[특허]Optically guided munition control system and method

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

Optically guided munition control system and method

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F42B-015/01 F42B-010/62 F42B-015/00 F42B-010/00
미국특허분류(USC)	244/003.16; 102/382; 102/384; 102/473; 102/501; 244/003.1; 244/003.15; 244/003.21; 244/003.24
출원번호	US-0632671 (2006-02-07)
등록번호	US-8450668 (2013-05-28)
국제출원번호	PCT/US2006/004157 (2006-02-07)
§371/§102 date	20080925 (20080925)
국제공개번호	WO2007/089243 (2007-08-09)
발명자 / 주소	Maynard, John A. Carlson, Mark A. Zemany, Paul D.
출원인 / 주소	BAE Systems Information and Electronic Systems Integration Inc.
대리인 / 주소	Sand & Sebolt
인용정보	피인용 횟수 : 2 인용 특허 : 38

초록
▼

An optically guided munition and control system has a replacement fuse assembly mounted on the front of a munition body or shell casing. An optical seeker subsystem detects an illuminated target and supplies signals to a processor. The processor develops steering commands sent to a flight control subsystem having a plurality of guidance canards which are actuated by drive motors through gear assemblies. The roll of the munition is established and left/right and up/down steering commands are sent to the canard drive motors based upon the optical seeker subsystem detection of the target illuminator. Range adjustment is based upon bore sight lockdown angle and cross range control is based upon left/right centering error. A code is contained in the optical radiation received from the illuminated target which must be validated by a preset code in the system processor to arm the munition.

