机载导弹空中动基座对准方法的仿真研究

Application of Adaptive Kalman Filter Technique in In-flight Moving Base Alignment for Inertial Navigation System

为了适应现代战争的需要,导弹需要从舰艇或飞机上发射,这时导弹上的惯导系统在投入工作时需要进行初始对准。针对机载导弹平台惯导系统初始对准关于对准精度以及快速性的要求,提出了以自适应卡尔曼滤波为基础的速度匹配空中动基座对准方案,最后通过模拟实际挂飞环境,结合游动自由方位平台惯导系统空中动基座对准,采用Sage和Husa自适应卡尔曼滤波算法进行了数学仿真。仿真结果证实了该方案具有较好的对准精度和快速性,由于采用了自适应卡尔曼滤波技术,使得在噪声统计特性不确切知道的情况下,仿真结果具有较强的鲁棒性。

To satisfy the requirement of modem war, missiles need to be launched from the naval ships or air- planes. The inertial navigation system of the missile should be aligned before going working. A velocity matching alignment approach based on adaptive Kalman filter is put forward for missile inertial navigation system on moving base in flight. The paper gives the simulation of in - flight moving base alignment, which adopted Sage ＆ Husa adaptive Kalman filter algorithm. The validity of the proposed means is proved by the simulation result.