空间近距离接近与绕飞轨道设计  

Near-approach and Fly-around Trajectory Design

作　　者：彭伟斌[1] 谢泽兵[1] 莫文骥[1] 张少波[1] 

机构地区：[1]中国运载火箭技术研究院研究与发展中心,北京100076

出　　处：《导弹与航天运载技术》2008年第2期1-3,共3页Missiles and Space Vehicles

摘　　要：利用多项式建立了空间飞行器相对目标的变轨加速度模型,给出了C-W方程的解析解;由此将在给定时间、初始及终端条件下完成空间近距离接近与绕飞的轨道设计问题转化为求解六元非线性方程组。文中给出了接近与绕飞典型问题的算例,验证了求解思路的正确性。The orbit-transfering acceleration model of the relative target of the spacecraft is established with the polynomial, and the analytical solution for Clohessy-Wiltshire function is given. Therefore, the problem of completing the near approach and fly-around trajectory design within given time, initial and final conditions is transferred to solving the nonlinear simultaneous equations with 6 variables. The typical problem example of near approach and fly-around is given, which verifies the solving thought.

关 键 词：空间飞行器 轨道设计 接近 绕飞 

分 类 号：V526[航空宇航科学与技术—人机与环境工程]