Optimal Guidance Law for a Lunar Lander using Homotopy Method

摘要

Guidance law of lunar lander is discussed in this paper. Minimum fuel trajectory is required for guidance law because most weight of lander is occupied by fuel. The landing point is specified from a view point of science interest. The trajectory is defined as an optimal control problem and the necessary condition of problem is described as two point boundary value problem. Homotopy method is applied to solve the problem. The optimal solution is provided to calculate finite integral. The computational time is predicted because the method does not use iterative calculation.