Accession Number:

AD0805072

Title:

ADVANCED COMPOSITE CARBIDE NOZZLES.

Descriptive Note:

Quarterly rept. no. 2, 1 Oct-31 Dec 66,

Corporate Author:

AEROJET-GENERAL CORP SACRAMENTO CA

Personal Author(s):

• Radtke, R. P.
• Swope, L. M.

Report Date:

1967-01-01

Pagination or Media Count:

44.0

Abstract:

The purpose of this program is to develop two thermal-shock-resistant composite carbide systems that can be reliably used with high-flame-temperature solid rocket propellants. These are a microcomposite of monocarbide tantalum, hafnium and a tantalum-carbide-coated, tantalum carbidegraphite hypereutectic. During this second quarter, the processing variables required to develop the microcomposite structure were established utilizing a hot-press fabrication technique. Work was initiated to develop a tantalum carbidegraphite hypereutectic composite by a fusion and drop casting technique. Author

Descriptors:

• *COMPOSITE MATERIALS)
• (*NOZZLE INSERTS
• MATERIALS)
• (*ROCKET NOZZLES
• CARBIDES)
• (*CARBIDES
• TANTALUM COMPOUNDS
• HAFNIUM COMPOUNDS
• GRAPHITE
• HOT PRESSING
• THERMAL SHOCK
• MICROSTRUCTURE

Subject Categories:

• Laminates and Composite Materials
• Rocket Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE