论文标题
具有有限观察窗口的多爆裂轨道操纵
Multiple-impulse orbital maneuver with limited observation window
论文作者
论文摘要
本文提出了一种在圆形轨道附近的多突动轨道操纵的解决方案，用于特殊情况，这些情况下轨道观测到全球可用，并且通过从地面或太空站的有限窗口观察到航天器。当前的研究对于小型私人发射公司特别有用，该公司在地球周围和/或其他行星周围的轨道动作范围有限，轨道观测仅限于现场设备。为了最大程度地减少总控制/冲动工作以及轨道不确定性，引入了适当的成本函数。随后证明，对于圆圈到圆圈操作，优化问题是相对于设计变量的准串联问题。对于近圆形轨迹，通过基于梯度的优化算法来最大程度地减少相同的成本函数，以提供相对于能源努力和轨道不确定性有效的亚最佳解决方案。作为一项相关的案例研究，模拟并分析了火星重力下的圆形轨道之间的四局轨道操纵，以证明所提出的算法的有效性。
This paper proposes a solution for multiple-impulse orbital maneuvers near circular orbits for special cases where orbital observations are not globally available and the spacecraft is being observed through a limited window from a ground or a space-based station. The current study is particularly useful for small private launching companies with limited access to global observations around the Earth and/or for orbital maneuvers around other planets for which the orbital observations are limited to the in situ equipment. An appropriate cost function is introduced for the sake of minimizing the total control/impulse effort as well as the orbital uncertainty. It is subsequently proved that for a circle-to-circle maneuver, the optimization problem is quasi-convex with respect to the design variables. For near circular trajectories the same cost function is minimized via a gradient based optimization algorithm in order to provide a sub-optimal solution that is efficient both with respect to energy effort and orbital uncertainty. As a relevant case study, a four-impulse orbital maneuver between circular orbits under Mars gravitation is simulated and analyzed to demonstrate the effectiveness of the proposed algorithm.
