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Technical Brief

Gain-Scheduling Attitude Control for Complex Spacecraft Based on HOSVD

[+] Author and Article Information
Bingyao Lei

School of Astronautics,
Beihang University,
Beijing 100191, China
e-mail: by_lei@buaa.edu.cn

Peng Shi

School of Astronautics,
Beihang University,
Beijing 100191, China
e-mail: shipeng@buaa.edu.cn

Changxuan Wen

Key Laboratory of Space Utilization,
Technology and Engineering Center for Space Utilization,
Chinese Academy of Sciences,
Beijing 100094, China
e-mail: wenchangxuan@gmail.com

Yushan Zhao

School of Astronautics,
Beihang University,
Beijing 100191, China
e-mail: yszhao@buaa.edu.cn

1Corresponding author.

Contributed by the Dynamic Systems Division of ASME for publication in the JOURNAL OF DYNAMIC SYSTEMS, MEASUREMENT,AND CONTROL. Manuscript received January 11, 2018; final manuscript received October 11, 2018; published online November 22, 2018. Assoc. Editor: Yang Shi.

J. Dyn. Sys., Meas., Control 141(3), 034503 (Nov 22, 2018) (7 pages) Paper No: DS-18-1018; doi: 10.1115/1.4041752 History: Received January 11, 2018; Revised October 11, 2018

In this paper, a robust gain-scheduling attitude control scheme for spacecrafts with large rotational appendages is proposed. First, by introducing the higher-order singular value decomposition (HOSVD) method, a polytopic linear parameter varying (LPV) model with a family of weighting coefficients is developed based on the kinetics of a flexible spacecraft. This model eliminates the need of verifying all the gridding points, which is required in conventional controller synthesis process, and reduces the calculation complexity. Second, a generalized plant is derived to guarantee both the system robust stability and the tracking performances. Based on the LPV control theory, a less conservative controller synthesis condition for the polytopic LPV system is deduced. With an online tuning unit, the convex combination of every vertex controller is obtained. For control implementation, the present scheduling parameter is taken as an input for the tuning unit. Numerical results demonstrate the effectiveness and efficiency of the proposed control scheme.

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Figures

Grahic Jump Location
Fig. 1

The generalized plant with online tuning unit

Grahic Jump Location
Fig. 2

The modified generalized plant with online tuning unit

Grahic Jump Location
Fig. 3

Weighting function value changing with varying parameters

Grahic Jump Location
Fig. 4

Roll, pitch, and yaw angles when tracking reference signal

Grahic Jump Location
Fig. 5

Roll, pitch, and yaw angles when disturbed by square wave torques

Grahic Jump Location
Fig. 6

Roll, pitch, and yaw control inputs for signal tracking

Grahic Jump Location
Fig. 7

Roll, pitch, and yaw control inputs when disturbed by square wave torques

Grahic Jump Location
Fig. 8

Roll, pitch, and yaw angular rates in proposed methods when tracking reference signal

Grahic Jump Location
Fig. 9

Roll, pitch, and yaw angular rates in proposed methods when disturbed by square wave torques

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