Sizing and Control of Trailing Edge Flaps on a Smart Rotor for Maximum Power Generation in Low Fatigue Wind Regimes

2014 ◽  
Author(s):  
Jeroen Smit ◽  
Lars Oliver Bernhammer ◽  
Leonardo Bergami ◽  
Mac Gaunaa
Keyword(s):  
Power Generation ◽  
Maximum Power ◽  
Trailing Edge ◽  
Trailing Edge Flaps ◽  
Wind Regimes ◽  
And Control

Sizing and control of trailing edge flaps on a smart rotor for maximum power generation in low fatigue wind regimes

Wind Energy ◽  
2015 ◽  
Vol 19 (4) ◽  
pp. 607-624 ◽  
Author(s):  
Jeroen Smit ◽  
Lars O. Bernhammer ◽  
Sachin T. Navalkar ◽  
Leonardo Bergami ◽  
Mac Gaunaa
Keyword(s):  
Power Generation ◽  
Maximum Power ◽  
Trailing Edge ◽  
Trailing Edge Flaps ◽  
Wind Regimes ◽  
And Control

scholarly journals Two-Axis Solar Tracker Analysis and Control for Maximum Power Generation

2011 ◽  
Vol 6 ◽  
pp. 457-462 ◽  
Author(s):  
S. Ozcelik ◽  
H. Prakash ◽  
R. Challoo
Keyword(s):  
Power Generation ◽  
Maximum Power ◽  
Solar Tracker ◽  
And Control

scholarly journals Helicopter Vibratory Loads Alleviation through Combined Action of Trailing-Edge Flap and Variable-Stiffness Devices

2015 ◽  
Vol 2015 ◽  
pp. 1-10 ◽  
Author(s):  
Massimo Gennaretti ◽  
Giovanni Bernardini ◽  
Jacopo Serafini ◽  
Marco Molica Colella
Keyword(s):  
Rotor Blade ◽  
Variable Stiffness ◽  
Control Procedure ◽  
Trailing Edge ◽  
Control Effort ◽  
Control Laws ◽  
Trailing Edge Flaps ◽  
Control Configuration ◽  
Helicopter Main Rotor ◽  
And Control

The aim of this paper is the assessment of the capability of controllers based on the combined actuation of flaps and variable-stiffness devices to alleviate helicopter main rotor vibratory hub loads. Trailing-edge flaps are positioned at the rotor blade tip region, whereas variable-stiffness devices are located at the pitch link and at the blade root. Control laws are derived by an optimal control procedure based on the best trade-off between control effectiveness and control effort, under the constraint of satisfaction of the equations governing rotor blade aeroelastic response. The numerical investigation concerns the analysis of performance and robustness of the control techniques developed, through application to a four-bladed helicopter rotor in level flight. The identification of the most efficient control configuration is also attempted.

Adaptive Neurocontrol of Simulated Rotor Vibrations Using Trailing Edge Flaps

1999 ◽  
Vol 10 (11) ◽  
pp. 855-871
Author(s):  
MICHAEL G. SPENCER ◽  
ROBERT M. SANNER ◽  
INDERJIT CHOPRA
Keyword(s):  
Trailing Edge ◽  
Trailing Edge Flaps

scholarly journals A Parametric Study of Trailing Edge Flap Implementation on Three Different Airfoils Through an Artificial Neuronal Network

Symmetry ◽  
2020 ◽  
Vol 12 (5) ◽  
pp. 828
Author(s):  
Igor Rodriguez-Eguia ◽  
Iñigo Errasti ◽  
Unai Fernandez-Gamiz ◽  
Jesús María Blanco ◽  
Ekaitz Zulueta ◽  
...  
Keyword(s):  
Aerodynamic Coefficients ◽  
Trailing Edge ◽  
High Lift ◽  
Trailing Edge Flaps ◽  
Artificial Neural Network Ann ◽  
Lift And Drag ◽  
Artificial Neuronal Network ◽  
Naca 0012 ◽  
Drag Ratio ◽  
Lift To Drag Ratio

Trailing edge flaps (TEFs) are high-lift devices that generate changes in the lift and drag coefficients of an airfoil. A large number of 2D simulations are performed in this study, in order to measure these changes in aerodynamic coefficients and to analyze them for a given Reynolds number. Three different airfoils, namely NACA 0012, NACA 64(3)-618, and S810, are studied in relation to three combinations of the following parameters: angle of attack, flap angle (deflection), and flaplength. Results are in concordance with the aerodynamic results expected when studying a TEF on an airfoil, showing the effect exerted by the three parameters on both aerodynamic coefficients lift and drag. Depending on whether the airfoil flap is deployed on either the pressure zone or the suction zone, the lift-to-drag ratio, CL/CD, will increase or decrease, respectively. Besides, the use of a larger flap length will increase the higher values and decrease the lower values of the CL/CD ratio. In addition, an artificial neural network (ANN) based prediction model for aerodynamic forces was built through the results obtained from the research.

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