以“嫦娥六号”任务搭载的巴基斯坦立方星为研究对象,系统分析了其轨道特性、力学环境及测量手段,重点探讨了影响轨道变化的主要摄动因素。在缺乏测距和甚长基线干涉测量(Very Long Baseline Interferometry,VLBI)支持的条件下,提出了...以“嫦娥六号”任务搭载的巴基斯坦立方星为研究对象,系统分析了其轨道特性、力学环境及测量手段,重点探讨了影响轨道变化的主要摄动因素。在缺乏测距和甚长基线干涉测量(Very Long Baseline Interferometry,VLBI)支持的条件下,提出了一种基于三向测速的轨道确定方法,建立了三向测速模型,并对测速误差进行分析;同时,设计了适用于稀疏观测模式的定轨策略,并完成了误差评估。此外,对立方星轨道的长期演化进行了深入分析。研究结果表明:三向多普勒测速残差的均方根误差为2 mm/s,轨道确定的位置精度优于1 km;立方星轨道主要受月球非球形引力摄动和地球质点引力摄动的影响,三体引力在其轨道演化中起到了重要作用。轨道演化预测显示,立方星的近月距离预计于2025年4月缩小至小于月球半径。研究为深空探测任务中的微小卫星轨道确定与演化分析提供了参考。展开更多
In this paper,we investigate analytical numerical iterative strategies for the pursuit-evasion game involving spacecraft with leader–follower information.In the proposed problem,the interplay between two spacecraft g...In this paper,we investigate analytical numerical iterative strategies for the pursuit-evasion game involving spacecraft with leader–follower information.In the proposed problem,the interplay between two spacecraft gives rise to a dynamic and real-time game,complicated further by the presence of perturbation.The primary challenge lies in crafting control strategies that are both efficient and applicable to real-time game problems within a nonlinear system.To overcome this challenge,we introduce the model prediction and iterative correction technique proposed in model predictive static programming,enabling the generation of strategies in analytical iterative form for nonlinear systems.Subsequently,we proceed by integrating this model predictive framework into a simplified Stackelberg equilibrium formulation,tailored to address the practical complexities of leader–follower pursuit-evasion scenarios.Simulation results validate the effectiveness and exceptional efficiency of the proposed solution within a receding horizon framework.展开更多
基金supported,in part,by the National Natural Science Foundation of China(Nos.12372050 and 62088101)the Zhejiang Provincial Natural Science Foundation of China(No.LR20F030003).
文摘In this paper,we investigate analytical numerical iterative strategies for the pursuit-evasion game involving spacecraft with leader–follower information.In the proposed problem,the interplay between two spacecraft gives rise to a dynamic and real-time game,complicated further by the presence of perturbation.The primary challenge lies in crafting control strategies that are both efficient and applicable to real-time game problems within a nonlinear system.To overcome this challenge,we introduce the model prediction and iterative correction technique proposed in model predictive static programming,enabling the generation of strategies in analytical iterative form for nonlinear systems.Subsequently,we proceed by integrating this model predictive framework into a simplified Stackelberg equilibrium formulation,tailored to address the practical complexities of leader–follower pursuit-evasion scenarios.Simulation results validate the effectiveness and exceptional efficiency of the proposed solution within a receding horizon framework.
