Test Firing of an Advanced Graphite Composite Material Throat Insert.
AIR FORCE ROCKET PROPULSION LAB EDWARDS AFB CA
Pagination or Media Count:
The test firing of an advanced graphite material throat insert, HRX 503-X, was conducted on the Air Force Rocket Propulsion Laboratory uncured propellant char motor. The throat insert material was installed into a test weight nozzle designed and fabricated by the Air Force. The test firing utilized a 16 percent aluminum, PBAN binder uncured solid propellant. The motor and test nozzle performed adequately, with a 600 psig, 28 second duration chamber pressure versus time trace being produced. Average nozzle insert surface regression was 0.00086 inches per second. Author
- Laminates and Composite Materials
- Solid Propellant Rocket Engines