先进上面级快速机动轨道优化设计

根据先进上面级的推力特点和任务需求,将快速机动轨道优化问题转化为有限推力下时间最优轨道机动问题。首先建立脉冲推力下的多约束时间最优优化模型,然后利用改进的微分进化法求解全局最优解。其次建立有限推力下的修正模型,对脉冲推力的优化结果进行修正,最终得到有限推力下时间最优轨道机动问题的解。通过快速轨道交会仿真验证了模型和算法的合理性,所得终端位置误差为1 km量级,在容许范围内,可通过末端轨道调整进一步修正。理论分析和仿真结果表明:结合脉冲变轨和有限推力修正的模型能更准确描述轨道机动的实际情况,采用的改进微分进化算法收敛速度快,稳定性好,对初值无明显要求。

Optimal Design on Quick Orbit Maneuver of Advanced Upper Stage

Advanced Upper Stage (AUS) is an important aircraft for future spaceflight. Based on AUS''s thrust characteristic and assignment demand, the problem of AUS''s quick orbit maneuver optimization is transformed to that of Minimum-time orbit maneuver using finite thrust. Firstly, a multi-restriction and minimum-time optimal model on impulse thrust is established, and the Improved Differential Evolution (IDE) algorithm is used to achieve global optimal solution. Secondly, a correct model on finite-thrust is built to modify the optimal solution by impulse thrust. Finally the solution of Minimum-time optimal orbit maneuver is obtained by finite-thrust. The simulation of quick orbital rendezvous has verified the reasonableness and correctness of the model and algorithm, the obtained terminal position error is 1.0 km magnitude and can be further corrected by terminal orbit adjustment.