基于太阳矢量和MEMS的自旋弹姿态估计系统研究

徐光延; 廖培冲; 张红梅

doi:doi:10.3969/j.issn.1671-637x.2017.08.003

电光与控制, 2017, 24 (8): 9, 网络出版: 2017-09-21

基于太阳矢量和MEMS的自旋弹姿态估计系统研究

On Attitude Estimation System of Spinning Missile Based on Solar Vector and MEMS

论文大纲

徐光延廖培冲张红梅

作者单位

沈阳航空航天大学, 沈阳 110136

自旋弹姿态估计卡尔曼滤波太阳矢量四元数 spinning missile attitude estimation Kalman filter solar vector quaternion

摘要

针对自旋弹提出了一种新的姿态估计方法。首先, 根据自旋弹的性质设计了一种特殊的太阳矢量测量装置,用来测量太阳矢量并替代常用的MEMS中的加速度计和地磁计来修正陀螺仪偏差。该太阳矢量测量装置包括透明外壳、光电池阵列、实时时钟和处理器, 太阳透过透明外壳照射光电池阵列, 该阵列将太阳能转换成电动势信号,并结合实时时钟、通过处理器处理得到该时刻的太阳矢量。然后, 通过四元数微分方程建立卡尔曼滤波状态方程和观测方程对自旋弹进行姿态估计。最后, 仿真结果表明该方法能够得到较高精度的自旋弹姿态角。

Abstract

A new method for estimating the attitude of spinning missile was proposed.Firstly, according to the nature of spinning missile, a special sun sensor is designed to measure the solar vector instead of the commonly used accelerometer and magnetometer in MEMS sensor to correct the gyro bias.The solar vector measuring device comprises a transparent shell, photocell array, real-time clock and controller.When the sun light illuminates the photocell array through the transparent shell, the photocell array can convert the solar energy into the electric potential signal.According to the size of the solar energy and the angle of the photocell, combined with the accurate time provided by the real-time clock, the solar vector of this moment is obtained through main controller processing.Then, the Kalman filer state equation and observation equation established by using the quaternion differential equation is adopted to estimate the spinning missile attitude.The simulation results show that this method can obtain the higher accuracy attitude angle of spinning missile.

参考文献

[1] 李兴城, 牛宏宇.基于磁阻传感器的旋转弹姿态测量算法研究［J］.计算机仿真学报, 2012, 29(5):51-54.

[2] 张民权, 刘东方, 王冬梅, 等.弹道修正弹发展综述［J］.兵工学报, 2010, 31(s2):127-130.

[3] WANG M, YANG Y C, HATCH R R, et al.Adaptive filter for a miniature MEMS based attitude and heading refe-rence system［C］//Position Location and Navigation Symposium, 2004:193-200.

[4] 李冠中,王雷.基于磁阻传感器的旋转弹飞行姿态测量方法［J］.弹箭与制导学报, 2009, 29(2):71-73, 86.

[5] CASTELLANOS J F G, LESECQ S, MARCHAND N, et al.A low cost air data attitude heading reference system for the tourism airplane applications［C］//Sensor, IEEE,2005.doi:10.1109/ICSENS.2005.1597968.

[6] ZHANG R H, JIA H G, CHEN T, et al.Attitude solution enginccring for strapdown inertial navigation system based on quaternion algorithm［J］.Optics Precision Engineering, 2008, 16(10):1963-1970.

[7] ANGRISANO A.GNSS/INS Integration methods［D］.Calgary:University of Calgary, 2010.

[8] GUERRERO-CASTELIANOS J F, MADRIGAL-SASTRE H, DURAND S, et al.Design and implementation of an attitude and heading reference system［C］//The 8th International Conference on Electrical Engineering, Computing Science and Automatic Control, Program and Abstract Book, 2011:1-5.

[9] 吴杰,闫建国.基于修正的卡尔曼滤波的姿态估计算法研究［J］.计算机仿真, 2012, 29(2):54-57.

[10] 薛亮, 姜澄宇, 常洪龙, 等.基于状态约束的MIMU/磁强计组合姿态估计滤波算法［J］.中国惯性技术学报, 2009, 17(3): 338-343.

[11] DENTI E, GALATOLO R, SCHETTINI F.An AHRS based on a Kalman filter for the integration of intertial, magnet-ometric an GPS data［C］//The 27th Internation Congress of the Aeronautical Sciences, 2010:1-9.

[12] 朱建新, 张秋阳, 王石林.模糊Kalman滤波在无人机姿态测量中的应用研究［J］.广西大学学报: 自然科学版, 2011, 36(2): 228-230.

徐光延, 廖培冲, 张红梅. 基于太阳矢量和MEMS的自旋弹姿态估计系统研究[J]. 电光与控制, 2017, 24(8): 9. XU Guang-yan, LIAO Pei-chong, ZHANG Hong-mei. On Attitude Estimation System of Spinning Missile Based on Solar Vector and MEMS[J]. Electronics Optics & Control, 2017, 24(8): 9.

基于太阳矢量和MEMS的自旋弹姿态估计系统研究

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