대표
청구항
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1. A system contained in a munition for optically guiding and controlling the munition toward a target, said system comprising: an optical seeker subsystem for detecting an illuminated target;a processor subsystem including a selector device for setting an authentication code in the munition requiring a match against a code transmitted by the illuminated target to arm the munition; a roll sensor for sensing the roll of the munition, and for developing steering commands based upon signals received from the roll sensor and from the optical seeker subsystem; anda flight control subsystem for operating a plurality of canards based upon the steering commands received from the processor subsystem for guiding the munition toward the illuminated target. 2. The guidance and control system defined in claim 1 wherein the processor subsystem includes at least three gyros for detecting the pitch, yaw and roll of the munition. 3. A method for optically guiding and controlling a munition flying in a ballistic path toward a target comprising the steps of: a) illuminating the target;b) detecting the illuminated target by an optical seeker mounted in the munition;c) establishing roll control of the munition;d) tracking the flight path of the munition toward the target by detection of the illuminated target by the optical seeker;e) providing steering commands to a plurality of flight control canards mounted on the munition based upon roll control and outputs from the optical seeker of the illuminated target for guiding the munition toward the illuminated target;f) detecting a code contained in radiation received from the illuminated target; andg) validating the detected code with respect to a code preset in the munition prior to launch. 4. The method defined in claim 3 including the step of arming the munition when the detected code is validated. 5. The method defined in claim 3 wherein the step of providing steering commands includes the steps of determining left/right centering error from the optical seeker and correcting any centering aiming error by moving certain canards. 6. A system contained in a munition for optically guiding and controlling the munition toward a target, said system comprising: an optical seeker subsystem for detecting an illuminated target;a processor subsystem including a roll sensor for sensing the roll of the munition, and for developing steering commands based upon signals received from the roll sensor and from the optical seeker subsystem;a flight control subsystem for operating a plurality of canards based upon the steering commands received from the processor subsystem for guiding the munition toward the illuminated target; anda Ram Air Turbine (RAT) in the munition for supplying the processor subsystem with time of flight signals and apogee determination signals. 7. A system contained in a munition for optically guiding and controlling the munition toward a target, said system comprising: an optical seeker subsystem for detecting an illuminated target;a processor subsystem including a roll sensor for sensing the roll of the munition and for developing steering commands based upon signals received from the roll sensor and from the optical seeker subsystem;at least three gyros for detecting the pitch, yaw and roll of the munition, and a Proportional-Integral-Derivative (PID) control circuit which derives inputs from the three gyros to deroll the munition; anda flight control subsystem for operating a plurality of canards based upon the steering commands received from the processor subsystem for guiding the munition toward the illuminated target. 8. The guidance and control system defined in claim 7 wherein the optical seeker subsystem includes an optic seeker and a detector array. 9. The guidance and control system defined in claim 8 wherein the detector array includes a plurality of photodetectors. 10. A system contained in a munition for optically guiding and controlling the munition toward a target, said system comprising: an optical seeker subsystem for detecting an illuminated target;a processor subsystem including a roll sensor for sensing the roll of the munition, and for developing steering commands based upon signals received from the roll sensor and from the optical seeker subsystem;a flight control subsystem for operating a plurality of canards based upon the steering commands received from the processor subsystem for guiding the munition toward the illuminated target; anda drive assembly for operating the canards including at least three shafts and four canards, one of said shafts being a common shaft for operating a pair of said canards and the other two shafts, each independently controlling another of said canards. 11. The guidance and control system defined in claim 10 wherein the drive assembly further includes a drive motor operationally connected to each of the three shafts through a gear assembly. 12. A method for optically guiding and controlling a munition flying in a ballistic path toward a target comprising the steps of: a) illuminating the target;b) detecting the illuminated target by an optical seeker mounted in the munition;c) establishing roll control of the munition;d) tracking the flight path of the munition toward the target by detection of the illuminated target by the optical seeker;e) providing steering commands to a plurality of flight control canards mounted on the munition based upon roll control and outputs from the optical seeker of the illuminated target for guiding the munition toward the illuminated target;f) determining the flight time of the munition to apogee;g) estimating the trajectory of the munition based upon the flight time to apogee; andh) determining the angle of attack (ACM) of the munition from the estimated trajectory. 13. A method for optically guiding and controlling a munition flying in a ballistic path toward a target comprising the steps of: a) illuminating the target;b) detecting the illuminated target by an optical seeker mounted in the munition;c) establishing roll control of the munition;d) tracking the flight path of the munition toward the target by detection of the illuminated target by the optical seeker;e) establishing roll control of the munition including derolling the munition by providing a Proportional-Integral-Derivative control loop comprising providing a pitch rate gyro for obtaining the proportional input, a yaw rate gyro for obtaining the integral input, and a roll rate gyro for obtaining the derivative input; andf) providing steering commands to a plurality of flight control canards mounted on the munition based upon roll control and outputs from the optical seeker of the illuminated target for guiding the munition toward the illuminated target. 14. A method for optically guiding and controlling a munition flying in a ballistic path toward a target comprising the steps of: a) illuminating the target;b) detecting the illuminated target by an optical seeker mounted in the munition;c) establishing roll control of the munition;d) tracking the flight path of the munition toward the target by detection of the illuminated target by the optical seeker; ande) providing steering commands to a plurality of flight control canards mounted on the munition for guiding the munition toward the illuminated target based upon roll control and outputs from the optical seeker of the illuminated target including the further steps of estimating the munitions trajectory, matching the estimated trajectory against allowable trajectories stored in a processor in the munition to determine the true angle of attack (ACM), and providing up/down steering corrections to certain canards based upon a comparison of the true vertical AOA against the desired AOA for range error correction. 15. The method defined in claim 14 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. 16. A method for optically guiding and controlling a munition flying in a ballistic path toward a target comprising the steps of: a) illuminating the target;b) detecting the illuminated target by an optical seeker mounted in the munition, said optical seeker including seeker optics and a detector array;c) establishing roll control of the munition;d) tracking the flight path of the munition toward the target by detection of the illuminated target by the optical seeker;e) centering the detector array on an optical axis of said array;f) canting the optical seeker downwardly with respect to the longitudinal axis of the munition; andg) providing steering commands to a plurality of flight control canards mounted on the munition based upon roll control and outputs from the optical seeker of the illuminated target for guiding the munition toward the illuminated target. 17. The method defined in claim 16 wherein the optical seeker is canted downwardly at an angle of approximately 6° relative to the axis of the munition.

이 특허에 인용된 특허 (38)

이 특허를 인용한 특허 피인용횟수: 2

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Optically guided munition control system and method

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Optically guided munition control system and method

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이 특허에 인용된 특허 (38)

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