Abstract
Vibration and control of cantilever blade with bending-twist coupling (BTC) based on trailing-edge flap (TEF) by restricted control input are investigated. The blade is a thin-walled structure using circumferentially asymmetric stiffness (CAS) configuration, with TEF embedded and hinged into the host composite structure along the entire blade span. The TEF structure is driven by quasi-steady aerodynamic forces. Vibration control is investigated based on linear matrix inequation (LMI) algorithm using restricted control input (LMI/RCI). Flutter suppression of BTC displacements and the angle of TEF (i.e. the practical control input) are illustrated, with apparently controlled effects demonstrated. The restricted control input signals are used to driven the TEF to explore the scope of the feasibility of the practical TEF angle, which is displayed by a virtual simulation platform. The platform verifies the feasibility of the hardware implementation for the control algorithms.
Highlights
Both wind turbine blades and helicopter blades have always been involved in classical flutter in actuation of linear flow state or quasi-steady fluid, thereby leading to fatigue problems or performance loss
Most of the structural modeling are based on 2D section subjected to bending-twist coupling (BTC) motions which are stimulated by various aerodynamic forces based on Navier-Stokes (NS) model, interaction model between Computational Fluid Dynamic (CFD) and Computational Structure Dynamic, fluid-structure model such as using Blade Element Momentum theory, or other models directly from third-party aerodynamic codes
For a large limited input, such as u=umax=1:2 rad, it can achieve the purpose of flutter suppression, it is still accompanied by a large vibration amplitude
Summary
Both wind turbine blades and helicopter blades have always been involved in classical flutter in actuation of linear flow state or quasi-steady fluid, thereby leading to fatigue problems or performance loss. Most of the literature on BTC flutter is based on the study of 2D airfoil structure that subjected to flap-wise bending and twist vibrations. Classical flutter means the combined flap-wise bending and twist motions of an aerofoil in the linear region of its polar curve on the one hand, and refers to a violent unstable dynamic condition in which the blade structure, under the influence of incident aerodynamic loads, undergoes the high-amplitude vibrations due to the coupling of the BTC modes.. Structure modeling and flutter analysis of an individual blade section, subjected to combined flapwise bending and twist motions, have been investigated by Chaviaropoulos et al., with NS model applied to analyze aeroelastic stability. An aeroelastic numerical model was described, which combined a NS-based CFD solver with an elastic model and two coupling schemes, to study the aeroelastic behavior of 2D
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