Control strategies for an experimental morphing wing model

2014 ◽  
Author(s):  
Lucian T. Grigorie ◽  
Ruxandra M. Botez
Keyword(s):  
Control Strategies ◽  
Morphing Wing ◽  
Wing Model

scholarly journals Fuzzy Logic-Based Control for a Morphing Wing Tip Actuation System: Design, Numerical Simulation, and Wind Tunnel Experimental Testing

Biomimetics ◽  
2019 ◽  
Vol 4 (4) ◽  
pp. 65
Author(s):  
Khan ◽  
Grigorie ◽  
Botez ◽  
Mamou ◽  
Mébarki
Keyword(s):  
Numerical Simulation ◽  
Fuzzy Logic ◽  
Wind Tunnel ◽  
Experimental Testing ◽  
Aviation Industry ◽  
Morphing Wing ◽  
Brushless Dc ◽  
Wing Model ◽  
Actuation System ◽  
Prime Concern

The paper presents the design, numerical simulation, and wind tunnel experimental testing of a fuzzy logic-based control system for a new morphing wing actuation system equipped with Brushless DC (BLDC) motors, under the framework of an international project between Canada and Italy. Morphing wing is a prime concern of the aviation industry and, due to the promising results, it can improve fuel optimization. In this idea, a major international morphing wing project has been carried out by our university team from Canada, in collaboration with industrial, research, and university entities from our country, but also from Italy, by using a full-scaled portion of a real aircraft wing equipped with an aileron. The target was to conceive, manufacture, and test an experimental wing model able to be morphed in a controlled manner and to provide in this way an extension of the laminar airflow region over its upper surface, producing a drag reduction with direct impact on the fuel consumption economy. The work presented in the paper aims to describe how the experimental model has been developed, controlled, and tested, to prove the feasibility of the morphing wing technology for the next generation of aircraft.

scholarly journals Artificial Neural Networks-Extended Great Deluge Model to predict Actuators Displacements for a Morphing Wing Tip System

2020 ◽  
Vol 12 (4) ◽  
pp. 13-24
Author(s):  
Abdallah BEN MOSBAH ◽  
Ruxandra Mihaela BOTEZ ◽  
Soumaya MEDINI MEDINI ◽  
Thien-My DAO
Keyword(s):  
Fiber Composite ◽  
Surface Shape ◽  
Viscous Drag ◽  
Main Role ◽  
Ann Model ◽  
Morphing Wing ◽  
Wing Model ◽  
Flexible Material ◽  
Artificial Neural ◽  
Artificial Neural Network Ann

Resin-based fiber composite materials have received attention in aerospace composite engineering, particularly in aircraft morphing structures, due to their high mechanical characteristics, such as stiffness, and because of their potential to highly reduce the structural mass of modern aircraft. Aircraft morphing is referred to as the ability of an aircraft’s surface to change its geometry in flight. The modelling of a dynamic morphing wing system is here studied. The morphing wing was controlled using four electric actuators situated inside of the wing model. The main role of these actuators was to modify the wing upper surface shape designed and manufactured with a flexible material, so that the laminar-to-turbulent flow transition point can move closer to the wing trailing edge, thus causing a minimum viscous drag, for various flow conditions. To determine the skin deflections in the four actuators points, both LVDT and dial indicator gages were positioned on the wing. Four Linear Variable Differential Transducers (LVDTs) were used to indicate the positions of the four actuators, and four Dial Indicators gages were positioned on the wing to measure the real deflections of the flexible composite skin in the four actuation points. The relationship between the Dial Indicators’ values and the LVDTs’ values for a same set-point command signal had a nondeterministic and unpredictable behavior (not a linear one). The values of the displacements given by the LVDTs were different than the values given by the Dial Indicators. In this paper, an Artificial Neural Network (ANN) model was investigated created with the aim to predict the displacements of the wing upper surface skin in real time using four actuators. The proposed model was trained using the Extended Great Deluge (EGD) algorithm.

