Fixed-Time Attitude Tracking Control for Rigid Spacecraft With Actuator Misalignments and Faults

Fixed-Time Attitude Tracking Control for Rigid Spacecraft With Actuator Misalignments and Faults

This paper investigates an attitude tracking maneuver problem for a rigid spacecraft with external disturbances, uncertain inertia parameters, actuator misalignments, and faults. First, all the uncertainty terms are split from the desired commanded control torque, and then, the nonsingular terminal...

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Bibliographic Details
Main Authors: Jiwei Gao, Sen Zhang, Zhumu Fu
Format: Article
Language:English
Published: IEEE 2019-01-01
Series:IEEE Access
Subjects:
Fixed-time convergence
fault-tolerant
adaptive law
NTSM
attitude tracking
Online Access:https://ieeexplore.ieee.org/document/8607986/

Internet

https://ieeexplore.ieee.org/document/8607986/

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