【作者】 张凌云； 郭雷； 杨照华；

【Author】 Zhang Lingyun Guo Lei Yang Zhaohua (Novel Inertial Instrument and Navigation System Technology Key Laboratory of Fundamental Science for National Defense,School of Instrument Science and Opto-Electronic Engineering,Beijing University of Aeronautics and Astronautics,Beijing 100191,China)

【机构】 北京航空航天大学仪器科学与光电工程学院新型惯性仪表与导航系统技术国防重点学科实验室；

【摘要】 姿态控制系统(ACS)是卫星必不可少的组成部分,而磁力矩器就是其中一种重要,可靠的姿控执行器件。本文设计并实现了一种用于徽纳卫星上的空芯磁力矩器。根据通电线圈在磁场中有洛伦兹力产生的原理设计了线圈及线圈骨架。利用PWM原理制作出线圈驱动电路及电流检测电路,实现了磁力矩器电流的幅值可测、方向可控。利用MATLAB软件仿真了轨道中磁力矩器产生的力矩曲线。实验表明该磁力矩器功耗小、剩磁小,可以很好地满足微纳卫星的姿控要求。更多还原

【Abstract】 The Attitude Control System(ACS)is a very important part of satellite,and the Magnetic Torquer is one of the attitude controlling executive devices that is important and reliable,an air core magnetic torquer used in the micro/nano satellites is designed and implemented in the paper.According to the principle that there is lorentz force when electrified conductors are put into the magnetic field,the coil and the stent are designed.The coil driving and current measuring circuit is made by using the PWM principle,which realizes the controllable and measurable of amplitude and direction of current.The moment curve of the magnetic torquer in the orbit is simulated by MATLAB.Experiments show that the magnetic torquer is of low energy, small remanence and can meet the requirments of the satellite attitude control.更多还原