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首页> 外文期刊>Journal of guidance, control, and dynamics >Optimal Rendezvous Trajectories of a Controlled Spacecraft and a Tumbling Object
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Optimal Rendezvous Trajectories of a Controlled Spacecraft and a Tumbling Object

机译：受控航天器和翻滚物体的最佳交会轨迹

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This paper formulates and solves the problem of minimum-time and minimum-energy optimal trajectories of rendezvous of a powered chaser and a passive tumbling target, in a circular orbit. Both translational and rotational dynamics are considered. In particular, ending conditions are imposed of matching the positions and velocities of two points of interest onboard the vehicles. A collision-avoidance condition is imposed as well. The optimal control problems are analytically formulated through the use of the Pontryagin minimum principle. The problems are then solved numerically, by using a direct collocation method based on the Gauss pseudospectral approach. Finally, the obtained solutions are verified through the minimum principle, solved by a shooting method. The simulation results show that the pseudospectral solver provides solutions very close to the optimal ones, except in the case of presence of singular arcs when it may not provide a feasible solution. The computational time needed by the pseudospectral solver is a small fraction of the one needed by the indirect approach, but it is still considerably too large to allow for its use in real-time onboard guidance.
机译：本文提出并解决了圆形轨道中动力追赶者与被动翻滚目标交会的最小时间和最小能量最优轨迹问题。平动和旋转动力学都被考虑。特别地，施加了使车辆上两个关注点的位置和速度匹配的结束条件。还施加了避免碰撞的条件。通过使用Pontryagin最小原理，可以分析得出最优控制问题。然后，使用基于高斯伪谱方法的直接配置方法在数值上解决问题。最后，通过最小原理验证所获得的解决方案，并通过射击方法进行求解。仿真结果表明，伪谱解算器提供的解非常接近于最佳解，除非在存在奇弧的情况下可能无法提供可行解。伪光谱求解器所需的计算时间仅是间接方法所需时间的一小部分，但仍过大而无法在实时机载制导中使用。

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