Stabilised LQR control and optimised spin rate control for nanosatellites

Ikechukwu Ofodile; Hendrik Ehrpais; Andris Slavinskis; Gholamreza Anbarjafari

doi:10.1109/RAST.2019.8767850

Stabilised LQR control and optimised spin rate control for nanosatellites

Ikechukwu Ofodile, Hendrik Ehrpais, Andris Slavinskis, Gholamreza Anbarjafari

University of Tartu

Research output: Chapter in Book/Report/Conference proceeding › Conference article in proceedings › Scientific › peer-review

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Abstract

This paper presents the design and study of cross product control, Linear-Quadratic Regulator (LQR)optimal control and high spin rate control algorithms for ESTCube-2/3 missions. The three-unit CubeSat is required to spin up in order to centrifugally deploy a 300-m long tether for a plasma brake deorbiting experiment. The algorithm is designed to spin up the satellite to one rotation per second which is achieved in 40 orbits. The LQR optimal controller is designed based on closed-loop step response with controllability and stability analysis to meet the pointing requirements of less than 0.1° for the Earth observation camera and the high-speed communication system. The LQR is based on linearised satellite dynamics with an actuator model. The preliminary simulation results show that the controllers fulfil the requirements set by payloads. While ESTCube-1 used only electromagnetic coils for high spin rate control, ESTCube-2 will make the use of electromagnetic coils, reaction wheels and cold gas thrusters to demonstrate technologies for a deep-space mission ESTCube-3. The attitude control algorithms will be demonstrated in low Earth orbit on ESTCube-2 as a stepping stone for ESTCube-3 which is planned to be launched to lunar orbit where magnetic control is not available.

Original language	English
Title of host publication	Proceedings of 9th International Conference on Recent Advances in Space Technologies, RAST 2019
Editors	S. Menekay, O. Cetin, O. Alparslan
Publisher	IEEE
Pages	715-722
Number of pages	8
ISBN (Electronic)	9781538694480
DOIs	https://doi.org/10.1109/RAST.2019.8767850
Publication status	Published - 1 Jun 2019
MoE publication type	A4 Conference publication
Event	International Conference on Recent Advances in Space Technologies - Istanbul, Türkiye Duration: 11 Jun 2019 → 14 Jun 2019 Conference number: 9

Conference

Conference	International Conference on Recent Advances in Space Technologies
Abbreviated title	RAST
Country/Territory	Türkiye
City	Istanbul
Period	11/06/2019 → 14/06/2019

Funding

The authors would like to thank everybody who has contributed to the development of ESTCube-2 and its attitude determination and control system. We would also like to thank all the partners involved in developing the ESTCube-2 nanosatellite. The research for this article was partly supported by the University of Tartu ASTRA project 2014-2020.4.01.16-0029 KOMEET “Benefits for Estonian Society from Space Research and Application”, financed by the EU European Regional Development Fund, Estonian Research Council Grants (PUT638), the Scientific and Technological Research Council of Turkey (TÜBITAK) (116E097), and the Estonian Centre of Excellence in IT (EXCITE) funded by the European Regional Development Fund. We thank three anonymous reviewers for a thorough and constructive feedback which helped to improve the paper.

Keywords

attitude control
control system analysis
ESTCube-2
feedback linearization
nonlinear systems
spin control

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10.1109/RAST.2019.8767850

ELEC_Slavinskis_Stabilised_LQR_Control_RASTAccepted author manuscript, 9.19 MB

Cite this

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title = "Stabilised LQR control and optimised spin rate control for nanosatellites",

abstract = "This paper presents the design and study of cross product control, Linear-Quadratic Regulator (LQR)optimal control and high spin rate control algorithms for ESTCube-2/3 missions. The three-unit CubeSat is required to spin up in order to centrifugally deploy a 300-m long tether for a plasma brake deorbiting experiment. The algorithm is designed to spin up the satellite to one rotation per second which is achieved in 40 orbits. The LQR optimal controller is designed based on closed-loop step response with controllability and stability analysis to meet the pointing requirements of less than 0.1° for the Earth observation camera and the high-speed communication system. The LQR is based on linearised satellite dynamics with an actuator model. The preliminary simulation results show that the controllers fulfil the requirements set by payloads. While ESTCube-1 used only electromagnetic coils for high spin rate control, ESTCube-2 will make the use of electromagnetic coils, reaction wheels and cold gas thrusters to demonstrate technologies for a deep-space mission ESTCube-3. The attitude control algorithms will be demonstrated in low Earth orbit on ESTCube-2 as a stepping stone for ESTCube-3 which is planned to be launched to lunar orbit where magnetic control is not available.",

keywords = "attitude control, control system analysis, ESTCube-2, feedback linearization, nonlinear systems, spin control",

author = "Ikechukwu Ofodile and Hendrik Ehrpais and Andris Slavinskis and Gholamreza Anbarjafari",

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Ofodile, I, Ehrpais, H, Slavinskis, A & Anbarjafari, G 2019, Stabilised LQR control and optimised spin rate control for nanosatellites. in S Menekay, O Cetin & O Alparslan (eds), Proceedings of 9th International Conference on Recent Advances in Space Technologies, RAST 2019., 8767850, IEEE, pp. 715-722, International Conference on Recent Advances in Space Technologies, Istanbul, Türkiye, 11/06/2019. https://doi.org/10.1109/RAST.2019.8767850

Stabilised LQR control and optimised spin rate control for nanosatellites. / Ofodile, Ikechukwu; Ehrpais, Hendrik; Slavinskis, Andris et al.
Proceedings of 9th International Conference on Recent Advances in Space Technologies, RAST 2019. ed. / S. Menekay; O. Cetin; O. Alparslan. IEEE, 2019. p. 715-722 8767850.

Research output: Chapter in Book/Report/Conference proceeding › Conference article in proceedings › Scientific › peer-review

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AB - This paper presents the design and study of cross product control, Linear-Quadratic Regulator (LQR)optimal control and high spin rate control algorithms for ESTCube-2/3 missions. The three-unit CubeSat is required to spin up in order to centrifugally deploy a 300-m long tether for a plasma brake deorbiting experiment. The algorithm is designed to spin up the satellite to one rotation per second which is achieved in 40 orbits. The LQR optimal controller is designed based on closed-loop step response with controllability and stability analysis to meet the pointing requirements of less than 0.1° for the Earth observation camera and the high-speed communication system. The LQR is based on linearised satellite dynamics with an actuator model. The preliminary simulation results show that the controllers fulfil the requirements set by payloads. While ESTCube-1 used only electromagnetic coils for high spin rate control, ESTCube-2 will make the use of electromagnetic coils, reaction wheels and cold gas thrusters to demonstrate technologies for a deep-space mission ESTCube-3. The attitude control algorithms will be demonstrated in low Earth orbit on ESTCube-2 as a stepping stone for ESTCube-3 which is planned to be launched to lunar orbit where magnetic control is not available.

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ER -

Stabilised LQR control and optimised spin rate control for nanosatellites

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