[특허]Burnout time estimation and early thrust termination determination for a boosting target

Lockheed Martin Corporation

검색어에 아래의 연산자를 사용하시면 더 정확한 검색결과를 얻을 수 있습니다.
검색연산자

검색연산자	기능	검색시 예
()	우선순위가 가장 높은 연산자	예1) (나노 (기계 \| machine))
공백	두 개의 검색어(식)을 모두 포함하고 있는 문서 검색	예1) (나노 기계) 예2) 나노 장영실
\|	두 개의 검색어(식) 중 하나 이상 포함하고 있는 문서 검색	예1) (줄기세포 \| 면역) 예2) 줄기세포 \| 장영실
!	NOT 이후에 있는 검색어가 포함된 문서는 제외	예1) (황금 !백금) 예2) !image
*	검색어의 *란에 0개 이상의 임의의 문자가 포함된 문서 검색	예) semi*
""	따옴표 내의 구문과 완전히 일치하는 문서만 검색	예) "Transform and Quantization"

과학기술 지식인프라 ScienceON

특허 상세정보

MyON담기

내보내기

Burnout time estimation and early thrust termination determination for a boosting target

국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F42B-015/01 G06F-019/00 F41G-007/00
미국특허분류(USC)	244/003.1; 342/061; 342/062; 342/175; 342/195; 089/001.11
출원번호	US-0646192 (2006-12-27)
등록번호	US-8134103 (2012-03-13)
발명자 / 주소	Luu, Thu-Van T. Boka, Jeffrey B. Harcourt, Michael J. Mookerjee, Purusottam
출원인 / 주소	Lockheed Martin Corporation
대리인 / 주소	Howard IP Law Group PC
인용정보	피인용 횟수 : 4 인용 특허 : 83

초록
▼

A system senses the presence of a boosting missile or target and processes the information by comparison of the data with a plurality of predetermined templates of nominal missile characteristics, in order to determine the state of the missile. The processing includes estimation of burnout time and of early thrust termination. Both are determined by generating current stage state estimates including position, velocity, time index error into the thrust template, and motor scale factor error. The change in motor scale factor is compared with a threshold to determine if early thrust termination has occurred. The estimated burnout time of the current stage is calculated from the burnout times of the current and the previous stage processed with the estimated motor scale factor and with state estimates from a filter.

대표
청구항
▼

1. A method for estimating staging of a boosting target, said method comprising the steps of: sensing position of the boosting target from moment to moment to thereby generate target position information;generating current stage state estimates including position, velocity, time index error de{circumflex over (l)}T into a thrust acceleration template, and motor scale factor {circumflex over (K)};determining estimated burnout time tBOEst of the current stage by tBOEst=(stageTimeCurrent-stageTimePast)K^+stageTimePastEst-offsetError+de⁢l^⁢⁢TK^wherestageTimeCurrent=nominal current stage burnout time;stageTimePast=nominal past stage burnout time;stageTimePastEst=estimated value of the previous stage burnout time;{circumflex over (K)} and de{circumflex over (l)}T=state estimates from the filter;offsetError=initial difference between template_index and measured Time;and using said estimated burnout time to predict a future location of said target. 2. The method of claim 1, further comprising using said prediction of a future location of said target to guide an antimissile asset toward said target. 3. The method of claim 1, wherein the sensing step is performed using a radar system. 4. The method of claim 1, wherein the sensing step is performed using an infrared sensor. 5. A method for determining early thrust termination of a boosting target, said method comprising the steps of: sensing position of the boosting target to thereby generate target position information;generating current stage state estimates including position, velocity, time index error into a thrust acceleration template, and motor scale factor {circumflex over (K)};determining if target has early thrust terminated using the motor scale factor. 6. The method of claim 5, wherein said determining step comprises the steps of: increasing a K covariance value relative to an initial K covariance value and decreasing a time error covariance value relative to an initial time index error covariance value;shifting a current estimate of {circumflex over (K)} into a temporary storage location, finite length K estimate register, with a corresponding storage time tag;calculating KDelta by taking difference between the newest {circumflex over (K)} in the register and an oldest {circumflex over (K)} in the register;comparing the value of KDelta with a threshold value; andif the change in KDelta is greater than the threshold value, indicating that early thrust termination has occurred. 7. The method of claim 6, wherein if the change in KDelta is less than the threshold value, continued thrusting of the boosting target is deemed to have occurred. 8. The method of claim 6, further comprising guiding an antimissile asset toward said target using said early thrust determination. 9. A system for estimating staging of a boosting target, said system comprising: a processor for executing instructions for: sensing a position of the boosting target to generate target position information;generating current stage state estimates for said boosting target including position, velocity, time index error into a thrust acceleration template, and motor scale factor;using said current, stage state estimates for said boosting target to determine an estimated burnout time of the boosting target; andusing said estimated burnout time of the boosting target to predict a future location of said boosting target. 10. The system of claim 9, wherein the step of determining estimated burnout time of the current stage employs the formula: tBOEst=(stageTimeCurrent-stageTimePast)K^+stageTimePastEst-offsetError+de⁢l^⁢⁢TK^where:tBOEst=estimated burnout timestageTimeCurrent=nominal current stage burnout time;stageTimePast=nominal past stage burnout time;stageTimePastEst=estimated value of the previous stage burnout time;{circumflex over (K)} and de{circumflex over (l)}T=state estimates from the filter;offsetError=initial difference between template_index and measured Time. 11. The system of claim 9, wherein the sensing step is performed using a radar system or an infrared sensor. 12. The method of claim 9, further comprising using said prediction of a future location of said target to guide an antimissile asset toward said target. 13. A system for determining early thrust termination of a boosting target, said system comprising: a processor for executing instructions for:sensing a position of the boosting target to generate target position information;generating current stage state estimates for said boosting target including position, velocity, time index error into a thrust acceleration template, and motor scale factor; anddetermining if the boosting target has an early thrust terminated using the motor scale factor. 14. The system of claim 13, wherein said determining step comprises the steps of: increasing a covariance value of the motor scale factor relative to an initial covariance value of the motor scale factor and decreasing a time error covariance value relative to an initial time index error covariance value;shifting a current estimate of the motor scale factor into a temporary storage register, with a corresponding storage time tag;calculating a difference between a newest motor scale factor in the register and an oldest motor scale factor in the register;comparing the difference with a threshold value; andusing the difference to determine if early thrust termination has occurred for the boosting target. 15. The system of claim 14, wherein if the difference is greater than a threshold value, early thrust termination is deemed to have occurred. 16. The system of claim 14, wherein if the difference is less than a threshold value, continued thrusting of the boosting target is deemed to have occurred. 17. The system of claim 13, wherein the sensing step is performed using a radar system or an infrared sensor. 18. The method of claim 13, further comprising guiding an antimissile asset toward said target using said early thrust determination.

