On June 8, 1990, Aerojet Propulsion division successfully hot-fire tested a flightweight liquid bipropellant propulsion system designed to provide divert delta V to a space-intercept kinetic kill vehicle. The propulsion system verified in this test is directly applicable to SBE, GBI, and Brilliant Pebbles kill vehicles. The subject propulsion system was tested as an autonomous system with four divert thrusters, one each fuel and oxidizer tank, two helium bottles, eight cold gas ACS thrusters, manifolds, and accessory hardware. The hot-fire test demonstrated the following operations in a 30 second duty cycle which accumulated 267 divert engine firings and 1,446 ACS thruster pulses: (1) waterhammer is controlled during system activation; (2) thrust accuracy of divert and ACS thrusters is maintained within +/- ten percent; (3) the system mixture ratio differs from single engine steady state mixture ratio; (4) the feed system remained stable during various rapid divert and ACS thruster firing cycles; and (5) the 90 cc, 9500 psia helium storage is adequate to supply the ACE, Pressurize propellants, and operate bipropellant valves.
Flightweight Divert Propulsion System Hot-Fire Test
1990
7 pages
Report
Keine Angabe
Englisch
FLIGHTWEIGHT DIVERT PROPULSION SYSTEM HOT-FIRE TEST
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