Induced-shear piezoelectric actuators for rotor blade trailing edge flaps and active tips

2001 ◽  
Author(s):  
Louis Centolanza ◽  
Edward Smith ◽  
Anthony Morris
Keyword(s):  
Rotor Blade ◽  
Piezoelectric Actuators ◽  
Trailing Edge ◽  
Trailing Edge Flaps

Induced-shear piezoelectric actuators for rotor blade trailing edge flaps

2002 ◽  
Vol 11 (1) ◽  
pp. 24-35 ◽  
Author(s):  
Louis R Centolanza ◽  
Edward C Smith ◽  
Brian Munsky
Keyword(s):  
Rotor Blade ◽  
Piezoelectric Actuators ◽  
Trailing Edge ◽  
Trailing Edge Flaps

Vibration reduction of helicopter with trailing-edge flaps at various flying conditions

2016 ◽  
Vol 231 (4) ◽  
pp. 770-784 ◽  
Author(s):  
SK Kodakkattu ◽  
ML Joy ◽  
K Prabhakaran Nair
Keyword(s):  
Rotor Blade ◽  
Torsional Stiffness ◽  
Trailing Edge ◽  
Control Power ◽  
Surface Method ◽  
Solidity Ratio ◽  
Helicopter Rotor Blade ◽  
Trailing Edge Flaps ◽  
Trailing Edge Flap ◽  
Improved Design

The aim of this study is to find the optimal torsional stiffness and trailing-edge flap locations of the helicopter rotor blade for minimum vibration and flap control power at flap lengths of 6% and 9% of the rotor-blade length. A three level orthogonal array based response surface method using polynomial functions is used to describe both vibration and flap control power. Pareto points minimizing hub vibration and flap control power are found at flap lengths of 6% and 9% of the rotor length. This study also explores the variation in rotor hub vibration and flap control power with flying conditions such as the advance ratio and the thrust-to-solidity ratio at the optimum design points. This gives a useful improved design with about a 60% decrease in hub vibration with a penalization of increased flap power at the normal flying regime of rotor-craft flight.

scholarly journals Identification of Flap Motion Parameters for Vibration Reduction in Helicopter Rotors with Multiple Active Trailing Edge Flaps

2011 ◽  
Vol 18 (5) ◽  
pp. 727-745 ◽  
Author(s):  
Uğbreve;ur Dalli ◽  
Şcedilefaatdin Yüksel
Keyword(s):  
Rotor Blade ◽  
Helicopter Rotor ◽  
System Response ◽  
Trailing Edge ◽  
Blade Root ◽  
Helicopter Rotor Blade ◽  
Blade Vibrations ◽  
Trailing Edge Flaps ◽  
Trailing Edge Flap ◽  
Blade Loads

An active control method utilizing the multiple trailing edge flap configuration for rotorcraft vibration suppression and blade loads control is presented. A comprehensive model for rotor blade with active trailing edge flaps is used to calculate the vibration characteristics, natural frequencies and mode shapes of any complex composite helicopter rotor blade. A computer program is developed to calculate the system response, rotor blade root forces and moments under aerodynamic forcing conditions. Rotor blade system response is calculated using the proposed solution method and the developed program depending on any structural and aerodynamic properties of rotor blades, structural properties of trailing edge flaps and properties of trailing edge flap actuator inputs. Rotor blade loads are determined first on a nominal rotor blade without multiple active trailing edge flaps and then the effects of the active flap motions on the existing rotor blade loads are investigated. Multiple active trailing edge flaps are controlled by using open loop controllers to identify the effects of the actuator signal output properties such as frequency, amplitude and phase on the system response. Effects of using multiple trailing edge flaps on controlling rotor blade vibrations are investigated and some design criteria are determined for the design of trailing edge flap controller that will provide actuator signal outputs to minimize the rotor blade root loads. It is calculated that using the developed active trailing edge rotor blade model, helicopter rotor blade vibrations can be reduced up to 36% of the nominal rotor blade vibrations.

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.

Design of an Intelligent Rotor Blade With a Trailing Edge Flap Manipulated by Piezoelectric Actuators

2009 ◽  
Author(s):  
JaeHwan Lee ◽  
TaeSeong Kim ◽  
SanJoon Shin
Keyword(s):  
Rotor Blade ◽  
Piezoelectric Actuators ◽  
Trailing Edge ◽  
Cross Sectional ◽  
Analysis And Design ◽  
Composite Blade ◽  
National University ◽  
Variational Asymptotic ◽  
Trailing Edge Flap ◽  
The Cross

This paper describes a procedure to design and fabricate an intelligent rotor blade with a trailing edge flap called as Seoul National University Flap blade (SNUF blade) manipulated by piezoelectric actuators. To develop a composite blade with a trailing-edge flap, specific design requirements for the SNUF blade are established by an analysis, UMARC (University of Maryland Advanced Rotorcraft Code). An analysis and design of the cross section are conducted first. In this paper, UM/VABS (University of Michigan/Variational Asymptotic Beam Section Analysis) is used for the cross sectional analysis. Prediction on the hinge moment induced in the flap is conducted for selection of the actuator by using FLUENT, a commercial CFD analysis. APA 200M actuator is selected as a candidate actuator to provide an enough stroke in the flap. The design illustrated in this paper includes a procedure only up to a part of the active region. More details of the design will be pursued and described in the final paper.

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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