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月球探测器返回具有再入速度大,动力学耦合剧烈以及误差作用明显的特点。利用标准弹道法研究了低升阻比月球探测器的再入制导问题。得到2 000 km和3 000 km航程的标准弹道;讨论了基于时间变量进行增益反馈的制导方法,给出2 000 km航程下的最大单项误差仿真结果,并针对两种航程进行了Monte-Carlo抽样。考虑到时间积分模式不能全面的采集关键点信息,引入能量作为标准弹道的离散量;针对有初始速度偏差时标准弹道与实际弹道初始能量不一致的情况,提出能量比例尺的概念,很好地解决了能量匹配的问题。Monte-Carlo仿真表明:基于能量的标准弹道法精度明显提高,2 000 km航程下纵程偏差在10 km以内,3 000 km航程基本控制在30 km以内。
Lunar probe returns have the characteristics of reentry speed, dynamic coupling and obvious error. Using the standard ballistic method, we study the reentry guidance of low lift-drag ratio moon detectors. The standard trajectory of 2 000 km and 3 000 km is obtained. The guidance method of gain feedback based on time variation is discussed. The maximum single error simulation result of 2 000 km range is given. The Monte-Carlo sampling . Considering that the time integral model can not comprehensively collect the key point information and introduce energy as the standard discrete trajectory, the concept of energy scale is proposed for the case that the initial trajectory of the initial velocity deviation is inconsistent with the initial energy of the actual trajectory. Energy matching problem. The Monte-Carlo simulation results show that the accuracy of the standard ballistic method based on energy is obviously improved. The deviation of the longitudinal course under 2 000 km is within 10 km and that of the 3 000 km is within 30 km.