Design, numerical simulation and experimental testing of a controlled electrical actuation system in a real aircraft morphing wing model

2015 ◽  
Vol 119 (1219) ◽  
pp. 1047-1072 ◽  
Author(s):  
R. M. Botez ◽  
M. J. Tchatchueng Kammegne ◽  
L. T. Grigorie
Keyword(s):  
Experimental Testing ◽  
Experimental Studies ◽  
Morphing Wing ◽  
Theoretical Simulation ◽  
Actuation Mechanism ◽  
Wing Model ◽  
Actuation System ◽  
Structural Rigidity ◽  
Bench Testing ◽  
And Control

AbstractThe paper focuses on the modelling, simulation and control of an electrical miniature actuator integrated in the actuation mechanism of a new morphing wing application. The morphed wing is a portion of an existing regional aircraft wing, its interior consisting of spars, stringers, and ribs, and having a structural rigidity similar to the rigidity of a real aircraft. The upper surface of the wing is a flexible skin, made of composite materials, and optimised in order to fulfill the morphing wing project requirements. In addition, a controllable rigid aileron is attached on the wing. The established architecture of the actuation mechanism uses four similar miniature actuators fixed inside the wing and actuating directly the flexible upper surface of the wing. The actuator was designed in-house, as there is no actuator on the market that could fit directly inside our morphing wing model. It consists of a brushless direct current (BLDC) motor with a gearbox and a screw for pushing and pulling the flexible upper surface of the wing. The electrical motor and the screw are coupled through a gearing system. Before proceeding with the modelling, the actuator is tested experimentally (stand alone configuration) to ensure that the entire range of the requirements (rated or nominal torque, nominal current, nominal speed, static force, size) would be fulfilled. In order to validate the theoretical, simulation and standalone configuration experimental studies, a bench testing and a wind-tunnel testing of four similar actuators integrated on the real morphing wing model are performed.

Seamless Morphing Wing with SMP Skin

2008 ◽  
Vol 47-50 ◽  
pp. 97-100 ◽  
Author(s):  
Wei Long Yin ◽  
Qi Jian Sun ◽  
Bo Zhang ◽  
Jing Cang Liu ◽  
Jin Song Leng
Keyword(s):  
Plane Deformation ◽  
Dimensional Change ◽  
Large Strains ◽  
Morphing Wing ◽  
Aircraft Wings ◽  
Flexible Skin ◽  
Aerodynamic Pressure ◽  
Wing Model ◽  
Out Of Plane ◽  
Sandwiched Structure

Morphing aircraft wings require flexible skins that can undergo large strains, have low in-plane stiffness. In this paper, the sandwiched structure is designed to maintain airfoil shape throughout transition and not to suffer from large out-of-plane deformation under aerodynamic pressure loads. It consists of honeycomb and flexible skin. Honeycomb which is high-strain capable in one direction without dimensional change in the perpendicular in-plane axis provides distributed support to the honeycomb. Flexible skin is used to create the smooth aerodynamic surface. The morphing wing structure is developed together with the sandwiched skin technology. It is capable of changing in chordwise and increasing chord by 20%. Elastomeric and SMP skins are selected for use. Embedded heating wire springs act as the activation system for the SMP. Experiment results show the morphing wing model with elastomeric or SMP skins can be driven successfully by DC motor.

scholarly journals Design and experimental testing of a control system for a morphing wing model actuated with miniature BLDC motors

2020 ◽  
Vol 33 (4) ◽  
pp. 1272-1287 ◽  
Author(s):  
Teodor Lucian GRIGORIE ◽  
Shehryar KHAN ◽  
Ruxandra Mihaela BOTEZ ◽  
Mahmoud MAMOU ◽  
Youssef MÉBARKI
Keyword(s):  
Control System ◽  
Experimental Testing ◽  
Morphing Wing ◽  
Wing Model

Adolescents' Use of Resource Control Strategies and Bullying Behaviors

2017 ◽  
Author(s):  
Kelly N. Clark ◽  
Nicole B. Dorio ◽  
Michelle K. Demaray ◽  
Christine K. Malecki
Keyword(s):  
Control Strategies ◽  
Resource Control ◽  
Bullying Behaviors
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