基于无迹卡尔曼滤波的迎角/侧滑角估计方法  

Estimation Method for Angle-of-Attack and Angle-of-Sideslip Based on Unscented Kalman Filter

作　　者：李鹏辉[1] 刘小雄[1] 徐恒[1] 王娟[1] 

机构地区：[1]西北工业大学自动化学院,陕西西安710072

出　　处：《测控技术》2014年第3期140-143,147,共5页Measurement & Control Technology

摘　　要：迎角和侧滑角是飞控系统的重要参数。针对迎角和侧滑角不能够精确测量(尤其在大机动情况下)的问题,研究了一种综合惯导系统数据和飞机的非线性动力学方程,利用无迹卡尔曼滤波来估计飞机的迎角和侧滑角的方法,实现了依靠算法代替传感器获得飞行参数,克服了对硬件(迎角、侧滑角传感器)的依赖性。该方法对系统数学模型的准确性有着较高的要求。仿真验证表明,该方法结构简单。且具有估计精度高、实时性好、抗干扰能力强的特点。The angle-of-attack（AOA） and angle-of-sideslip（AOS） are important parameters for flight control system. Considering that AOA and AOS cannot be measured accurately especially in the case of large maneu ver, a method depending on data from inertial navigation system（INS） and nonlinear dynamic equation of air craft is introduced, in which an unscented Kalman filter（UKF） is used to estimate AOA and AOS. Therefore, the flight parameters are gotten by algorithm instead of sensors, and the dependence on hardware （sensor of AOA and sensor of AOS） is overcome. However, this method has a high dependence on the accuracy of system model. Simulation results show that the method has good real-time, high estimation accuracy, and good robust ness against disturbance.

关 键 词：迎角 侧滑角 无迹卡尔曼滤波 飞行动力学 惯性导航系统 

分 类 号：V249.1[航空宇航科学与技术—飞行器设计]