Hostname: page-component-78c5997874-t5tsf Total loading time: 0 Render date: 2024-11-13T04:26:17.478Z Has data issue: false hasContentIssue false
  • English
  • Français

Simulink-based simulation platform design and faults impact analysis of attitude control systems

Published online by Cambridge University Press:  04 October 2021

H. Song Open the ORCID record for H. Song [Opens in a new window] ,
S.L. Hu  and
W.Z. Chen
H. Song
Affiliation:
School of Automation and Information Engineering, Xi’an University of Technology, Xi’an, 710048, China
S.L. Hu*
Affiliation:
School of Automation, Guangdong University of Petrochemical Technology, Maoming, 528000, China School of Artificial Intelligence, Henan University, Kaifeng, 475001, China
W.Z. Chen
Affiliation:
School of Automation and Information Engineering, Xi’an University of Technology, Xi’an, 710048, China
*
*Corresponding: hfkth@126.com
Get access Rights & Permissions [Opens in a new window]

Abstract

The satellite attitude control system (SACS) is a complicated system. In order to reflect the relationship among different components in SACS and analyse the impact of component faults on system performance, a complete simulation platform of the SACS based on Simulink is built in this paper. With the embedding of the specific reaction flywheel, gyroscope and earth sensor model, and the design of the controller based on the quaternion feedback, the simulation platform can not only simulate the real SACS at the component level, but it can also realise the injection of component faults for analysing the system performance. Simulations are conducted to verify the performance of the simulation platform. Simulation results show that this simulation platform has the ability to accurately reflect the control performance of the SACS, and the output accuracy of the component model is high. The research results reveal that this simulation platform can provide model support for verifying the algorithm of fault diagnosis, prediction and tolerant control of the SACS. This simulation platform is easy to use and can be expanded and improved.

Keywords

attitude control systemsreaction flywheelsattitude sensorssystem simulation
Type
Research Article
Information
The Aeronautical Journal , Volume 126 , Issue 1297 , March 2022 , pp. 475 - 499
Check for updates
Copyright
© The Author(s), 2021. Published by Cambridge University Press on behalf of Royal Aeronautical Society

