航天器近距离相对运动轨迹设计与控制

Mission Trajectory Design and Control for Spacecraft Proximity Relative Motion

航天器近距离相对运动是当前航天领域的重要研究热点。针对圆(近圆)轨道目标航天器,综合利用C-W方程、脉冲控制和优化理论,系统地解决了航天器相对运动的轨迹设计与控制问题。从C-W方程解析解出发,给出了自然轨迹和受限轨迹的数学描述;以此为基础,考虑碰撞避免,研究了全局绕飞轨迹和局部限制轨迹的设计与控制。对于全局绕飞轨迹,研究提出了自然椭圆绕飞、自然螺旋绕飞、单脉冲"水滴"形绕飞、多脉冲圆形绕飞和多脉冲"田径场"形绕飞五种轨迹模式;对于局部限制轨迹,研究提出了自然椭圆V-bar限制轨迹、单脉冲R-bar限制轨迹和多脉冲任意方位限制轨迹三种模式。分析了每种轨迹模式的形成过程和能量消耗,给出了每种轨迹的设计参数,利用仿真算例验证了有效性。此外,对多脉冲圆形绕飞轨迹和多脉冲任意方位限制轨迹,建立了脉冲位置和脉冲时间间隔的优化模型。

The spacecraft proximity relative motion has been a key concern in space mission design. For the target in a circular orbit, the relative motion trajectory design and control is investigated based on C-W equations, impulsive control and optimal theory. Firstly, the natural trajectory and forced trajectory are formulated by the analytical solution of C-W e- quations. Then, considering collision avoidance, the flyaround trajectories and local constrained trajectories are studied respectively. For the former, five trajectory modes, named natural elliptical flyaround, natural spiral flyaround, single-impulse tear-drop flyaround, multi-impulse circular flyaround and multi-impulse gymkhana flyaround, are presented. For the latter, three mission patterns named natural elliptical V-bar constrained trajectory, single-impulse R-bar constrained trajectory and multi-impulse arbitrary constrained trajectory are presented. For each trajectory pattern, the design parameters are induced by analyzing the fuel costs and process of mission. And the simulations validate the efficiency. Furthermore, the optimal models of multi-impulse circular flyaround and multi-impulse arbitrary constrained trajectory are formulated.