有限推力航天器轨迹优化问题的一种双模型直接配置法  

Optimization of Finite-Thrust Spacecraft Trajectories Using Dual-Model Direct Collocation Method

作　　者：潘伟[1] 路长厚[1] 葛培琪[1] 冯维明[2] 

机构地区：[1]山东大学机械学院,济南250061 [2]山东大学土建学院,济南250061

出　　处：《宇航学报》2009年第2期442-447,共6页Journal of Astronautics

摘　　要：直接配置法在有限推力航天器的轨迹优化问题中得到了广泛的应用,但它所构造的非线性规划问题存在维数多,求解精度低等困难。针对有限推力航天器最优轨迹由最大推力弧和零推力弧构成这一特点,分别使用球坐标动力学方程和高斯方程对二者建模,并解决了由此带来的配置过程中的区间化分问题。这种双模型的直接配置法易于引入各种摄动因素的影响,从而提高求解精度,同时,构造的非线性规划问题的变量较少,降低了时间消耗。最后通过算例演示了求解过程,并证实了上述优点。The direct collocation method for solving optimal finite-thrust spacecraft trajectory problems involves the use of a discrete approximation to the original dynamics differential functions. In this paper, dynamics differential functions in Spherical coordinates are used for maximum thrust arcs, and Gaussian functions for coast arcs. A technique for changing the discretization in both kinds of arcs to improve the accuracy of the approximation is described. When compared with the standard method, the dual-model direct collocation method has the advantage of higher solution accuracy with minimal additional computational effort. A rendezvous trajectory optimization problem for a finite-thrust spacecraft is used to demonstrate the benefits of using such a method.

关 键 词：有限推力 摄动 直接配置法 轨迹优化 

分 类 号：V412[航空宇航科学与技术—航空宇航推进理论与工程]