北京航空航天大学学报 ›› 2011, Vol. 37 ›› Issue (4): 462-465.

• 论文 • 上一篇    下一篇

惯性平台在系统中多位置翻滚自标定方法

包为民, 申功勋, 李华滨   

  1. 北京航空航天大学 宇航学院, 北京 100191
  • 收稿日期:2010-05-22 出版日期:2011-04-29 发布日期:2011-04-29
  • 作者简介:包为民(1960-),男,浙江镇海人,博士生,baoweimin@163.com.

Investigation on inertial platform multi-position rolling self-calibration

Bao Weimin, Shen Gongxun, Li Huabin   

  1. 北京航空航天大学 宇航学院, 北京 100191
  • Received:2010-05-22 Online:2011-04-29 Published:2011-04-29

摘要: 影响惯性制导导弹命中精度的主要因素是制导工具误差,而平台的测量误差是其中的主要成分.深入研究惯性平台在系统中的在线标定方法,建立了惯性平台的陀螺仪误差模型及加速度表误差模型,提出了最优多位置翻滚试验方法,通过惯性平台多位置翻滚自标定仿真试验分析了自标定精度的影响因素.仿真结果表明,该方法能有效分离各误差系数,绝大多数误差系数分离精度优于99%,从而提高了导弹的命中精度.

Abstract: The guidance instrument errors are the main factors of reducing the hitting accuracy of inertial-guided missile. The measuring error of inertial platform is the major part. So the multi-position rolling self-calibration approach for inertial platform was studied. The gyroscope error models and the accelerometer error models were firstly built, and multi-position rolling self-calibration test was designed. Based on the scheme, numerical multi-position rolling self-calibration simulations were conducted, and influence factors were anglicized. Simulation results show that this approach can effectively separate the error coefficients. Under normal locked errors, the error coefficients separation precision is better than 99%, accordingly, the hitting accuracy of missile is increased.

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