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针对探月任务多窗口发射需求和目标轨道受到明显月球引力摄动的特点,提出一种快速高效的发射轨道设计方法:在星箭分离前的发射段,各发射窗口对应的发射轨道的一、二级飞行段完全相同,仅调整三级工作段程序角和无动力滑行时间,以满足入轨要求;在末级排放段,微调末级速度方向,利用月球摄动抬高末级近地点高度,使之超过GEO受保护区。该方法可统一火箭一、二级飞行段状态,缩小子级残骸落区范围,增强入轨参数设计的灵活性,显著提高星箭入轨参数迭代和相关分析工作的效率,明显改善末级离轨效果,符合空间安全相关要求,可推广应用于其他深空探测任务的多窗口发射轨道设计。
Aiming at the requirement of multi-window launch of lunar mission and the obvious orbits of the target orbit being obviously gravitationally perturbed by the moon, a fast and efficient launch orbit design method is proposed: in the launching section before the separation of stars and arrows, The second stage of flight is exactly the same, only adjust the three working stage program angle and no power taxi time to meet the requirements of the orbit; In the last stage of emissions, fine-tuning the final speed direction, the use of the lunar perturbation elevation last level near the height, Make it over GEO Protected Area. The method can unify the state of the first and second flight stages of the rocket, narrow down the falling range of the child debris, enhance the flexibility of the orbital parameter design, significantly improve the efficiency of iteration and correlation analysis of the orbital orbital parameters, and obviously improve the final distance Rail effect, in line with the relevant requirements of space security, can be extended to other deep space exploration mission multi-window launch track design.