2017
DOI: 10.21595/jve.2017.18240
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The limit cycle oscillation of divergent instability control based on classical flutter of blade section

Abstract: Numerical simulation of a novel fuzzy control and back propagation neural network (BPNN) control for divergent instability based on classical flutter of 5-DOF wind turbine blade section driven by pitch adjustment has been investigated. The work is dedicated to solving destructive flap/lag/twist divergent instability from classical flutter, which might occur during the gust wind action, and might cause fracture failure of the blade itself and tower body. In order to investigate the optimal control method, the p… Show more

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Cited by 8 publications
(13 citation statements)
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“…Figure 1 shows the blade section at a distance r = L/4 from the hub, with the length of the blade being L = 8 m. The flap-wise direction is denoted by z, and lead-lag direction is denoted by y. u is the twist displacement and a is the angle of attack. The angle of trailing-edge flap is illustrated as b, wind speed is U = 10 m s 21 , the chord length is c = 0.67 m Considering the cross-sectional model without trailing-edge flap in the work by Liu, 14 and ignoring the nonlinear and lead-lag vibration of the structure, the equations of flap-wise bending (z) and twist (u) motions are obtained…”
Section: Modeling Of Aeroelastic Systemmentioning
confidence: 99%
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“…Figure 1 shows the blade section at a distance r = L/4 from the hub, with the length of the blade being L = 8 m. The flap-wise direction is denoted by z, and lead-lag direction is denoted by y. u is the twist displacement and a is the angle of attack. The angle of trailing-edge flap is illustrated as b, wind speed is U = 10 m s 21 , the chord length is c = 0.67 m Considering the cross-sectional model without trailing-edge flap in the work by Liu, 14 and ignoring the nonlinear and lead-lag vibration of the structure, the equations of flap-wise bending (z) and twist (u) motions are obtained…”
Section: Modeling Of Aeroelastic Systemmentioning
confidence: 99%
“…13 The members of our research group have also carried out the limit cycle vibration analysis and the intelligent proportional-integral-derivative (PID) control strategy to analyze bending-torsional aeroelastic instability of the 2D blade in the previous work. 14 In this study, based on the segmented pendulum structure with revolute pair connection, a simpler chordwise rigid trailing-edge flap, the effect of theoretical aerodynamic model on the aeroelastic stability of blade section is studied. The aerodynamic model is derived and modified from the helicopter blade with chordwise trailing-edge structure in the work by Sahjendra and Woosoon.…”
Section: Introductionmentioning
confidence: 99%
“…However, the fuzzy algorithm itself is tedious. For the other neural network algorithm, although the numerical simulation of control effect is more ideal, because of the complex integration problem, it is difficult to be implemented in the PLC hardware [21]. Hence the feasibility analysis of the hardware implementation of PPMO algorithm needs further discussion.…”
Section: Feasibility Analysis Of Hardware Implementation Of Control Amentioning
confidence: 99%
“…Hence the feasibility analysis of the hardware implementation of PPMO algorithm needs further discussion. In present study, a hardware-in-the-loop simulation platform is built by OPC technology [21] between PLC controller system and MATLAB/SIMUILINK simulation environment to test the feasibility of hardware implementation. Figure 9 shows the experimental system, including the main interface of the human-machine interface (HMI), and the PPMO control interface, respectively.…”
Section: Feasibility Analysis Of Hardware Implementation Of Control Amentioning
confidence: 99%
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