大攻角下基于卡尔曼滤波的大气参数修正算法

Correction Algorithm for Air Data Based on Kalman Filter at High Angle of Attack

针对新一代航空飞行器在大攻角飞行时大气数据系统测量精度严重下降问题,提出了基于卡尔曼滤波的大气参数修正算法。该算法利用大气数据测量信息和惯性导航信息,基于飞行器力学方程构建卡尔曼滤波器,通过卡尔曼滤波的方法实现对大气参数的修正。仿真结果表明,经卡尔曼滤波修正后的大气参数能够有效消除大攻角下原始大气参数的剧烈波动性误差,并与真实大气参数吻合较好,有效地提高了大气数据系统在大攻角飞行状态下的测量精度和可靠性。

Because the accuracy of Air Data System（ADS） declines remarkably when new generation of aviation aircraft is at high angle of attack,the correction algorithm based on the theory of Kalman filter is designed.Using air data and inertial navigation information,Kalman filter is constructed based on the aircraft mechanics equations.The air data is corrected by using the Kalman filter method.The simulation results show that the air data,which is corrected by the Kalman filter,could effectively eliminate the violent fluctuations of the measured air data at high angle of attack.And its tendency coincides with the true air data with a small error.The correction algorithm could improve the measurement accuracy and reliability of air data system when aircraft is at high angle of attack.