机抖激光陀螺捷联惯导系统的温度补偿方法

Methods for compensating temperature of strap-down inertial navigation system with mechanically dithered ring laser gyroscope

分析了系统温度对机抖激光陀螺捷联惯性导航系统的影响因素,介绍了降低和补偿捷联系统温度误差的4种方法。通过重复性温度实验,利用逐步回归法分析了激光陀螺零偏与温度的关系;通过多项式拟合,分别得到了加速度计的零偏、标度因子和IF转换电路的温度补偿模型,并在捷联系统中得到应用。对其中的两种方法进行了实验研究和导航测试,并对两种方法的补偿效果进行了对比。结果表明:通过温度实验得到惯性器件的温度补偿模型对其温度误差进行实时补偿是捷联系统最理想的补偿方法。补偿后系统定位测试1 h的圆概率误差(CEP)优于0.3 n mile/h,达到国内先进水平。

The influence of temperature on the strap-down inertial navigation system（SINS） with the mechanically dithered ring laser gyroscope（RLG） were analyzed,and four methods to reduce temperature error were discussed.The relationship between gyroscope bias and temperature in repeating experiments was analyzed by using the stepwise regression method.The temperature compensation models for the accelerometer bias,scale and the I/F conversion circuit were obtained by polynomial fitting of experimental data,and these models were applied in the SINS.Temperature experiments and navigation testing by use of two methods were performed and compared with each other.The result shows that the real-time compensating method based on the experimental dynamic temperature models for inertial devices is the best choice for the SINS.In the position location tests,the circular error probable（CEP） of the compensated system is less than 0.3 n mile/h.