In this paper, an integrated optimal flight plan with a guidance plan in a general transfer orbit is considered. Due to the need to simultaneously reduce energy consumption and flight time in some space missions, the spacecraft trajectory is optimized based on two criteria to minimize fuel consumption and flight time in the orbital transfer process. For this purpose, the total velocity impulse on both sides of the transition orbit and the elapsed time are defined as the criteria of the objective function which includes the spacecraft’s insertion conditions and orbital parameters related to the shape of the trajectory. The optimal transition (coasting) trajectory is then obtained using the multi-objective genetic algorithm (MOGA) search method. Subsequently, the velocity-to-be-gained guidance steering scheme is integrated to track the trajectory onboard and reach the final orbit. The numerical results of the proposed algorithm are extracted in three case studies and compared with other references that show its ability to find the optimal transfer.

本文考虑了在通用转移轨道上带有制导计划的综合最优飞行计划。由于在某些太空任务中需要同时降低能耗和飞行时间，航天器轨迹基于两个标准进行优化，以最大限度地减少轨道转移过程中的燃料消耗和飞行时间。为此，将过渡轨道两侧的总速度脉冲和经过时间定义为目标函数的标准，其中包括航天器的插入条件和与轨迹形状相关的轨道参数。然后使用多目标遗传算法 (MOGA) 搜索方法获得最佳过渡（滑行）轨迹。随后，集成了获得速度的制导转向方案，以跟踪机载轨迹并到达最终轨道。在三个案例研究中提取了所提出算法的数值结果，并与其他参考文献进行了比较，表明其能够找到最佳转移。