Accession Number : AD0163905

Title :   Thrust Control System for Hybrid Rocket Motors.

Descriptive Note : Patent,

Corporate Author : DEPARTMENT OF THE AIR FORCE WASHINGTON D C

Personal Author(s) : Vickland,Clayton W.

Report Date : 18 JUL 1972

Pagination or Media Count : 3

Abstract : The patent relates to a tactical missile whereby a high specific impulse rocket motor having the impulse delivered at two thrust levels with restart capability has oxidizer supplied to an aft injector and to a plurality of primary injectors located within the forward ends of a plurality of fuel grain ports. The flow of oxidizer is controlled by two solenoid valves which control the sustain flow and the boost flow of oxidizer. Poppet valves are provided in the primary injectors and the aft injector and are opened by the pressure of the oxidizer delivered through the sustain system.

Descriptors :   (*CHECK VALVES, *PATENTS), (*HYBRID ROCKET ENGINES, *CONTROLLABLE-THRUST ROCKET MOTORS), SPECIFIC IMPULSE, HYPERGOLIC ROCKET PROPELLANTS, THRUST, CONTROL SYSTEMS

Subject Categories : Pumps, Filters, Pipes, Tubing, Fittings & Vlvs
      Guided Missiles

Distribution Statement : APPROVED FOR PUBLIC RELEASE