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morphing wing flaps for large civil aircraft:Evolution of a smart technology across the Clean Sky program

Chinese Journal of Aeronautics 2021年第7期34卷 13-28页

作者： Rosario Pecora Department of Industrial Engineering Aerospace DivisionUniversity of Naples“Federico II”80125 NapoliItaly

Abstract morphing wing structures are widely considered among the most promising technologies for the improvement of aerodynamic performances in large civil *** controlled adaptation of the wing shape to external operative conditions naturally enables the maximization of aircraft aerodynamic efficiency,with positive fallouts on the amount of fuel burned and pollutant *** benefits brought by morphing wings at aircraft level are accompanied by the criticalities of the enabling technologies,mainly involving weight penalties,overconsumption of electrical power,and safety *** attempt to solve such criticalities passes through the development of novel design approaches,ensuring the consolidation of reliable structural solutions that are adequately mature for certification and in-flight *** this work,the development phases of a multimodal camber morphing wing flap,tailored for large civil aircraft applications,are outlined with specific reference to the activities addressed by the author in the framework of the Clean Sky *** flap is morphed according to target shapes depending on aircraft flight conditions and defined to enhance high-lift performances during takeoff and landing,as well as wing aerodynamic efficiency during *** innovative system based on finger-like robotic ribs driven by electromechanical actuators is proposed as morphing-enabling technology;the maturation process of the device is then traced from the proof of concept to the consolidation of a true-scale demonstrator for pre-flight ground validation tests.A step-by-step approach involving the design and testing of intermediate demonstrators is then carried out to show the compliance of the adaptive system with industrial standards and safety *** technical issues encountered during the development of each intermediate demonstrator are critically analyzed,and justifications are provided for all the adopted engineering ***,the layout

关键词： Electro-mechanical actuators(EMA) Green regional aircraft Mechanical systems morphing flap morphing wing Smart aircraft Smart structures Variable camber airfoil

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Gust response of an elasto-flexible morphing wing using fluid–structure interaction simulations

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Chinese Journal of Aeronautics 2024年第2期37卷 45-57页

作者： Jonathan PFLÜGER Christian BREITSAMTER Department of Mechanical Engineering Technical University of MunichGarching 85748Germany

Small and micro unmanned aircraft are the focus of scientific interest due to their wide range of *** often operate in a highly unstable flight environment where the application of new morphing wing technologies offers the opportunity to improve flight *** investigated concept comprises port and starboard adjustable wings,and an adaptive elastoflexible membrane serves as the lifting *** focus is on the benefits of the deforming membrane during the impact of a one-minus-cosine type *** a low Reynolds number of Re=264000,the morphing wing model is investigated numerically by unsteady fluid-structure interaction ***,the numerical results are validated by experimental data from force and moment,flow field,and deformation ***,with the rigid wing as the baseline,the flexible case is investigated,focusing on the advantages of the elastic *** all configurations studied,the maximum amplitude of the lift coefficient under gust load shows good agreement between the experimental and numerical *** the decay of the gust,they differ more the higher the aspect ratio of the *** considering the flow field,the main differences are due to the separation behavior on the upper side of the *** flow reattaches earlier in the experiments than in the simulations,which explains the higher lift values observed in the *** at one intermediate configuration does the lift amplitude of the rigid configuration exceeds that of the flexible by about 12%,with the elastic membrane resulting in a smaller and more uniform peak load,which is also evident in the wing loading and hence in the root bending moment.

