[특허]Integrated propulsion and attitude control system from a common pressure vessel for an interceptor

Raytheon Company

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Integrated propulsion and attitude control system from a common pressure vessel for an interceptor

국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F42B-010/66 F42B-015/01 F42B-010/00 F42B-015/00
미국특허분류(USC)	244/003.22; 244/003.1; 244/003.15; 244/003.21; 244/003.24
출원번호	US-0551221 (2012-07-17)
등록번호	US-8975565 (2015-03-10)
발명자 / 주소	Strassman, Doron Elkanick, Mark E.
출원인 / 주소	Raytheon Company
대리인 / 주소	Gifford, Eric A.
인용정보	피인용 횟수 : 0 인용 특허 : 11

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An interceptor is provided with an integrated propulsion and attitude control system (ACS) in which propellant burn forms a common pressure vessel for high-pressure gas. An aft port in the rocket motor directs gas through one or more main nozzles that expel high-velocity gas in a generally axial direction to propel the interceptor. A forward port directs gas through one or more attitude control nozzles that expel high-velocity gas in a generally radial direction to control the attitude of the interceptor. The main nozzle(s) and stabilization fins are fix...

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1. An interceptor, comprising: an airframe;a plurality of fixed aerodynamic stabilization fins on the airframe;a rocket motor within the airframe, said motor comprising a motor can having ports forward and aft and a rocket propellant therein, wherein propellant burn forms a common pressure vessel for high-pressure gas;one or more fixed main nozzles having a throat in communication with the aft port and the common pressure vessel to convert high-pressure gas into a first high-velocity gas and expel the first high-velocity gas in a generally axial direction to propel the interceptor;an attitude control system (ACS) comprising, one or more fixed attitude control nozzles having a throat in communication with the forward port and the common pressure vessel to convert high-pressure gas into a second high-velocity gas and expel the second high-velocity gas through one or more output ports in generally radial directions offset from a center of gravity (Cg) of the interceptor to change the attitude of the interceptor; andone or more valves to control the flow of the second high-velocity gas through the one or more attitude control nozzles; anda flight control system responsive to guidance commands to command the one or more valves to direct flow through the one or more attitude control nozzles to maneuver the interceptor. 2. The interceptor of claim 1, wherein the interceptor is less than 6.8 kilograms, 61 cm in length and 8 cm in diameter. 3. The interceptor of claim 1, wherein the attitude control system uses less than 10% of the energy produced from propellant burn. 4. The interceptor of claim 1, wherein the rocket propellant is configured to either burn radially inside-to-out or axially from both ends. 5. The interceptor of claim 1, wherein the one or more main nozzles are configured to expel the first high-velocity gas to impart a roll to the interceptor, said one or more attitude control nozzles comprising a single attitude control nozzle that expels the second high-velocity gas through the output port in the generally radially direction to control pitch and yaw of the interceptor. 6. The interceptor of claim 1, where said one or more attitude control nozzles comprise first, second, third and fourth attitude control nozzles placed around the airframe to expel the second high-velocity gas through respective output ports in generally radially directions that are each offset from the center of the airframe to control pitch, yaw and roll of the interceptor. 7. The interceptor of claim 6, wherein each of the first, second, third and fourth attitude control nozzles includes its own throat. 8. The interceptor of claim 6, wherein the first, second, third and fourth attitude control nozzles share a common throat that converts the high pressure gas to the high-velocity gas. 9. The interceptor of claim 8, wherein the common throat comprises a Mach 1 choke port. 10. The interceptor of claim 6, wherein the valves are binary on/off valves, and wherein all the valves are normally on and are turned off to control pitch, yaw and roll. 11. An interceptor, comprising: an airframe;a plurality of fixed aerodynamic stabilization fins on the airframe;a rocket motor within the airframe, said motor comprising a motor can having ports forward and aft and a rocket propellant therein, wherein propellant burn forms a common pressure vessel for high-pressure gas;one or more fixed main nozzles having a throat in communication with the aft port and the common pressure vessel to convert high-pressure gas into a first high-velocity gas and expel the first high-velocity gas in a generally axial direction to propel the interceptor;an attitude control system (ACS) comprising, four fixed attitude control nozzles including a common throat in communication with the forward port and the common pressure vessel to convert high-pressure gas into a second high-velocity gas and first, second, third and fourth output ports placed around the airframe offset from a center of gravity (Cg) of the interceptor to expel the second high-velocity gas in generally radially directions that are each offset from the center of the airframe to change the pitch, yaw and roll of the interceptor; andfirst, second, third and fourth valves to control the flow of the second high-velocity gas through the respective attitude control nozzles; anda flight control system responsive to guidance commands to command the one or more valves to direct flow through the attitude control nozzles to maneuver the interceptor in yaw, pitch and roll. 12. The interceptor of claim 11, wherein the flight control system commands different pairs of the four valves to direct flow of the second high-velocity gas through different pairs of the four attitude control nozzles to maneuver the interceptor in yaw, pitch and roll. 13. The interceptor of claim 11, wherein the interceptor is less than 6.8 kilograms, 61 cm in length and 8 cm in diameter. 14. The interceptor of claim 11, wherein the attitude control system uses less than 10% of the energy produced from propellant burn. 15. An interceptor, comprising: an airframe;a plurality of fixed aerodynamic stabilization fins on the airframe;a rocket motor within the airframe, said motor comprising a motor can having ports forward and aft and a rocket propellant therein, wherein propellant burn forms a common pressure vessel for high-pressure gas;one or more fixed main nozzles having a throat in communication with the aft port and the common pressure vessel to convert high-pressure gas into a first high-velocity gas and expel the first high-velocity gas in a generally axial direction to propel the interceptor and to impart roll to the interceptor;an attitude control system (ACS) comprising, a single fixed attitude control nozzle having a throat in communication with the forward port and the common pressure vessel to convert high-pressure gas into a second high-velocity gas and expel the second high-velocity gas through an output port in a generally radial directions offset from a center of gravity (Cg) of the interceptor; anda valve to control the flow of the second high-velocity gas through the attitude control nozzle; anda flight control system responsive to guidance commands to command the valve to direct flow through the attitude control nozzle to maneuver the interceptor in yaw and pitch. 16. The interceptor of claim 15, wherein the interceptor is less than 6.8 kilograms, 61 cm in length and 8 cm in diameter. 17. The interceptor of claim 15, wherein the attitude control system uses less than 10% of the energy produced from propellant burn.

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Integrated propulsion and attitude control system from a common pressure vessel for an interceptor

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Integrated propulsion and attitude control system from a common pressure vessel for an interceptor

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IPC 상세정보(version : 201201)

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