Vibration Control Of Flexible Spacecraft Integrating A Momentum Exchange Controller And A Distributed Piezoelectric Actuator

Li, Z.; Bainum, Peter M.

doi:10.1006/jsvi.1994.1450

Cited by 39 publications

(19 citation statements)

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“…Figure 9 shows the voltages applied to the piezoelectric actuators bonded to the right appendage. It is clear that the magnitudes of voltages applied to piezoelectric actuators are in permissible limit (1400 V) [34]. The voltages of the sensors and actuators of the left appendage are similar to those of the right one.…”

Section: Simulation Results and Discussionmentioning

confidence: 77%

Dynamics and control of a smart flexible satellite moving in an orbit

et al. 2015

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In this paper, the three axes maneuver control and vibration suppression of a smart flexible satellite moving in a circular orbit are studied. First, by using Lagrange-RayleighRitz technique and assumed mode method, the governing equations of a flexible satellite with PZT (lead zirconate titanate) piezoelectric patches are obtained. The flexibility of the appendages and the assumption of a large angle trajectory cause the governing equations to be nonlinear and coupled. The piezoelectric layers, attached to both sides of the appendages, are considered as sensors and actuators. A thorough look at the resulting equations reveals that the flexible satellite dynamics that include the appendage vibrations and rigid maneuver occur in two different time scales. By using the singular perturbation theory, the system dynamics is divided into two fast and slow subsystems. The slow and fast subsystems are associated with rigid motion dynamics and flexible appendages dynamics, respectively. A hybrid controller, which is proposed for use, consists of a variable structure controller (VSC) for maneuvering control of the slow subsystem, and a Lyapunov based controller for vibration suppression of the fast subsystem. The stability of the controllers is studied using the Lyapunov stability theory. Finally, the system behavior is simulated and the simulation results show the efficient performance of the proposed hybrid controller.

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Section: Simulation Results and Discussionmentioning

confidence: 77%

Dynamics and control of a smart flexible satellite moving in an orbit

et al. 2015

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“…6, the controller applies the admissible voltages to the actuators. 19 The mid vibrations of the right appendage have been shown in Fig. 5.…”

Section: Simulation Resultsmentioning

confidence: 99%

Robust Inverse Dynamic Control of a Maneuvering Smart Flexible Satellite with Piezoelectric Layers

Azadi¹,

Azadi²,

Fazelzadeh³

2017

IJAV

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In this paper, a satellite with two flexible appendages and a central hub is considered. The piezoelectric layers are attached to both side of the appendages and used as actuators. The governing equations of motion are derived based on Lagrange method. Using Rayleigh-Ritz technique ordinary differential equations of motion are obtained. A robust inverse dynamic control is applied to the system to not only control the three axes manoeuvre of the satellite but also suppress the vibrations of the flexible appendages. Finally, the system is simulated and simulation results show good performance of this controller.

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“…Light weight arms with flexible behaviour could be a possible solution to low payload/weight ratios in current industrial robots and, moreover, in aerospace environment [16]. Here a simplified model of a cantilever flexible sandwich beam which can be considered as an appendage of a flexible spacecraft is analysed [16].…”

Section: Robot Arm Dynamicsmentioning

confidence: 99%

“…Here a simplified model of a cantilever flexible sandwich beam which can be considered as an appendage of a flexible spacecraft is analysed [16]. The arm is considered with a length of 5 m, a width of 0.1 m and total thickness of 0.088 m. The ratio between core and face sheets thickness is 20.…”

Section: Robot Arm Dynamicsmentioning

confidence: 99%