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Tsinghua Science and Technology 2019, 24(6): 694-705 https://doi.org/10.26599/TST.2018.9010094
Open Access | Issue | Published: 05 December 2019

Adaptive Prescribed Performance Control for Flexible Spacecraft with Input Saturation and Actuator Misalignment

Show Author's Information Jiawei Tao,  Tao Zhang*( ),  Yongfang Nie
Department of Automation, Tsinghua University, Beijing 100084, China.
Department of Strategic Missile and Underwater Weapon, Naval Submarine Academy, Qingdao 266071, China.
Keywords:
flexible spacecraft, modal observer, vibration suppression, prescribed performance, input saturation, actuator misalignment
Cite this article:
Tao J, Zhang T, Nie Y. Adaptive Prescribed Performance Control for Flexible Spacecraft with Input Saturation and Actuator Misalignment. Tsinghua Science and Technology, 2019, 24(6): 694-705. https://doi.org/10.26599/TST.2018.9010094
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Abstract Full text About this article

In this paper, a flexible spacecraft attitude control scheme that guarantees vibration suppression and prescribed performance on transient-state behavior is proposed. Here, parametric uncertainty, external disturbance, unmeasured elastic vibration, actuator saturation, and even configuration misalignment are considered. To guarantee prescribed performance bounds on the transient- and steady-state control errors, a performance constrained control law is formulated with an error transformed function. An elastic modal observer is employed to estimate the unmeasured flexible modal variables, and a command filter is adopted to avoid the tedious analytical computations of time derivatives of virtual control inherent in the control design. Subsequently, a novel auxiliary system is developed to compensate the adverse effects of the actuator saturation constraints, and a compensation term is integrated into the control law to tackle the configuration misalignment. A comparative simulation study is carried out to illustrate the effectiveness and advantages of the proposed approach.


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Adaptive Prescribed Performance Control for Flexible Spacecraft with Input Saturation and Actuator Misalignment

Show Author's information Jiawei Tao, Tao Zhang*( ), Yongfang Nie
Department of Automation, Tsinghua University, Beijing 100084, China.
Department of Strategic Missile and Underwater Weapon, Naval Submarine Academy, Qingdao 266071, China.

Abstract

In this paper, a flexible spacecraft attitude control scheme that guarantees vibration suppression and prescribed performance on transient-state behavior is proposed. Here, parametric uncertainty, external disturbance, unmeasured elastic vibration, actuator saturation, and even configuration misalignment are considered. To guarantee prescribed performance bounds on the transient- and steady-state control errors, a performance constrained control law is formulated with an error transformed function. An elastic modal observer is employed to estimate the unmeasured flexible modal variables, and a command filter is adopted to avoid the tedious analytical computations of time derivatives of virtual control inherent in the control design. Subsequently, a novel auxiliary system is developed to compensate the adverse effects of the actuator saturation constraints, and a compensation term is integrated into the control law to tackle the configuration misalignment. A comparative simulation study is carried out to illustrate the effectiveness and advantages of the proposed approach.

Keywords: flexible spacecraft, modal observer, vibration suppression, prescribed performance, input saturation, actuator misalignment

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Publication history

Received: 11 February 2018
Revised: 18 April 2018
Accepted: 19 April 2018
Published: 05 December 2019
Issue date: December 2019

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© The author(s) 2019

Acknowledgements

This work was supported by the National Natural Science Foundation of China (Nos. 61703228 and 61673239).

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