Presentation of my PhD work about a preliminary design tool for flapping-wing systems. The presentation is about the definition/implementation of an aeroelastic framework that coupled an aerodynamic model of insect flight with a FEM solver, its numerical and experimental validation for preliminary design tasks and finally about its applications to the specific case of a resonant nano-air vehicle: the OVMI. Thus the designers can evaluate quickly the performance of a wing and then determine a wing geometry via an optimization environment. Enjoy!
Complex Oxide Based Resistance RAM(RRAM)_Thesis Defense_2012Gurudatt Rao
PCMO is a p-type semiconducting while exhibiting para-magnetic insulator behavior at room temperature. In this work, PrxCa1-xMnO3(x=3) was investigated in the form of thin films to observe memristor characteristics for memristor behavior by forming MIM capacitors. Also, the of deposition parameters on film morphology and its correlation with overall device performance was ascertained.
ANSYS HFSS has been the mainstay, gold-standard electromagnetic simulation technology for many years. There are many key pieces to its reliable technology — such as hierarchical vector basis functions for robust solutions to Maxwell’s equations, two-dimensional port solving technology, the trans-finite element method for fast extraction of s-parameter models, state-of-the-art fast and scalable matrix solving technology, and its flexible and easy-to-use parametric interfaces. Read More:
This document discusses modeling a hot compression test using finite element analysis in ABAQUS. It describes:
1) Creating parts for the deformable bulk material and rigid press and assembling them, defining materials, contacts, steps, and meshing.
2) Developing a viscoplastic constitutive model and implementing it in ABAQUS through user subroutines UMAT and VUMAT.
3) Running a simulation of hot plain strain compression of copper and comparing results from UMAT and VUMAT.
This document provides an overview of a course on the finite element method. The course objectives are for students to learn how to write simple programs to solve problems using FEM. Assessment includes assignments, quizzes, a course project, midterm exam, and final exam. Fundamental agreements include electronic homework submission and using MATLAB or Mathematica. References on FEM are also provided. The document outlines numerical methods for solving boundary value problems and introduces weighted residual methods like the collocation method, subdomain method, and Galerkin method.
The document discusses the benefits of exercise for both physical and mental health. It notes that regular exercise can reduce the risk of diseases like heart disease and diabetes, improve mood, and reduce feelings of stress and anxiety. The document recommends that adults get at least 150 minutes of moderate exercise or 75 minutes of vigorous exercise per week to gain these benefits.
The document discusses the benefits of exercise for mental health. Regular physical activity can help reduce anxiety and depression and improve mood and cognitive functioning. Exercise causes chemical changes in the brain that may help boost feelings of calmness, happiness and focus.
Complex Oxide Based Resistance RAM(RRAM)_Thesis Defense_2012Gurudatt Rao
PCMO is a p-type semiconducting while exhibiting para-magnetic insulator behavior at room temperature. In this work, PrxCa1-xMnO3(x=3) was investigated in the form of thin films to observe memristor characteristics for memristor behavior by forming MIM capacitors. Also, the of deposition parameters on film morphology and its correlation with overall device performance was ascertained.
ANSYS HFSS has been the mainstay, gold-standard electromagnetic simulation technology for many years. There are many key pieces to its reliable technology — such as hierarchical vector basis functions for robust solutions to Maxwell’s equations, two-dimensional port solving technology, the trans-finite element method for fast extraction of s-parameter models, state-of-the-art fast and scalable matrix solving technology, and its flexible and easy-to-use parametric interfaces. Read More:
This document discusses modeling a hot compression test using finite element analysis in ABAQUS. It describes:
1) Creating parts for the deformable bulk material and rigid press and assembling them, defining materials, contacts, steps, and meshing.
2) Developing a viscoplastic constitutive model and implementing it in ABAQUS through user subroutines UMAT and VUMAT.
3) Running a simulation of hot plain strain compression of copper and comparing results from UMAT and VUMAT.
This document provides an overview of a course on the finite element method. The course objectives are for students to learn how to write simple programs to solve problems using FEM. Assessment includes assignments, quizzes, a course project, midterm exam, and final exam. Fundamental agreements include electronic homework submission and using MATLAB or Mathematica. References on FEM are also provided. The document outlines numerical methods for solving boundary value problems and introduces weighted residual methods like the collocation method, subdomain method, and Galerkin method.
The document discusses the benefits of exercise for both physical and mental health. It notes that regular exercise can reduce the risk of diseases like heart disease and diabetes, improve mood, and reduce feelings of stress and anxiety. The document recommends that adults get at least 150 minutes of moderate exercise or 75 minutes of vigorous exercise per week to gain these benefits.
The document discusses the benefits of exercise for mental health. Regular physical activity can help reduce anxiety and depression and improve mood and cognitive functioning. Exercise causes chemical changes in the brain that may help boost feelings of calmness, happiness and focus.
In this paper three different cut patterns of brake disc are studied for heat transfer rate. Heat transfer rate increases with number of cuts in the disc. This is because large area is exposed to air which makes more heat transfer through conduction and convection. But increase in number and size of cuts decreases the strength of disc. And analysed thermally in ANSYS for different material and design created in CREO 3.0.
A study on DOE of tubular rear axle twist beam using HyperStudyAltair
In terms of the compliance with new legal requirements and reduction of greenhouse gas effect , automotive industry focuses on weight reduction of vehicle components. Furthermore, manufacturers studies on new concept designs, processes and new generation materials without compromising the safety of the vehicle components. The optimization tools take up significant place in the automotive industry to analyze feasibility of parts quickly due to competitive market requirements. Furthermore, Hyperstudy offers a solution for rapid DOE opportunity in the product development cycle, minimizing optimization challenges and also costs.
In this study, DOE methodology is used in order to optimize tubular rear axle twist beam which meets forces from ground to car body and belongs to semi-independent suspension system by using Hyperstudy.
Speakers
Metin Çalli, FEA Responsible, COSKUNOZ A.S. R&D Department
This document provides an overview of a course on engineering design and rapid prototyping. It discusses the finite element method (FEM) which will be covered in class. FEM involves cutting a structure into small elements and connecting them at nodes to form algebraic equations that can be solved numerically. This allows for approximate solutions to complex problems. The document outlines the typical FEM procedure of preprocessing, analysis, and postprocessing using software. It also discusses sources of errors in the FEM approach and mistakes users may make.
This document describes a simplified SPICE model for simulating DC motors. It includes 10 sections that describe: 1) the benefits of the model, 2) the model features, 3) how to set the model parameters, 4) an example motor specification, 5) simulating motor start up at normal load, 6) simulating start up at half load, 7) how the motor inductance Lj affects simulations, 8) an application example circuit, 9) how the motor inductance Lm affects simulations, and 10) how the motor resistance Rm affects simulations. The document also provides an index of simulation examples.
ADAMS is an automatic dynamic analysis software for multibody systems created by MSC Software. It is used by over 10,000 companies worldwide, including automakers like Ford, Jaguar, and Land Rover for modeling 3D geometry, motion analysis, and simulations. MSC Software was originally founded to create engineering simulation tools and was acquired by Symphony Technology Group in 2009.
Seminar presentation made by me for the topic of 'Resources for Sentiment Analysis' at IIT Bombay. Includes a set of bonus slides for additional information which was not actually presented.
Second Generation of TSMC’s Integrated Fan-Out (inFO) Packaging for the Apple...system_plus
The latest Apple application processor engine : from the stacked board to the A11, and reverse costing of TSMC's updated inFO packaging
More information on that report at http://www.systemplus.fr/reverse-costing-reports/second-generation-of-tsmcs-integrated-fan-out-info-packaging-for-the-apple-a11-found-in-the-iphone-x/
- The document provides a full reverse costing analysis of the Transphorm TPH3206PS 600V GaN-on-silicon HEMT power transistor.
- The analysis includes detailed photos and SEM analysis of the epitaxial layers and transistor structure, as well as an examination of the Quiet-Tab packaging.
- The manufacturing process flows for the GaN HEMT, resistor, MOSFET, and packaging are presented, along with an in-depth cost breakdown analysis.
- Estimates of the manufacturing cost and suggested manufacturer price are provided, and comparisons are made to Transphorm's TPH3002 and GaN Systems' GS66504B.
This document discusses subsonic flow analysis of a tailless aircraft using computational fluid dynamics (CFD). It begins with an introduction to tailless aircraft design and blended wing body (BWB) concepts. It then provides an overview of CFD, the software tools CATIA, Hypermesh, and Fluent that will be used in the analysis. The document outlines the methodology that will be followed, including designing the aircraft models in CATIA, meshing in Hypermesh, and performing CFD simulations and analysis in Fluent. It concludes that the results and discussion will provide comparisons of aerodynamic characteristics like lift, drag, pressure and velocity distributions between the tailless BWB design and a conventional aircraft design.
The document discusses graphs and their representations. It begins with definitions of simple graphs, directed graphs, and graph terminology such as vertices, edges, degrees, and adjacency. It then covers special graphs like complete graphs, cycles, wheels, and bipartite graphs. The document also discusses operations on graphs like unions and subgraphs. Finally, it introduces ways to represent graphs using adjacency matrices and incidence matrices.
This document is the main project report for a 2D robotic plotter (CNC model) created by four students at the Government Engineering College Idukki. It describes the hardware and software used to build a 2D robotic plotter controlled by an Arduino microcontroller. The plotter uses stepper motors for the X and Y axes and a servo motor to control the pen. Software like Inkscape, CAMotics, Arduino IDE and Processing were used to design drawings, generate gcode files, and program the Arduino. The report provides details of the various components, software programs, and overall design and functioning of the 2D robotic plotter built as part of fulfilling B.Tech degree requirements.
