一种非偏置动量单飞轮加磁控制算法  

Attitude Control Method with a Non-Biased Momentum Wheel and Magnetorquers

作　　者：王献忠 张肖 

机构地区：[1]上海航天控制技术研究所,上海200233 [2]上海市空间智能控制技术重点实验室,上海200233

出　　处：《空间控制技术与应用》2014年第6期48-52,共5页Aerospace Control and Application

基　　金：国家高技术研究发展计划(863)资助项目(2011AA7100009)

摘　　要：为了提高飞轮控制可靠性,针对仅一个飞轮的非偏置动量三轴稳定控制问题,提出了飞轮不同安装方式下基于单飞轮和磁力矩器的稳定控制算法.仿真试验结果表明单个飞轮在XZ平面斜装时控制精度在0.3°左右,适合在纳星、皮星等微小卫星上应用,飞轮正装时仍可粗精度对地定向,适合多个飞轮故障情况下应用.In order to improve the reliability of attitude control with reaction wheel, a control law is put forward, which is based on one reaction wheel and three magnetorquers in different fixing mode. The sim- ulation results show that the precision of attitude control is about 0.3 °, when the reaction wheel is in- stalled with a certain angle from X axis in XZ plane. The control method is applicable for micro-satelfite. When the wheel is installed along the roll or yaw axis, the satellite attitude can still be controlled. The control method can be used to a sick satellite.

关 键 词：姿态控制 非偏置动量 飞轮 磁力矩器 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]