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 : JAN 1967

Pagination or Media Count : 44

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 carbide/graphite 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 carbide/graphite 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