[특허]Ballistic guidance control for munitions

BAE Systems Information and Electronic Systems Integration Inc.

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특허 상세정보

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내보내기 페이스북 공유 트위터 공유 카카오톡 공유

Ballistic guidance control for munitions

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F42B-015/01 F42B-010/60 F42B-010/62 F42B-015/00 F42B-010/00
미국특허분류(USC)	244/003.15; 244/003.16; 244/003.19; 244/003.21; 102/382; 102/384; 102/473; 102/501; 701/200; 701/224
출원번호	UP-0629060 (2006-02-07)
등록번호	US-7834300 (2011-01-16)
국제출원번호	PCT/US2006/004531 (2006-02-07)
§371/§102 date	20061208 (20061208)
국제공개번호	WO06/086528 (2006-08-17)
발명자 / 주소	Zemany, Paul D. Carlson, Mark A. Maynard, John A.
출원인 / 주소	BAE Systems Information and Electronic Systems Integration Inc.
대리인 / 주소	Sand & Sebolt
인용정보	피인용 횟수 : 10 인용 특허 : 30

초록
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A method and system for guiding and controlling an ordinance body having a trajectory and a bore sight angle including making corrections to the trajectory based on bore sight angle vs. time history. The system is incorporated with existing fuse components in a replacement kit for existing munitions. The method determines nominal time values of the ballistic trajectory of the munition in relation to launch time and determines deviation from the nominal time values by an algorithm by analyzing signals received from a source of radiation located at the tar...

