针对半球谐振陀螺平台惯导系统初始对准过程中存在的航向效应的问题, 研究探讨了航向效应误差对半球谐振陀螺平台惯导系统初始对准精度的影响。为了消除航向效应误差的影响, 结合导弹实际应用要求, 设计了航向效应的自标定方案。实验结果表明, 半球谐振陀螺平台惯导系统航向效应标定方法能够有效补偿航向效应误差, 提高半球谐振陀螺平台惯导系统的初始对准精度。

Aiming at the issue of heading effect of Hemisphere Resonator Gyro (HRG) platform Inertial Navigation System (INS) during the initial alignment, we studied the influence of heading effect error on the initial alignment accuracy of HRG INS. In order to eliminate the influence of heading error effect, we designed a self-calibration scheme of the heading effect based on the practical application requirements of the missile. The experimental results shows that this HRG INS heading effect calibration method can effectively compensate for the heading effect error and improve the accuracy of self-aligned HRG platform INS.