Abstract

The task of guidance of a spacecraft, returning from the Moon, to a given landing area, under an effect of “magnified” disturbing factors, is considered. The earlier developed terminal algorithm for control of the descent from a near-Earth orbit was substantially modified, as applied to skip trajectories, with two entries into Earth’s atmosphere, in order to meet the given restrictions on landing accuracy, load factor, and propellant consumption. The modified version of the algorithm includes the “separate” logic of adaptation to the real conditions of motion, with measuring the components of apparent acceleration. The reliability of results is confirmed by a large volume of statistical tests.

中文翻译：

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从月球返回后“放大”扰动下下降的终端控制算法的修改

摘要

考虑了在“放大”干扰因素的作用下，从月球返回到给定着陆区的航天器引导任务。为了满足对着陆精度，载荷系数和推进剂消耗的既定限制，对用于近距离轨道下降的控制的较早开发的终端算法进行了重大修改，该算法适用于跳过轨迹，并且两次进入地球大气层。该算法的修改版本包括对“真实”运动条件的自适应“分离”逻辑，并测量视在加速度的分量。大量统计测试证实了结果的可靠性。