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
- 저널정보
- 한국항공우주학회 한국항공우주학회 학술발표회 초록집 Proceedings of KSAS-JSASS Joint International Symposium on Aerospace Engineering
- 발행연도
- 2008.11
- 수록면
- 496 - 499 (4page)
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초록· 키워드
오류제보하기
the authors have been studying an application of Multidisciplinary Design Optimization (MDO) to the future missiles. For the purpose, a new design procedure on guidance and control system is proposed in this paper. For the future missiles, high maneuvering and high responsiveness are required. Then, the authors have been studying on guidance and control system design of the missile that uses the useful side thruster method for the high maneuvering and high responsiveness in the future missile. The side thruster method has an independent gas generator. The maximum thrust does not depend on dynamic pressure and is enabled even in the low-speed region immediately after launching or the high altitude area. It is expected that this method is useful in high maneuvering and high responsiveness in the future missiles. It is assumed that the side thruster device can change the amplitude of thrust continuously in this paper. In our previous studies, we solved the minimum time problem with the open loop and calculated optimal solution. The optimum thrust is no bang-bang control, but intermediate value is also used. The numerical results verified the usefulness. In this paper, we propose the closed-loop control system which is calculated inputs in real time due to aim toward the guidance and control system of more realistic missiles, verified by simulation.
목차
Abstract
1. INTRODUCTION
2. MISSILE MODEL
3. NEW DESIGN PROCEDURE
4. RESULTS
5. CONCULSION
REFERENCES
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