ADVANCED COMPOSITE CARBIDE NOZZLES.
Interim progress rept. 1 Jul 67-29 Mar 68,
AEROJET-GENERAL CORP SACRAMENTO CA
Pagination or Media Count:
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 and hafnium and a tantalum-carbide-coated, tantalum carbidegraphite hypereutectic. During this reporting period, the characterization of ambient and elevated temperature properties has been completed on both the microcomposite and TaC-C hypereutectic composite systems. Thermal shock resistance and chemical corrosion evaluation tests have been completed on both composite systems. Testing was conducted in a hyperthermal environmental simulator using subscale inserts. The fusion casting of 4.2-in.-dia TaC-C hypereutectic billets are presently in progress for fabricating full-scale nozzle inserts. Author
- Laminates and Composite Materials
- Properties of Metals and Alloys
- Rocket Engines