基于轨迹成型法星际小推力转移轨道快速设计  

A Shape-based Approach to Rapidly Design Interplanetary Low-thrust Trajectories

作　　者：叶立军[1,2] 孟占峰[3] 韩潮[2] 

机构地区：[1]上海航天控制工程研究所,上海200233 [2]北京航空航天大学宇航学院,北京100191 [3]中国空间技术研究院总体部,北京100094

出　　处：《航天控制》2009年第6期56-60,65,共6页Aerospace Control

摘　　要：给出了一种基于轨迹成型法星际小推力转移轨道的快速设计方法。首先介绍了基于轨迹成型法的有关内容,并通过与Hohmann变轨相对比验证了该方法描述小推力变轨的可用性。鉴于这种方法数学模型收敛性强,计算速度快的特点,以地火转移轨道为例,提出了不同推力条件下发射窗口的搜索方法。最后,利用基于轨迹成型法和真实数值仿真之间误差小、线性度好的特点,通过几次简单的线性迭代设计出小推力转移轨道。A shape-based approach to design interplanetary low-thrust trajectories is presented in this paper. Firstly some relative contents of shape-based approach are introduced, by comparing with Hohmann trans- ferring trajectory, and the usefulness of this shape-based approach in solving low-thrust trajectories is proved. In view of the fact that the mathematic model of this approach is good at convergence and rapid computation, the search approach to launch window of Mars explorer under the conditions of various thrust forces is proposed. Finally, using the shape-based approach to design Earth-Mars trajectory is verified by numerical simulation.

关 键 词：轨迹成型 火星探测 小推力 发射窗口 

分 类 号：V412.4[航空宇航科学与技术—航空宇航推进理论与工程]