[특허]Propulsion and maneuvering system with axial thrusters and method for axial divert attitude and control

Raytheon Company

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Propulsion and maneuvering system with axial thrusters and method for axial divert attitude and control

국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F42B-015/01 F41G-007/22 F42B-010/60 F42B-015/00 F41G-007/00 F42B-010/00
미국특허분류(USC)	244/003.22; 244/003.1; 244/003.15; 244/003.16; 244/003.19; 244/003.21
출원번호	US-0030307 (2011-02-18)
등록번호	US-8735788 (2014-05-27)
발명자 / 주소	Preston, Kenneth G. Leal, Michael A. Wilson, Rondell J. Hussey, Richard C.
출원인 / 주소	Raytheon Company
대리인 / 주소	Schwegman, Lundberg & Woessner, P.A.
인용정보	피인용 횟수 : 14 인용 특허 : 35

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Embodiments of a propulsion and maneuvering system that may be suitable for use during a terminal phase in an interceptor are generally described herein. The propulsion and maneuvering system may include one or more axial thrusters to provide thrust along axial thrust lines that run through a center-of-gravity of the interceptor and a plurality of divert thrusters to provide thrust in radial directions. The combination of divert and axial thrusters may allow the interceptor to respond to a maneuvering target and may allow the interceptor to increase its ...