Qorvo QPF4006 39GHz GaN MMIC Front End Modulesystem_plus
The first MMIC FEM targeting 5G base stations and terminals using a 0.15µm GaN-on-SiC process.
More information on that report at: https://www.systemplus.fr/reverse-costing-reports/qorvo-qpf4006-39ghz-gan-mmic-front-end-module/
This document provides an overview of finite element analysis using Abaqus. It discusses the basics of Abaqus including preprocessing with Abaqus/CAE, solving models with Abaqus/Standard, and postprocessing output files. It also describes the various components and steps involved in building an Abaqus model including geometry creation, material properties, meshing, boundary conditions, loads, and running an analysis job. An example is presented demonstrating how to model an overhead hoist frame.
This document provides guidance on failure mode and effects analyses (FMEAs) for the marine industry. It discusses what an FMEA is, its objectives, and when they are carried out. FMEAs are used to identify potential failure modes and their effects on systems to improve safety. They follow standards from classification societies. The document outlines the FMEA process, including defining the system boundaries, identifying failure modes and detection/correction methods. It provides information on vessel audits, testing, and incorporating additional analyses like criticality and risk assessments to strengthen FMEAs. The goal is to identify unacceptable failure modes and ensure corrective actions are implemented to improve safety.
Introduction to NX Nastran SOL 200 - Design OptimizationAswin John
In this webinar, Dr. David Cross will demonstrate how to setup and post-process a Nastran Design Optimization (SOL 200) analysis in Femap. In the first example, plate thicknesses of a stiffened rectangular plate will be optimized for mass minimization subject to displacement and stress constraints. The second example will demonstrate optimization of the rib and skin thicknesses of a wing model for multiple load cases. General modeling guidelines and tips for design optimization in Femap and NX Nastran will be discussed through the webinar.
A Report The Alleged Seelampur Communal Riotssabrangsabrang
The document discusses the benefits of exercise for mental health. Regular physical activity can help reduce anxiety and depression and improve mood and cognitive function. Exercise causes chemical changes in the brain that may help protect against mental illness and improve symptoms for those who already suffer from conditions like depression and anxiety.
Mems and sensors packaging technology and trends presentation held by Amandin...Yole Developpement
MEMS & sensors transitioning towards 3 main Hubs…
The inertial hub
Examples of MEMS companies with a «sensors integration» road (e.g., mCubewith iGyro, Spectral Engines with integrated spectrometer, Bosch with environmental combo sensors, AMS with optical combos, InvenSense with IMUs ….
This document summarizes the design and results of a test rig to measure lift force generated by flapping wings. Numerical modeling was used to predict lift values based on wing geometry and motion parameters like frequency and angle of attack. An experimental test rig was designed and built with servo motors in the wings to control twisting instead of relying on flexibility. Force measurements from the rig were taken using a load cell as frequency and angle of attack were varied. Results showed that increasing frequency and angle of attack both increased lift force as expected based on the numerical predictions. The document provides context on bio-inspired flight and reviews other flapping wing projects to inform the design of the test rig.
This was my final year project thesis, based on the results from NASA Langley Research Centre’s work on the PRANDTL-D project which was into minimizing the induced drag of a wing body along with elimination of adverse yaw.
In this paper three different cut patterns of brake disc are studied for heat transfer rate. Heat transfer rate increases with number of cuts in the disc. This is because large area is exposed to air which makes more heat transfer through conduction and convection. But increase in number and size of cuts decreases the strength of disc. And analysed thermally in ANSYS for different material and design created in CREO 3.0.
A study on DOE of tubular rear axle twist beam using HyperStudyAltair
In terms of the compliance with new legal requirements and reduction of greenhouse gas effect , automotive industry focuses on weight reduction of vehicle components. Furthermore, manufacturers studies on new concept designs, processes and new generation materials without compromising the safety of the vehicle components. The optimization tools take up significant place in the automotive industry to analyze feasibility of parts quickly due to competitive market requirements. Furthermore, Hyperstudy offers a solution for rapid DOE opportunity in the product development cycle, minimizing optimization challenges and also costs.
In this study, DOE methodology is used in order to optimize tubular rear axle twist beam which meets forces from ground to car body and belongs to semi-independent suspension system by using Hyperstudy.
Speakers
Metin Çalli, FEA Responsible, COSKUNOZ A.S. R&D Department
This document provides an overview of a course on engineering design and rapid prototyping. It discusses the finite element method (FEM) which will be covered in class. FEM involves cutting a structure into small elements and connecting them at nodes to form algebraic equations that can be solved numerically. This allows for approximate solutions to complex problems. The document outlines the typical FEM procedure of preprocessing, analysis, and postprocessing using software. It also discusses sources of errors in the FEM approach and mistakes users may make.
This document describes a simplified SPICE model for simulating DC motors. It includes 10 sections that describe: 1) the benefits of the model, 2) the model features, 3) how to set the model parameters, 4) an example motor specification, 5) simulating motor start up at normal load, 6) simulating start up at half load, 7) how the motor inductance Lj affects simulations, 8) an application example circuit, 9) how the motor inductance Lm affects simulations, and 10) how the motor resistance Rm affects simulations. The document also provides an index of simulation examples.
ADAMS is an automatic dynamic analysis software for multibody systems created by MSC Software. It is used by over 10,000 companies worldwide, including automakers like Ford, Jaguar, and Land Rover for modeling 3D geometry, motion analysis, and simulations. MSC Software was originally founded to create engineering simulation tools and was acquired by Symphony Technology Group in 2009.
Seminar presentation made by me for the topic of 'Resources for Sentiment Analysis' at IIT Bombay. Includes a set of bonus slides for additional information which was not actually presented.
Second Generation of TSMC’s Integrated Fan-Out (inFO) Packaging for the Apple...system_plus
The latest Apple application processor engine : from the stacked board to the A11, and reverse costing of TSMC's updated inFO packaging
More information on that report at http://www.systemplus.fr/reverse-costing-reports/second-generation-of-tsmcs-integrated-fan-out-info-packaging-for-the-apple-a11-found-in-the-iphone-x/
- The document provides a full reverse costing analysis of the Transphorm TPH3206PS 600V GaN-on-silicon HEMT power transistor.
- The analysis includes detailed photos and SEM analysis of the epitaxial layers and transistor structure, as well as an examination of the Quiet-Tab packaging.
- The manufacturing process flows for the GaN HEMT, resistor, MOSFET, and packaging are presented, along with an in-depth cost breakdown analysis.
- Estimates of the manufacturing cost and suggested manufacturer price are provided, and comparisons are made to Transphorm's TPH3002 and GaN Systems' GS66504B.
This document discusses subsonic flow analysis of a tailless aircraft using computational fluid dynamics (CFD). It begins with an introduction to tailless aircraft design and blended wing body (BWB) concepts. It then provides an overview of CFD, the software tools CATIA, Hypermesh, and Fluent that will be used in the analysis. The document outlines the methodology that will be followed, including designing the aircraft models in CATIA, meshing in Hypermesh, and performing CFD simulations and analysis in Fluent. It concludes that the results and discussion will provide comparisons of aerodynamic characteristics like lift, drag, pressure and velocity distributions between the tailless BWB design and a conventional aircraft design.
The document discusses graphs and their representations. It begins with definitions of simple graphs, directed graphs, and graph terminology such as vertices, edges, degrees, and adjacency. It then covers special graphs like complete graphs, cycles, wheels, and bipartite graphs. The document also discusses operations on graphs like unions and subgraphs. Finally, it introduces ways to represent graphs using adjacency matrices and incidence matrices.
This document is the main project report for a 2D robotic plotter (CNC model) created by four students at the Government Engineering College Idukki. It describes the hardware and software used to build a 2D robotic plotter controlled by an Arduino microcontroller. The plotter uses stepper motors for the X and Y axes and a servo motor to control the pen. Software like Inkscape, CAMotics, Arduino IDE and Processing were used to design drawings, generate gcode files, and program the Arduino. The report provides details of the various components, software programs, and overall design and functioning of the 2D robotic plotter built as part of fulfilling B.Tech degree requirements.
Qorvo QPF4006 39GHz GaN MMIC Front End Modulesystem_plus
The first MMIC FEM targeting 5G base stations and terminals using a 0.15µm GaN-on-SiC process.
More information on that report at: https://www.systemplus.fr/reverse-costing-reports/qorvo-qpf4006-39ghz-gan-mmic-front-end-module/
This document provides an overview of finite element analysis using Abaqus. It discusses the basics of Abaqus including preprocessing with Abaqus/CAE, solving models with Abaqus/Standard, and postprocessing output files. It also describes the various components and steps involved in building an Abaqus model including geometry creation, material properties, meshing, boundary conditions, loads, and running an analysis job. An example is presented demonstrating how to model an overhead hoist frame.
This document provides guidance on failure mode and effects analyses (FMEAs) for the marine industry. It discusses what an FMEA is, its objectives, and when they are carried out. FMEAs are used to identify potential failure modes and their effects on systems to improve safety. They follow standards from classification societies. The document outlines the FMEA process, including defining the system boundaries, identifying failure modes and detection/correction methods. It provides information on vessel audits, testing, and incorporating additional analyses like criticality and risk assessments to strengthen FMEAs. The goal is to identify unacceptable failure modes and ensure corrective actions are implemented to improve safety.
