PROPELLANT FROSTING EFFECTS.
Final rept. Apr-Sep 65,
AIR FORCE ROCKET PROPULSION LAB EDWARDS AFB CA
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This report presents the results of the propellant frosting and system blockage investigation. The purpose was to determine the conditions that affect propellant forsting and system blockage resulting from valve leakage in a space environment. Tests were conducted at simulated altitudes of 250,000 and 500,000 feet and programmed leak rates of 18 to 40 ccsec. No attempt was made to determine ignition characteristics as the system used was a single propellant system. Forty-eight tests were conducted with N2O4 and two with 50 N2H4-50 UDMH. Analysis of the data revealed that propellant valve leakage does produce system blockage and is a potential hazard to system operation. Although the injectors were never blocked in any of the runs made, motion-picture observation indicated that long-duration runs Greater than 1 hour would result in injector blockage. The conclusions reached indicate that additional effort should be expanded in this area to establish initial conditions that can cause blockage and system failure. Author
- Liquid Rocket Propellants