论文标题
使用可及性分析的多目标低潮航天器轨迹设计
Multi-objective low-thrust spacecraft trajectory design using reachability analysis
论文作者
论文摘要
航天器轨迹设计中的基本问题之一是找到最佳的转移轨迹，该轨迹同时可以最大程度地减少推进剂的消耗和传输时间。我们将其作为多目标最佳控制（MOC）问题提出，涉及对初始或最终状态进行优化，但要受状态约束。利用可达性分析的最新发展受状态约束，我们表明，可以将提出的MOC问题表示为一个优化问题，但要受到涉及准差异不平等的粘度解决方案的子级集合的约束。然后，我们将这种方法概括为Bolza形式中更一般的最佳控制问题。我们将这些问题与已开发的多目标程序的帕累托前线联系起来。在旋转小行星周围的两个低头轨道转移问题上证明了所提出的方法。
One of the fundamental problems in spacecraft trajectory design is finding the optimal transfer trajectory that minimizes the propellant consumption and transfer time simultaneously. We formulate this as a multi-objective optimal control (MOC) problem that involves optimizing over the initial or final state, subject to state constraints. Drawing on recent developments in reachability analysis subject to state constraints, we show that the proposed MOC problem can be stated as an optimization problem subject to a constraint that involves the sub-level set of the viscosity solution of a quasi-variational inequality. We then generalize this approach to account for more general optimal control problems in Bolza form. We relate these problems to the Pareto front of the developed multi-objective programs. The proposed approach is demonstrated on two low-thrust orbital transfer problems around a rotating asteroid.
