[특허]System and method for attitude control of a flight vehicle using pitch-over thrusters

Raytheon Company

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System and method for attitude control of a flight vehicle using pitch-over thrusters

국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F42B-015/01 F42B-010/00 F42B-015/00
미국특허분류(USC)	244/003.21; 244/003.1; 244/003.15; 244/003.22; 244/158.1; 244/171.1
출원번호	UP-0470900 (2006-09-07)
등록번호	US-7851732 (2011-02-10)
발명자 / 주소	Brinkerhoff, Robert S. Mahnken, Michael J. Loehr, Richard D. Cook, James M
출원인 / 주소	Raytheon Company
대리인 / 주소	Gifford, Eric A.
인용정보	피인용 횟수 : 6 인용 특허 : 29

초록

A reliable and inexpensive attitude control system uses a plurality of pitch-over thrusters to perform rapid and precise attitude maneuvers for a flight vehicle. The pitch-over thrusters create rotational moments that directly pitch and yaw the flight vehicle. The use of very simple thrusters and control techniques provides for a reliable and cost effective solution. The ability to perform overlapping pitch and yaw maneuvers with single-shot fixed-impulse thrusters provides for high-speed maneuverability.

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We claim: 1. An attitude control system for a flight vehicle selected from a missile, kill vehicle (KV) or space craft, comprising: at least four thrusters on the flight vehicle and displaced from the vehicle center of gravity, said thruster generating thrust vectors with a fixed impulse that produce rotational moments to directly pitch and yaw the flight vehicle; and a fire controller configured to issue start firing commands to a first set of said thrusters to slew the flight vehicle and to issue stop firing commands to a second set of said thrusters to stop the flight vehicle at a specified pitch and yaw. 2. The attitude control system of claim 1, wherein all of the thrusters generate thrust vectors with the same fixed impulse. 3. The attitude control system of claim 1, wherein each thruster can generate a single fixed impulse thrust vector. 4. The attitude control system of claim 3, further comprising multiple sets of said at least four thrusters to perform respective attitude control maneuvers. 5. An attitude control system-for a flight vehicle selected from a missile, kill vehicle (KV) or space craft, comprising: at least four thrusters on the flight vehicle and displaced from the vehicle center of gravity, said thrusters including a first pair of thrusters whose thrust vectors are collinear in a pitch plane and a second pair of thrusters whose thrust vectors are collinear in a yaw plane that produce rotational moments to directly pitch and yaw the flight vehicle; and a fire controller configured to issue start firing commands to a first set of said thrusters to slew the flight vehicle and to issue stop firing commands to a second set of said thrusters to stop the flight vehicle at a specified pitch and yaw. 6. An attitude control system for a flight vehicle selected from a missile, kill vehicle (KV) or space craft, comprising: at least four thrusters on the flight vehicle and displaced from the vehicle center of gravity so that their thrust vectors produce rotational moments to directly pitch and yaw the flight vehicle; and a fire controller configured to store a table of start and stop times for a plurality of yaw and pitch maneuvers for issuing start and stop firing commands, for a specified maneuver said fire controller issues start firing commands to a first set of said thrusters to slew the flight vehicle and issues stop firing commands to a second set of said thrusters to stop the flight vehicle at a specified pitch and yaw. 7. The attitude control system of claim 6, wherein the fire controller operates open loop and issues the start and stop firing commands at the times stored in the table for the specified pitch and yaw. 8. The attitude control system of claim 6, wherein the fire controller issues the start firing commands at the times stored in the table for the specified pitch and yaw, receives measurements of the pitch and yaw as the vehicle slews and adjusts the stop times stored in the table to issue the stop firing commands. 9. An attitude control system for a flight vehicle selected from a missile, kill vehicle (KV) or space craft, comprising: at least four thrusters on the flight vehicle and displaced from the vehicle center of gravity so that their thrust vectors produce rotational moments to directly pitch and yaw the flight vehicle; and a fire controller configured to issue start firing commands to a first set of said thrusters to slew the flight vehicle so that the pitch and yaw slewing overlap at least partially in time and to issue stop firing commands to a second set of said thrusters to stop the flight vehicle at a specified pitch and yaw. 10. An attitude control system for a flight vehicle selected from a missile, kill vehicle (KV) or space craft, comprising: a first pair of thrusters on the flight vehicle and displaced from the vehicle center of gravity, each said thruster being configured to generate a single thrust vector with a fixed-impulse to produce a rotational moment to slew the vehicle in a pitch plane; a second pair of thrusters on the flight vehicle and