICS
• PHENOLIC PLASTICS
• FOAM
• CERAMIC MATERIALS
• LAMINATED PLASTICS
• SYNTHETIC RUBBER
• ASBESTOS
• GLASS TEXTILES
• NYLON
• EPOXY RESINS

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