飞行器动力学信息辅助MEMS惯导系统

Aircraft dynamics-aided MEMS inertial navigation system

使用微机械电子(micro electro mechanical systems,MEMS)惯导系统(inertial navigation system,INS)的飞行器由于其MEMS惯性器件测量精度低,致使导航误差快速发散。针对该问题,提出了一种利用飞行器动力学(aircraft dynamics,AD)信息辅助MEMS惯导解算的方法。它基于AD建立的飞行器运动模型和运动误差模型,利用实时解算的飞行器运动状态构建卡尔曼滤波器对MEMS惯导误差进行估计和修正。在此基础上,进一步考虑了INS/全球定位系统(global positioning system,GPS)组合导航时该方法的改进算法,提出了一种利用GPS定位信息和预测滤波器对飞行器动力学模型误差估计的方法。最后的半实物仿真实验结果表明,飞行器动力学信息辅助滤波器可以有效地减小系统误差,提高MEMS惯导系统输出精度。

The micro electro mechanical systems（MEMS）inertial navigation system（INS）of an aircraft has low measure accuracy,so that the navigation error rapidly drifts.For this shortage,an aircraft dynamics（AD）-aided MEMS INS method is proposed.The method is based on the AD model and the dynamic error model,using real-time dynamic calculation information to build Kalman filter to estimate and correct MEMS INS error.Further more,considering the improved algorithm when integrating INS/global positioning system（GPS）navigation,an arithmetic is proposed which evaluates aircraft dynamic error by making use of GPS information and the predictive filter.Finally,the hardware-in-the-loop simulation test result shows that the aircraft dynamics-aided system can effectively reduce INS system error and improve the MEMS INS output accuracy.