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
- 학술저널
- 저자정보
- 저널정보
- 대한전기학회 International Journal of Control Automation and Systems International Journal of Control Automation and System Vol.5 No.4
- 발행연도
- 2007.8
- 수록면
- 397 - 409 (13page)
이용수
초록· 키워드
오류제보하기
In this paper, we propose a nonlinear guidance law for missiles against maneuvering targets. First, we derive the equations of motion described in the line-of-sight reference frame and then we define the equilibrium subspace of the nonlinear system to guarantee target interception within a finite time. Using Sontag's formula, we derive a nonlinear guidance law that always delivers the state to the equilibrium subspace. If the speed of the missile is greater than that of the target, the proposed law has global capturability in that, under any initial launch conditions, the missile can intercept the maneuvering target. The proposed law also minimizes the integral cost of the control energy and the weighted square of the state. The performance of the proposed law is compared with the augmented proportional navigation guidance law by means of numerical simulations of various initial conditions and target maneuvers.
목차
Abstract
1. INTRODUCTION
2. SONTAG‘S FORMULA
3. MISSILE KINEMATICS AND EQUILIBRIUM SUBSPAPCE
4. NONLINEAR GUIDANCE LAW
5. NUMERICAL EXAMPLES
6. CONCLUSION
APPENDIX : AUGMENTED PROPORTIONAL NAVIGATION LAWS
REFERENCES
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UCI(KEPA) : I410-ECN-0101-2010-560-001921199