이 특허에 인용된 특허 (83)

이 특허를 인용한 특허 피인용횟수: 4

IPC 상위 출원인

내보내기

상세정보
내보내기 구분	파일저장 인쇄 메일전송
구성항목	관리번호, 국가코드, 자료구분, 상태, 출원번호, 출원일자, 공개번호, 공개일자, 등록번호, 등록일자, 발명명칭(한글), 발명명칭(영문), 출원인(한글), 출원인(영문), 출원인코드, 대표IPC 관리번호, 국가코드, 자료구분, 상태, 출원번호, 출원일자, 공개번호, 공개일자, 공고번호, 공고일자, 등록번호, 등록일자, 발명명칭(한글), 발명명칭(영문), 출원인(한글), 출원인(영문), 출원인코드, 대표출원인, 출원인국적, 출원인주소, 발명자, 발명자E, 발명자코드, 발명자주소, 발명자 우편번호, 발명자국적, 대표IPC, IPC코드, 요약, 미국특허분류, 대리인주소, 대리인코드, 대리인(한글), 대리인(영문), 국제공개일자, 국제공개번호, 국제출원일자, 국제출원번호, 우선권, 우선권주장일, 우선권국가, 우선권출원번호, 원출원일자, 원출원번호, 지정국, Citing Patents, Cited Patents
저장형식	Text(ASCII format) Excel format PIAS분석(.xls)
메일정보	받는사람 (필수) @ 보내는사람 (선택) @ 제목 내용 KISTI 검색결과 이메일 서비스
안내	> 총 건의 자료가 검색되었습니다. > 다운받으실 자료의 인덱스를 입력하세요. (1-10,000) > 검색결과의 순서대로 최대 10,000건 까지 다운로드가 가능합니다. > 데이타가 많을 경우 속도가 느려질 수 있습니다.(최대 2~3분 소요) > 다운로드 파일은 UTF-8 형태로 저장됩니다. 파일의 내용이 제대로 보이지 않을실 때는 웹브라우저 상단의 보기 -> 인코딩 -> 자동선택 여부를 확인하십시오 > ~ > Text(ASCII format) Excel format

과학기술 지식인프라 ScienceON

ScienceON Chatbot

특허 상세정보

Burnout time estimation and early thrust termination determination for a boosting target

초록
▼

대표
청구항
▼

이 특허에 인용된 특허 (83)

이 특허를 인용한 특허 피인용횟수: 4

IPC 상위 출원인

과제정보

상세정보조회

원문조회

IPC 상세정보(version : 201201)

연구과제 성과물(0)

참여연구원의 다른 문헌(0)

처리중입니다.

잠시만 기다려주세요.

ScienceON Chatbot

특허 상세정보

Burnout time estimation and early thrust termination determination for a boosting target

초록 ▼

대표청구항 ▼

이 특허에 인용된 특허 (83)

이 특허를 인용한 특허 피인용횟수: 4

IPC 상위 출원인

과제정보

상세정보조회

원문조회

IPC 상세정보(version : 201201)

연구과제 성과물(0)

참여연구원의 다른 문헌(0)

처리중입니다.

잠시만 기다려주세요.

초록
▼

대표
청구항
▼