displaced from the vehicle center of gravity, each said thruster being configured to generate a single thrust vector with a fixed-impulse to produce a rotational moment to slew the vehicle in a yaw plane; a look-up table that stores start and stop firing times for said first and second pairs of thrusters for a plurality of pitch and yaw maneuvers; and a fire controller that looks up the start and stop firing times for a specified pitch and yaw maneuver, issues start firing commands to one of the thrusters in each of said first and second pairs at said start firing times to slew the flight vehicle, and issues stop firing commands to the other one of said thrusters in each of said first and second pairs based on said stop firing times to stop the flight vehicle at the specified pitch and yaw maneuver. 11. The attitude control system of claim 10, wherein the fire controller operates open loop and issues the stop firing commands at the times stored in the table for the specified pitch and yaw maneuver. 12. The attitude control system of claim 10, wherein the fire controller receives measurements of the pitch and yaw as the vehicle slews and adjusts the stop times stored in the table to issue the stop firing commands. 13. The attitude control system of claim 10, wherein fire controller issues the start firing commands so that the pitch and yaw slewing overlap at least partially in time. 14. The attitude control system of claim 10, wherein the pitch and yaw maneuver from the first start firing command to the last stop firing command takes less than 200 ms. 15. An active protection system, comprising: a threat detection system for detecting and tracking a target and providing a launch command and pitch and yaw commands for a desired attitude to the target; a missile having a main thruster for providing thrust, a long a body axis of the missile and at least four thrusters displaced from the missile center of gravity whose thrust vectors produce rotational moments to directly pitch and yaw the missile; a launch thruster to launch the missile upon receipt of the launch command; and a fire controller on the missile configured to issue start firing commands to a first set of said thrusters to slew the missile and to issue stop firing commands to a second set of said thrusters to stop the missile at a specified pitch and yaw to achieve the desired attitude to the target, said fire controller then issuing a command to ignite the main thruster to fire the missile along the desired attitude to the target. 16. The active protection system of claim 15, wherein the thrusters generate thrust vectors with a fixed-impulse, said fire controller further comprising a look-up table that stores start and stop firing times for said thrusters for a plurality of pitch and yaw commands. 17. The active protection system of claim 16, wherein said at least four thrusters includes a first and second pairs of thrusters that slew the missile in pitch and yaw planes, respectively, said look-up tablestoring one start and one stop time for each pair. 18. The active protection system of claim 16, wherein the fire controller operates open loop and issues the stop firing commands at the times stored in the table for the specified pitch and yaw maneuver. 19. The attitude control system of claim 16, wherein the fire controller receives measurements of the pitch and yaw as the vehicle slews and adjusts the stop times stored in the table to issue the stop firing commands. 20. The attitude control system of claim 16, wherein fire controller issues the start firing commands so that the pitch and yaw slewing overlap at least partially in time. 21. An attitude control system for a flight vehicle selected from a missile, kill vehicle (KV) or space craft, comprising: at least four thrusters on the flight vehicle and displaced from the vehicle center of gravity so that their thrust vectors produce rotational moments to directly pitch and yaw the flight vehicle in pitch and yaw planes, respectively; and a fire controller configured to issue start firing commands to a first set of said thrusters to slew the flight vehicle and to issue stop firing commands to a second set of said thrusters so that the sum of the rotational moments in each of the pitch and yaw planes is zero to stop the flight vehicle at a specified pitch and yaw. 22. The attitude control system of claim 21, wherein all of the thrusters are displaced the same distance from the center of gravity, the total impulse of the first set of thrusters is equal to the total impulse of the second set of thrusters. 23. The attitude control system of claim 22, wherein each said thruster produces the same fixed-impulse.

이 특허에 인용된 특허 (29)

이 특허를 인용한 특허 피인용횟수: 6

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System and method for attitude control of a flight vehicle using pitch-over thrusters

초록

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System and method for attitude control of a flight vehicle using pitch-over thrusters

초록

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이 특허에 인용된 특허 (29)

이 특허를 인용한 특허 피인용횟수: 6

IPC 상위 출원인

상세정보조회

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IPC 상세정보(version : 201201)

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