Introduction to NX Nastran SOL 200 - Design OptimizationAswin John
In this webinar, Dr. David Cross will demonstrate how to setup and post-process a Nastran Design Optimization (SOL 200) analysis in Femap. In the first example, plate thicknesses of a stiffened rectangular plate will be optimized for mass minimization subject to displacement and stress constraints. The second example will demonstrate optimization of the rib and skin thicknesses of a wing model for multiple load cases. General modeling guidelines and tips for design optimization in Femap and NX Nastran will be discussed through the webinar.
A Report The Alleged Seelampur Communal Riotssabrangsabrang
The document discusses the benefits of exercise for mental health. Regular physical activity can help reduce anxiety and depression and improve mood and cognitive function. Exercise causes chemical changes in the brain that may help protect against mental illness and improve symptoms for those who already suffer from conditions like depression and anxiety.
Mems and sensors packaging technology and trends presentation held by Amandin...Yole Developpement
MEMS & sensors transitioning towards 3 main Hubs…
The inertial hub
Examples of MEMS companies with a «sensors integration» road (e.g., mCubewith iGyro, Spectral Engines with integrated spectrometer, Bosch with environmental combo sensors, AMS with optical combos, InvenSense with IMUs ….
This document summarizes the design and results of a test rig to measure lift force generated by flapping wings. Numerical modeling was used to predict lift values based on wing geometry and motion parameters like frequency and angle of attack. An experimental test rig was designed and built with servo motors in the wings to control twisting instead of relying on flexibility. Force measurements from the rig were taken using a load cell as frequency and angle of attack were varied. Results showed that increasing frequency and angle of attack both increased lift force as expected based on the numerical predictions. The document provides context on bio-inspired flight and reviews other flapping wing projects to inform the design of the test rig.
This was my final year project thesis, based on the results from NASA Langley Research Centre’s work on the PRANDTL-D project which was into minimizing the induced drag of a wing body along with elimination of adverse yaw.
Design and Computational Fluid Dynamic Analysis of Spiroid Winglet to Study i...IRJET Journal
This document describes a study on the design and computational fluid dynamic (CFD) analysis of a spiroid winglet to analyze its effects on aircraft performance. Spiroid winglets are bio-inspired wingtip devices that can reduce lift-induced drag. The study involves modifying an existing spiroid winglet design with a 3600 blended wingtip and conducting CFD simulations to evaluate the aerodynamic performance. The CFD analysis is conducted using commercial software Fluent to simulate airflow around the modified spiroid winglet design. Results are compared to an earlier study to validate the CFD methodology. Preliminary results show the modified spiroid winglet design improves aircraft performance by further reducing wingtip vortices and
IRJET- Effects of Dimples on Aerodynamic Performance of Horizontal Axis W...IRJET Journal
This document discusses research into the effects of adding dimples to the surfaces of horizontal axis wind turbine blades. It aims to investigate how dimples impact the aerodynamic performance of wind turbine blades. The researchers used computational fluid dynamics software to simulate flow over a baseline wind turbine blade design with and without various dimple configurations. The simulations found that blades with dimples experienced delayed flow separation, resulting in enhanced aerodynamic performance and increased power extraction compared to the baseline blade without dimples. Validation with experimental wind tunnel testing of a scaled down model supported the numerical results.
Optimisation of the design of uav wing j.alexander, Prakash, BSM Augustinesathyabama
The document discusses the optimization of the design of UAV wings. It analyzes two types of rectangular wings using aerodynamic and structural design methods. Aerodynamic analysis using vortex lattice modeling found lift coefficients for the wings. Structural analysis using CATIA found that using composite materials instead of isotropic materials reduced mass by 34%. The optimum design of each wing maximized strength while minimizing mass and displacement.
Optimisation of the design of uav wing j.alexandersathyabama
The document discusses the optimization of the design of unmanned aerial vehicle (UAV) wings. It analyzes two types of rectangular wings using vortex lattice CFD software to determine aerodynamic loads and CATIA V5 software for structural analysis. When composite materials are used instead of isotropic materials, a 34% mass reduction is achieved. The optimum design is determined for each wing based on minimum mass, stress, and displacement.
1) A prototype twisting wing was developed using shape memory alloy actuators to enable variable wing twist.
2) Benchtop and wind tunnel testing showed that the wing could be twisted up to 10 degrees using a PID controller to precisely control wing twist.
3) Wind tunnel tests measured how lift and drag coefficients varied with angle of attack for different levels of controlled wing twist.
Numerical Simulation Over Flat-Disk Aerospike at Mach 6Abhishek Jain
Above Research Paper can be downloaded from www.zeusnumerix.com
The research paper aims to study the effect of Aerospikes on hypersonic missiles in the reduction of drag and heat flux. Parametric study if the aerospike geometry has been carried out by varying the L/D ratio of the spike. The results have been compared with experimental data at Mach 6. Up to 73.6% decrease in drag is seen at zero angles of attack. The reduction becomes lesser at higher angles of attack. There is a significant increase in pitching moment at an angle of attack and this needs to be further studied. Authors - Vivek Warade (Zeus Numerix), Rahul Pawar and Prof NR Gilke (KJ Somaiya COE)
IRJET- Analysing the Performance of Solar Powered Wing (UAV)IRJET Journal
This document analyzes the performance of a solar-powered wing for an unmanned aerial vehicle (UAV) consisting of two different airfoil sections. Computational fluid dynamics (CFD) software is used to model and analyze wings with the Eppler 421 and Selig 1223 airfoils individually and as a combined wing. Results show that the combined wing profile has lift and drag characteristics between the individual airfoils. Specifically, the Selig 1223 airfoil produces higher lift but also higher drag. The combined wing design and CFD analysis indicate that a solar-powered wing could provide long endurance flights for UAVs.
This document summarizes a computational fluid dynamics (CFD) study comparing the aerodynamic performance of a bio-inspired corrugated dragonfly wing aerofoil to conventional flat plate and NACA airfoils. CFD simulations were conducted at Reynolds numbers of 20,000-100,000 and angles of attack from 0-25 degrees. Results showed that the corrugated aerofoil had improved aerodynamic performance over the other airfoils, with a higher stall angle and increased lift. This is due to the corrugations reducing flow separation. The corrugated aerofoil design could potentially be incorporated into micro air vehicles (MAVs) to enhance their aerodynamic performance.
This document discusses the conceptual design, structural analysis, and flow analysis of an unmanned aerial vehicle (UAV) wing. It begins by providing background on UAVs and listing the design requirements and parameters for the wing. It then describes selecting a rectangular wing planform and NACA 2415 airfoil based on the design criteria. Aerodynamic analysis is conducted to determine performance parameters like lift coefficient and drag. Structural analysis of the wing is performed using two spar designs - a tubular spar with and without a strut. Maximum stresses and bending moments are calculated and compared for straight and tapered wing configurations. Flow simulation will also be conducted on the finalized wing design.
IRJET- Aerodynamic Analysis of Aircraft Wings using CFDIRJET Journal
This document discusses computational fluid dynamics (CFD) analysis of aircraft wings using NACA 4412 airfoils at various angles of attack. The study uses ANSYS software to simulate air flow over the airfoil and calculate lift and drag coefficients. The results show that lift increases with angle of attack up to 25 degrees, at which point lift is highest before drag starts to dominate as the airfoil stalls. Contour plots of pressure and velocity are presented for the airfoil at angles of attack of 0, 8, 16, and 20 degrees. The CFD analysis provides insight into airfoil aerodynamic performance without requiring expensive wind tunnel testing.
IRJET- Aerodynamic Performance Analysis on a Wing with “M” Shaped Serrate...IRJET Journal
1. Researchers analyzed the aerodynamic performance of a wing with an "M" shaped serrated trailing edge using wind tunnel testing.
2. Results showed that the serrated trailing edge design produced up to 25% more lift and 61% less drag compared to a normal wing at certain angles of attack.
3. The maximum improvement in lift-to-drag ratio occurred at an angle of attack of 10 degrees. The study demonstrates that the "M" shaped serrated trailing edge can enhance the aerodynamic performance of wings.
It is a major project report on DIFFERENT TYPES OF WINGLETS AND THEIR CORRESPONDING VORTICES, and it can be helpful for a person looking for specifically about winglet and vortex formation and relation among them. It is a very good source for aerospace engineering student as well coz they will get to knew about vortex and winglet.
A Review of Flight Dynamics and Numerical Analysis of an Unmanned Aerial Vehi...Designage Solutions
A brief study of flight dynamics and different types of simulation and analysis are presented here.
Find case studies in my next PPT.- http://www.slideshare.net/HarshadaGurav/flight-dynamics-and-numerical-analysis-of-an-unmanned-aerial-vehicle-uav
International Journal of Engineering Research and Applications (IJERA) is an open access online peer reviewed international journal that publishes research and review articles in the fields of Computer Science, Neural Networks, Electrical Engineering, Software Engineering, Information Technology, Mechanical Engineering, Chemical Engineering, Plastic Engineering, Food Technology, Textile Engineering, Nano Technology & science, Power Electronics, Electronics & Communication Engineering, Computational mathematics, Image processing, Civil Engineering, Structural Engineering, Environmental Engineering, VLSI Testing & Low Power VLSI Design etc.
This document presents a methodology for performing static structural analysis of fighter aircraft wing spars to identify critical stresses. It involves calculating bending, shear and von mises stresses analytically and numerically under different loading conditions. CAD models of the wing and spars are imported into ANSYS for finite element analysis. Von Mises yield theory is used to identify stresses exceeding the yield limit, which indicate critical stresses and locations. Results from analytical calculations and ANSYS simulations are analyzed to mark stresses exceeding the safety factor of 1.5 as critical. Locations with critical stresses are identified as the attachment points of wing spars.
