Adaptive Attitude Controller Design for a Rigid Satellite with Feedback Linearization Approach
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Adaptive Attitude Controller Design for a Rigid Satellite with Feedback Linearization Approach Akram Adnane 1,2 & Abdellatif Bellar 1 & Mohammed Arezki Si Mohammed 1 & Jiang Hong 3 & Zoubir Ahmed Foitih 2 # American Astronautical Society 2020
Abstract 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. Keywords Satellite . Attitude control . Adaptive feedback linearization . Actuator
uncertainties
Introduction In view of the advanced evolution in aerospace engineering, the satellite mission requirements are becoming more and more complex. Therefore, the techniques used
* Akram Adnane [email protected]
1
Département de Recherche en Mécanique Spatiale, Centre de Développement des Satellites (CDS), BP 4065 Ibn Rochd USTO, Oran, Algeria
2
Université des Sciences et de la Technologie d’Oran Mohamed Boudiaf, USTO-MB, BP 1505, El M’naouer, 31000 Oran, Algeria
3
School of Automation Science and Electrical Engineering, BeiHang University, Beijing 100191, China
The Journal of the Astronautical Sciences
to control the attitude of the satellite have been evolved significantly over time. In realistic environment, the uncertain actuator parameters including torque magnitude error and misalignment are frequently encountered in practical applications owing to manufacturing imperfections or aging and wearing out of the mechanical and electrical parts of actuators [10]. Accordingly, these uncertainties may result an unfavourable effect to the attitude control accuracy, which is necessary to be well considered in the attitude controller design in order to guarantee the desired stability performance for the satellite. In general, many approaches related to the satellite attitude control have been widely recognized in numerous papers such as adaptive control [14, 15], robust control [8], and feedback linearization [6, 21] and so on. Specially, the fixed-gain Proportional Derivative (PD) controller was cited as proper way to maintain the attitude at the desired attitude, and has been advantageously implemented for its short transient response and accurate steady state error [5, 20]. Likewise, the non-linear recursive control approach, called backstepping control, has been extensively applied in the attitude
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