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.
논문 기본 정보
- 자료유형
- 학술대회자료
- 저자정보
- 발행연도
- 2013.10
- 수록면
- 55 - 60 (6page)
이용수
초록· 키워드
오류제보하기
An integrated guidance and control law for agile dual missiles is proposed using sliding mode control. For tight integration, engagement kinematics and missile dynamics are combined without linearization. Then, two sliding surfaces are defined because dual missiles have two degrees of freedom for control. One surface is defined for making line of sight (LOS) angle rate converge, and the other for fast response of the missile. Response speed of the missile is adjusted flexibly with the control. If heading error exists, a fast controller that consumes large input is applied. On the contrary, a relatively slow controller consuming smaller input is applied when heading error is zero. For this strategy, transition control technique is applied. As a result, an integrated guidance and control law with fast response speed is derived. Performance of the proposed integrated law is evaluated with highly maneuverable target using nonlinear simulations.
목차
Abstract
1. INTRODUCTION
2. MODEL FORMULATION
3. INTEGRATION OF GUIDANCE AND FLIGHT CONTROL SYSTEMS
4. SIMULATION AND ANALYSIS
5. CONCLUSIONS
REFERENCES
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