针对地月直接转移任务上升段末期，二级发动机提前关机并进入大椭圆轨道的故障场景，传统“调相轨道+直接转移”应急轨道重构策略存在总脉冲大、应急窗口受月球周期约束等问题，提出“调相轨道+弱稳定边界（Weak Stability Boundary, WSB）”应急轨道重构策略。首先，基于大椭圆轨道定轨结果搜索候选转移窗口，利用多圈调相轨道调整日地月相位关系；其次，采用正向分段打靶抬升远地点高度，使航天器进入弱稳定边界区域，通过远地点深空机动和太阳引力摄动，使航天器从远地点返回时抵达月球附近；最后，利用微分修正迭代修正转移轨道，精确满足环月轨道入轨约束。相较于传统“调相轨道+直接转移”策略，该方法有效降低了转移总脉冲并拓展了应急轨道窗口。数值仿真以嫦娥五号应急轨道重构为例，在不同入轨半长轴偏差条件下，“调相轨道+WSB”策略可在一个月内获得连续约20天的应急转移窗口，若要进一步降低总脉冲可采用“调相轨道+月球借力（Lunar Gravity Assist, LGA）+WSB”应急策略，总脉冲最多可降低186.67 m/s，但应急窗口缩减为每月一次。提出的方法可为我国后续月球任务应急轨道设计提供参考。
To address the contingency scenario in which the second-stage engine shuts down prematurely at the end of the ascent phase in Earth–Moon direct transfer missions, thereby injecting the spacecraft into a large elliptical orbit, the conventional contingency trajectory reconstruction strategy of “phasing orbit + direct transfer” exhibits significant limitations, including a large total impulse and emergency windows constrained by the sidereal month. To address these issues, a contingency trajectory reconstruction strategy of “phasing orbit + Weak Stability Boundary (WSB)” is proposed. First, candidate transfer windows are identified based on orbital elements of the large elliptical orbit, and the Sun–Earth–Moon phase configuration is adjusted via multi-revolution phasing orbits. Second, a forward multi-step shooting method is employed to raise the apogee altitude, enabling the spacecraft to enter the WSB region. Combined with deep-space maneuvers at the apogee and solar gravitational perturbation, the spacecraft arrives in the vicinity of the Moon upon returning from apogee. Finally, differential correction is applied to iteratively correct the transfer trajectory, precisely satisfying the lunar low orbit (LLO) insertion constraints. Numerical simulations are conducted for the contingency trajectory reconstruction of the Chang’e-5 mission. The results show that, under different injection semi-major axis deviations, the “phasing orbit + WSB” strategy provides a continuous emergency transfer window of approximately 20 days within one month. Further integration of the Lunar Gravity Assist (LGA) scheme reduces the total impulse by up to 186.67 m/s, though the available window is restricted to once per month. The proposed strategy offers an effective technical reference for emergency trajectory design in future lunar exploration missions.
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