A Hardware Implementation of Flexible Attitude Determination and Control System for Two-Axis-Stabilized CubeSat

被引:6
作者
Gaber, Khaled [1 ]
El Mashade, Mohamed B. [1 ]
Aziz, Ghada A. Abdel [2 ]
机构
[1] Al Azhar Univ, Dept Elect Engn, Cairo, Egypt
[2] Elect Res Inst, Power Elect & Energy Convers Dept, Cairo, Egypt
关键词
CubeSat; MEMS; Attitude determination; Gyroscope; SI PI controller; SENSOR;
D O I
10.1007/s42835-020-00352-6
中图分类号
TM [电工技术]; TN [电子技术、通信技术];
学科分类号
0808 ; 0809 ;
摘要
This paper presents a hardware implementation of flexible and low-cost attitude determination and control system (ADCS) for two-axis-stabilized CubeSat. As small satellite missions are increasing, the CubeSat requires precise ADCS with attitude drift adjustment. This attitude drift if not properly compensated, will cause a slow attitude information loss as the error in attitude rises between the actual and estimated signals. The proposed ADCS comprises two steps; the attitude determination which estimates the current CubeSat's attitude and a novel simplified intelligent proportional-integral control algorithm that accurately adjusts the attitude. The control algorithm is based on the multi degree-of-freedom controller concept and has no controller gains parameters. The proposed ADCS employs sun sensor, magnetometer, and a micro-electro-mechanical gyroscope sensor to correct the attitude drift by offering a comparative attitude that is utilized for updating the estimated attitude delivered to the Kalman filter for determining the CubeSat's attitude and angular velocity. The ADCS model verification and validation are accomplished via Matlab/Simulink and hardware implementation. A comparison with other ADCS techniques is presented. The ADCS simulated model demonstrates precision results with error of less than 0.1 degrees.
引用
收藏
页码:869 / 882
页数:14
相关论文
共 25 条
[1]  
[Anonymous], 2010, THESIS
[2]  
Arash AM, 2017, CUBESAT DESIGN SPECI
[3]   GNSS attitude determination method through vectorisation approach [J].
Chang, Guobin ;
Xu, Tianhe ;
Wang, Qianxin ;
Li, Shengquan ;
Deng, Kailiang .
IET RADAR SONAR AND NAVIGATION, 2017, 11 (10) :1477-1482
[4]  
Dillow C, 2015, HERES WHY SMALL SATE
[5]   Signal Conditioning for the Kalman Filter: Application to Satellite Attitude Estimation with Magnetometer and Sun Sensors [J].
Esteban, Segundo ;
Giron-Sierra, Jose M. ;
Polo, Oscar R. ;
Angulo, Manuel .
SENSORS, 2016, 16 (11)
[6]   ATTITUDE DETERMINATION BY KALMAN FILTERING [J].
FARRELL, JL .
AUTOMATICA, 1970, 6 (03) :419-+
[7]  
Fritz M, 2019, 2019 IEEE AER C MAR, P1
[8]  
Gaber K, 2017, 2017 INTL CONF ON ADVANCED CONTROL CIRCUITS SYSTEMS (ACCS) SYSTEMS & 2017 INTL CONF ON NEW PARADIGMS IN ELECTRONICS & INFORMATION TECHNOLOGY (PEIT), P158, DOI 10.1109/ACCS-PEIT.2017.8303036
[9]   Modeling the Stochastic Drift of a MEMS-Based Gyroscope in Gyro/Odometer/GPS Integrated Navigation [J].
Georgy, Jacques ;
Noureldin, Aboelmagd ;
Korenberg, Michael J. ;
Bayoumi, Mohamed M. .
IEEE TRANSACTIONS ON INTELLIGENT TRANSPORTATION SYSTEMS, 2010, 11 (04) :856-872
[10]   Robust Concurrent Attitude-Position Control of a Swarm of Underactuated Nanosatellites [J].
Haghighi, Reza ;
Pang, Chee Khiang .
IEEE TRANSACTIONS ON CONTROL SYSTEMS TECHNOLOGY, 2018, 26 (01) :77-88