IRJET- Design and Fabrication of an Open Circuit Subsonic Wind Tunnel for Edu...IRJET Journal
This document describes the design and fabrication of a low-cost subsonic wind tunnel for educational purposes. Key aspects include:
1) The wind tunnel was designed and built by students and a professor to support fluid mechanics experiments at their university on a limited budget.
2) Design considerations included achieving a test section air speed over 10m/s, compact size, ease of use, and longevity.
3) Components like the contraction cone, diffuser, test section, and flow conditioner were designed and fabricated based on guidelines from literature.
4) Experimental testing showed average air speeds in the test section of 12.9m/s, with variations within 1m/s. CFD simulation
A Study of Wind Turbine Blade Power Enhancement Using Aerodynamic Properties IJMER
Technological advancements have improvised them over time. In this paper we shall glance at
the features. Wind energy is the most popular renewable energy. In order to increase the use of wind
energy, it is important to develop wind turbine rotor models with high rotation rates and power
coefficients. These elemental forces are summed along the span of the blade to calculate the total forces
and moments exerted on the turbine. This study aimed at manufacturing highly efficient wind turbine
rotor models using NACA profiles.
Design, Fabrication and Aerodynamic Analysis of RC Powered Aircraft WingIRJET Journal
This document describes the design, fabrication, and aerodynamic analysis of a radio-controlled aircraft wing. The researchers designed a rectangular wing with a Gottingen 526 airfoil profile using computational fluid dynamics software to analyze lift and drag coefficients. The wing structure and control surfaces were fabricated based on the optimal design parameters. Wind tunnel testing was then used to validate the aerodynamic performance and characteristics of the wing.
A tale of scale & speed: How the US Navy is enabling software delivery from l...sonjaschweigert1
Rapid and secure feature delivery is a goal across every application team and every branch of the DoD. The Navy’s DevSecOps platform, Party Barge, has achieved:
- Reduction in onboarding time from 5 weeks to 1 day
- Improved developer experience and productivity through actionable findings and reduction of false positives
- Maintenance of superior security standards and inherent policy enforcement with Authorization to Operate (ATO)
Development teams can ship efficiently and ensure applications are cyber ready for Navy Authorizing Officials (AOs). In this webinar, Sigma Defense and Anchore will give attendees a look behind the scenes and demo secure pipeline automation and security artifacts that speed up application ATO and time to production.
We will cover:
- How to remove silos in DevSecOps
- How to build efficient development pipeline roles and component templates
- How to deliver security artifacts that matter for ATO’s (SBOMs, vulnerability reports, and policy evidence)
- How to streamline operations with automated policy checks on container images
“An Outlook of the Ongoing and Future Relationship between Blockchain Technologies and Process-aware Information Systems.” Invited talk at the joint workshop on Blockchain for Information Systems (BC4IS) and Blockchain for Trusted Data Sharing (B4TDS), co-located with with the 36th International Conference on Advanced Information Systems Engineering (CAiSE), 3 June 2024, Limassol, Cyprus.
Pushing the limits of ePRTC: 100ns holdover for 100 daysAdtran
At WSTS 2024, Alon Stern explored the topic of parametric holdover and explained how recent research findings can be implemented in real-world PNT networks to achieve 100 nanoseconds of accuracy for up to 100 days.
In the rapidly evolving landscape of technologies, XML continues to play a vital role in structuring, storing, and transporting data across diverse systems. The recent advancements in artificial intelligence (AI) present new methodologies for enhancing XML development workflows, introducing efficiency, automation, and intelligent capabilities. This presentation will outline the scope and perspective of utilizing AI in XML development. The potential benefits and the possible pitfalls will be highlighted, providing a balanced view of the subject.
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Generative AI Deep Dive: Advancing from Proof of Concept to ProductionAggregage
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Dr. Sean Tan, Head of Data Science, Changi Airport Group
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In his public lecture, Christian Timmerer provides insights into the fascinating history of video streaming, starting from its humble beginnings before YouTube to the groundbreaking technologies that now dominate platforms like Netflix and ORF ON. Timmerer also presents provocative contributions of his own that have significantly influenced the industry. He concludes by looking at future challenges and invites the audience to join in a discussion.
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Cosa hanno in comune un mattoncino Lego e la backdoor XZ?Speck&Tech
ABSTRACT: A prima vista, un mattoncino Lego e la backdoor XZ potrebbero avere in comune il fatto di essere entrambi blocchi di costruzione, o dipendenze di progetti creativi e software. La realtà è che un mattoncino Lego e il caso della backdoor XZ hanno molto di più di tutto ciò in comune.
Partecipate alla presentazione per immergervi in una storia di interoperabilità, standard e formati aperti, per poi discutere del ruolo importante che i contributori hanno in una comunità open source sostenibile.
BIO: Sostenitrice del software libero e dei formati standard e aperti. È stata un membro attivo dei progetti Fedora e openSUSE e ha co-fondato l'Associazione LibreItalia dove è stata coinvolta in diversi eventi, migrazioni e formazione relativi a LibreOffice. In precedenza ha lavorato a migrazioni e corsi di formazione su LibreOffice per diverse amministrazioni pubbliche e privati. Da gennaio 2020 lavora in SUSE come Software Release Engineer per Uyuni e SUSE Manager e quando non segue la sua passione per i computer e per Geeko coltiva la sua curiosità per l'astronomia (da cui deriva il suo nickname deneb_alpha).
Cosa hanno in comune un mattoncino Lego e la backdoor XZ?
PhD Defense
1. Aeroelastic framework of insect-like
flapping-wing applied to the design of a
resonant NAV
T. Vanneste
July 04, 2013
2. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Flapping-wing vs fixed or rotary wing
Grasmeyer and Keennon [2001] Bitcraze AB [2012]
+ Large operations panel
+ Adequate for outdoor uses
+ Payload
+ Endurance
- Inadequate for confined areas
- Costly stationary flight
- Noise signature
- Inadequate for small wingspan
Flapping-wing is an efficient solution for wingspan below 20cm
T. Vanneste 04/07/2013 2 / 35
3. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Flapping-wing vs fixed or rotary wing
Grasmeyer and Keennon [2001] Bitcraze AB [2012]
+ Large operations panel
+ Adequate for outdoor uses
+ Payload
+ Endurance
- Inadequate for confined areas
- Costly stationary flight
- Noise signature
- Inadequate for small wingspan
Flapping-wing is an efficient solution for wingspan below 20cm
T. Vanneste 04/07/2013 2 / 35
4. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Flapping-wing vs fixed or rotary wing
Grasmeyer and Keennon [2001] Bitcraze AB [2012]
+ Large operations panel
+ Adequate for outdoor uses
+ Payload
+ Endurance
- Inadequate for confined areas
- Costly stationary flight
- Noise signature
- Inadequate for small wingspan
Flapping-wing is an efficient solution for wingspan below 20cm
T. Vanneste 04/07/2013 2 / 35
5. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Flapping-wing problematics
Flexible structure in large
displacement
Low Reynolds aerodynamics
(Re ∼ 10-1000)
Unsteady phenomena:
LEV + wing-wake interaction
All-in-one efficient system
Andrew Mountcastle website
Animal Flight Group website, Oxford university
T. Vanneste 04/07/2013 3 / 35
6. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Current flapping-wing systems
DelFly Micro, TU Delft
Wingspan: ∼ 10cm
Weight: ∼ 3g
Actuator: Electric motor
Articulation: Yes
Hummingbird, AeroVironment Inc.
