Dual pressure solid propellant control system

Details Dual pressure solid propellant control system Dual pressure solid propellant control system

1982-06-28

1985-11-05

Jordan, Charles T.

Aeronautics and astronautics

Missile stabilization or trajectory control

Automatic guidance

244169, F41G 700

Patent

active

045508887

ABSTRACT:
A dual pressure solid propellant control system capable of operating at temperatures of approximately 3000.degree. F. and at multiple pressures. A solid propellant gas generator is connected to a plurality of valve clusters by a manifold, the valves and manifold being of a high temperature material and each valve being independently operable. A pressure feedback loop maintains the system pressure at a commanded value by effectively increasing or decreasing the gas exit area by varying the pulse duration modulation of the valves.

REFERENCES:
patent: 3139725 (1964-07-01), Webb
patent: 3243313 (1966-03-01), Aves
patent: 3478965 (1969-11-01), Llewellyn
patent: 3736749 (1973-06-01), Kretschmer et al.

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