Patent ID: 7464535
Filing Date: 2008-12-16
Classification: F02K

Abstract:
1. A rocket motor, comprising: a motor having an inner surface defining a combustion chamber, the combustion chamber configured to receive a propellant therein and supply combustion gas upon ignition of the propellant; a nozzle including at least an inlet section, a primary throat, and an outlet section fluidly coupled in flow-series, the nozzle inlet section in fluid communication with the combustion chamber and including an inner surface defining a nozzle inlet passage having a convergent cross sectional flow area, the nozzle outlet section including an inner surface defining a nozzle outlet flow passage having a divergent cross sectional flow area; an injection duct having an inlet port, an outlet port, and an injection flow passage there between, the inlet port adapted to receive a flow of fluid, the outlet port disposed downstream of, and in fluid communication with, the primary nozzle throat; and a control valve mounted on the injection duct and moveable between at least (i) a closed position, in which the injection duct inlet port is fluidly isolated from the injection duct outlet port, and (ii) an open position, in which the injection duct inlet port is fluidly coupled to the injection duct outlet port, whereby fluid supplied to the injection duct inlet port is injected downstream of the primary nozzle throat, wherein the fluid is injected one of either (i) radially into the throat or (ii) into the nozzle throat tangential to combustion gas flow through the nozzle throat.