基于GNSS的飞行器姿态确定算法研究  

Aircraft Attitude Determination Method Based on GNSS

作　　者：刘帅[1] 赵国荣[2] 王元鑫[1] 曹唯一 LIU Shuai;WANG Yuanxin;ZHAO Guorong;CAO Weiyi(Graduate Students..Brigade,Naval Aeronautical and Astronautical University,Yantai 264001;Department of Control Engineering,Naval Aeronautical and Astronautical University,Yantai 264001;Students..Brigade one,Naval Aeronautical and Astronautical University,Yantai 264001)

机构地区：[1]海军航空工程学院研究生管理大队,烟台264001 [2]海军航空工程学院控制工程系,烟台264001 [3]海军航空工程学院学员一旅,烟台264001

出　　处：《计算机与数字工程》2017年第6期1077-1080,共4页Computer & Digital Engineering

摘　　要：论文对基于GNSS的飞行器姿态测量进行研究。考虑姿态测量系统基线长度固定的特点,建立了单基线测量的载波相位差分姿态方程。在解算姿态方程时,为克服可能出现的载波相位观测值异常情况,提出了基于抗差卡尔曼滤波的飞行器姿态解算算法。仿真结果表明,该算法具有比最小二乘法更高的姿态解算精度和稳定性。This paper mainly studies on the attitude determination of aircraft based on GNSS.Considering the fact that thebaseline of attitude determination system is fixed,the carrier phase single difference equation is build to compute the attitude.Amethod based on the robust kalman filtering is presented to solve the problem of gross error in measurement data.The simulation re?sult shows that the precision and reliability of the presented method is better than the least squares method.

关 键 词：姿态测量 载波相位单差方程 抗差卡尔曼滤波 

分 类 号：TP301[自动化与计算机技术—计算机系统结构]