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基于磁控及角速率估计的微卫星姿态稳定研究

发表时间:2008-01-31  浏览量:1875  下载量:560
全部作者: 刘海颖,王惠南,陈志明,吴海亮
作者单位: 南京航空航天大学高新技术研究院,南京航空航天大学自动化究院
摘 要: 本文提出了一种采用偏置动量轮和磁力矩器进行微卫星三轴姿态稳定控制的方法,同时基于星敏感器,给出了一种无陀螺测量的角速率估计技术。推导了在引力梯度及其它干扰下偏置动量轮卫星运动方程,根据磁场随轨道周期变化将时变系统转化为时不变系统,应用常系数LQR法设计最优反馈控制律。仿真结果表明,直接采用磁力矩器进行控制要比动量轮控制效果好,应用本文的控制方法,可以采用常速动量轮,从而避免动量阻尼以及饱和卸载。姿态确定系统,应用轨道模型提供参考欧拉角,在一个卡尔曼滤波器里针对俯仰通道以及滚动-偏航通道采用两个线性模型,应用最优控制律提供反馈控制,该新方法能简捷有效得估计姿态信息。
关 键 词: 导航、制导与控制;微卫星;三轴稳定;姿态控制;磁力矩器;角速率估计
Title: Three-axis attitude control of micro-satellite based on magnetic torque and angular rate estimation
Author: LIU Haiying, WANG Huinan, CHEN Zhiming, WU Hailiang
Organization: Academy of Frontier Science, Nanjing University of Aeronautics and Astronautics;College of Automatic Control, Nanjing University of Aeronautics and Astronautics
Abstract: A method of utilizing a single pitch momentum wheel and three magnetic torque rods to do three-axis satellites attitude control is developed. An attitude and attitude rate estimation technique based on star sensor to provide all the required angular rates without dynamic gyro is presented. Nonlinear equations of motion are developed and then linearized in a time varying form. The equations are reduced to linear time invariant using the periodic nature of the equations in an orbit. Magnetic control laws are developed using constant coefficient linear quadratic regulator. For the attitude determination, orbital model is used to generate reference Euler angle, and two more linear system models are used within a Linear Kalman Filter-one for the roll and yaw of the satellite and a second for the pitch. Optimal Control Law is used to provide negative feedback control. The new algorithms can provide a simple yet effective means of determining and controlling satellite attitude
Key words: Navigation Guidance and Control;micro-satellite; three-axis; attitude control; magnetic torque; angular rate estimation
发表期数: 2008年5月第2期
引用格式: 刘海颖,王惠南,陈志明,等. 基于磁控及角速率估计的微卫星姿态稳定研究[J]. 中国科技论文在线精品论文,2008,1(2):146-152.
 
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