The ASRTU Microsatellite is a 12U CubeSat managed by the Harbin Institute of Technology and developed under the cooperation of the China-Russia University of Technology Alliance (ASRTU). This paper presents the design of an attitude control system for the ASRTU microsatellite mission. The control indicators of the ASRTU Microsatellite are first introduced and the main performance indicators of the attitude sensor and actuator are determined through index decomposition. Then, according to the configuration of the on-board sensor, a variety of positioning and control scheme designs are presented, and the switching logic between each control mode is described.The extended Kalman filter algorithm based on gyro and star sensors was used for satellite attitude determination, and the deviation quaternion and the deviation angular velocity feedback PD control method was used for attitude control. Simulation results indicate that the accuracy of attitude determination system when the star sensor is valid is better than 20". Moreover, the control accuracy and stability are better than 0.05° and 0.01 (°)/s, respectively.The results indicate that the proposed design meets the mission requirements of ASRTU CubeSat.