인문학
사회과학
자연과학
공학
의약학
농수해양학
예술체육학
복합학
DBpia AI
AI 에이전트
AI 아이디어
AI 리더
AI 뷰어
Citeasy
크롬 서지관리 다운로드
지원사업
학술연구/단체지원/교육 등 연구자 활동을 지속하도록 DBpia가 지원하고 있어요.
커뮤니티
연구자들이 자신의 연구와 전문성을 널리 알리고, 새로운 협력의 기회를 만들 수 있는 네트워킹 공간이에요.
초록·키워드
In this study, the design and test evaluation results of an in-flight transfer alignment technique that aligns the SINS of a guided missile using navigation information transferred from the MINS of a fighter are presented for the first time in Korea. To design the in-flight transfer alignment technique in an environment that operates under high dynamics and has a large flexure error, the influence of error sources in transfer alignment on performance according to various measurements of transfer alignment filter was theoretically analyzed and confirmed through simulations. Performance analysis results revealed that the in-flight transfer alignment technique based on velocity integral measurements had the best attitude error estimation performance under a large flexure error environment and the excellent convergence rate in attitude error estimation. Therefore, a 16th order transfer alignment filter based on velocity integral measurements was finally designed. The designed in-flight transfer alignment technique based on velocity integral measurements was tested and evaluated through van and fighter mounting tests. The test and evaluation results revealed that the in-flight transfer alignment performance was excellent. Finally, through a flight test of the guided missile, after the transfer alignment was completed, the fired guided missile hit a determined target accurately. This flight test results further proved that the transfer alignment was operating normally.
본문·목차
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오류를 발견하셨다면 해당 부분을 드래그한 후 ' 를 통해 신고해주세요.
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