Displaying similar documents to “Experimental active vibration control in truss structures considering uncertainties in system parameters.”

Designing a ship course controller by applying the adaptive backstepping method

Anna Witkowska, Roman Śmierzchalski (2012)

International Journal of Applied Mathematics and Computer Science

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The article discusses the problem of designing a proper and efficient adaptive course-keeping control system for a seagoing ship based on the adaptive backstepping method. The proposed controller in the design stage takes into account the dynamic properties of the steering gear and the full nonlinear static maneuvering characteristic. The adjustable parameters of the achieved nonlinear control structure were tuned up by using the genetic algorithm in order to optimize the system performance....

Switching LPV control design with MDADT and its application to a morphing aircraft

Yong He, Chunjuan Li, Weiguo Zhang, Jingping Shi, Yongxi Lü (2016)

Kybernetika

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In flight control of a morphing aircraft, the design objective and the dynamics may be different in its various configurations. To accommodate different performance goals in different sweep wing configurations, a novel switching strategy, mode dependent average dwell time (MDADT), is adopted to investigate the flight control of a morphing aircraft in its morphing phase. The switching signal used in this note is more general than the average dwell time (ADT), in which each mode has its...

Control of an induction motor using sliding mode linearization

Erik Etien, Sébastien Cauet, Laurent Rambault, Gérard Champenois (2002)

International Journal of Applied Mathematics and Computer Science

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Nonlinear control of the squirrel induction motor is designed using sliding mode theory. The developed approach leads to the design of a sliding mode controller in order to linearize the behaviour of an induction motor. The second problem described in the paper is decoupling between two physical outputs: the rotor speed and the rotor flux modulus. The sliding mode tools allow us to separate the control from these two outputs. To take account of parametric variations, a model-based approach...

Robust quasi NID aircraft 3D flight control under sensor noise

Marian J. Błachuta, Valery D. Yurkevich, Konrad Wojciechowski (1999)

Kybernetika

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In the paper the design of an aircraft motion controller based on the Dynamic Contraction Method is presented. The control task is formulated as a tracking problem for Euler angles, where the desired decoupled output transients are accomplished under assumption of high-level, high-frequency sensor noise and incomplete information about varying parameters of the system and external disturbances. The resulting controller has a simple form of a combination of a low-order linear dynamical...