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A variable cycle propulsion system for a supersonic airplane, the system comprising at least one engine having means for producing exhaust gas and a gas exhaust nozzle for generating thrust for supersonic flight speeds, and at least one separate auxiliary propulsion assembly dissociated from said en

A variable cycle propulsion system for a supersonic airplane, the system comprising at least one engine having means for producing exhaust gas and a gas exhaust nozzle for generating thrust for supersonic flight speeds, and at least one separate auxiliary propulsion assembly dissociated from said engine, having no gas generator, and capable of generating thrust for takeoff, landing, and subsonic flight speeds. The system further comprises gas flow tapping means movable between a position in which they tap off at least a fraction of the exhaust gas produced by said engine and feed it to said propulsion assembly to enable it to generate thrust for takeoff, landing, and subsonic cruising flight, and a position in which the gas produced by the engine is directed solely to the engine nozzle for supersonic cruising flight.

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1. A variable cycle propulsion system for a supersonic airplane, the system comprising:at least one engine comprising means for producing exhaust gas and a gas exhaust nozzle configured to generate thrust for supersonic flight speeds; a propulsion assembly dissociated from said engine, having no gas

1. A variable cycle propulsion system for a supersonic airplane, the system comprising:at least one engine comprising means for producing exhaust gas and a gas exhaust nozzle configured to generate thrust for supersonic flight speeds; a propulsion assembly dissociated from said engine, having no gas generator, and configured to generate thrust for takeoff, landing, and subsonic flight speeds; and gas flow tapping means movable between a position in which the gas flow tapping means taps off at least a portion of the exhaust gas and feeds the tapped off exhaust gas to said propulsion assembly for generating thrust for takeoff, landing, and subsonic cruising flight, and a position in which the exhaust gas is directed solely to the engine nozzle for supersonic cruising flight, wherein the propulsion assembly comprises a turbine and a fan configured to be rotated by the turbine, and wherein the propulsion assembly is integrated within a fuselage of the airplane and configured to reduce drag and to improve sound insulation, and wherein the at least one engine comprises at least two engines configured to feed the propulsion assembly with gas. 2. The system according to claim 1, wherein the gas flow tapping means comprises flaps and a tube opening into an inlet of the turbine.3. The system according to claim 1, wherein the at least one engine comprises at least three engines configured to feed the propulsion assembly.4. The system according to claim 1, wherein the at least one engine comprises at least two engines, and the propulsion assembly is offset from both engines.5. A propulsion system comprising:at least one engine configured to generate an exhaust gas, the engine comprising a nozzle; a propulsion assembly disposed within a fuselage of an airplane; and means for directing a portion of the exhaust gas otherwise directed to the nozzle to the propulsion assembly under a first set of conditions, wherein the at least one engine comprises at least two engines. 6. The system according to claim 5, wherein the first set of conditions comprises at least one of takeoff, landing, and subsonic flight.7. The system according to claim 6, wherein the first set of conditions comprises takeoff, landing, and subsonic flight.8. The system according to claim 5, wherein the means is configured to direct all the exhaust gas to the nozzle during supersonic flight.9. The system according to claim 5, wherein the propulsion assembly is not configured to generate an exhaust gas.10. The system according to claim 5, wherein the propulsion assembly comprises a turbine and a fan configured to be rotated by the turbine.11. The system according to claim 5, wherein the at least two engines comprises three engines.12. The system according to claim 5, wherein the means is disposed within the fuselage of the aircraft.13. The system according to claim 12, wherein the means comprises at least one of a flap positionable to permit and to prevent exhaust gas flow to the nozzle.