The optimization of low-thrust, multirevolution orbit-transfer trajectories is often regarded as a difficult problem in modern astrodynamics. In this paper, a flexible and computationally efficient approach is presented for the optimization of low-thrust orbit transfers under eclipse constraints. The proposed approach leverages a new dynamic model of the orbital motion and a Lyapunov-based initial-guess generation scheme that is very easy to tune. A multi-objective, single-phase formulation of the optimal control problem is devised, which provides a convenient way to trade off fuel consumption and time of flight. A distinctive feature of such a formulation is that it requires no prior information about the structure of the optimal solution. Simulation results for two benchmark orbit-transfer scenarios indicate that minimum-time, minimum-fuel, and mixed time/fuel-optimal instances of the control problem can be readily solved via direct collocation, while incurring a significantly lower computational demand with respect to existing techniques.

低推力、多公转轨道转移轨迹的优化通常被认为是现代天体动力学中的一个难题。在本文中，提出了一种灵活且计算效率高的方法，用于优化日食约束下的低推力轨道转移。所提出的方法利用了一种新的轨道运动动力学模型和一种非常容易调整的基于 Lyapunov 的初始猜测生成方案。设计了最优控制问题的多目标、单阶段公式，它提供了一种权衡燃料消耗和飞行时间的便捷方法。这种公式的一个显着特点是它不需要关于最优解结构的先验信息。两个基准轨道转移场景的模拟结果表明，最短时间、最少燃料、