STORABLE PROPELLANT DATA FOR THE TITAN II PROGRAM
BELL AEROSYSTEMS CO BUFFALO NY
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Material compatibility tests were conducted with metals and nonmetals and the Titan II propellants, N2O4 as the oxidizer and a 5050 blend of UDMH and N2H4 as the fuel. Tests were conducted with butyl and ethylene-propylene rubbers to determine seal capabilities with 5050 fuel blend under pressures to 500 psig. Fire h zards of various materials were determined during separ te rip tests wi h N2O4 and 5050 fuel blend. Permeability data are pres nted from tests with various Teflons exposed to N2O4. Also presented is information regarding t e compatibility of lubricants with the Titan II propellants, obtained from contractors principally using this propellant combination.
- Liquid Rocket Propellants