大攻角下基于信息融合的攻角/侧滑角估计方法  

Estimation Method for Angle-of-Attack and Sideslip Angle Based on Information Fusion at High Angle of Attack

作　　者：马航帅[1] 雷廷万[1,2] 李荣冰[1] 刘建业[1] 

机构地区：[1]南京航空航天大学自动化学院导航研究中心,南京210016 [2]成都飞机设计研究所,成都610041

出　　处：《电光与控制》2012年第8期1-5,共5页Electronics Optics & Control

基　　金：国家自然科学基金(91016019;60804058);航空科研基金(200903611182)

摘　　要：攻角和侧滑角是飞控系统和导航系统的重要参数。针对高性能飞行器在大攻角飞行时攻角和侧滑角不能精确测量问题,引入飞行动力学模型,选取姿态、姿态角速率、气流角和速度等飞行参数作为状态向量,以惯性导航系统提供的姿态、姿态角速率、加速度组成观测向量,构建扩展卡尔曼滤波器,融飞行动力学模型求解和状态估计的过程为一体,实现攻角和侧滑角实时精确估计。利用X-Plane系统的飞行仿真数据对攻角/侧滑角估计方法的可行性和有效性进行了验证。仿真结果表明,该方法不仅具有较高的精度、良好的稳定性和鲁棒性,而且可提高大气数据系统的测量范围和可靠性,能够有效地适用于大攻角飞行环境下攻角和侧滑角的测量。The angle of attack and sideslip angle are important parameters of flight control system and navigation system. Considering that the angle of attack and the sideslip angle cannot be measured accurately when high-performance aircraft was at high angle of attack, a flight dynamics model was introduced in this paper. An Extended Kalman Filter （EKF） was constructed by taking the attitude, attitude angular rate, flow angle and velocity as state vectors, the attitude, attitude angular rate and acceleration provided by inertial navigation system（INS） as the observation vector. The filter combined the solving of flight dynamics model with the process of state estimation, and could obtain the accurate estimates of angle of attack and sideslip angle in real-time. Flight simulation data based on X-Plane was used to validate the feasibility and effectiveness of the estimation method. The simulation results show that the proposed method can not only has better accuracy, stability and robustness, but also improve the measurement range and reliability of air data system, which can measured angle of attack and sideslip angle at high angle of attack efficiently.

关 键 词：惯性导航系统 大气数据系统 飞行动力学 飞行控制 大攻角 

分 类 号：V249.32[航空宇航科学与技术—飞行器设计]