关键词： Membrane wing morphing wing Flexible wing surface Computational fluid dynam-ics Fluid-structure interaction Unsteady inflow condition Gust response

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Design and experiment of concentrated flexibility-based variable camber morphing wing

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Chinese Journal of Aeronautics 2022年第5期35卷 455-469页

作者： Yuzhu LI Wenjie GE Jin ZHOU Yonghong ZHANG Donglai ZHAO Zhuo WANG Dianbiao DONG School of Mechanical Engineering Northwestern Polytechnical UniversityXi’an 710072China School of Aeronautic Science and Engineering Beihang UniversityBeijing 100083China

The morphing wing has a significant positive effect on the aerodynamic performance of the *** paper describes a leading-edge of variable camber wing with concentrated flexibility based on the geared five-bar *** driving points of morphing skin formed by the glass fibre composite sheet were optimized to make the skin deformation smooth.A geared fivebar kinematic mechanism rigidly connected to the skin was proposed to drive the leading-edge ***,a new kind of concentrated flexure hinge was designed using the pseudorigid-body method and applied to the joint between the rigid mechanism and the ***,the leading-edge prototypes with traditional hinges and flexure hinges were produced,*** feasibility of the concentrated flexibility leading-edge was verified through the comparative experiments of ground ***,aerodynamic analysis was carried out to compare the concentrated flexure leading-edge wing with the original airfoil.

关键词： Aircraft Concentrated flexure hinge Leading-edge morphing wing Pseudo-rigid-body model

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Optimization and design of an aircraft's morphing wing-tip demonstrator for drag reduction at low speed, Part Ⅰ–Aerodynamic optimization using genetic, bee colony and gradient descent algorithms

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Chinese Journal of Aeronautics 2017年第1期30卷 149-163页

作者： Andreea Koreanschi Oliviu Sugar Gabor Joran Acotto Guillaume Brianchon Gregoire Portier Ruxandra Mihaela Botez Mahmoud Mamou Youssef Mebarki LARCASE Laboratory of Applied Research in Active Control Avionics and Aeroservoelasticity Ecole de Technologie Superieure Montreal H3C1K3 Canada Aerodynamics Laboratory NRC Aerospace National Research Council Canada Ottawa K1A0R6 Canada

In this paper, an ‘in-house＇ genetic algorithm is described and applied to an optimization problem for improving the aerodynamic performances of an aircraft wing tip through upper surface morphing. The algorithm＇s performances were studied from the convergence point of view, in accordance with design conditions. The algorithm was compared to two other optimization methods,namely the artificial bee colony and a gradient method, for two optimization objectives, and the results of the optimizations with each of the three methods were plotted on response surfaces obtained with the Monte Carlo method, to show that they were situated in the global optimum region. The optimization results for 16 wind tunnel test cases and 2 objective functions were presented. The 16 cases used for the optimizations were included in the experimental test plan for the morphing wing-tip demonstrator, and the results obtained using the displacements given by the optimizations were evaluated.

关键词： Artificial bee colony Airfoil optimization Genetic algorithm morphing wing Optimization

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Proportional fuzzy feed-forward architecture control validation by wind tunnel tests of a morphing wing

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Chinese Journal of Aeronautics 2017年第2期30卷 561-576页

作者： Michel Joёl Tchatchueng Kammegne Ruxandra Mihaela Botez Lucian Teodor Grigorie Mahmoud Mamou Youssef Mebarki Ecole de Technologie Superieure Montreal H3C1K3 Canada University of Craiova Craiova Dolj 200585 Romania Aerodynamics Laboratory NRC Aerospace National Research Council Canada Ottawa K1AOR6 Canada

In aircraft wing design,engineers aim to provide the best possible aerodynamic performance under cruise flight conditions in terms of lift-to-drag *** control surfaces such as flaps,ailerons,variable wing sweep and spoilers are used to trim the aircraft for other flight *** appearance of the morphing wing concept launched a new challenge in the area of overall wing and aircraft performance improvement during different flight segments by locally altering the flow over the aircraft＇s *** paper describes the development and application of a control system for an actuation mechanism integrated in a new morphing wing *** controlled actuation system includes four similar miniature electromechanical actuators disposed in two parallel actuation *** experimental model of the morphing wing is based on a full-scale portion of an aircraft wing,which is equipped with an *** upper surface of the wing is a flexible one,being closed to the wing tip;the flexible skin is made of light composite *** four actuators are controlled in unison to change the flexible upper surface to improve the flow quality on the upper surface by delaying or advancing the transition point from laminar to turbulent *** actuators transform the torque into vertical *** bases are fixed on the wing ribs and their top link arms are attached to supporting plates fixed onto the flexible skin with *** actuators push or pull the flexible skin using the necessary torque until the desired vertical displacement of each actuator is *** four vertical displacements of the actuators,correlated with the new shape of the wing,are provided by a database obtained through a preliminary aerodynamic optimization for specific flight *** control system is designed to control the positions of the actuators in real time in order to obtain and to maintain the desired shape of the wing for a specified flight *** feas

