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针对滑翔段到巡航段的过渡段控制问题,在考虑地球自转和冲压约束及巡航段初始状态约束条件下,建立了导弹控制律设计模型.运用Gauss伪谱法将最优控制问题转换为非线性规划问题,利用SNOPT对非线性规划问题进行求解.仿真结果表明Gauss伪谱法对导弹滑翔段到巡航段的过渡段最优控制律求解是有效的。
Aiming at the problem of the transition from gliding segment to cruising segment, a model of missile control law is established considering the constraint of the rotation and stamping of the earth and the initial state of the cruise segment. The Gauss pseudospectral method is used to convert the optimal control problem to nonlinear And solve the nonlinear programming problem by using SNOPT.The simulation results show that the Gauss pseudospectral method is effective in solving the optimal control law for the transition from gliding segment to cruising segment of missile.