The small astronomical satellite has demands on both pointing accuracy and attitude maneuverability , so this thesis modeled the attitude control subsystem based on reaction wheels . under the fine precision pointing mode , a pd control law and a variable structure ( vs ) control law were studied respectively , and the simulation validated that vs control is more effective under fine precision pointing mode . furthermore , the vs controller for rapid large - angle maneuver was also designed 2 ) svom卫星同时对指向精度和姿态机动性有着很高的要求，因此本文建立了基于反作用飞轮的svom卫星姿态控制系统模型，在高精度惯性定向三轴稳定模式下分别设计了pd控制律和变结构控制律，通过仿真验证了变结构控制对于svom卫星的有效性，并基于变结构控制研究了svom卫星快速大角度机动的方法。
