Abstract This paper presents a real-time implementation of a novel simplified intelligent (SI PI) control for a low-cost attitude determination and control system (ADCS) for CubeSat. As small satellite missions are increasing, the CubeSat requires precise ADCS with attitude drift adjustment. This attitude drift if not properly compensated, the attitude knowledge will be lost as the error will increase between the actual and estimated attitudes. The proposed ADCS comprises two steps; the attitude determination which estimates the current CubeSat’s attitude and a novel simplified intelligent proportional-integral (SI PI) control algorithm that accurately adjusts the attitude. The control algorithm has no controller gains parameters and is based on the multi degree-of-freedom concept. To correct the attitude drift, the proposed ADCS utilizes magnetometer, sun sensor, and a micro-electro-mechanical (MEMS) gyroscope sensor which offers a comparative attitude that is utilized to update the estimated attitude delivered to the Kalman filter to determine the CubeSat’s angular velocity and attitude. ADCS model validation and verification are performed via MATLAB R2019b and hardware implementation. Comparison with other ADCS techniques is presented. ADCS simulated model proves precision results with error no more than 0.1 degree.

中文翻译：

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CubeSat 姿态确定系统鲁棒简化智能比例积分控制的实时实现

摘要 本文介绍了一种用于 CubeSat 的低成本姿态确定和控制系统 (ADCS) 的新型简化智能 (SI PI) 控制的实时实现。随着小型卫星任务的增加，CubeSat 需要具有姿态漂移调整功能的精确 ADCS。这种姿态漂移如果没有得到适当的补偿，姿态知识就会丢失，因为实际姿态和估计姿态之间的误差会增加。提议的 ADCS 包括两个步骤；估计当前CubeSat姿态的姿态确定和精确调整姿态的新型简化智能比例积分（SI PI）控制算法。控制算法没有控制器增益参数，基于多自由度概念。为了纠正姿态漂移，拟议的 ADCS 使用磁力计、太阳传感器和微机电 (MEMS) 陀螺仪传感器，提供比较姿态，用于更新传递给卡尔曼滤波器的估计姿态，以确定 CubeSat 的角速度和姿态。ADCS 模型验证和验证通过 MATLAB R2019b 和硬件实现进行。介绍了与其他 ADCS 技术的比较。ADCS仿真模型证明了精度结果，误差不超过0.1度。ADCS 模型验证和验证通过 MATLAB R2019b 和硬件实现进行。介绍了与其他 ADCS 技术的比较。ADCS仿真模型证明了精度结果，误差不超过0.1度。ADCS 模型验证和验证通过 MATLAB R2019b 和硬件实现进行。介绍了与其他 ADCS 技术的比较。ADCS仿真模型证明了精度结果，误差不超过0.1度。