Patent ID: 6619031
Filing Date: 2003-09-16
Classification: B64G,F02K

Abstract:
A multi-mode multi-propellant rocket engine capable of operating in a plurality of selected modes comprising, in combination,a combustor chamber opening through a throat into a wide nozzle; a propellant injector head in said combustor chamber; a propellant fuel supply tank containing liquid hydrogen; a propellant oxidizer supply tank containing liquid oxygen; a jacket covering said combustor chamber and nozzle and defining therewith a heat exchange chamber; a hydrogen pump for supplying liquid hydrogen fuel from said hydrogen supply tank through said jacket heat exchanger to said injector head; a control valve for controlling the supply of liquid hydrogen to said injector head; an air liquefaction chamber for receiving and liquefying air; a mixer for receiving liquefied air from said air liquefaction chamber and liquid oxygen from said oxygen supply tank and mixing the same; an oxidizer pump for supplying liquid oxygen from said oxidizer supply tank to said injector head, for supplying a mixture of liquid oxygen and liquid air to said injector head and for supplying a mixture of liquid oxygen and liquid air to said air liquefaction chamber; a spray manifold in said air liquefaction chamber for receiving said liquid air and liquid oxygen mixture and spraying the same into the air being liquefied; a heat exchanger in said air liquefaction chamber for receiving liquid hydrogen from said liquid hydrogen supply pump, said liquid hydrogen heat exchanger cooling said air to effect liquefaction thereof; a control valve for controlling the supply of liquefied air and injected oxygen to said mixer; an oxygen pump for supplying liquid oxygen and liquid air oxidizer from said mixer to said injector head; a control valve for controlling the supply of liquid oxygen and liquid air to said injector head; and a turbine for operatively receiving a supply of expanded hydrogen for driving said hydrogen pump and said oxygen pump; the operation of said control valves determining and controlling the ratio of propellant fuel and oxidizer components in each mode of operation of the rocket engine.