期刊文献+

基于地磁滚转角测量系统陀螺在线标定技术

On-Line Calibration Technique of the Gyroscope Based on the Geomagnetic Roll Angle Measurement System
下载PDF
导出
摘要 针对弹载陀螺在发射过程中产生较大过载导致陀螺零点和灵敏度发生变化的问题,提出了一种利用地磁测量信息对陀螺进行在线标定的方法。该方法是利用最小二乘法对地磁场提供的滚转角信息与陀螺的数据进行拟合得到陀螺的标定参数:零点误差和灵敏度误差。通过仿真实验表明,采样点数为10时标定的效果最好。接着研究了速率对陀螺标定精度的影响。在外场实验中在线标定方法角速率误差为7.86°/s,相比速率标定方法,该角速率误差减小到原来的1/10。仿真实验和外场实验都表明在线标定方法所得到的角速率精度有明显提高。 For the problem that ballistic axial gyroscope can produce a larger overload resulting in the changes of its zero point and sensitivity during the launching process, an on-line calibration method of the gyroscope was proposed by using the geomagnetic measurement information. To obtain the calibration parameters of the gyroscope, i. e. , the zero point error and sensitivity error, the least squares method was used to fit the gyroscope data and roll angle information provided by the geomagnetic field. The simulation experiment shows that the calibration effect is the best when the sampling number is 10. Then the effect of the rate on the calibration accuracy of the gyroscope was studied. In the out-field experiment, the angular rate error of the on-line cali- bration method is 7.86 ~/s, which reduces to 1/10 compared with that of the rate calibration method. Both the simulation and out-field experiments show that the accuracy of the angular rate is improved significantly by using the on-line calibration method.
出处 《微纳电子技术》 北大核心 2017年第6期431-435,共5页 Micronanoelectronic Technology
基金 国家自然科学基金资助项目(51375463)
关键词 陀螺 在线标定 最小二乘法 地磁信息 速率标定法 gyroscope on-line calibration least square method geomagnetic information rate
  • 相关文献

参考文献6

二级参考文献49

  • 1马云峰,周百令,万振刚,赵立业.微惯性测量组合标定系统的研究[J].测控技术,2004,23(10):56-58. 被引量:3
  • 2潘泉,杨峰,叶亮,梁彦,程咏梅.一类非线性滤波器——UKF综述[J].控制与决策,2005,20(5):481-489. 被引量:231
  • 3华冰,刘建业,熊智,祝燕华.SINS/北斗/星敏感器组合导航系统研究[J].应用科学学报,2006,24(2):120-124. 被引量:6
  • 4陆志东,王磊.捷联惯导系统的空中标定方法[J].中国惯性技术学报,2007,15(2):136-138. 被引量:32
  • 5Kok-Lam Lai,Amherst N Y,Crassidis J.Real-time attitude-independent gyro calibration from three-axis magnetometer measurements[C]//AIAA/AAS Astrodynamics Specialist Conference.Aug.16-19,2004:1-11.
  • 6Crassidis J L.Survey of nonlinear attitude estimation methods[J].Journal of Guidance,Control,and Dynamics,2007,30(1):12-28.
  • 7Marschke J M,Crassidis J L.Attitude estimation without rate gyros using generalized multiple model adaptive estimation[C]//AIAA Guidance,Navigation,and Control Conference.Austin,Texas,11-14 August 2003.
  • 8Chang Honglong,Xue Liang,Qin Wei,et al.An integrated MEMS gyroscope array with higher accuracy output[J].Sensors,2008,8(4):2886-2899.
  • 9Virtual Ionosphere,Thermosphere,Mesosphere Observatory (VITMO).DGRF/IGRF geomagnetic field model 1900-2015 and related parameters.[2011-03-20]http://omniweb.gsfc,nasa.gov/vitmo/igrf_vitmo.html.
  • 10Soken H E,Hajiyev C.Adaptive unscented Kalman filter with multiple fading factors for pico satellite attitude estimation[C]//Recent Advances in Space Technologies 4th International Conference,2009:541-546.

共引文献49

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