低轨微小卫星姿态控制方案  

Attitude Control of Low-orbit Micro-satellite

作　　者：王鹏[1] 郑伟[1] 张洪波[1] 吴杰[1] 

机构地区：[1]国防科技大学航天与材料工程学院,湖南长沙410073

出　　处：《国防科技大学学报》2011年第3期18-22,共5页Journal of National University of Defense Technology

摘　　要：针对轨道高度低于500km微小卫星姿态控制问题,从充分利用环境力矩的角度出发,提出一种主动磁控+气动稳定力矩的姿态控制方案。该方案较好地解决了局部稳定控制律的全局稳定问题。仿真结果表明:特征距离dcc是影响该控制方案的主要因素。dcc值越大,对控制越有利,但随着dcc值的增大,卫星总体设计难度也会加大,因此实际中应选择合适的dcc值,既满足卫星姿态控制的要求,又保证卫星总体结构设计的难度不至于过大。A new scheme of attitude control with active magnetic torque and aerodynamic stabilization torque was proposed for low- orbit micro-satellite （orbit altitude lower than 500km）, in order to take full advantage of environmental torque. Simulation results show that the characteristic distance of satellite dce is the linchpin which influences the attitude control scheme. Suitable magnitude of dce should be chosen in order to meet the request of satellite attitude control system, All this shows that the satellite structure proposed in the cttrrem study has the potentiality of being used for experimental teaching and research.

关 键 词：微小卫星 姿态控制 主动磁控 气动稳定力矩 环境力矩 

分 类 号：V412.4[航空宇航科学与技术—航空宇航推进理论与工程]