基于椭圆形参考轨道的航天器泪滴形绕飞轨道设计  

Designing Teardrop-Shaped Diversion Orbit of Spacecraft Based on Elliptic Reference Orbit

作　　者：何康乐[1] 和兴锁[1] 宋明[1] 陈翠红[1] 

机构地区：[1]西北工业大学工程力学系,陕西西安710129

出　　处：《西北工业大学学报》2012年第1期145-148,共4页Journal of Northwestern Polytechnical University

摘　　要：文章通过建立较小偏心率、以真近点角为变量的椭圆一阶无摄动相对运动方程,实现泪滴形绕飞轨道设计。在基于椭圆一阶无摄动相对运动方程和相应状态转移矩阵的基础上,对其相对运动初始值选取的约束条件(即封闭条件)进行了推导。最后由得出的新型零接近速度制导律,实现了在椭圆一阶无摄动相对运动上泪滴形绕飞轨道的设计和仿真。We design the teardrop-shaped diversion orbit by establishing the first-order elliptical relative motion equations without perturbation but with small eccentricity and with true anomaly as the only independent variable. Sections 1, 2 and 3 explain our design. The three subsections of section 3 are entitled： Derivation of New Zero Close to Speed Guidance Law （ subsection 3.1 ）, Design of Teardrop-Shaped Diversion Orbit （ subsection 3.2 ）, Simulation Results of Numerical Example and Their analysis （ subsection 3.3 ）. The results and analysis of subsection 3.3 show preliminarily that the design of the teardrop-shaped diversion orbit, which is based on the first-order elliptical relative motion equations without perturbation, is indeed feasible.

关 键 词：椭圆形轨道 一阶无摄动方程 泪滴形绕飞 封闭条件 新型零接近速度制导律 

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]