Attitude control of pico-satellite using flywheel based on fractional order sliding mode

Liwei Deng; Shenmin Song

doi:10.1109/MIC.2013.6758070

Attitude control of pico-satellite using flywheel based on fractional order sliding mode

Liwei Deng
, Shenmin Song

School of Astronautics

Harbin Institute of Technology

Research output: Contribution to conference › Paper › peer-review

6 Scopus citations

Abstract

A quaternion based attitude model of a spacecraft that describes the three-axis stabilized pico-satellite equipped with momentum wheel considering gravity gradient torque disturbance is proposed in this paper. A linearized state space model that includes only three angle velocities and three components of the quaternion is derived from Taylor expansion and Jacobian matrix. Based on the linearized model, a fractional order sliding mode controller is designed in the light of Lyapunov stability theorem. Numerical simulations are also provided to show the proposed results and to validate the effectiveness of the new robust fractional sliding mode controller.

Original language	English
Pages	756-761
Number of pages	6
DOIs	https://doi.org/10.1109/MIC.2013.6758070
State	Published - 2013
Event	2013 2nd International Conference on Measurement, Information and Control, ICMIC 2013 - Harbin, China Duration: 16 Aug 2013 → 18 Aug 2013

Conference

Conference	2013 2nd International Conference on Measurement, Information and Control, ICMIC 2013
Country/Territory	China
City	Harbin
Period	16/08/13 → 18/08/13

Keywords

Flywheel
Fractional calculus
Fractional order sliding
Spacecraft attitude

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10.1109/MIC.2013.6758070

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title = "Attitude control of pico-satellite using flywheel based on fractional order sliding mode",

abstract = "A quaternion based attitude model of a spacecraft that describes the three-axis stabilized pico-satellite equipped with momentum wheel considering gravity gradient torque disturbance is proposed in this paper. A linearized state space model that includes only three angle velocities and three components of the quaternion is derived from Taylor expansion and Jacobian matrix. Based on the linearized model, a fractional order sliding mode controller is designed in the light of Lyapunov stability theorem. Numerical simulations are also provided to show the proposed results and to validate the effectiveness of the new robust fractional sliding mode controller.",

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author = "Liwei Deng and Shenmin Song",

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doi = "10.1109/MIC.2013.6758070",

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AU - Deng, Liwei

AU - Song, Shenmin

PY - 2013

Y1 - 2013

N2 - A quaternion based attitude model of a spacecraft that describes the three-axis stabilized pico-satellite equipped with momentum wheel considering gravity gradient torque disturbance is proposed in this paper. A linearized state space model that includes only three angle velocities and three components of the quaternion is derived from Taylor expansion and Jacobian matrix. Based on the linearized model, a fractional order sliding mode controller is designed in the light of Lyapunov stability theorem. Numerical simulations are also provided to show the proposed results and to validate the effectiveness of the new robust fractional sliding mode controller.

AB - A quaternion based attitude model of a spacecraft that describes the three-axis stabilized pico-satellite equipped with momentum wheel considering gravity gradient torque disturbance is proposed in this paper. A linearized state space model that includes only three angle velocities and three components of the quaternion is derived from Taylor expansion and Jacobian matrix. Based on the linearized model, a fractional order sliding mode controller is designed in the light of Lyapunov stability theorem. Numerical simulations are also provided to show the proposed results and to validate the effectiveness of the new robust fractional sliding mode controller.

KW - Flywheel

KW - Fractional calculus

KW - Fractional order sliding

KW - Spacecraft attitude

UR - https://www.scopus.com/pages/publications/84897479822

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DO - 10.1109/MIC.2013.6758070

M3 - 论文

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T2 - 2013 2nd International Conference on Measurement, Information and Control, ICMIC 2013

Y2 - 16 August 2013 through 18 August 2013

ER -

Attitude control of pico-satellite using flywheel based on fractional order sliding mode

Abstract

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Keywords

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