阿斯图微卫星姿态控制系统设计

Design of attitude control system for ASRTU microsatellite

阿斯图微卫星是一颗由哈尔滨工业大学牵头研制,在中俄工科大学联盟(ASRTU)合作框架下研制的一颗12U立方星,本文针对阿斯图微卫星任务进行了姿态控制系统设计及仿真分析。首先介绍了阿斯图微卫星的控制指标,通过指标分解确定了姿态敏感器及执行机构的主要性能指标。接着,根据星上敏感器的配置情况,设计了多种定姿和控制方案,并对各控制模式间的切换逻辑进行了设计。卫星姿态确定采用了基于陀螺和星敏感器的扩展卡尔曼滤波算法,姿态控制采用了偏差四元数和偏差角速度反馈的PD控制方法。仿真结果表明星敏感器有效时,姿态确定精度优于20″,姿态指向精度优于0.05°,稳定度优于0.01(°)/s,能够满足阿斯图立方星的任务要求。

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.