基于自适应伪谱法的升力式飞行器火星进入段快速轨迹优化

Mars Entry Trajectory Quick Optimization Method for Lifting Vehicle Based on Adaptive GPM

针对升力式火星飞行器定点着陆任务的轨迹优化问题,给出了基于自适应伪谱法的快速优化算法.综合考虑探测器火星大气进入过程中的动力学约束、边界约束、路径约束以及控制约束条件,利用自适应伪谱法将轨迹优化问题转换为离散的非线性规划问题,采用序列二次规划算法进行求解,得到性能指标最优的进入轨迹.通过仿真验证,给出了实现火星进入过程燃料消耗最优的状态量和控制量轨迹.仿真结果表明,在Matlab中采用自适应伪谱法,能够在800 s内采用267个配点,给出近似精度为10-6的火星进入过程中消耗能量最优的参考轨迹.

A new method is given based on adaptive Gauss pseudospectral method for quick trajectory optimization problem of Mars entry.This method converts the trajectory optimization problem to a non-linear programming problem,taking into account for the dynamic constrains,the boundary constrains,the path constrains and the control constrains during the Mars entry of the lifting vehicle.And then,sequential quadratic programming is adapted to solve the non-linear programming problem,and the optimal fuel-consuming trajectory is obtained.In combination with the adaptive Gauss pseudospectral method and sequential quadratic programming in Matlab software,the numerical results of the optimal trajectory with 267 collocations could be obtained in 800s with an approximation accuracy of 10-6.The numerical results are smooth and meet all constrains during the Mars entry process,which suggests that the method introduced in this paper is available and of great practical application.