Active Vibration Control of a Maneuvering Flexible Spacecraft Using Hybrid Actuators: A Lyapunov-Based Control Approach

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َAzimi Milad; Moradi Samad

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Journal: Journal of Space Science and Technology Year:2022 | Volume: | Issue: Page(s): 1-13

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Information Journal Paper

Title

Active Vibration Control of a Maneuvering Flexible Spacecraft Using Hybrid Actuators: A Lyapunov-Based Control Approach

Author(s)

َAzimi Milad | Moradi Samad | Issue Writer Certificate

Keywords

Active vibration controlQ4

Flexible spacecraftQ4

Hybrid actuatorsQ4

Lyapunov designQ4

Piezoelectric patchesQ4

Abstract

This paper presents a study concerning Active vibration control of a smart Flexible spacecraft during attitude maneuver using thrusters and reaction wheels (RW) in combination and piezoelectric (PZT) sensor/actuator patches. The large-angle maneuver and residual vibration of the spacecraft are controlled using an extended Lyapunov-based design (ELD) and strain rate feedback (SRF) theory for a two-mode mission. The single-axis fully coupled nolinear rigidflexible dynamic of the system is derived applying a Lagrangian approach and Finite Element Method (FEM). The overall stability of the system including energetic terms covering a hub and two flexible appendages, torsional spring, RW, and PZT dynamics, has been proved and the control law has been derived accordingly. A pulse-width pulse-frequency (PWPF) modulation is used to alleviate the excitations of high-frequency flexible modes. However, due to the fast maneuver, there are still residual vibrations in the system. Hence, the SRF algorithm using PZT is applied to prepare further vibration suppression. A great feature of the proposed hybrid actuator system is the switching time of the thrusters and RW, which is based on total systems energy. The numerical results for a Flexible spacecraft with large-angle, agile and precise maneuver requirements through a comparative study verify the merits of the proposed approach

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