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论文类型：会议论文

发表时间：2009-08-05

收录刊物：EI、CPCI-S、Scopus

页面范围：681-+

关键字：Feedback control; Lunar module; Soft landing

摘要：In this paper, the optimal control problem to achieve lunar module soft landing with least fuel consumption is considered. The precise three dimensional dynamics is employed to describe the motion of the lunar module. By introducing two new state equations, a closed loop optimal control law is designed with a parameter matrix K to be determined which is the solution of a riccati like differential equation. We present a practical method to calculate the matrix K, such that it is avoided to solve the complex riccati like differential equation. Simulation results show the efficiency of the proposed method.