Demonstration Test Firing of a Water-Cooled Nozzle on a Solid Propellant Motor.
Rept. for 15 Oct 67-18 Jun 68,
AIR FORCE ROCKET PROPULSION LAB EDWARDS AFB CA
Pagination or Media Count:
The objective of this test program was to evaluate the feasibility of using a water-cooled nozzle on large solid propellant motors. The support requirement for this second nozzle test was 1100 galmin coolant water flow with an inlet coolant pressure of 850 psi. The nozzle was successfully tested with no indication of burn-through or film boiling occurring. Test duration was 62 seconds at an average chamber pressure of 380 psi. Results of this test indicated the entire system operated satisfactorily at maximum operating conditions. Author
- Surface-Launched Guided Missiles
- Rocket Engines
- Solid Propellant Rocket Engines