期刊文献+
任意字段
题名或关键词
题名
关键词
文摘
作者
第一作者
机构
刊名
分类号
参考文献
作者简介
基金资助
栏目信息

基于线性协方差的月球上升器主动段误差分析 被引量：1

Error Analysis Based on Linear Covariance for Lunar Powered Ascent Phase
下载PDF
导出
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. 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.
作者 王志文 张洪华
机构地区 北京控制工程研究所
出处 《空间控制技术与应用》 2014年第3期25-30,共6页 Aerospace Control and Application
关键词 线性协方差 月球上升器主动段 PEG制导 linear covariance lunar powered ascent phase PEG
分类号 V448.2 [航空宇航科学与技术—飞行器设计]
  • 相关文献

参考文献9

  • 1KOS L D,POLSGROVE T T,SOSTARIC R R,et al. Al- tair descent and ascent reference trajectory design and initial dispersion analyes[ R]. 20100035768, 2010.
  • 2SOSTARIC R R,MERRIAM R S. Lunar ascent and ren- dezvous trajectory design[ R]. 20080009584, 2008.
  • 3BENNETT F V. Apollo experience report mission plan- ning for lunar module descent and ascent [ R ]. 19720018205, 1972.
  • 4ROSE M B, GELLER D. Linear covariance techniques for powered ascent[ R]. AIAA20108175,2010.
  • 5MCHENRY R L, BRAND T J, LONG A D, et al, Space shuttle ascent guidance, navigation, and control[ J ]. Journal of Astronautical Sciences, 1979,28 ( 1 ) : 1-38.
  • 6SPRINGMANN P, PROULX R, FILL T. Lunar descent using sequential engine shutdown [ R ]. 2006-6678, 2006.
  • 7GELLER D K, ROSE M B, WOFFINDEN D C. Event trigger in linear covariance analysis with application to orbital rendezvous [ J ]. Journal of Guidance, Control, and Dynamics, 2009,32( 1 ) : 102-111.
  • 8GELLER D K, CHRISTENSEN D P. Linear covariance analysis for powered lunar descent and landing[ J]. Jour- nal of Spacecraft and Rockets ,2009,46 ( 6 ) : 1231 - 1235.
  • 9MOESSER T J. Guidance and navigation linear covariance analysis for lunar powereddescent [ D ]. Logan Utah State:Utah State University,2010.

同被引文献6

  • 1ROSE M B, GELLER D. Linear covariance techniquesfor powered ascent [ C ]//AIAA Guidance, Navigation, and Control Conference. Washiton D. C. : AIAA., 2010 : 1-21.
  • 2MCHENRY R. , BRAND T J, LONG A D, et al, Space shuttle ascent guidance, navigation, and control [ J ]. Journal of Astronautical Sciences, 28 (1) : 1979 : 1-38.
  • 3SPRINGMANN P, PROULX R, Fill T. Lunar descent using sequential engine shutdown [ C ]//AIAA/AAS As- trodynamics Specialist Conference and Exhibit. Washi- ton D. C. AIAA: ,2006:1-18.
  • 4BRAND T J, BROWN D W; HIGGINS J P. Space shuttle GNC equation document NO. 24 unified powered flight guidance [ R]. Cambridge: Charles Stark Draper Laboratory, 1974 : 1-21.
  • 5SEARS N E. Apollo guidance and navigation [ R ]. Cambridge : Instrumentation Laboratory, 1979:495-497.
  • 6ZARCHAN P, MUSOFF H. Fundamentals of Kalman filtering: a practical approach [ M ]. Reston, VA: A- merican Institute of Aeronautics and Astronautics, 2000 : 129-182.

引证文献1

二级引证文献2

空间控制技术与应用
2014年 第3期

相关作者

内容加载中请稍等...

相关机构

内容加载中请稍等...

相关主题

内容加载中请稍等...

浏览历史

内容加载中请稍等...
;
使用帮助 返回顶部