论文部分内容阅读
变长度的测量基线与空间构型的多样性是航天器以编队方式执行深空探测任务的优势之一,该优势的发挥与航天器编队构型重构能力密切相关。针对Halo轨道编队构型重构问题开展研究,分析了Halo轨道编队的构型特性,推导了Halo轨道编队构型重构最优控制的Hamilton方程,基于第一类生成函数构造了最优控制Hamilton方程的迭代求解方法;分别在圆型限制性三体模型和双圆型限制性四体模型中,对地月Halo轨道编队构型重构的最优控制问题进行了仿真计算,验证了迭代求解方法的有效性;仿真结果表明,太阳引力摄动对地月Halo轨道编队构型重构的控制能耗具有较大的影响,选取恰当的重构时机可降低控制能耗。
Variable length of the baseline and the spatial configuration of the diversity of survey is one of the advantages of the spacecraft to the formation of deep space exploration missions to perform one of the advantages of play and spacecraft formation reconfiguration ability is closely related. Aiming at the configuration reconstruction of Halo orbit formation, the configuration characteristics of Halo orbit formation are analyzed. The Hamilton equation of Halo orbit formation reconfiguration optimal control is deduced. Based on the first generation function, the optimal control Hamilton The iterative method is used to solve the optimal control problem of Halo orbital formation reconfiguration in the Moon-constrained three-body model and the bivariate constrained four-body model respectively. The iterative solution The simulation results show that the solar gravitational perturbation has a great influence on the control energy consumption of Halo orbital formation reconfiguration in the lunar month, and choosing the appropriate reconstruction timing can reduce the control energy consumption.