| 中高精度捷联惯导系统的无转台标定 |
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| 引用本文： | 康宇航,周绍磊,祁亚辉,等. 中高精度捷联惯导系统的无转台标定[J]. 战术导弹技术, 2014, 0(2): 85-90 |
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| 作者姓名： | 康宇航 周绍磊 祁亚辉 等 |
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| 作者单位： | [1]海军航空工程学院控制科学与工程系,山东烟台264000 [2]海军航空工程学院训练部,山东烟台264000 |
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| 摘 要： | 阐述了一种无转台标定中高精度惯导系统的方法,依据正交轴上加速度计输出矢量和等于重力的原理,标定出加速度计输出模型中相关参数。对于陀螺参数的标定,先通过翻转法得到陀螺标度因数的粗略值,再通过观测导航系统速度误差,求出陀螺相关安装误差并修正陀螺标度因数,最后根据静止时陀螺输出矢量相对关系得到陀螺零位。仿真和实际试验验证了这种标定方法的可行性。
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| 关 键 词： | 捷联惯导系统 无转台标定 模观测 导航误差 |
Non-turntable Calibration in Moderate and High Precision SINS |
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| Kang Yuhang,Zhou Shaolei,Qi Yahui,Yu Jiahui. Non-turntable Calibration in Moderate and High Precision SINS[J]. Tactical Missile Technology, 2014, 0(2): 85-90 |
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| Authors: | Kang Yuhang Zhou Shaolei Qi Yahui Yu Jiahui |
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| Affiliation: | 1. Department of Control Engineering, Naval Aeronautical and Astronautical University, Yantai Shandong 264000, China; 2. Department of Training, Naval Aeronautical and Astronautical University, Yantai Shangdong 264000, China) |
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| Abstract: | A non-turntable calibration method for moderate and high precision SINS is described. Ac- cording to the principle that the sum of orthogonal axes accelerometer output vector is equal to gravity, the related parameters in the output model can be calibrated. With regard of gyro parameters, the rough value of scale factor can be calibrated by flipping method, and then through observing the speed error of the navigation system, the gyro＇s installation error can be calculated and scale factor can be corrected. Fi- nally, according to the relative relationship of gyro＇ s static output vector, the gyro zero position is obtained. Simulation and practical test all prove the feasibility of this calibration method. |
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| Keywords: | SINS non-turntable calibration norm observations navigation error |
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