Wingspan: ∼ 16.5cm
Weight: ∼ 19g
Actuator: Electric motor
Articulation: Yes
T. Vanneste 04/07/2013 4 / 35
7. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Current flapping-wing systems
Robobees, Harvard University
Wingspan: ∼ 3cm
Weight: 80mg
Actuator: Piezoelectric
Articulation: Yes
T. Vanneste 04/07/2013 4 / 35
8. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Current flapping-wing systems
Robobees, Harvard University
Wingspan: ∼ 3cm
Weight: 80mg
Actuator: Piezoelectric
Articulation: Yes
OVMI, IEMN Lille
Wingspan: ∼ 3cm
Weight: ∼ 30mg
Actuator: Electromagnet/EAP
Articulation: No
T. Vanneste 04/07/2013 4 / 35
9. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
OVMI Concept
Actuation on a resonant mode
Mode-shape set to an active bending and passive torsion
Forced oscillations provide maximum amplification for minimum energy
consumption
Safe through any small perturbations
Generated wing kinematics similar to the insect one
T. Vanneste 04/07/2013 5 / 35
10. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
OVMI Concept
Actuation on a resonant mode
Mode-shape set to an active bending and passive torsion
Forced oscillations provide maximum amplification for minimum energy
consumption
Safe through any small perturbations
Generated wing kinematics similar to the insect one
T. Vanneste 04/07/2013 5 / 35
11. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
OVMI Concept
Actuation on a resonant mode
Mode-shape set to an active bending and passive torsion
Forced oscillations provide maximum amplification for minimum energy
consumption
Safe through any small perturbations
Generated wing kinematics similar to the insect one
T. Vanneste 04/07/2013 5 / 35
12. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
OVMI Prototype
Bending Torsion
Needs to better predict the wing behavior towards aerodynamic forces
T. Vanneste 04/07/2013 6 / 35
13. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Requirements for a preliminary design tool
Physics:
Accounting for the wing flexibility
Accounting for flapping-wing aerodynamics
Accounting for the aeroelastic effects
Design:
Accounting for various actuation types and wing geometries
Aimed for an hovering attitude
Implementation:
Rapidity
Robust
Modularity
As suggested by Zbikowski [2002], Combes and Daniel [2003] and Blair,
Parker, Beran, and Snyder [2007]:
FEM solver for structural computation
No CFD for aerodynamic computation
T. Vanneste 04/07/2013 7 / 35
14. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Requirements for a preliminary design tool
Physics:
Accounting for the wing flexibility
Accounting for flapping-wing aerodynamics
Accounting for the aeroelastic effects
Design:
Accounting for various actuation types and wing geometries
Aimed for an hovering attitude
Implementation:
Rapidity
Robust
Modularity
As suggested by Zbikowski [2002], Combes and Daniel [2003] and Blair,
Parker, Beran, and Snyder [2007]:
FEM solver for structural computation
No CFD for aerodynamic computation
T. Vanneste 04/07/2013 7 / 35
15. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Requirements for a preliminary design tool
Physics:
Accounting for the wing flexibility
Accounting for flapping-wing aerodynamics
Accounting for the aeroelastic effects
Design:
Accounting for various actuation types and wing geometries
Aimed for an hovering attitude
Implementation:
Rapidity
Robust
Modularity
As suggested by Zbikowski [2002], Combes and Daniel [2003] and Blair,
Parker, Beran, and Snyder [2007]:
FEM solver for structural computation
No CFD for aerodynamic computation
T. Vanneste 04/07/2013 7 / 35
16. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Requirements for a preliminary design tool
Physics:
Accounting for the wing flexibility
Accounting for flapping-wing aerodynamics
Accounting for the aeroelastic effects
Design:
Accounting for various actuation types and wing geometries
Aimed for an hovering attitude
Implementation:
Rapidity
Robust
Modularity
As suggested by Zbikowski [2002], Combes and Daniel [2003] and Blair,
Parker, Beran, and Snyder [2007]:
FEM solver for structural computation
No CFD for aerodynamic computation
T. Vanneste 04/07/2013 7 / 35
17. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Outline
1 Aerodynamic model:
Define an aerodynamic model compatible with wing flexibility and
preliminary design requirements
2 Aeroelastic framework:
Define and implement an aeroelastic framework compatible with preliminary
design tasks
3 Validation:
Numerical stress-test of the framework capabilities
Generate an experimental database compatible with high-frequency
resonant and flexible wing
Compare numerical prediction with experimental data
4 Applications to the OVMI
Basic assistance to the designer
Advanced assistance to the designer: the wing design
T. Vanneste 04/07/2013 8 / 35
18. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Outline
1 Aerodynamic model:
Define an aerodynamic model compatible with wing flexibility and
preliminary design requirements
2 Aeroelastic framework:
Define and implement an aeroelastic framework compatible with preliminary
design tasks
3 Validation:
Numerical stress-test of the framework capabilities
Generate an experimental database compatible with high-frequency
resonant and flexible wing
Compare numerical prediction with experimental data
4 Applications to the OVMI
Basic assistance to the designer
Advanced assistance to the designer: the wing design
T. Vanneste 04/07/2013 8 / 35
19. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Outline
1 Aerodynamic model:
Define an aerodynamic model compatible with wing flexibility and
preliminary design requirements
2 Aeroelastic framework:
Define and implement an aeroelastic framework compatible with preliminary
design tasks
3 Validation:
Numerical stress-test of the framework capabilities
Generate an experimental database compatible with high-frequency
resonant and flexible wing
Compare numerical prediction with experimental data
4 Applications to the OVMI
Basic assistance to the designer
Advanced assistance to the designer: the wing design
T. Vanneste 04/07/2013 8 / 35
20. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Outline
1 Aerodynamic model:
Define an aerodynamic model compatible with wing flexibility and
preliminary design requirements
2 Aeroelastic framework:
Define and implement an aeroelastic framework compatible with preliminary
design tasks
3 Validation:
Numerical stress-test of the framework capabilities
Generate an experimental database compatible with high-frequency
resonant and flexible wing
Compare numerical prediction with experimental data
4 Applications to the OVMI
Basic assistance to the designer
Advanced assistance to the designer: the wing design
T. Vanneste 04/07/2013 8 / 35
21. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Outline
1 Introduction
2 Aerodynamic model
3 Aeroelastic framework
4 Num. & Exp. Validation
5 Applications to the OVMI
6 Summary and Perspectives
T. Vanneste 04/07/2013 9 / 35
22. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Accounting for the wing flexibility
Flexibility is actively sought for resonant wings
Andrew Mountcastle website
Real blade profile i.e. camber + effective angle of attack
Change in the chordwise kinematics
Position of the shedding vortices
Relative position of the wake against the wing
Both spanwise and chordwise flexibilities needed in modeling
successfully flapping-wing aerodynamics
T. Vanneste 04/07/2013 9 / 35
23. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Accounting for the wing flexibility
Flexibility is actively sought for resonant wings
Andrew Mountcastle website
Real blade profile i.e. camber + effective angle of attack
Change in the chordwise kinematics
Position of the shedding vortices
Relative position of the wake against the wing
Both spanwise and chordwise flexibilities needed in modeling
successfully flapping-wing aerodynamics
T. Vanneste 04/07/2013 9 / 35
24. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Literature review
Sane and Dickinson [2002]
Singh [2006]
Quasi-steady models
Aerodynamics
- Accuracy
- Flow physics
Structure
- Unidirectional approach
Implementation
+ Simple formulation
+ Low computational load
Unsteady models
Aerodynamics
+ Accuracy
+ Flow physics
Structure
+ Bidirectional approach
Implementation
- Complex formulation
- High computational load
T. Vanneste 04/07/2013 10 / 35
25. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Literature review
Sane and Dickinson [2002]
Singh [2006]
Quasi-steady models
Aerodynamics
- Accuracy
- Flow physics
Structure
- Unidirectional approach
Implementation
+ Simple formulation
+ Low computational load
Unsteady models
Aerodynamics
+ Accuracy
+ Flow physics
Structure
+ Bidirectional approach
Implementation
- Complex formulation
- High computational load
T. Vanneste 04/07/2013 10 / 35
26. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Literature review
Sane and Dickinson [2002]
Singh [2006]
Quasi-steady models
Aerodynamics
- Accuracy
- Flow physics
Structure
- Unidirectional approach
Implementation
+ Simple formulation
+ Low computational load
Unsteady models
Aerodynamics
+ Accuracy
+ Flow physics
Structure
+ Bidirectional approach
Implementation
- Complex formulation
- High computational load
T. Vanneste 04/07/2013 10 / 35
27. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
The quasi-steady model of Sane and Dickinson [2002]
T. Vanneste 04/07/2013 11 / 35
28. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
The quasi-steady model of Sane and Dickinson [2002]
T. Vanneste 04/07/2013 11 / 35
29. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
The quasi-steady model of Sane and Dickinson [2002]
Faero = Ftrans + Fadded + Frot
T. Vanneste 04/07/2013 11 / 35
30. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
The quasi-steady model of Sane and Dickinson [2002]
Faero = Ftrans + Fadded + Frot
Each component experimentally validated
Depends on global geometrical and
kinematics data
Not compatible at first sight with flexibility
T. Vanneste 04/07/2013 11 / 35
31. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
The quasi-steady model of Sane and Dickinson [2002]
Faero = Ftrans + Fadded + Frot
Each component experimentally validated
Depends on global geometrical and
kinematics data
Not compatible at first sight with flexibility
Go back to the theory behind these components
T. Vanneste 04/07/2013 11 / 35
32. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Aerodynamic model overview
Use of local information to handle the flexibility
Two components computed: Translational & Added-mass forces
Rotational forces are assumed to be accounted by the translational
forces through the chordwise discretization
Formulation in the local ξη frame of each cell of the wing
T. Vanneste 04/07/2013 12 / 35
33. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Aerodynamic model overview
Use of local information to handle the flexibility
Two components computed: Translational & Added-mass forces
Rotational forces are assumed to be accounted by the translational
forces through the chordwise discretization
Formulation in the local ξη frame of each cell of the wing
T. Vanneste 04/07/2013 12 / 35
34. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Aerodynamic model overview
Use of local information to handle the flexibility
Two components computed: Translational & Added-mass forces
Rotational forces are assumed to be accounted by the translational
forces through the chordwise discretization
Formulation in the local ξη frame of each cell of the wing
T. Vanneste 04/07/2013 12 / 35
35. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Outline
1 Introduction
2 Aerodynamic model
3 Aeroelastic framework
4 Num. & Exp. Validation
5 Applications to the OVMI
6 Summary and Perspectives
T. Vanneste 04/07/2013 13 / 35
36. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Overview
To develop an aeroelastic framework sufficiently quick and accurate to serve
as a preliminary design tool for flapping-wing systems
Structure M, C and K(q)
FEM with Rayleigh damping
Aerodynamic forces F
Bidirectional model for coupled analysis
Unidirectional model only for uncoupled analysis
Aeroelasticity =
Explicit coupling enhanced by the stroke
periodicity
FEM Model with aerodynamic forces calculated with FE-kinematics at each
time step
T. Vanneste 04/07/2013 13 / 35
37. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Overview
To develop an aeroelastic framework sufficiently quick and accurate to serve
as a preliminary design tool for flapping-wing systems
