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改进的内框架驱动式硅MEMS陀螺温度误差模型

房建成 李建利 盛蔚

房建成, 李建利, 盛蔚等 . 改进的内框架驱动式硅MEMS陀螺温度误差模型[J]. 北京航空航天大学学报, 2006, 32(11): 1277-1280.
引用本文: 房建成, 李建利, 盛蔚等 . 改进的内框架驱动式硅MEMS陀螺温度误差模型[J]. 北京航空航天大学学报, 2006, 32(11): 1277-1280.
Fang Jiancheng, Li Jianli, Sheng Weiet al. Improved temperature error model of silicon MEMS gyroscope with inside frame driving[J]. Journal of Beijing University of Aeronautics and Astronautics, 2006, 32(11): 1277-1280. (in Chinese)
Citation: Fang Jiancheng, Li Jianli, Sheng Weiet al. Improved temperature error model of silicon MEMS gyroscope with inside frame driving[J]. Journal of Beijing University of Aeronautics and Astronautics, 2006, 32(11): 1277-1280. (in Chinese)

改进的内框架驱动式硅MEMS陀螺温度误差模型

基金项目: 国防基础科研基金资助项目(k1204060116); 新世纪优秀人才支持计划资助项目(NCET-04-0162)
详细信息
    作者简介:

    房建成(1965-),男,山东临沂人,教授,fangjiancheng@buaa.edu.cn.

  • 中图分类号: U 666.1; V 241.6

Improved temperature error model of silicon MEMS gyroscope with inside frame driving

  • 摘要: 温度误差是MEMS(Micro Electronic Mechanical System)陀螺仪的主要误差源之一,为了消除温度对内框架驱动式硅MEMS陀螺仪性能的影响,提出了一种改进的温度误差模型.基于硅材料的赛贝克(Seebeek)效应,结合表头温度变形,分析了陀螺仪零偏误差;利用温度引起的干扰力矩,分析了陀螺仪输出与比力及角加速度有关项误差;针对温度引起系统谐振频率的变化,分析了陀螺仪标度因数误差.试验结果表明:在温度变化过程中,比力引起的干扰力矩是导致陀螺仪温度误差的主要因素,验证了改进的温度误差模型的正确性,补偿后陀螺仪的零偏稳定性提高了53.75倍,标度因数精度提高了19.6倍,改进的温度误差模型也适用于其它MEMS陀螺仪.

     

  • [1] Jia Ruigao,Wang Jinsong,Feng Guanping.Temperature coefficient of sensitivity dependence of the measurement error quartz crystal resonators International Frequency Control Symposium. :IEEE, 1996:493-500 [2] Dauderstadt U A, Sarro P M, Middelhoek S.Temperature dependence and drift of a thermal accelerometer International Conference on Solid Sensors and Actuators. Chicago:IEEE, 1997:1209-1212 [3] Victor E D,Vladimir M P.The determined chaos in disturbed by temperature dynamic systems with gyros[J].IEEE,2003:638-643 [4] 李万玉,阮爱武,罗晋生,等.微机械梳状驱动音叉陀螺仪的误差源研究[J].航空学报, 1999, 20(5):426-429 Li Wanyu,Yuan Aiwu, Luo Jinsheng,et al.Error sources in micromachined comb-drive tuning-fork gyroscope[J].Acta Aeronautica et Astronautica Sinica, 1999, 20(5):426-429(in Chinese) [5] Ashwin A S. Integrated micromecchehanical resonant sensor for inertial measurement system . Berkeley :School of Electrical Engineering and Computer Science,University of California,2002 [6] Wyatt O D. Mechanical analysis and design of vibratory micromachined gyroscopes . Berkeley :School of Mechanical Engineering,University of California,2001 [7] Jason K P H. Modeling and indentification of the jet propulsion laboratory vibratory rate microgyroscope . Los Angeles:School of Mechanical Engineering, University of California,2002 [8] 王寿荣.硅微惯性器件理论及应用[M].南京:东南大学出版社,2000:56-61 Wang Shourong.The theories and application of silicon inertial microsensor[M].Nanjing:Southeast University Press,2000:56-61(in chinese) [9] Itzhack Y B,Richard R H.Implicit and explicit spacecraft gyro calibration AIAA Guidance,Navigation,and Control Conference and Exhibit. Providence:AIAA,2004:1-17 [10] 徐丽娜,邓正隆,张广莹.陀螺仪温度试验与建模研究[J].宇航学报,1999, 20(2):99-103 Xu Lina, Deng Zhenglong,Zhang Guangying. Temperatue test and modeling research of gyroscope[J].Journal of Astronautics, 1999, 20(2):99-103(in Chinese)
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出版历程
  • 收稿日期:  2006-04-30
  • 网络出版日期:  2006-11-30

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