| 基于线性协方差的月球上升器主动段误差分析 |
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| 引用本文： | 王志文,张洪华.基于线性协方差的月球上升器主动段误差分析[J].空间控制技术与应用,2014(3):25-30. |
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| 作者姓名： | 王志文 张洪华 |
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| 作者单位： | 北京控制工程研究所; |
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| 摘 要： | 提出一种线性协方差误差分析方法用于月球上升器主动段多种误差源影响分析.给出了动力上升段动力显式制导(PEG,powered explicit guidance)制导律线性化解析方法,得到了PEG 3个制导参数的线性化显式表达.在此基础上用于分析月球上升器主动段在存在初始状态偏差、参数不确定等情况下,终端时刻的高度偏差、速度大小偏差以及飞行路径角偏差.通过和蒙特卡洛的仿真对比,验证了上述线性化方法的有效性.
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| 关 键 词： | 线性协方差 月球上升器主动段 PEG制导 |
Error Analysis Based on Linear Covariance for Lunar Powered Ascent Phase |
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| WANG Zhiwen,ZHANG Honghua.Error Analysis Based on Linear Covariance for Lunar Powered Ascent Phase[J].Aerospace Contrd and Application,2014(3):25-30. |
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| Authors: | WANG Zhiwen ZHANG Honghua |
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| Institution: | ( Beijing Institute of Control Engineering, Belting 100190, China) |
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| Abstract: | A new analytic linear covariance method for powered explicit guidance（PEG）is proposed, and the method is capable of obtaining the explicit expressions of PEG＇ s three parameters. The method is applied to analyze the final altitude dispersion, velocity magnitude dispersion and flight path angle dispersion with the existence of original state errors and parameter uncertainties in the lunar powered ascent phase. In contrast with Monte Carlo simulation results, the method is proved to be valid. |
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| Keywords: | linear covariance lunar powered ascent phase PEG |
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