Adaptive Attitude Controller Design for a Rigid Satellite with Feedback Linearization Approach

This paper investigates a novel adaptive attitude controller design for rigid microsatellite based on feedback linearization approach, in which an accurate attitude pointing is required within a strict power limitation for space environment. The control strategy is performed to guarantee the stabili...

Full description

Saved in:
Bibliographic Details
Published in:The Journal of the astronautical sciences 2020-12, Vol.67 (4), p.1445-1469
Main Authors: Adnane, Akram, Bellar, Abdellatif, Mohammed, Mohammed Arezki Si, Hong, Jiang, Foitih, Zoubir Ahmed
Format: Article
Language:English
Subjects:
Aerospace Technology and Astronautics
Engineering
Mathematical Applications in the Physical Sciences
Original Article
Space Exploration and Astronautics
Space Sciences (including Extraterrestrial Physics
Citations: Items that this one cites
Items that cite this one
Online Access:Get full text
Tags: Add Tag
No Tags, Be the first to tag this record!
Description
Summary:This paper investigates a novel adaptive attitude controller design for rigid microsatellite based on feedback linearization approach, in which an accurate attitude pointing is required within a strict power limitation for space environment. The control strategy is performed to guarantee the stability of the satellite attitude under the effect of uncertain actuator parameters such as torque magnitude error and misalignment. The controller estimates the total torque fault through an observer in order to provide a reliable attitude control during the satellite manoeuvre. The stability of the closed-loop dynamic of the designed control law is proven via Lyapunov analysis. Finally, a comparative study with the well-known controllers from the literature is examined through numerical simulations to demonstrate the feasibility and effectiveness of the proposed control method.
ISSN:0021-9142
2195-0571
DOI:10.1007/s40295-020-00227-y