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弹箭与制导学报 >

2012 , Vol. 32 >Issue 4: 57 - 60

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2012.04.039

导弹与制导技术

基于制导精度最优的惯性组合射前测试数据应用方法

  • 肖正林 ,
  • 牟建华 ,
  • 陈芳 ,
  • 付敏
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  • 第二炮兵装备研究院,北京 100085

肖正林(1971-),男,湖南益阳人,副研究员,博士,研究方向:导航制导与控制。

收稿日期: 2011-11-02

  网络出版日期: 2025-05-29

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The Using Method of IMU Testing Data Before Launching Based on the Best Guidance Precise

  • XIAO Zhenglin ,
  • MOU Jianhua ,
  • CHEN Fang ,
  • FU Min
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  • The Second Artillery Equipment Academy, Beijing 100085, China

Received date: 2011-11-02

  Online published: 2025-05-29

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摘要

研究提出了一种利用捷联惯性测量组合射前测试数据,进一步提高捷联惯导精度的方法。该方法通过落点偏差估计系数将惯性测量组合测试观测方程与落点偏差联系起来。通过对落点偏差估计值的圆概率误差最小化得到落点偏差最优估计系数。讨论了具体应用的方法,并通过仿真验证了方法的有效性。

关键词： 惯性测量组合(IMU); 制导精度; 弹道导弹

本文引用格式

肖正林 , 牟建华 , 陈芳 , 付敏 . 基于制导精度最优的惯性组合射前测试数据应用方法[J]. 弹箭与制导学报, 2012 , 32(4) : 57 -60 . DOI: 10.15892/j.cnki.djzdxb.2012.04.039

Abstract

A method discussed to further improve strapdown inertial guidance by making full use of IMU data before launching. The deviation of impact point related with equations of IMU through estimating coefficient. he optimal estimating coefficients obtained by minimizing the (CEP) of the estimating error of the deviation of impact point. The application method presented and the simulation result its effectiveness.

Key words： inertial-measurement-unit(IMU); guidance precise; ballistic missile

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参考文献

[1]
钟万登 液浮惯性器件[M]. 北京: 中国宇航出版社, 1994.
[2]
肖正林, 徐军辉, 钱培贤. 惯性组合误差射前标定方法研究. 弹箭与制导学报, 2004, 24 (4): 362- 366.
[3]
鲜勇, 钱培贤. 惯性组合误差射前等效补偿方法研究[]. 飞行力学, 2001, 19 (3): 77- 79.
[4]
陈世年. 控制系统设计[M]. 北京: 中国宇航出版社, 1996.
[5]
周小刚, 肖正林, 钱培贤. 惯性测量组合射前动态标定误差分析. 战术导弹控制技术, 2004 (4): 27- 29.
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