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research-article

Fault-tolerant Attitude Controller Design for Deep Space Probe via Adaptive Fast Terminal Sliding Mode Control

[+] Author and Article Information
Ruiyun Qi

College of Automation Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 211106, China
ruiyun.qi@nuaa.edu.cn

Weiwei Su

College of Automation Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 211106, China
sww0606@126.com

Yizhen Meng

College of Automation Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 211106, China
1722569382@qq.com

1Corresponding author.

ASME doi:10.1115/1.4042548 History: Received December 28, 2017; Revised January 09, 2019

Abstract

For deep space probe subject to uncertain time-varying inertia matrix, unknown external disturbances, actuator faults and misalignment, a fault-tolerant attitude controller is designed in this paper, which is based on adaptive control law and fast terminal sliding mode control theory. A new method to handle actuator uncertainties is developed, which redefines the effectiveness matrix and the misalignment matrix. Moreover, an explicit sufficient condition is presented in order to construct the fault-tolerant attitude controller. The proposed controller can stabilize the attitude control system within finite time with a fast convergence rate and high precision. Numerical simulations are made to demonstrate the superior performance of the proposed controller.

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