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

Han, Y., James, D.B. and Cui, N.G. Adaptive Fault-Tolerant Control of Spacecraft Attitude Dynamics with Actuator Failures, J. Guid. Control. Dyn., 2015, 38, (10), pp 2033–2042. https://doi.org/10.2514/1.G000921 CrossRefGoogle Scholar
Cui, R.J. Design and Research of the Integrated Simulation Platform for Satellites Attitude Control System, Zhejiang University, Thesis, 2017 .Google Scholar
Yu, Y.T. and Liang, J.H. Attitude Determination and Control of Small Satellites Based on Simulink, Comput. Simul., 2006, (11), pp 71–74. doi: CNKI:SUN:JSJZ.0.2006-11-018 Google Scholar
Bai, X.L. and Bei, C. Rapid Design of Small Satellite Attitude Control System Based on Simulink, the 5th Chinese and Overseas Aerospace Science and Technology Seminar, 2009. http://www.doc88.com/p-3458094045058.html Google Scholar
Peng, R. and Bai, J.X. Research on Universal Hardware-in-Loop Simulation Test System of Satellite AOCS, Digit. Technol. Appl., 2011, (09), pp 58–59+61. doi: 10.19695/j.cnki.cn12-1369.2011.09.040 Google Scholar
Tortora, P., Giulietti, F., Corbelli, A., et al. ALMASat attitude control hardware-in-the-loop simulation, AIAA 57th International Astronautical Congress, 2006, 7, pp 4787–4795. https://doi.org/10.2514/6.IAC-06-C1.P.2.03 Google Scholar
Qiao, L., Zhang, M., Osborne, B., et al. Attitude Determination and Control System (ADCS) of UNSW QB50 project “UNSW EC0”, Proceedings of the 13 th Australian Space Science Conference, Sydney, Australia, 2013. Google Scholar.Google Scholar
He, S.J., Yang, L. and Chen, X.Q. Design of a Satellite Orbit Prediction Visualization Platform Based on LabVIEW and STK, Sci. Technol. Eng., 2011, 11, (23), pp 5702–5706+5717. doi: CNKI: SUN: KXJ S.0.2011-23-053 Google Scholar
Haddox, P.G. The development of a hardware-in-the-loop attitude determination and control simulator for IlliniSat-2, 52 nd Aerospace Sciences Meeting, 2014, 0007. Google Scholar.CrossRefGoogle Scholar
Ure, N.K., Kaya, Y.B., Inalhan, G. The Development of a Software and Hardware-in-the-Loop Test System for ITU-PSAT II nano satellite ADCS, 2011 Aerospace Conference, 2011, pp 1–15. Google Scholar.Google Scholar
Liang, X.J. Simulation of 3-Axis Stable Satellite Attitude Control System Based on Modularization, Comput. Simul., 2012, 29, (09), pp 91–95. doi: CNKI:SUN:JSJZ.0.2012-09-023 Google Scholar
Tu, S.C. Satellite Attitude Dynamics and Control, Beijing: China Astronautic Publishing House, 2009. https://xueshu.baidu.com/usercenter/paper/show?paperid=78be72110e9159dfe35b34a6f4487da6 Google Scholar
Chen, F.F., Zhang, G.F. and Chen, Y.F. Non-linear modelling and simulation technique for momentum wheel of small satellites, J. Astronaut., 2003, (06), pp 651–655. doi: CNKI:SUN:YHXB.0.2003-06-022 Google Scholar
Jiang, R., Wei, J.L. and Cen, Z.H. Simulation Modelling of Satellite Attitude Control System Based on Quaternion Feedback, J. Syst. Simul., 2009, 21, (19), pp 6260–6265. doi: CNKI:SUN:XTFZ.0.2009-19-070 Google Scholar
Bauer, R.J., Hong, T. and Hughes, P.C. Augmented system identification of reaction wheel friction. Canad. Aeronau. Spac. J., 2001, 47, (2), pp 51–56. Google Scholar.Google Scholar
Zhang, R.W. Satellite Orbit Attitude Dynamics and Control, Beihang University Press, 1998, Beijing. Google Scholar.Google Scholar
Bian, Z.Q., Cheng, W.Q. and Xue, X.B. Satellite Attitude Determination Algorithm Based on Gyro and Star-sensor, Spacecr. Eng., 2011, 20, (02), pp 29–34. doi: CNKI:SUN:HTGC.0.2011-02-007 Google Scholar
Zhu, Q.H. and Li, Y.B. Extended Kalman Filter for Attitude Determination Using Gyros and Quaternion, Aerosp. Shanghai, 2005, (04), pp 1–5+59. doi: 10.19328/j.cnki.1006-1630.2005.04.001 Google Scholar
Yang, B., Yu, X.Y. and Miao, J. A Method of Starlight Navigation Using the Infrared Horizon Sensor, J. Astronaut., 2016, 37, (09), pp 1089–1097. doi: 10.3873/j.issn.1000-1328.2016.09.008 Google Scholar
Wang, H.J., Xing, F. and You, Z. Numerical analysis and experiment study of navigation algorithm withtriple-FOV infrared earth sensor, Chin. J. Sci. Instrum., 2016, 37, (06), pp 1201–1209. doi: 10.19650/j.cnki.cjsi.2016.06.001 Google Scholar
Han, Y. Spacecraft Attitude Fault-Tolerant Control Methods with Actuator Fault, Harbin Institute of Technology, Thesis, 2016. https://kns.cnki.net/KCMS/detail/detail.aspx?dbname=CDFDLAST2017&filename=1016739814.nh Google Scholar
Schwabacher, M. Machine learning for rocket propulsion health monitoring, SAE Trans., 2005, pp 1192–1197. https://www.jstor.org/stable/44682813 Google Scholar