Smart Morphing and Sensing for Aeronautical Configurations: Prototypes, Experimental and Numerical Findings from the H2020 N° 723402 SMS EU Project

Description

This book reports on advanced strategies to design, modeling and testing morphing wings for aeronautical applications. Covering the major outcomes of the multidisciplinary project “Smart Morphing & Sensing” (H2020 N° 723402 SMS), funded by the European Union between 2017 and 2020, it presents a complete set of theories and methods that have been used and developed to integrate novel electroactive actuators and sensors in wings, for the purpose of increasing their aerodynamic efficiency and attenuate vibrations and noise. Topics include: integrated aeroelastic design of morphing wings using high-fidelity computational fluid dynamics and structural mechanics, distributed sensing using a new generation of high-fidelity fiber optics sensors, and controller design by appropriate flight control commands. Further, the book reports on advanced experimental techniques to validate novel actuation and sensing systems on the built prototypes via wind tunnel tests at subsonic (take-off and landing) and transonic (cruise) speeds. All in all, this volume provides readers with extensive and timely information on research and developments of bioinspired aircraft wings. Preface Acknowledgements Contents 1 The SMS Project: Introduction and Overview 1.1 Objectives 1.2 The SMS Structure and Methodology 1.3 Affiliation List 1.4 Summary of the Project Results References 2 Reduced Scale Prototype Morphing Achievements in Subsonic and Transonic Regimes 2.1 Model Specifications 2.2 Higher Frequency-Lower Amplitude Trailing Edge Vibrations 2.3 RS Prototype B: Transonic Reduced Scale (tRS) Design 2.3.1 Final Geometry of the Test Section 2.3.2 Experimental Verification and Proof of the Morphing/Sensing Efficiency-sRS References 3 Large Scale Morphing Prototype: Design and Experiments 3.1 Optimal Design of the Electromechanical Actuators (EMA) System 3.1.1 Electromechanical Actuator System 3.1.2 Electromechanical Actuator Design 3.2 Sensing System 3.2.1 Theory 3.2.2 Fiber Bragg Grating (FBG) Sensor Technology 3.2.3 Experimental Set-Up 3.2.4 Reynolds Number Variation 3.2.5 Angle of Attack Variation 3.2.6 Synthesis 3.2.7 Comparison of the Results with the Numerical Simulations 3.2.8 Multi-point Sensing 3.2.9 Conclusion—Sensing System 3.3 Controller Hardware Construction 3.3.1 Large-Scale—Controller Interface (iF) 3.3.2 Conclusion—Hardware Controller and Interface 3.4 Experimental Verification—INPT/IMFT-LAPLACE 3.4.1 Mean Pressure Measurements 3.4.2 Unsteady Pressure Measurements 3.4.3 Conclusion—Experimental Verification References 4 High-Fidelity Numerical Simulations 4.1 Morphing sRS Prototype—Numerical Simulations 4.2 Three-Dimensional Morphing Effects 4.3 Performances of the Hybrid Morphing: Cambering + Actuation 4.4 Structural Modelling of the sRS with Embedded SMA (Shape Memory Alloys) 4.4.1 Structural Control of the Wing Equipped with SMA Actuators 4.5 MDO (Multi-disciplinary Design Optimisation) Results Incorporating Experimental Results and High-Fidelity CFD Simulations 4.5.1 Introduction 4.5.2 Scientific and Technological Background 4.5.3 Investigation of the Reduced Scale (RS) Prototype—RSP 4.5.4 Investigation of the Large-Scale (LS) Prototype—LSP 4.5.5 Conclusions—MDO 4.6 Hi-Fi Simulations on the tRS Prototype (INPT) 4.7 Hi-Fi Simulations on the Large Scale (LS) Prototype 4.7.1 Take-off Configuration 4.7.2 Landing Configuration 4.7.3 Aerodynamic Performance by Hi-Fi Simulations Around the Full A320 Aircraft 4.7.4 Hybrid Morphing—Full Aircraft, Landing—CFSE 4.8 Aircraft Trajectories, Polars and Fuel Consumption 4.8.1 Introduction 4.8.2 Defining Relevant Conditions for Fluid Dynamics Computations 4.8.3 Identifying Polar Models from Results of Fluid Dynamics Computations 4.8.4 Extrapolating to Aircraft Performance 4.8.5 Computing Benefit in Fuel Consumption 4.8.6 Conclusion on Fuel Consumption Evaluation Through Aircraft Trajectories 4.9 Conclusions References 5 Aerodynamic Evaluation 5.1 TRS Prototype Aerodynamic Evaluation 5.1.1 Transonic Reduced Scale Profile—Reference Case 5.1.2 Transonic Reduced Scale Profile with Flapping Trailing Edge 5.1.3 Conclusions for the Transonic Prototype tRS 5.2 Large Scale Cambered Prototype Design and Experimental Evaluation 5.2.1 Overview and Specifications 5.2.2 Problem Description 5.2.3 Design and Construction of the Wing Model 5.3 GVPM Wind Tunnel 5.4 CAD Drawings for the High-Lift Flap 5.4.1 Morphing Wing Concept 5.5 Interface Definition and Camber Control of the High-Lift Flap 5.5.1 Modelling of the System and Feedback Control Design 5.5.2 Camber Control 5.6 Model Specifications and Preliminary Investigation in a Scaled Wind Tunnel (1:9 Scale) 5.6.1 The Model 5.6.2 Test-Matrix 5.6.3 Test Rig, Instrumentation and Sensor Layout 5.6.4 PIV Set-Up 5.6.5 Shape-Measurement Set-Up 5.6.6 Results 5.6.7 PIV Campaign Results 5.6.8 Shape-Measurement Results 5.7 Data Sharing of SMS and Workflows Through Ontology-Based Data Access in the Platform CALMIP/CALLISTO 5.7.1 The Sharing of Data for SMS 5.7.2 Ontology-Based Data Description and Workflow Execution 5.7.3 Practical Use of CALLISTO for SMS and Data Reusability 5.7.4 Conclusions on the Data Sharing Access 5.8 Conclusions References 6 General Conclusions 6.1 Obtained Benefits and Conclusion Summary 6.2 Impact: Communication and Dissemination of the Results