北京航空航天大学学报 ›› 2018, Vol. 44 ›› Issue (8): 1755-1763.doi: 10.13700/j.bh.1001-5965.2017.0604

• 论文 • 上一篇    下一篇

一种新型陀螺的力矩器非圆性误差补偿方法

陈国越, 王华, 任元, 辛朝军   

  1. 航天工程大学 宇航科学与技术系, 北京 101416
  • 收稿日期:2017-09-26 修回日期:2018-01-05 出版日期:2018-08-20 发布日期:2018-08-29
  • 通讯作者: 任元 E-mail:renyuan_823@aliyun.com
  • 作者简介:陈国越,男,硕士研究生。主要研究方向:磁悬浮控制敏感陀螺的测量;王华,男,博士,教授,博士生导师。主要研究方向:飞行器测试与发射;任元,男,博士,副教授,硕士生导师。主要研究方向:导航制导与控制。
  • 基金资助:
    国家自然科学基金(51475472,61403396)

A new gyro torquer's non-circular error compensation method

CHEN Guoyue, WANG Hua, REN Yuan, XIN Chaojun   

  1. Department of Aerospace Science and Technology, Space Engineering University, Beijing 101416, China
  • Received:2017-09-26 Revised:2018-01-05 Online:2018-08-20 Published:2018-08-29
  • Supported by:
    National Natural Science Foundation of China (51475472, 61403396)

摘要: 为提高磁悬浮控制敏感陀螺(MSCSG)对陀螺载体姿态的敏感精度,基于其洛伦兹力磁轴承(LFMB)的设计结构,提出了一种力矩器非圆性误差补偿方法。首先,针对一种新型双球形包络面转子MSCSG,介绍了MSCSG的结构特点与陀螺载体姿态角速度敏感原理,并分别建立了MSCSG力矩器半径误差模型、转子偏转干扰力矩模型与陀螺载体姿态角速度敏感误差模型。其次,通过实验测量了力矩器的圆度,通过MATLAB进行数据拟合得到了力矩器的非圆特性,采用勒让德多项式级数对力矩器非圆性进行了描述,并有效补偿了因力矩器非圆性误差导致的姿态角速度敏感误差。最后,对误差补偿效果进行了仿真验证,结果表明该补偿方法使陀螺载体姿态角速度敏感误差降低了83.5%。此外,本文方法还可以解决LFMB陀螺的相关共性问题。

关键词: 磁悬浮控制敏感陀螺(MSCSG), 力矩器, 洛伦兹力磁轴承(LFMB), 姿态角速度敏感, 非圆性误差补偿

Abstract: Based on the structural design of the Lorentz force magnetic bearing (LFMB), a kind of torquer's non-circular error compensation method is put forward to enhance the sensitivity accuracy of magnetically suspended control sensitive gyroscope (MSCSG) to gyro carrier attitude. First, for a new type MSCSG with double spherical envelope rotor, the structure features of MSCSG and the attitude angular velocity measurement principle of the gyro carrier are introduced and the radius error model of MSCSG torquer, the interference torque model of rotor's deflection and the measurement error model of the gyro carrier's attitude angular velocity are set up. Then, the roundness of torquer is measured through the experiment, and data fitting is conducted by MATLAB to obtain the non-circular characteristic of the torquer. The non-circular characteristic is described by Legendre polynomial series, and the measurement error of the gyro carrier's attitude angular velocity caused by the torquer's non-circular error is compensated effectively. Finally, the effect of error compensation is verified by the simulation and the results show that the compensation method makes the measurement error of the gyro carrier's attitude angular velocity reduce by 83.5%. In addition, the proposed method can solve the common problems related to LFMB gyro.

Key words: magnetically suspended control sensitive gyroscope (MSCSG), torquer, Lorentz force magnetic bearing (LFMB), attitude angular velocity sensitivity, non-circular error compensation

中图分类号: 


版权所有 © 《北京航空航天大学学报》编辑部
通讯地址:北京市海淀区学院路37号 北京航空航天大学学报编辑部 邮编:100191 E-mail:jbuaa@buaa.edu.cn
本系统由北京玛格泰克科技发展有限公司设计开发