M¨q + C ˙q + K(q)q = F(t, q, ˙q, ¨q)
Structure M, C and K(q)
FEM with Rayleigh damping
Aerodynamic forces F
Bidirectional model for coupled analysis
Unidirectional model only for uncoupled analysis
Aeroelasticity =
Explicit coupling enhanced by the stroke
periodicity
FEM Model with aerodynamic forces calculated with FE-kinematics at each
time step
T. Vanneste 04/07/2013 13 / 35
38. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Overview
To develop an aeroelastic framework sufficiently quick and accurate to serve
as a preliminary design tool for flapping-wing systems
M¨q + C ˙q + K(q)q = F(t, q, ˙q, ¨q)
Structure M, C and K(q)
FEM with Rayleigh damping
Aerodynamic forces F
Bidirectional model for coupled analysis
Unidirectional model only for uncoupled analysis
Aeroelasticity =
Explicit coupling enhanced by the stroke
periodicity
FEM Model with aerodynamic forces calculated with FE-kinematics at each
time step
T. Vanneste 04/07/2013 13 / 35
39. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Overview
To develop an aeroelastic framework sufficiently quick and accurate to serve
as a preliminary design tool for flapping-wing systems
M¨q + C ˙q + K(q)q = F(t, q, ˙q, ¨q)
Structure M, C and K(q)
FEM with Rayleigh damping
Aerodynamic forces F
Bidirectional model for coupled analysis
Unidirectional model only for uncoupled analysis
Aeroelasticity =
Explicit coupling enhanced by the stroke
periodicity
FEM Model with aerodynamic forces calculated with FE-kinematics at each
time step
T. Vanneste 04/07/2013 13 / 35
40. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Overview
To develop an aeroelastic framework sufficiently quick and accurate to serve
as a preliminary design tool for flapping-wing systems
M¨q + C ˙q + K(q)q = F(t, q, ˙q, ¨q)
Structure M, C and K(q)
FEM with Rayleigh damping
Aerodynamic forces F
Bidirectional model for coupled analysis
Unidirectional model only for uncoupled analysis
Aeroelasticity =
Explicit coupling enhanced by the stroke
periodicity
FEM Model with aerodynamic forces calculated with FE-kinematics at each
time step
T. Vanneste 04/07/2013 13 / 35
41. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Overview
To develop an aeroelastic framework sufficiently quick and accurate to serve
as a preliminary design tool for flapping-wing systems
M¨q + C ˙q + K(q)q = F(t, q, ˙q, ¨q)
Structure M, C and K(q)
FEM with Rayleigh damping
Aerodynamic forces F
Bidirectional model for coupled analysis
Unidirectional model only for uncoupled analysis
Aeroelasticity =
Explicit coupling enhanced by the stroke
periodicity
FEM Model with aerodynamic forces calculated with FE-kinematics at each
time step
T. Vanneste 04/07/2013 13 / 35
42. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Flowchart
T. Vanneste 04/07/2013 14 / 35
43. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Flowchart
T. Vanneste 04/07/2013 14 / 35
44. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Flowchart
T. Vanneste 04/07/2013 14 / 35
45. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Flowchart
T. Vanneste 04/07/2013 14 / 35
46. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Flowchart
T. Vanneste 04/07/2013 14 / 35
47. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Flowchart
Seat back and relax: automatized process within Python
T. Vanneste 04/07/2013 14 / 35
48. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Outline
1 Introduction
2 Aerodynamic model
3 Aeroelastic framework
4 Num. & Exp. Validation
5 Applications to the OVMI
6 Summary and Perspectives
T. Vanneste 04/07/2013 15 / 35
49. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Validation requirements
Need to validate:
1 Structural model M, C and K
2 Aerodynamic model F
3 Aeroelastic coupling =
T. Vanneste 04/07/2013 15 / 35
50. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Validation requirements
Need to validate:
1 Structural model M, C and K
2 Aerodynamic model F
3 Aeroelastic coupling =
How?
1 Define a set of academic wings
2 Check the soundness of the bidirectional
model
Compare with unidirectional prediction
3 Characterize the aeroelastic response of the
wings
Conduct experiments in vacuum and in air
Determine the material properties
T. Vanneste 04/07/2013 15 / 35
51. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Validation requirements
Need to validate:
1 Structural model M, C and K
2 Aerodynamic model F
3 Aeroelastic coupling =
How?
1 Define a set of academic wings
2 Check the soundness of the bidirectional
model
Compare with unidirectional prediction
3 Characterize the aeroelastic response of the
wings
Conduct experiments in vacuum and in air
Determine the material properties
T. Vanneste 04/07/2013 15 / 35
52. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Validation requirements
Need to validate:
1 Structural model M, C and K
2 Aerodynamic model F
3 Aeroelastic coupling =
How?
1 Define a set of academic wings
2 Check the soundness of the bidirectional
model
Compare with unidirectional prediction
3 Characterize the aeroelastic response of the
wings
Conduct experiments in vacuum and in air
Determine the material properties
T. Vanneste 04/07/2013 15 / 35
53. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Validation requirements
Need to validate:
1 Structural model M, C and K
2 Aerodynamic model F
3 Aeroelastic coupling =
How?
1 Define a set of academic wings
2 Check the soundness of the bidirectional
model
Compare with unidirectional prediction
3 Characterize the aeroelastic response of the
wings
Conduct experiments in vacuum and in air
Determine the material properties
T. Vanneste 04/07/2013 15 / 35
54. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Bidirectional model vs unidirectional one - Wing skeleton
Wing skeleton
Faero=Ftrans+Fadded +(Frot )
T. Vanneste 04/07/2013 16 / 35
55. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Bidirectional model vs unidirectional one - Wing skeleton
Wing skeleton
Faero=Ftrans+Fadded +(Frot )
T. Vanneste 04/07/2013 16 / 35
56. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Bidirectional model vs unidirectional one - Wing skeleton
Wing skeleton
Faero=Ftrans+Fadded +(Frot )
T. Vanneste 04/07/2013 16 / 35
57. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Bidirectional model vs unidirectional one - Complete wing
Complete wing
Faero=Ftrans+Fadded +(Frot )
T. Vanneste 04/07/2013 17 / 35
58. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Bidirectional model vs unidirectional one - Complete wing
Complete wing
Faero=Ftrans+Fadded +(Frot )
T. Vanneste 04/07/2013 17 / 35
59. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Bidirectional model vs unidirectional one - Complete wing
Complete wing
Faero=Ftrans+Fadded +(Frot )
T. Vanneste 04/07/2013 17 / 35
60. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Bidirectional model vs unidirectional one - Summary
Wing skeleton Complete wing
Translational forces accounting for some rotational forces
Added-mass forces underestimated
Qualitatively agreement
Correct order of magnitude
T. Vanneste 04/07/2013 18 / 35
61. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Bidirectional model vs unidirectional one - Summary
Wing skeleton Complete wing
Translational forces accounting for some rotational forces
Added-mass forces underestimated
Qualitatively agreement
Correct order of magnitude
T. Vanneste 04/07/2013 18 / 35
62. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Bidirectional model vs unidirectional one - Summary
Wing skeleton Complete wing
Translational forces accounting for some rotational forces
Added-mass forces underestimated
Qualitatively agreement
Correct order of magnitude
T. Vanneste 04/07/2013 18 / 35
63. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Bidirectional model vs unidirectional one - Summary
Wing skeleton Complete wing
Translational forces accounting for some rotational forces
Added-mass forces underestimated
Qualitatively agreement
Correct order of magnitude
Bidirectional model cleared for preliminary design tasks
T. Vanneste 04/07/2013 18 / 35
64. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Literature review: Experimental validation
Dickinson lab Wu and Ifju [2010]
Experiments in a liquid medium
Flow forces preponderant over
inertial/elastic forces
Rigid or moderately flexible
wings favored
Mostly around 0.2Hz
Experiments in air
Better balance of the
inertial/elastic forces
More flexible wings favored
Resonant wing barely studied
Up to 40Hz
New database needed for very flexible, high-frequency resonant wings
T. Vanneste 04/07/2013 19 / 35
65. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Literature review: Experimental validation
Dickinson lab Wu and Ifju [2010]
Experiments in a liquid medium
Flow forces preponderant over
inertial/elastic forces
Rigid or moderately flexible
wings favored
Mostly around 0.2Hz
Experiments in air
Better balance of the
inertial/elastic forces
More flexible wings favored
Resonant wing barely studied
Up to 40Hz
New database needed for very flexible, high-frequency resonant wings
T. Vanneste 04/07/2013 19 / 35
66. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Characterizing the wing aeroelastic response
Two methods available:
Tracking the wing deformation:
High-speed camera and vibrometer
Measuring the aerodynamic forces:
Balance
T. Vanneste 04/07/2013 20 / 35
67. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Characterizing the wing aeroelastic response
Two methods available:
Tracking the wing deformation:
High-speed camera and vibrometer
Measuring the aerodynamic forces:
Balance
Only the wing deformation method is
here used
T. Vanneste 04/07/2013 20 / 35
68. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Characterizing the wing aeroelastic response
Two methods available:
Tracking the wing deformation:
High-speed camera and vibrometer
Measuring the aerodynamic forces:
Balance
Only the wing deformation method is
here used
T. Vanneste 04/07/2013 20 / 35
69. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Validation for wing skeleton - Vacuum
T. Vanneste 04/07/2013 21 / 35
70. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Validation for wing skeleton - Vacuum
Structural model validated in vacuum
T. Vanneste 04/07/2013 21 / 35
71. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Validation for wing skeleton - Air
T. Vanneste 04/07/2013 22 / 35
72. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Validation for wing skeleton - Air
Aeroelastic coupling validated in air
Aeroelastic framework validated for wing skeleton
T. Vanneste 04/07/2013 22 / 35
73. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Validation for complete wing - Vacuum
T. Vanneste 04/07/2013 23 / 35
74. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Validation for complete wing - Vacuum
T. Vanneste 04/07/2013 23 / 35
75. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Validation for complete wing - Vacuum
Reasonable agreement of the structural model in vacuum
T. Vanneste 04/07/2013 23 / 35
76. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Validation for complete wing - Air
T. Vanneste 04/07/2013 24 / 35
77. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Validation for complete wing - Air
Qualitatively agreement of the aeroelastic response in air
Aerodynamic damping well caught
T. Vanneste 04/07/2013 24 / 35
78. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Experimental validation
Aeroelastic framework cleared for preliminary design tasks
Preliminary design tool for flapping-wing systems devised
Further experimental investigations are mandatory
T. Vanneste 04/07/2013 25 / 35
79. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Experimental validation
Aeroelastic framework cleared for preliminary design tasks
Preliminary design tool for flapping-wing systems devised
Further experimental investigations are mandatory
T. Vanneste 04/07/2013 25 / 35
80. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Experimental validation
Aeroelastic framework cleared for preliminary design tasks
Preliminary design tool for flapping-wing systems devised
Further experimental investigations are mandatory
T. Vanneste 04/07/2013 25 / 35
81. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Outline
1 Introduction
2 Aerodynamic model
3 Aeroelastic framework
4 Num. & Exp. Validation
5 Applications to the OVMI
6 Summary and Perspectives
T. Vanneste 04/07/2013 26 / 35
82. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Choosing an actuation strategy: the mode
What type of actuation is better for my FWNAV?