关键词： Actuators Control Experimental validation morphing wing Wind tunnel test

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Integrated optimization design of smart morphing wing for accurate shape control

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Chinese Journal of Aeronautics 2021年第1期34卷 135-147页

作者： Xiaojun GU Kaike YANG Manqiao WU Yahui ZHANG Jihong ZHU Weihong ZHANG Unmanned System Research Institute Northwestern Polytechnical UniversityXi'an 710072China State IJR Center of Aerospace Design and Additive Manufacturing Northwestern Poly technical UniversityXi'an 710072China Science and Technology on Space Physics Laboratory China Academy of Launch Vehicle TechnologyBeijing 100076China

Smart morphing wing, which is equipped with smart materials and able to change structural geometry adaptively, can further improve aerodynamic efficiency of aircraft. This paper presents a new integrated layout and topology optimization design for morphing wing driven by shape memory alloys(SMAs). By simultaneously optimizing the layout of smart actuators and topology of wing substrate, the ultimately determined configuration can achieve smooth, continuous and accurate geometric shape changes. In addition, aerodynamic analysis is carried out to compare smart morphing wing with traditional hinged airfoil. Finally, the optimized smart wing structure is constructed and tested to demonstrate and verify the morphing functionality. Application setbacks are also pointed out for further investigation.

关键词： Layout optimization morphing wing Shape memory alloy Shape morphing Topology optimization

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Modeling and Experiment of a morphing wing Integrated with a Trailing Edge Control Actuation System

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Chinese Journal of Mechanical Engineering 2012年第2期25卷 248-254页

作者： HE Yuanyuan GUO Shijun School of Aerospace Engineering Beijing Institute of TechnologyBeijing10081China Department of Aerospace Engineering School of EngineeringCranfield UniversityMK430ALUK

morphing wing has attracted many research attention and effort in aircraft technology development because of its advantage in lift to draft ratio and flight *** wing technology combines the lift and control surfaces into a seamless wing and integrates the primary structure together with the internal control *** makes use of the wing aeroelastic deformation induced by the control surface to gain direct force control through desirable redistribution of aerodynamic *** some unknown mechanical parameters of the control system and complexity of the integrated structure become a main challenge for dynamic modeling of morphing *** solve the problem,a method of test data based modal sensitivity analysis is presented to improve the morphing wing FE model by evaluating the unknown parameters and identifying the modeling boundary *** innovative seamless morphing wing with the structure integrated with a flexible trailing edge control system is presented for the *** experimental model of actuation system driven by a servo motor for the morphing wing is designed and *** performing a vibration test and the proposed modal sensitivity analysis,the unknown torsional stiffness of the servo motor and the boundary condition of the actuation mechanism model is identified and *** with the test data,the average error of the first four modal frequency of the improved FE model is reduced significantly to less than 4%.To further investigate the morphing wing modeling,a wing box and then a whole morphing wing model including the skin and integrated with the trailing edge actuation system are established and *** using the proposed method,the FE model is improved by relaxing the constraint between the skin and actuation *** results show that the average error of the first three modal frequency of the improved FE model is reduced to less than 6%.The research results demonstrate that the presen

关键词： morphing wing seamless trailing edge control surface actuation system modeling and vibration test