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The invention claimed is: 1. A method for guiding and controlling a munition having an in-flight trajectory and a bore sight angle by making corrections to the ballistic trajectory based on an observed bore sight angle including the step of derolling the munition before making corrections to the trajectory by providing a Proportional-Integral-Derivative control loop; providing a pitch rate gyro for obtaining the proportional input to the control loop, a yaw rate gyro for obtaining the integral input, and a roll rate gyro for obtaining the derivative input; and supplying, pitch, yaw and roll steering commands to flight control surfaces mounted on the munition from signals received from the pitch, yaw and roll rate gyros for guiding and controlling the munition. 2. A method for guiding and controlling a munition having an in-flight trajectory toward a target comprising the steps of: determining nominal time values of the ballistic trajectory in relation to launch time values; determining deviation from the nominal time values of the munition during flight by an algorithm by analyzing signals received from the target; making up/down steering corrections to the munition based upon the deviation from the nominal time values to correct for range error; derolling the munition; determining a nominal look down angle of the munition to the target; determining a true look down angle of the munition by the algorithm analyzing signals received from the target; and applying upward corrections to the munition if the nominal angle is less than the true angle. 3. A system for guidance and control of a projectile following an in-flight path toward a target, said target having a homing signal being radiated therefrom, said system comprising: a plurality of guidance surfaces mounted on the projectile; a projectile guidance and control algorithm located in the projectile for supplying signals to the guidance surfaces for directing the projectile toward the target, said algorithm including: a roll angle estimator for determining the roll angle of the projectile; a roll controller for receiving signals from the roll angle estimator and for developing steering commands supplied to certain of the flight control surfaces for controlling the roll of the projectile; a trajectory estimator for estimating the trajectory of the projectile; a left/right (L/R) steering loop and an up/down (U/D) steering loop for supplying guidance signals to the flight control surfaces; and a seeker subsystem for receiving homing signals from the target and supplying error correction signals to the L/R and U/D steering loops for changing the trajectory of the projectile. 4. The system defined in claim 3 wherein the projectile includes a Ram Air Turbine (RAT) which inputs the launch speed and time of flight of the projectile to the trajectory estimator. 5. The system defined in claim 3 wherein the roll controller is a Proportional-Integral-Derivative (PID) loop; in which the projectile contains a roll gyro, a pitch gyro and a yaw gyro, said roll gyro supplying signals to the PID loop and said pitch and yaw gyros supplying signals to the roll angle estimator. 6. The system defined in claim 5 wherein the pitch and yaw gyros provide signals to a pitch/yaw oscillation estimator which supplies signals to the L/R and U/P steering loops. 7. A method for guiding and controlling a munition having an in-flight trajectory comprising the steps of determining the launch speed of the munition and the estimated flight time of the munition to apogee; estimating the trajectory of the munition based upon the estimated flight time to apogee and determined launch speed; determining the desired angle of attack (AOA) of the munition from the estimated trajectory; receiving homing signals from a target; determining the true angle of attack from the received homing signals; and supplying flight correction signals to flight control surfaces on the munition based upon deviations of the true angle of attack from the desired angle of attack. 8. The method defined in claim 7 including the step of derolling the munition before making corrections to the trajectory. 9. A method for guiding and controlling a munition having an in-flight trajectory by making corrections to the trajectory comprising the steps of receiving homing signals from the target; determining a nominal look down angle of the munition to the target; comparing the nominal look down angle to a seeker value derived from the homing signals; and applying an up/down steering command to a plurality of flight control surfaces mounted on the munition to compensate for a difference between the nominal look down angle and the seeker value. 10. A method for guiding and controlling a munition having an in-flight trajectory comprising the steps of providing an optical seeker on the munition; canting the optical seeker toward a target with respect to a central axis of the munition; looking at pixel crossing times with the optical seeker when a target homing device is emitting optical signals; and comparing the pixel crossing times to nominal crossing times of an allowable trajectory stored in a processor in the munition; and making corrections to the trajectory by supplying corrections to flight controls on the munition based upon deviations of the looked at pixel crossing times from the nominal crossing times. 11. A method for guiding and controlling a munition having an in-flight trajectory by making corrections to the trajectory comprising the steps of derolling the munition; receiving homing signals from a target; developing the bore sight angle of the munition from the homing signals; developing the time history of the munition by comparing an estimated trajectory of the munition against a nominal trajectory of the munition stored in a processor in the munition; and supplying steering commands to flight control surfaces of the munition for guiding and controlling the munition based upon the developed time history of the munition to control the trajectory of the munition. 12. A method for guiding and controlling a munition having an in-flight trajectory and a bore sight angle by making corrections to the trajectory based on observed bore sight angle including the steps of: receiving homing signals from a target as the munition follows the in-flight trajectory toward the target; generating steering commands based upon the received signals; providing said steering commands to a plurality of flight control surfaces mounted on the munition which includes the further steps of: estimating the munition's trajectory; matching the estimated trajectory against nominal trajectories stored in a processor in the munition to determine the true angle of attack (AOA); and providing up/down steering corrections to certain control surfaces based upon a comparison of the true vertical AOA against a desired AOA for range error correction. 13. The method defined in claim 12 including the steps of determining the remaining time of flight of the munition to the target; and combining said time with the estimated trajectory of the munition to determine the true vertical AOA. 14. A method for guiding and controlling a munition having an in-flight trajectory and a bore sight angle by making corrections to the trajectory based on observed bore sight angle including the steps of: receiving homing signals from a target as the munition follows the in-flight trajectory toward the target; providing the homing signal with a code; validating the homing signal code with respect to a code stored in a processor in the munition prior to arming the munition; generating steering commands based upon the received signals; and providing said steering commands to a plurality of flight control surfaces mounted on the munition. 15. The method defined in claim 14 wherein the step of providing steering commands includes the step of determining left/right centering error from the received signals and correcting any centering error by moving certain flight control surfaces. 16. A method for guiding and controlling a munition having an in-flight trajectory and a bore sight angle by making corrections to the trajectory based on observed bore sight angle including the steps of: determining the launch speed of the munition and the estimated flight time of the munition to the apogee of the trajectory; estimating the trajectory of the munition based upon the flight time to apogee and launch speed; determining the angle of attack (AOA) of the munition from the estimated trajectory; receiving homing signals from a target as the munition follows the in-flight trajectory toward the target; generating steering commands based upon the received signals; and providing said steering commands to a plurality of flight control surfaces mounted on the munition. 17. A method for guiding and controlling a munition having an in-flight trajectory and a bore sight angle by making corrections to the trajectory based on observed bore sight angle including the steps of: receiving homing signals from a target as the munition follows the in-flight trajectory toward the target; generating steering commands based upon the received signals; providing said steering commands to a plurality of flight control surfaces mounted on the munition; and sensing gravity induced overturning moment of the munition to provide a down reference to the munition for subsequently controlling the roll of the munition.

이 특허에 인용된 특허 (30)

이 특허를 인용한 특허 피인용횟수: 10

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Ballistic guidance control for munitions

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이 특허에 인용된 특허 (30)

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Ballistic guidance control for munitions

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이 특허에 인용된 특허 (30)

이 특허를 인용한 특허 피인용횟수: 10

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