偏置动量轮控卫星姿态控制  

Attitude Control for Momentum Biased Satellites with Wheels

作　　者：吕建婷[1] 马广富[1] 宋斌[1] 

机构地区：[1]哈尔滨工业大学控制科学与工程系,黑龙江哈尔滨150001

出　　处：《控制工程》2007年第6期569-571,575,共4页Control Engineering of China

基　　金：教育部博士点基金资助项目(20050213010)

摘　　要：研究了轮控的三轴稳定的偏置动量卫星姿态控制问题。卫星的俯仰回路采用偏置动量轮,滚动/偏航轴上各安装一个反作用飞轮来完成姿态控制。小姿态角下俯仰回路可以单独设计,利用测量的俯仰角来实现其姿态控制;滚动/偏航回路利用滚动信息,采用基于偏航观测器的滑模控制器设计。磁力矩器提供的磁矩与地磁场作用产生的力矩实现了飞轮的动量卸载。对卫星姿态控制系统进行的仿真研究结果表明,所设计的控制方案在飞轮输出力矩工作范围内,可使卫星达到很高的姿态控制精度。The problems of the controller design for a three-axis stabilized momentum-biased satellite with wheels are studied. The pitch-loop control is achieved by a biased momentum wheel. The roll/yaw loop control is achieved through two reaction wheels equipped along the principal axes. The pitch control is attained by the measurement of the pitch angle. The roll/yaw loop design is composed of two parts of a sliding mode controller based on yaw observer and a wheel deeoupling function. Magnetic torque rods generate magnetic dipole moments whose interaction with the Earth＇s magnetic field could produce the magnetic torques necessary to remove the excess momentum of wheels. Numerical simulation result shows that the control scheme could achieve high pointing accuracy within the operating range of wheel torques.

关 键 词：姿态控制 偏置动量 偏航观测器 滑模控制 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]