一种基于导航点的航天器相对运动轨迹生成策略

A Trajectory Generation Strategy Based on Way-points for Spacecraft Relative Motion

针对圆(近圆)轨道航天器相对运动的固定时间状态转移问题,提出了一种基于导航点的多脉冲优化轨迹生成策略。从相对运动动力学出发,应用最优控制理论给出了基于连续推力的最优转移轨线,将引入的导航点限定在最优转移轨线上得到其位置参数;然后利用导航点位置参数建立了脉冲约束下的基于多脉冲的优化轨迹生成模型,采用二次规划算法求解,通过改变导航点位置和脉冲间隔优化轨迹。仿真算例验证了策略的有效性。

An optimal trajectory generation strategy based on way-points is presented to solve the fixed-time state transition for spacecraft relative motion in a circular orbit. According to the dynamics of relative motion, the optimal transfer trajectory with continuous thrust is investigated by applying optimal control theory. Furthermore, a set of way-points constrained to be along the optimal transfer trajectory are introduced to parameterize the trajectory with impulsive eonstraints by multi-impulse control. By changing the positions of way-points and the time between two neighboring impulsive bums, the generated trajectory is optimized with quadratic programming algorithm. The simulations show that the strategy is practical and efficient.