摘要
为有效提高半球谐振陀螺惯导系统导航精度,解决温度变化对快速启动性以及实际应用精度产生显著影响的问题,分析了系统级标定误差参数的温度特性,并建立了温度误差模型,最后设计了温度补偿试验以及平台模式标定试验对补偿效果进行检验。试验结果表明,建立的温度误差补偿模型准确有效,误差参数稳定性得到提升,提高了启动阶段半球谐振陀螺惯导系统的性能,且计算量较小,具有较高的工程应用价值。
In order to improve the navigation accuracy of hemispherical resonator gyroscope inertial navigation system effectively,and solve the problem that temperature has great influence on fast start-up and practical application precision of the product,the temperature characteristics of system-level calibration error parameters are analyzed in this paper,and the temperature error model is established.Finally,the temperature compensation experiment and the platform mode calibration experiment are designed to verify the compensation effect.The experiment results show that the established temperature error compensation model is accurate and effective,the stability of error parameters is improved,and the performance of hemispherical resonator gyroscope inertial navigation system is improved in the start-up phase.The calculation amount is small,and it has high engineering application value.
作者
陶陶
乔相伟
陈志豪
梁爱琦
王雷
石琪
TAO Tao;QIAO Xiang-wei;CHEN Zhi-hao;LIANG Ai-qi;WANG Lei;SHI Qi(The 16^(th)Institution,China Aerospace Science and Technology Corporation,Xi’an 710100)
出处
《导航与控制》
2023年第4期74-80,共7页
Navigation and Control
关键词
高精度
半球谐振陀螺惯导系统
温度误差补偿
系统级标定
high-precision
hemispherical resonator gyroscope inertial navigation system
temperature error compensation
system-level calibration
