Genetic algorithm for LQG/LTR design parameters. a flight control system application

García, Luis Antonio Ribot; López, Manuel J.

doi:10.1016/s1474-6670(17)32536-3

Cited by 2 publications

(2 citation statements)

References 3 publications

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“…Up to now, most of the LQG/LTR algorithms are based on the LLO scheme at the plant output, while the LLI scheme is rare in the related literature. Based on preliminary analysis of the LLI controller, for the first time, the detailed implementation plan of the LLI controller was given (Garcia and Lopez, 2003). It consists of modifying the free design parameters of the observer so that the open loop transfer function recovers the characteristics of the target open loop of the sysgtem model.…”

Section: Vibration Controlmentioning

confidence: 99%

“…One is to realize LTR at output of the plant by tuning gain matrix of optimal state-feedback matrix, in other words, to realize controller of “LQG using LTR at plant output” (LLO); the other is to realize LTR at input of the plant by tuning gain matrix of Kalman-filter, which is exactly the LLI controller mentioned above. Two theorems of LQG/LTR have been deduced to realize system control and stability analysis, which was a leading study in the application of this technology (Garcia and Lopez, 2003). At present, most of the researches belong to the first kind of implementation method.…”

Section: Introductionmentioning

confidence: 99%

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Theoretical modeling and vibration control for pre-twisted composite blade based on LLI controller

Liu

Gong

2019

Transactions of the Institute of Measurement and Control

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Theoretical modeling and vibration control for divergent motion of thin-walled pre-twisted wind turbine blade have been investigated based on “linear quadratic Gaussian (LQG) controller using loop transfer recovery (LTR) at plant input” (LLI). The blade section is a single-celled composite structure with symmetric layup configuration of circumferentially uniform stiffness (CUS), exhibiting displacements of vertical/lateral bending coupling. Flutter suppression for divergent instability is investigated, with blade driven by nonlinear aerodynamic forces. Theoretical modeling of CUS-based structure is implemented based on Hamilton variational principle of elasticity theory. The discretization of aeroelastic equations is solved by Galerkin method, with blade tip responses demonstrated. The LLI controller is characterized by LTR at the plant input. The effects of LLI controller are achieved and illustrated by displacement responses, controller responses and frequency spectrum analysis, respectively.

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Section: Vibration Controlmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%