Fuel injection subsystem for supersonic combustion
阅读：653发布：2021-07-17
专利汇可以提供Fuel injection subsystem for supersonic combustion专利检索，专利查询，专利分析的服务。并且A fuel injection subsystem for a missile having an engine provided with a predetermined fixed geometry for subsonic and supersonic operation. The subsystem utilizes both solid and liquid fuels to provide a multiplicity of engine operating conditions. According to the operating requirements, a central control station provided for gases from the solid fuel to: (a) be ducted to various points in the combustor; (b) pressurize the liquid fuel tanks, and; (c) function as a pilot light for the liquid propellant. The liquid fuels are: (a) throttled for variable flow; (b) secondarily injected to redirect hot gases from the solid fuel, and; (c) used as a regenerative coolant.，下面是Fuel injection subsystem for supersonic combustion专利的具体信息内容。
1. A missile having a propulsion system including solid and liquid propellants for operation of said missile at subsonic and supersonic velocities comprising: a casing enclosing said solid propellant and having a first combustion chamber for expanding gases produced by said solid propellant responsive to ignition thereof; a tank enclosing a liquid propellant, said tank disposed in communication with said first combustion chamber for receiving said gases for pressurizatiOn of said tank to effect liquid propellant flow therefrom; a second combustion chamber having an air inlet for passage of air therein and first and second groups of injection ports, each group respectively disposed in fluid communication with said first combustion chamber and said liquid propellant tank; directing means disposed for selectively routing said gases and said liquid propellant to said first group of said injection ports for the supersonic combustion or to a second plurality of injection ports for subsonic combustion; control means disposed for actuating said directing means for the routing of said gases and said liquid propellant.
2. A missile propulsion system as in claim 1 wherein said directing means includes a pair of fluid valves, the first of said fluid valves disposed in communication with said first combustion chamber and provided with a pair of outlets, the first of said outlets disposed in communication with the atmosphere, the second of said outlets having said second fluid valve disposed therein, said second fluid valve having a pair of outlets respectively disposed in communication with said groups of injection ports for selectively directing said gases therein.
3. A propulsion system as in claim 2 wherein said directing means further includes mechanism for injecting said liquid propellant into said fluid valves to divert the direction of said gases passing therethrough to a selected one of said outlets.
4. A propulsion system as in claim 3 including a plurality of conduits connecting said liquid propellant tank to said second combustion chamber and flow control means carried in said conduits to control the flow of said liquid propellant.
5. A propulsion system as in claim 4 including a conduit connecting said solid propellant to said liquid propellant tank, and pressure control means carried in said conduit to control the pressure of said gases entering said liquid fuel tank for pressurization thereof.
6. A propulsion system as in claim 5 including a plurality of cooling jackets disposed in communication with said liquid propellant tank to receive said liquid propellant therefrom, said cooling jackets disposed for cooling said gases entering said liquid propellant tank and said second combustion chamber.
7. A propulsion system as in claim 6 wherein said liquid propellant tank is provided with a diaphragm for coacting with said gases entering said propellant tank.
8. A missile propulsion system as in claim 7 wherein said control means includes a central control station disposed for receiving signals from predetermined points through said system indicative of missile speed and altitude, liquid propellant tanks pressurization and temperature, solid propellant pressure and temperature, and engine operating requirements, said control station disposed for operation of said fluid valves, said pressure control means, and said flow control means responsive to receiving said signals, whereby said propulsion system operates in the supersonic or subsonic mode.
9. A missile propulsion system as in claim 8 wherein said second combustion chamber is provided with a nozzle and said first of said groups of injection ports are disposed in the forward portion of said second combustion chamber in proximity of said air inlet and disposed to receive said liquid propellant therein, and said second of said groups of said injection ports disposed in said combustion chamber rearwardly of said first group and disposed to receive said gases from said solid propellant, whereby said liquid propellant, said gases and said air entering said air inlet are mixed in said second combustion chamber and discharged through said nozzle for the supersonic combustion.
10. A propulsion system as in claim 9 wherein said fluid valves are a pair of fluid amplifiers.
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