Patent ID: 8215097
Filing Date: 2012-07-10
Classification: F02K

Abstract:
1. A rocket thruster assembly comprising: a nozzle comprising an interior surface bounding a passageway including a converging region that converges in cross section into a throat region, and a diverging region located aft of the throat; a substantially annular inner feed chamber in communication with the converging region of the nozzle, an outer feed chamber surrounding the inner feed chamber, and at least one aperture extending through a wall therebetween; a valve subassembly comprising a pintle with a head portion coaxial with the passageway and having a truncated, substantially conical surface region facing the converging region and the throat region; a bleed passageway opening to the nozzle passageway in communication with a passage leading through the head portion from the truncated, substantially conical surface region to a bleed cavity located adjacent an opposite side of the head portion; and a thrust control subassembly comprising an actuator operatively coupled to the pintle for moving the pintle axially back and forth relative to the throat region and retaining the pintle at a plurality of open positions in which the head portion is spaced from the interior surface of the nozzle, and at a closed position in which the head portion contacts the interior surface of the nozzle to close at least one of the throat region and the converging region of the passageway.