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初始对准性能是影响智能弹药姿态控制与弹道修正效果的重要因素之一。针对弹载MEMS捷联惯性导航系统,研究了一种基于常规捷联惯导系统结构的3轴加速度计斜装余度配置系统结构改进方案,以及该结构的系统在大俯仰角条件下的初始对准方法,并在高精度转台上进行了对准方法的实际性能验证。实验结果表明了MEMS惯导系统的改进结构与初始对准方法,在载体大俯仰角条件下提高初始对准精度与加速度计偏置稳定性的有效性。本文的研究可为弹载环境下的MEMS惯性导航系统提供理论研究与工程应用参考。
Initial alignment performance is one of the important factors that affect the attitude control and ballistic correction of intelligent ammunition. Aiming at the missile strap-down inertial navigation system of inertial navigation system (MEMS), an improved scheme of 3-axis accelerometer slack redundancy configuration system based on the conventional strapdown inertial navigation system structure was studied. The initial configuration of the system under large pitch angle Align the method and verify the actual performance of the alignment method on a high precision turntable. The experimental results show the improved structure and initial alignment method of MEMS inertial navigation system. The validity of initial alignment accuracy and accelerometer bias stability under large carrier pitch angle conditions are demonstrated. The research in this paper can provide theoretical and engineering reference for MEMS inertial navigation system in missile-borne environment.