Active Flap Controller Evaluation

2015 ◽  
pp. 103-111
Author(s):  
Ranjan Ganguli ◽  
Dipali Thakkar ◽  
Sathyamangalam Ramanarayanan Viswamurthy
Keyword(s):  
Active Flap

An Active Flap Deployment System for Blade–Disturbance Interaction Alleviation

2004 ◽  
Vol 126 (6) ◽  
pp. 1006-1014 ◽  
Author(s):  
Carter T. Nelson ◽  
Othon K. Rediniotis
Keyword(s):  
Vortex Generator ◽  
Leading Edge ◽  
Experimental Tests ◽  
Design Tool ◽  
Trailing Edge ◽  
Blade Vortex Interaction ◽  
Aeroelastic Model ◽  
Trailing Edge Flap ◽  
Ultimate Objective ◽  
Active Flap

A new, actively deployable trailing edge flap system is introduced and an experimental investigation is undertaken to determine its effects on the disturbances created during blade–disturbance interactions (BDI), with blade–vortex interaction (BVI) alleviation being the ultimate objective. Experimental tests were conducted using a two-dimensional (2D) wind tunnel setup incorporating a pressure instrumented airfoil section with a deployable 20% trailing edge flap and an upstream vortex generator to produce the disturbance. Results of this study showed that the disturbances, caused by BDI events, to the pressure distribution over the airfoil occur mostly at the leading edge. Carefully synchronized deployment of the trailing edge flap during BDI events resulted in a reduction of this pressure disturbance. The aeroelastic response of the active flap was modeled via unsteady linear theory and the model was validated experimentally. The aeroelastic model shows good agreement with experimental results, which supports its use as a preliminary design tool for the actuation parameters of the active flap system.

A review on electroactive polymers development for aerospace applications

2018 ◽  
Vol 29 (19) ◽  
pp. 3681-3695 ◽  
Author(s):  
Musavir Bashir ◽  
Parvathy Rajendran
Keyword(s):  
Smart Materials ◽  
Electroactive Polymers ◽  
Fast Response ◽  
Polymer Materials ◽  
Electroactive Polymer ◽  
Sensors And Actuators ◽  
Aerospace Applications ◽  
Current Trends ◽  
Potential Applications ◽  
Active Flap

Newfangled smart materials have inspired the researchers to look for more efficient materials that can respond to specific stimuli and retain the original shape. Electroactive polymers are such materials which are capable of sensing and real-time actuation. Various electroactive polymers are excellent candidates due to high strain rate, fast response, reliability and high mechanical compliance despite tough manufacturing. In this study, electroactive polymers are reviewed and the general enabling mechanisms employing their distinct characteristics are presented, and the factors influencing the properties of various electroactive polymers are also discussed. Our study also enumerates the current trends in the development of electroactive polymers along with its progress in aerospace discipline. The electromechanical properties of electroactive polymer materials endow them the capability to work as both sensors and actuators in the field of aerospace. Hence, we provide an overview of various applications of electroactive polymers in aerospace field, notably aircraft morphing. These actuators are vastly used in aerospace applications like Mars Nano-rover, space robotic, flapping wings and active flap. Therefore, the electroactive polymer applications such as effective actuators can be investigated more in their materials, molecular interactions, electromechanics and actuation mechanisms. Considering electroactive polymers unique properties, they will endeavour the great potential applications within aerospace industry.

Design and Modeling of the Fowler Flap With Adaptive Elements

Aerospace ◽  
2006 ◽  
Author(s):  
Oleksandr Kozlov
Keyword(s):  
Finite Element ◽  
Finite Element Model ◽  
Deformation Behaviour ◽  
Leading Edge ◽  
Element Model ◽  
High Lift ◽  
Aerodynamic Efficiency ◽  
Transport Aircraft ◽  
Sma Actuators ◽  
Active Flap

This paper describes the process of the designing of the Fowler flap with adaptive elements. Modern passenger and transport aircraft use high lift devices for take off and landing. Of great importance for the creation of high lift during take off and landing is the shape and size of the gap between wing and extended Fowler flap. To improve the deformation behaviour of the leading edge of this flap, and to improve the geometry of the gap, it was decided to use shape memory alloy (SMA) actuators in the flap structure. First, the complex finite element model of the passive flap was created and then this model was extended with active elements, which are modelling the SMA actuators. As a result, the complex finite element model of the active flap was obtained. This modelling was done using software MATLAB and a finite element model was created using software ANSYS. The main result of this work is that with help of SMA actuators integrated in the flap it was possible to influence and improve the geometry of the gap between the wing and the extended flap, resulting in the aerodynamic efficiency of this flap being increased.

scholarly journals Field test of an active flap system on a full-scale wind turbine

2021 ◽  
Vol 6 (1) ◽  
pp. 33-43
Author(s):  
Alejandro Gomez Gonzalez ◽  
Peder B. Enevoldsen ◽  
Athanasios Barlas ◽  
Helge A. Madsen
Keyword(s):  
Wind Turbine ◽  
Static Load ◽  
Load Control ◽  
Atmospheric Conditions ◽  
Control Authority ◽  
Aeroelastic Simulations ◽  
Active Flap ◽  
Validation Tests ◽  
Load Impact

Abstract. This article describes a series of validation tests of an active flap system (AFS) on a multi-megawatt wind turbine. A single blade of a 4 MW turbine with 130 m rotor diameter (SWT-4.0-130) is retrofitted in the outer 15–20 m with the AFS. The AFS is controlled remotely with a pneumatic pressure supply system located in the hub of the turbine. The measurements were performed between October 2017 and June 2019 using two different AFS configurations on the blade. A description of the system setup is given, as well as comparisons of measurements and aeroelastic simulations. The measurements quantify the static load control authority of the AFS in atmospheric conditions, providing a preliminary estimate of load impact potential for the concept. This article presents, furthermore, a new method for the characterization of the load impact of such a system and its dynamic response under atmospheric conditions based on a blade-to-blade load comparison.

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