Accession Number : AD0776405

Title :   Study of Production Methods for High Temperature Solid Propellant Motor Nozzles.

Descriptive Note : Final rept. 22 Dec 72-22 Jan 74,

Corporate Author : HERCULES INC CUMBERLAND MD ALLEGANY BALLISTICS LAB

Personal Author(s) : McComas,T. D. ; Vicario,A. A. ; Casseday,E. D.

Report Date : 01 MAR 1974

Pagination or Media Count : 173

Abstract : The program investigated low-cost fabrication processes to permit the use of advanced materials in nozzles to achieve high performance in a severe motor environment (2000 psi - 20 sec - 100 lb/sec flow). Three materials and manufacturing processes were selected as primary candidates by an initial screening process. Detailed full-scale nozzle designs were developed for each of the candidates. Performance was evaluated in subscale motor firings. A final selection was made and is recommended for demonstration in a full size nozzle test. The sleected material is a carbon-carbon composite, manufactured from a graphite cloth layup (preform) by carbonization and successive resin infiltration/carbonization cycles for densification (> 1.45 gm/cc) and graphitization. A program plan was developed to manufacture and test the nozzle in the specified motor environment. (Author)

Descriptors :   *Rocket nozzles, Composite materials, Carbon, Production, Processing, Graphite, Thermal properties, Structural properties, Strength(Mechanics), Solid propellant rocket engines

Subject Categories : Solid Propellant Rocket Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE