Flexible satellite control via fixed-time prescribed performance control and fully adaptive component synthesis vibratio
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ORIGINAL PAPER
Flexible satellite control via fixed-time prescribed performance control and fully adaptive component synthesis vibration suppression Liang Zhang
. Shijie Xu . Xiaozhe Ju . Naigang Cui
Received: 2 January 2020 / Accepted: 24 April 2020 Ó Springer Nature B.V. 2020
Abstract In this work, the problems of active vibration suppression and high accuracy attitude control for a flexible satellite with piezoelectric actuators are studied. Firstly, the attitude error dynamic equation is developed. By utilizing a novel hyperbolic cosecant function and the error transformation equation, the attitude errors can be transferred into new prescribed performance state variables. In order to further ensure better convergence of the new variables, a fixed-time sliding mode control is proposed. Subsequently, a novel fully adaptive component synthesis vibration suppression method is presented to realize vibration suppression during the attitude maneuver by utilizing piezoelectric actuators. Stability analysis of the proposed prescribed performance control is given. Finally, abundant numerical simulation results demonstrate the excellent performances of the proposed control scheme.
L. Zhang (&) Sun Yat-sen University, Guangzhou 510275, China e-mail: [email protected] S. Xu Beijing Institute of Space Long March Vehicle, Beijing 100076, China X. Ju N. Cui School of Astronautics, Harbin Institute of Technology, Harbin 150001, China
Keywords Flexible satellite Prescribed performance control Fixed-time sliding mode control Component synthesis vibration suppression
1 Introduction In recent years, China has developed multiple spacecrafts in the field of space application such as space station, new weather satellites, ocean observation satellites, Beidou navigation satellites, Lunar spacecrafts and deep space spacecrafts. Most of these spacecrafts adopt large solar panels to provide adequate power supply for the equipment on the spacecraft. The installation of flexible appendages such as solar panels or large antennas outside the spacecraft body is increasingly common. However, it brings significant vibration problem under the condition of disturbances and attitude control actuators, thus exerts more and more obvious influence on the attitude of the spacecraft itself. Due to the high cost of spacecraft manufacturing and the high complex characteristics of space launch missions, the performance requirements of spacecraft are more stringent. Traditional classical control methods cannot satisfy the requirements of high precision attitude control and good vibration suppression performance of flexible appendages. In order to improve the attitude control accuracy of spacecraft, the modern control methods
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such as robust control [1], active disturbance rejection control [2], sliding mode control [3] and adaptive control [4] have been widely concerned and applied by scholars. Nevertheless, the vibration suppression of flexible appendages is still a diff
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