基于高斯伪谱法和有限差分结合的飞行器燃料最优轨道转移优化  

Trajectory Optimization with Optimal Fuel Consumption Based on GPM and Finite-difference Method

作　　者：周珺仪 刘佳琪[1,2] 焦胜海 段红亮 陈晓光 Zhou Jun-yi;Liu Jia-qi;Jiao Sheng-hai;Duan Hong-liang;Chen Xiao-guang(Beijing Institute of Space Long March Vehicle,Beijing,100076;National Key Laboratory of Science and Technology on Test Physics&Numerical Mathematical,Beijing,100076)

机构地区：[1]北京航天长征飞行器研究所,北京100076 [2]试验物理与计算数学国家级重点实验室,北京100076

出　　处：《导弹与航天运载技术》2021年第2期116-120,共5页Missiles and Space Vehicles

摘　　要：为解决最优轨道短时快速转移优化问题,将高斯伪谱法和有限差分法相结合,求解最优控制的直接法和间接法,提出基于Lambert边值求解的初值范围,加快高斯伪谱法的收敛速度。并利用伪谱法得到的协态变量初值带入有限差分求解两点边值问题的精确解。仿真结果表明,对于短时间轨道转移,同伪谱法相比,改进方法的控制过程稳定无误差,精度更高。The low-thrust trajectory optimization with optimal fuel consumption is obtained with GPM and finite-difference method.The direct and indirect methods for optimal control are introduced.The initial value range based on Lambert boundary is proposed to accelerate the convergence speed of GMP.Then,the exact solution of the finite-difference boundary value problem is using the initial values of the costate variables which are given by GPM.The simulation results show that the improved method is more stable,convergent and accurate than the GPM.

关 键 词：小推力变轨 燃料最优 伪谱法 有限差分法 

分 类 号：V412[航空宇航科学与技术—航空宇航推进理论与工程]