基于INS/ILS/RA组合导航的自动着陆系统

Automatic landing system based on INS/ILS/RA integrated navigation

针对民航机精密进近着陆过程容易受地场环境、电磁干扰等空间噪声和接收机噪声的影响,对波束误差信号进行滤波相位滞后的问题,提出基于INS/ILS/RA组合导航的自动着陆系统(ALS)。该系统将仪表着陆系统(ILS)及无线电高度表(RA)和惯性导航系统(INS)输出的位置之差作为量测,运用卡尔曼滤波器进行估计,将组合导航系统的输出航迹角及纵向轨迹角替代波束偏差,分别送入横纵向控制回路。仿真结果表明,INS/ILS/RA组合位置解算方位角偏差精度优于0.3°,下滑角偏差精度优于0.2°。该系统可显著改善波束误差控制信号的动态品质,降低噪声影响,提高ILS自动进场着陆控制回路的稳定性和闭环性能。

During precision approach and landing,the civil aircraft is susceptible to the receiver noises and space noises such as field environment and electromagnetic interference.In view of the problems in filtering out the phase lag of beam error signal,an automatic landing system（ALS） based on INS/ILS/RA integrated navigation is put forward.The measurement signal is an error signal achieved by comparing the output position of the inertial navigation system（INS） with that of the instrument landing system（ILS） and radio altimeter（RA）.Then using a Kalman filter to estimate the results,the beam deviation will be replaced by two outputs of the integrated system-the course angle and pitch angle,which are then looped back to the control circuit respectively.The simulation results show that the directions angle error is superior to 0.3°,and the gliding angle error is superior to 0.2°.The integrated system can significantly improve the dynamic quality of the beam error control signal,reduce the noise influence and improve the stability and closed-loop performance.