T. Vanneste 04/07/2013 26 / 35
83. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Choosing an actuation strategy: the mode
What type of actuation is better for my FWNAV?
Heaving Flapping
T. Vanneste 04/07/2013 26 / 35
84. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Choosing an actuation strategy: the mode
What type of actuation is better for my FWNAV?
Flapping actuation strategy implemented on the OVMI
T. Vanneste 04/07/2013 26 / 35
85. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Choosing an actuation strategy: the mode
What type of actuation is better for my FWNAV?
Flapping actuation strategy implemented on the OVMI
T. Vanneste 04/07/2013 26 / 35
86. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Choosing an actuation strategy: the mode
What type of actuation is better for my FWNAV?
Flapping actuation strategy implemented on the OVMI
T. Vanneste 04/07/2013 26 / 35
87. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Assisting the wing design
How to find the appropriate wing compatible with
our FWNAV requirements?
Relatively large design space
Multiple local optimum
Need for an automatic and fast tools to outline
possible airborne wing design
Coupling an optimizer to our aeroelastic
framework
Keennon [2012]
T. Vanneste 04/07/2013 27 / 35
88. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Assisting the wing design
Combes and Daniel [2003]
How to find the appropriate wing compatible with
our FWNAV requirements?
Relatively large design space
Multiple local optimum
Need for an automatic and fast tools to outline
possible airborne wing design
Coupling an optimizer to our aeroelastic
framework
Keennon [2012]
T. Vanneste 04/07/2013 27 / 35
89. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Assisting the wing design
Combes and Daniel [2003]
How to find the appropriate wing compatible with
our FWNAV requirements?
Relatively large design space
Multiple local optimum
Need for an automatic and fast tools to outline
possible airborne wing design
Coupling an optimizer to our aeroelastic
framework
Keennon [2012]
T. Vanneste 04/07/2013 27 / 35
90. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Optimization environment
Why genetic algorithm?
GA avoids local minima and initialization problems
T. Vanneste 04/07/2013 28 / 35
91. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Optimization environment
Why genetic algorithm?
GA avoids local minima and initialization problems
Three complementary levels of preliminary design:
Unidirectional (uncoupled) aerodynamic model in SD
Bidirectional (coupled) aerodynamic model in SD
Computational parameters set to lower the load at the cost of accuracy
T. Vanneste 04/07/2013 28 / 35
92. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Optimization environment
Why genetic algorithm?
GA avoids local minima and initialization problems
Three complementary levels of preliminary design:
Unidirectional (uncoupled) aerodynamic model in SD
Bidirectional (coupled) aerodynamic model in SD
Bidirectional (coupled) aerodynamic model in LD
Computational parameters set to lower the load at the cost of accuracy
T. Vanneste 04/07/2013 28 / 35
93. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Optimization environment
Why genetic algorithm?
GA avoids local minima and initialization problems
Three complementary levels of preliminary design:
Unidirectional (uncoupled) aerodynamic model in SD
Bidirectional (coupled) aerodynamic model in SD
Bidirectional (coupled) aerodynamic model in LD
Computational parameters set to lower the load at the cost of accuracy
T. Vanneste 04/07/2013 28 / 35
94. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Optimization environment
Why genetic algorithm?
GA avoids local minima and initialization problems
Three complementary levels of preliminary design:
Unidirectional (uncoupled) aerodynamic model in SD
Bidirectional (coupled) aerodynamic model in SD
Bidirectional (coupled) aerodynamic model in LD
Computational parameters set to lower the load at the cost of accuracy
T. Vanneste 04/07/2013 28 / 35
95. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Setting the objective function
Objective function
J =
¯L
Mwing · g
· C1
Optimizer tends to increase the
resonant frequency
Including a penalization into the
objective function
T. Vanneste 04/07/2013 29 / 35
96. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Setting the objective function
Objective function
J =
¯L
Mwing · g
· C1
Optimizer tends to increase the
resonant frequency
Including a penalization into the
objective function
T. Vanneste 04/07/2013 29 / 35
97. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Setting the objective function
Ellington [1999]
Objective function
J =
¯L
Mwing · g
· C1
Optimizer tends to increase the
resonant frequency
Including a penalization into the
objective function
T. Vanneste 04/07/2013 29 / 35
98. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Optimization levels
Objective function
J =
Lift
Mwing · g
·C1− | fwing −ftarget | ·C2
T. Vanneste 04/07/2013 30 / 35
99. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Optimization levels
Objective function
J =
Lift
Mwing · g
·C1− | fwing −ftarget | ·C2
Complementary optimization
Uncoupled
f = 54.89Hz in ∼5.4h
Coupled
f = 50.11Hz in ∼57.2h
T. Vanneste 04/07/2013 30 / 35
100. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Optimization levels
Objective function
J =
Lift
Mwing · g
·C1− | fwing −ftarget | ·C2
Complementary optimization
Uncoupled
f = 54.89Hz in ∼5.4h
Coupled
f = 50.11Hz in ∼57.2h
Similar performance whatever the optimization type
Coupled optimization refines the design to favor behavior seen in nature
Optimization environment working smoothly and ready to be unleashed
T. Vanneste 04/07/2013 30 / 35
101. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Optimization levels
Objective function
J =
Lift
Mwing · g
·C1− | fwing −ftarget | ·C2
Complementary optimization
Uncoupled
f = 54.89Hz in ∼5.4h
Coupled
f = 50.11Hz in ∼57.2h
Similar performance whatever the optimization type
Coupled optimization refines the design to favor behavior seen in nature
Optimization environment working smoothly and ready to be unleashed
T. Vanneste 04/07/2013 30 / 35
102. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Outline
1 Introduction
2 Aerodynamic model
3 Aeroelastic framework
4 Num. & Exp. Validation
5 Applications to the OVMI
6 Summary and Perspectives
T. Vanneste 04/07/2013 31 / 35
103. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Summary
Aerodynamic model compatible with the full wing flexibility
Framework providing a comprehensive insight in the aeroelastic
response of flapping-wing systems
Experimental database for high-frequency, resonant and flexible wings
Preliminary design tool working smoothly
Optimization environment ready to be unleashed
T. Vanneste 04/07/2013 31 / 35
104. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Summary
Aerodynamic model compatible with the full wing flexibility
Framework providing a comprehensive insight in the aeroelastic
response of flapping-wing systems
Experimental database for high-frequency, resonant and flexible wings
Preliminary design tool working smoothly
Optimization environment ready to be unleashed
T. Vanneste 04/07/2013 31 / 35
105. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Summary
Aerodynamic model compatible with the full wing flexibility
Framework providing a comprehensive insight in the aeroelastic
response of flapping-wing systems
Experimental database for high-frequency, resonant and flexible wings
Preliminary design tool working smoothly
Optimization environment ready to be unleashed
T. Vanneste 04/07/2013 31 / 35
106. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Summary
Aerodynamic model compatible with the full wing flexibility
Framework providing a comprehensive insight in the aeroelastic
response of flapping-wing systems
Experimental database for high-frequency, resonant and flexible wings
Preliminary design tool working smoothly
Optimization environment ready to be unleashed
T. Vanneste 04/07/2013 31 / 35
107. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Summary
Aerodynamic model compatible with the full wing flexibility
Framework providing a comprehensive insight in the aeroelastic
response of flapping-wing systems
Experimental database for high-frequency, resonant and flexible wings
Preliminary design tool working smoothly
Optimization environment ready to be unleashed
T. Vanneste 04/07/2013 31 / 35
108. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Perspectives
David Kleinert
Continuing the development of experimental hardware and
methodologies
Completing further the validation especially for membrane wings
Extending the framework’s capabilities to more realistic wings
Enhancing the aerodynamic model with yet unaccounted phenomena
T. Vanneste 04/07/2013 32 / 35
109. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Perspectives
David Kleinert
Continuing the development of experimental hardware and
methodologies
Completing further the validation especially for membrane wings
Extending the framework’s capabilities to more realistic wings
Enhancing the aerodynamic model with yet unaccounted phenomena
T. Vanneste 04/07/2013 32 / 35
110. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Perspectives
David Kleinert
Continuing the development of experimental hardware and
methodologies
Completing further the validation especially for membrane wings
Extending the framework’s capabilities to more realistic wings
Enhancing the aerodynamic model with yet unaccounted phenomena
T. Vanneste 04/07/2013 32 / 35
111. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
List of publications and conferences I
International conferences with lecture committee
J.-B. Paquet, T. Vanneste, A. Bontemps, S. Grondel, and E. Cattan (2013). “Aerodynamic FMAV with vibrating
wings at insect size”. 48th International Symposium of Applied Aerodynamics. St Louis, France.