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1. A propulsion and maneuvering system for use during a terminal phase of an interceptor, the system comprising: one or more axial thrusters to provide thrust along axial thrust lines that run through a center-of-gravity of the interceptor;a plurality of divert thrusters to provide thrust in radial directions; anda common propellant distribution manifold for distributing pressurized fuel to both the axial thrusters and the divert thrusters. 2. The propulsion and maneuvering system of claim 1 wherein the propulsion and maneuvering system includes two axial thrusters, and wherein each of the axial thrusters is canted at an angle with respect to an axial direction. 3. The propulsion and maneuvering system of claim 2 wherein providing thrust along the axial thrust lines allows a seeker of the interceptor to maintain a line-of-sight (LOS) with a target as the axial thrusters are engaged. 4. The propulsion and maneuvering system of claim 3 further comprising: a propulsion system controller; anda set of valves to control a release of the pressurized fuel from the common propellant distribution manifold in response to control signals from the propulsion system controller,wherein the propulsion system controller is to configure the valves regulate the release of the pressurized fuel between the axial thrusters and one or more of the divert thrusters to allow varying amounts of thrust to be provided axially and laterally. 5. The propulsion and maneuvering system of claim 4 wherein the seeker is configured to track the target and maintain the LOS with the target as the target maneuvers, wherein the seeker is further configured to generate command signals for the propulsion system controller, andwherein based on the command signals from the seeker, the propulsion system controller is configured to:recalculate an intercept point with the target and control the valves to selectively deploying a combination of both the axial thrusters and the divert thrusters to change a burn-out velocity (Vbo) of the interceptor and cause the interceptor to follow a flight path to the recalculated intercept point. 6. The propulsion and maneuvering system of claim 5 wherein the propulsion system controller is configured to determine when the target is maneuvering based on changes in an angle between the LOS and the flight path of the interceptor. 7. The propulsion and maneuvering system of claim 5 wherein the valves include: at least one axial thrust control valve coupled to the common propellant distribution manifold and configured for selectively releasing pressurized fuel into combustion chambers of one or more of the axial thrusters for mixing and combustion to provide the axial thrust and to increase a velocity along the LOS; andat least one maneuver control valve coupled to the common propellant distribution manifold and configured for selectively releasing pressurized fuel into combustion chambers of one or more of the divert thrusters for mixing and combustion to provide lateral thrust for maneuvering the interceptor. 8. The propulsion and maneuvering system of claim 7 wherein the propulsion system controller is configured to control at least one maneuver control valve and at least one axial thrust control valve in response to a comparison of a commanded propellant mass flow discharge rate and a calculated actual propellant mass flow discharge rate from the pressure vessel. 9. The propulsion and maneuvering system of claim 8 wherein the controller includes a burn-rate controller configured to calculate a burn rate from a measured pressure within pressurization tanks and to control the valves to adjust the burn rate in response to a comparison between the measured pressure and an estimated pressure based on the recalculated intercept point. 10. The propulsion and maneuvering system of claim 2 wherein when the propulsion and maneuvering system includes two axial thrusters provided at an aft-end of the interceptor and four of the divert thrusters provided at ninety-degree radial positions on the interceptor, and wherein the net sum of the axial thrusters is configured to provide at least twice an amount of thrust of any of the divert thrusters. 11. The propulsion and maneuvering system of claim 1 wherein the interceptor is a liquid-fueled interceptor, and wherein the propulsion and maneuvering system further comprises a fuel tank and an oxidizer tank, andwherein one of the fuel tank and the oxidizer tank has a toroidal shape when provided between the divert thrusters and the axial thrusters of the interceptor. 12. The propulsion and maneuvering system of claim 1 wherein the interceptor is a solid-fueled interceptor. 13. A method for operating a propulsion and maneuvering system for intercepting a target, the method comprising: providing a control signal from a seeker in response to tracking the target for intercepting the target;controlling a release of pressurized fuel from a common propellant distribution manifold between axial thrusters and one or more divert thrusters of an interceptor in response to the control signal; andvarying amounts of thrust to be provided axially and laterally in response to the release of pressurized fuel. 14. A method for operating a propulsion and maneuvering system for intercepting a target, the method comprising: providing a control signal from a seeker in response to tracking the target;controlling a release of pressurized fuel between axial thrusters and one or more divert thrusters of an interceptor in response to the control signal;varying amounts of thrust to be provided axially and laterally in response to the release of pressurized fuel;determining when the target is maneuvering; andproviding axial thrust to increase a velocity along a line-of-sight (LOS) with the target to reduce target impact time in response to a determination that the target is maneuvering. 15. The method of claim 14 wherein providing axial thrust comprises providing the axial thrust along axial thrust lines that run through a center-of-gravity of the interceptor. 16. The method of claim 15 further comprising: maintaining the LOS with the target using a seeker; anddetermining when the target is maneuvering the based on changes in an angle between a LOS to the target and a flight path of the interceptor. 17. The method of claim 16 further comprising configuring a set of valves to control the release of the pressurized fuel from a common propellant distribution manifold to the axial thrusters and one or more divert thrusters in response to control signals from the seeker. 18. An interceptor comprising: a seeker configured to maintain a line-of-sight (LOS) with a target; andthe propulsion and maneuvering system that includes:one or more axial thrusters to provide thrust along axial thrust lines that run through a center-of-gravity of the interceptor;a plurality of divert thrusters to provide thrust in radial directions; anda propulsion system controller responsive to control signals from the seeker to regulate a release of pressurized fuel between the axial thrusters and one or more of the divert thrusters to allow varying amounts of thrust to be provided axially and laterally to intercept the target. 19. The interceptor of claim 18 wherein the propulsion system controller is configured to determine when the target is maneuvering and increase an amount of axial thrust to increase velocity along the LOS to reduce target impact time. 20. The interceptor of claim 19 further comprising: a common propellant distribution manifold for distributing pressurized fuel to both the axial thrusters and the divert thrusters; anda set of valves to control a release of the pressurized fuel from the common propellant distribution manifold in response to control signals from the propulsion system controller. 21. A method for intercepting a target comprising: identifying when the target is maneuvering to generate control signals based on changes in an angle between a line-of-sight (LOS) to the target and a flight path of an interceptor; andcontrolling a release of pressurized fuel between axial thrusters and divert thrusters to allow varying amounts of thrust to be provided axially and laterally in response to the control signals. 22. The method of claim 21 further comprising providing axial thrust to increase velocity along the LOS to reduce target impact time.

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이 특허를 인용한 특허 피인용횟수: 14

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Propulsion and maneuvering system with axial thrusters and method for axial divert attitude and control

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Propulsion and maneuvering system with axial thrusters and method for axial divert attitude and control

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