역최적 문제를 통한 충돌각 제어 최적유도법칙의 개루프 비행궤적 특성 및 Time-to-go 예측 = The Characteristics of Open-loop Trajectory and Time-to-go Estimation for Impact Angle Control Optimal Guidance through Inverse Optimal Problem

다국어 초록 (Multilingual Abstract)

This paper presents the features of an impact angle constrained open-loop optimal trajectory which is given by a function of initial conditions and optimal guidance gains. Using missile motion described by linearized kinematic equations and a proper form of performance index, an inverse optimal problem is suggested to investigate the gains related to the performance index. The flight trajectory and time-to-go can be shaped in terms of the optimal guidance gains. The results are evaluated by 3-DOF simulation.

참고문헌 (Reference)

1 이진익, "충돌각 제어 호밍유도법칙의 역최적 문제" 한국항공우주학회 35 (35): 412-418, 2007

2 김을곤, "유도탄의 Time-to-go 변수 예측" 332-337, 1994

3 김을곤, "비례항법상수 N에 따른 개루프 궤적 및 Time-to-go 특성" 27 (27): 115-120, 1998

4 C. K. Ryoo, "Time-to-Go Weighted Optimal Guidance with Impact Angle Constraints" 14 (14): 483-492, 2006

5 A. Jameson, "Inverse Problem of Linear Optimal Control" 11 (11): 1-19, 1973

6 A. E. Bryson, Jr., "Applied Optimal Control" Hemisphere Publishing Co., 148-167, 1975