T. Vanneste, J.-B. Paquet, S. Grondel, and E. Cattan (2012a). “Aeroelastic simulation of flexible flapping wing
based on structural FEM and quasi steady aerodynamic model”.
28th International Congress of the Aeronautical Sciences. Brisbane, Australia.
T. Vanneste, J.-B. Paquet, S. Grondel, and E. Cattan (2012b). “Design of a lift-optimized flapping-wing using a
finite element aeroelastic framework of insect flight”.
53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference. Honolulu, HI,
USA.
X. Q. Bao, T. Vanneste, A. Bontemps, S. Grondel, J.-B. Paquet, and E. Cattan (2011). “Microfabrication of
bio-inspired SU-8 wings and initial analyses of their aeroelastic behaviours for microrobotic insects”.
2011 IEEE International Conference on Robotics and Biomimetics (ROBIO2011). Phuket, Thailand.
T. Vanneste, A. Bontemps, X. Q. Bao, J.-B. Paquet, S. Grondel, and E. Cattan (2011). “Polymer-based
flapping-wing robotic insects: Progresses in wing fabrication, conception and simulation”.
International Mechanical Engineering Congress and Exposition 2011. Denver, CO, USA.
X. Q. Bao, A. Bontemps, T. Vanneste, J.-B. Paquet, S. Grondel, and E. Cattan (2011). “Fabrication and
actuation of flapping-wing robotic insect prototype using selected polymer”.
International Workshop on Bio-inspired Robots. Nantes, France.
T. Vanneste, J.-B. Paquet, X. Q. Bao, T. Dargent, S. Grondel, and E. Cattan (2010). “Conception of Resonant
Wings on an Insect-Scale”. International Micro Air Vehicle Conference and Flight Competition (IMAV2010).
Braunschweig, Germany.
T. Vanneste 04/07/2013 33 / 35
112. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
List of publications and conferences II
Journal
A. Bontemps, T. Vanneste, J.-B. Paquet, T. Dietsch, S. Grondel, and E. Cattan (Jan. 2013). “Design and
performance of an insect-inspired nano air vehicle”. Smart Materials and Structures 22.1, p. 014008.
International conferences without lecture committee
A. Bontemps, T. Vanneste, J.-B. Paquet, S. Grondel, and E. Cattan (2011). “Prototyping of an insect-like nano
aerial vehicle”. Poster session of the International Mechanical Engineering Congress and Exposition 2011.
Denver, CO, USA.
A. Bontemps, T. Vanneste, X. Q. Bao, J.-B. Paquet, S. Grondel, and E. Cattan (2011). “Prototyping of a like
insect flapping wing object”. Poster session of the International Workshop on Bio-inspired Robots. Nantes,
France.
National conference with lecture committee
T. Vanneste, J.-P. Bourez, J.-B. Paquet, S. Grondel, and E. Cattan (2011). “Visualisation de l’écoulement autour
d’une aile d’insecte artificielle”.
14ème Congrès Français de Visualisation et de Traitement d’Images en Mécanique des Fluides. Lille,
France.
T. Vanneste 04/07/2013 34 / 35
113. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
Introduction Aerodynamic model Aeroelastic framework Num. & Exp. Validation Applications to the OVMI Summary and Perspectives
Thank you for your attention !
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114. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
References I
J. M. Grasmeyer and M. T. Keennon (2001). “Development of the Black Widow Micro Air Vehicle”.
39th AIAA Aerospace Sciences Meeting and Exhibit. Vol. 195. Reno, NV, USA.
Bitcraze AB (2012). About Bitcraze. URL: http://www.bitcraze.se/about/.
R. W. Zbikowski (2002). “On aerodynamic modelling of an insect-like flapping wing in hover for micro air
vehicles”.
Philosophical Transactions of the Royal Society A: Mathematical, Physical and Engineering Sciences
360.1791, pp. 273–290.
S. A. Combes and T. L. Daniel (2003). “Flexural stiffness in insect wings I. Scaling and the influence of wing
venation”. The Journal of Experimental Biology 206.17, pp. 2979–2987.
M. Blair, G. H. Parker, P. S. Beran, and R. D. Snyder (2007). “A Computational Design Framework for Flapping
Micro Air Vehicles”. 45th AIAA Aerospace Sciences Meeting and Exhibit. Reno, NV, USA.
S. P. Sane and M. H. Dickinson (2002). “The aerodynamic effects of wing rotation and a revised quasi-steady
model of flapping flight”. The Journal of Experimental Biology 205.8, pp. 1087–1096.
B. Singh (2006). “Dynamics and Aeroelasticity of Hover-Capable Flapping Wings: Experiments and Analysis”.
PhD thesis. University of Maryland, p. 214.
P. Wu and P. G. Ifju (2010). “Micro Air Vehicle Flapping Wing Effectiveness, Efficiency and Aeroelasticity
Relationships”.
48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition.
Orlando, FL, USA.
M. T. Keennon (2012). “Tailless Flapping Wing Propulsion and Control Development for the Nano Hummingbird
Micro Air Vehiclee”.
American Helicopter Society (AHS) International Future Vertical Lift Aircraft Design Conference. San
Francisco, CA, USA.
T. Vanneste 04/07/2013 36 / 35
115. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
References II
C. P. Ellington (1999). “The novel aerodynamics of insect flight: applications to micro-air vehicles”.
The Journal of Experimental Biology 202.23, pp. 3439–3448.
J.-B. Paquet, T. Vanneste, A. Bontemps, S. Grondel, and E. Cattan (2013). “Aerodynamic FMAV with vibrating
wings at insect size”. 48th International Symposium of Applied Aerodynamics. St Louis, France.
T. Vanneste, J.-B. Paquet, S. Grondel, and E. Cattan (2012a). “Aeroelastic simulation of flexible flapping wing
based on structural FEM and quasi steady aerodynamic model”.
28th International Congress of the Aeronautical Sciences. Brisbane, Australia.
T. Vanneste, J.-B. Paquet, S. Grondel, and E. Cattan (2012b). “Design of a lift-optimized flapping-wing using a
finite element aeroelastic framework of insect flight”.
53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference. Honolulu, HI,
USA.
X. Q. Bao, T. Vanneste, A. Bontemps, S. Grondel, J.-B. Paquet, and E. Cattan (2011). “Microfabrication of
bio-inspired SU-8 wings and initial analyses of their aeroelastic behaviours for microrobotic insects”.
2011 IEEE International Conference on Robotics and Biomimetics (ROBIO2011). Phuket, Thailand.
T. Vanneste, A. Bontemps, X. Q. Bao, J.-B. Paquet, S. Grondel, and E. Cattan (2011). “Polymer-based
flapping-wing robotic insects: Progresses in wing fabrication, conception and simulation”.
International Mechanical Engineering Congress and Exposition 2011. Denver, CO, USA.
X. Q. Bao, A. Bontemps, T. Vanneste, J.-B. Paquet, S. Grondel, and E. Cattan (2011). “Fabrication and
actuation of flapping-wing robotic insect prototype using selected polymer”.
International Workshop on Bio-inspired Robots. Nantes, France.
T. Vanneste, J.-B. Paquet, X. Q. Bao, T. Dargent, S. Grondel, and E. Cattan (2010). “Conception of Resonant
Wings on an Insect-Scale”. International Micro Air Vehicle Conference and Flight Competition (IMAV2010).
Braunschweig, Germany.
T. Vanneste 04/07/2013 37 / 35
116. Aeroelastic framework of insect-like flapping-wing applied to the design of a resonant NAV
References III
A. Bontemps, T. Vanneste, J.-B. Paquet, T. Dietsch, S. Grondel, and E. Cattan (Jan. 2013). “Design and
performance of an insect-inspired nano air vehicle”. Smart Materials and Structures 22.1, p. 014008.
A. Bontemps, T. Vanneste, J.-B. Paquet, S. Grondel, and E. Cattan (2011). “Prototyping of an insect-like nano
aerial vehicle”. Poster session of the International Mechanical Engineering Congress and Exposition 2011.
Denver, CO, USA.
A. Bontemps, T. Vanneste, X. Q. Bao, J.-B. Paquet, S. Grondel, and E. Cattan (2011). “Prototyping of a like
insect flapping wing object”. Poster session of the International Workshop on Bio-inspired Robots. Nantes,
France.
T. Vanneste, J.-P. Bourez, J.-B. Paquet, S. Grondel, and E. Cattan (2011). “Visualisation de l’écoulement autour
d’une aile d’insecte artificielle”.
14ème Congrès Français de Visualisation et de Traitement d’Images en Mécanique des Fluides. Lille,
France.
T. Vanneste 04/07/2013 38 / 35