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

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Chinese Journal of Aeronautics 2020年第4期33卷 1272-1287页

作者： Teodor Lucian GRIGORIE Shehryar KHAN Ruxandra Mihaela BOTEZ Mahmoud MAMOU Youssef MéBARKI ETS Laboratory of Active ControlsAvionics and AeroServoElasticity LARCASEMontreal H3C-1K3QuebecCanada Military Technical Academy"Ferdinand I" Bucharest 040531Romania Aerodynamics Laboratory NRC AerospaceNational Research Council CanadaOttawa K1A0R6OntarioCanada

The paper deals with the design and experimental validation of the actuation mechanism control system for a morphing wing *** experimental morphable wing model manufactured in this project is a full-size scale wing tip for a real aircraft equipped with an *** morphing actuation of the model is based on a mechanism with four similar in house designed and manufactured actuators,positioned inside the wing on two parallel *** of the four actuators used a BrushLess Direct Current(BLDC)electric motor integrated with a mechanical part performing the conversion of the angular displacements into linear *** following have been chosen as successive steps in the design of the actuator control system:(A)Mathematical and software modelling of the actuator;(B)Design of the control system architecture and tuning using Internal Model Control(IMC)methodology;(C)Numerical simulation of the controlled actuator and its testing on bench and wind *** morphing wing experimental model is tested both at the laboratory level,with no airflow,to evaluate the components integration and the whole system functioning,but also in the wind tunnel,in the presence of airflow,to evaluate its behavior and the aerodynamic gain.

关键词： BLDC motor Control tuning morphing wing Simulation and experimental testing Wind tunnel

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Constrained cooperative control design for distributed morphing wing systems

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Journal of Systems Engineering and Electronics 2012年第4期23卷 588-595页

作者： Zhen He Yuping Lu College of Automation Engineering Nanjing University of Aeronautics and AstronauticsNanjing 210016P.R.China

An efficient design method is proposed for the cooperative control problem of morphing wing systems with distributed structures and bounded control inputs. The multi-agent model of the distributed morphing wing system is established. The cooperative controllers with saturation constraints are presented. By introducing the concepts in consensus algorithms, the cooperative information links in the controllers are described by graphs, and the corresponding Laplacian matrix is defined. The design conditions of the cooperative controllers are proposed, in the form of linear matrix inequalities. For the case of undirected information links, the controller design conditions are simplified as algebraic inequalities, which highly reduce the computation cost. The designed controllers are implemented on a distributed morphing wing platform, and experiments are carried out. Simulation and experiment results show that the controllers can make all the actuating units in the morphing wing system cooperatively achieve the desired positions, which demonstrates the effectiveness of the proposed theory.

关键词： morphing wing cooperative control saturation con-straints consensus algorithm.

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Tensile Deformation Properties of Corrugated Style Fiber Reinforced Composite Skin for a morphing wing

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International Journal of Plant Engineering and Management 2011年第1期16卷 41-46页

作者： ZHOU Chun-hua WANG Bang-feng LIU Zhao MOU Chang-wei College of Civil Aviation Nanjing University of Aeronautics and Astronautics Nanjing 210016 P. R. China

A type of skin structure which is made by a Circular Arc Corrugated Style Fiber Reinforced Composite （CACSFRC） is proposed to meet the requirements of the large and continuous deformation and high load capacity of a morphing wing skin. A mechanical model is developed to predict the tensile deformation properties and equiva- lent elastic modulus of the composite skin. Corrugated and plane skin samples are manufactured and tested. The theoretical analysis and tension tests show that CCSFRC skin has markedly much more tensile deforming capability than plane skin in the range of elasticity. The quantity of tensile deformation is in direct proportion to the number of ripples, and in inverse proportion to the cubic of ratio thickness, while the equivalent elastic modulus is in direct proportion to the cubic of ratio thickness approximately. Experiments prove that the predicted theoretical models are reliable and effective.

关键词： morphing wing skin composite mechanics analysis

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