基于UKF的四元数载体姿态确定  

Attitude Measurement Using Quaternion Based on UKF

作　　者：刘海颖[1] 王惠南[1] 刘新文[1] 

机构地区：[1]南京航空航天大学自动化学院,南京210016

出　　处：《南京航空航天大学学报》2006年第1期37-42,共6页Journal of Nanjing University of Aeronautics & Astronautics

基　　金：教育部博士点基金(20030287005)资助项目

摘　　要：对于低精度高噪声的传感器组成的低成本姿态测量系统,本文引入U nscen ted K a lm an filtering(UKF)用于姿态确定,设计了有陀螺测量和四元数差分法的无陀螺测量两种UKF滤波器;应用四元数避免了欧拉角法的奇异问题;用高斯-牛顿误差最小法将六维参考向量转化为四元数,作为观测量的一部分,使九维非线性观测方程转化为七维线性方程进行滤波,减少了计算量;应用仿真数据进行算法验证,成功得到姿态估计;对两种算法在低速和高速状态下进行验证,仿真结果表明了该方法的有效性。For a low-cost attitude measurement system made up of less accurate and high noise sensors, the unscented Kalman filtering （UKF） is used for the determination of the attitude. Two UKF algorithms are designed. One of which incorporates rate measurement and the other relays on differencing quaternion. The quaternion is used to avoid the singularity problem of Eular angles. Gauss-Newton error minimization is used to reduce six-dimensional reference vector to the quaternion as a part of observations for UKF. Nine-dimensional nonlinear observation equation is turned into seven-dimensional linear to reduce the computational requirement. Simulation data are used to test algorithms and obtain attitude estimates. Two algorithms are also tested in low and high rate attitude motion. Simulation examples illustrate the effectiveness of the approach.

关 键 词：姿态测量 UKF 四元数 高斯-牛顿误差最小法 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]