Importance

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Abstract

A solid propellant thrust control system, method, and apparatus for controlling combustion of solid propellants in an opposing grains solid propellant rocket engine (OGRE) is provided. In particular, an opposing grains rocket engine and propulsion system is provided, in which actuator means connected are connected to solid propellant grains disposed in the pressure vessel of the engine. The actuator means are operable to selectively move the solid propellant grains together or apart relative to one another, such that the burning ends of the solid propellant grains decrease or increase relative to one another. This action controls the rate of combustion of the solid propellant grains by varying spacing distance between the burning ends of the solid propellant grains, and enables extinguishment and reignition of the OGRE. Further, a method is providing for controlling the burn rate of solid propellant grains undergoing combustion in an opposing grains rocket engine.

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First Claim