Accession Number:

AD0276038

Title:

DEVELOPMENT OF REFRACTORY COMPOSITE MATERIALS SYSTEMS FOR SOLID PROPELLANT ROCKET MOTORS

Descriptive Note:

Corporate Author:

HUGHES TOOL CO CULVER CITY CALIF

Personal Author(s):

Report Date:

1961-12-04

Pagination or Media Count:

1.0

Abstract:

Progress is reported on the development of composite rocket nozzle systems for use with high temperature, high alumina content solid propellants. Material thickness requirements were determined by heat transfer analysis. The differential equations governing heat flow were solved by utilizing finite difference techniques with the computing performed on an IBM 704 machine. A major portion of the effort was devoted to the development of methods to form carbides mp greater than 4000 F on graphite. The most successful method consisted of sintering or melting and carburizing metal powders on graphite between 2200 and 5000 F in a carbon resistance furnace. A number of carbide systems were developed with excellent adherence and show promise for use as the flame surface of graphite nozzles. Flexural strength properties of metal wire reinforced chemically bonded high temperature oxides, for use as backup structures to a carbide coated graphite nozzle, were determined. Author

Subject Categories:

Distribution Statement:

APPROVED FOR PUBLIC RELEASE