Surrogate models for Rapid Sizing of Structures
|
|
- Piers Watts
- 6 years ago
- Views:
Transcription
1 ESAZO Stéphane Grihon Expert in Structure Optimization Surrogate models for Rapid Sizing of Structures An experience of surrogate models for structure optimization at AIRBUS
2 Summary Introduction Various R&T approaches Gradual industrialization Conclusions & next steps Page 2
3 Summary Introduction Various R&T approaches Gradual industrialization Conclusions & next steps Page 3
4 Strength analysis process Basis for structural optimisation GLOBAL ANALYSIS process: full aircraft / component level GLOBAL FINITE ELEMENT MODEL STATIC LINEAR ANALYSIS [ K ] D = F N = external loads [ A]D NASTRAN ISAMI ELEMENTARY INTERNAL LOADS LOCAL ANALYSIS : part / element level STRESS/STRENGTH -Metallic -Fatigue/Damage tolerance -Composite SEMI-EMPIRICAL METHODS Page 4
5 Sizing process Structural Analysis & Design Input data Loads Geometry Analysis tools (FE-based / analytical) Structural responses Reserve Factors (failure modes) Ratios between structural responses and allowables (linked to material / geometry) : RF 1 : structure feasible RF< 1 : structure not feasible Structural design : Find Geometry with minimum weight and RF 1 Optimisation problem Structural design is an optimisation problem Page 5
6 Sizing variables Typical structure optimisation variables with largest weight influence Airframe structures: thin-walled structures stiffened panels (to withstand buckling) Sizing variables = - stiffener profile dimensions summarised as a stiffener area: A - panel lay-up (composite stacking) summarised as a thickness: t Page 6
7 Structure sizing optimization Simplified formulation for strength sizing Min s ( P) s s s. t. i M s RF i, j, k = m( s ( s i= 1.. N i, N i, j i ) ) 1 s i : sizing variables i : element, j:load case, k: failure modes RF( s, N ) Vector of <10 outputs: one RF per failure mode <10 geometrical inputs: sizing variables <10 internal load inputs: typically Nxx,Nxy,Nyy for a super-stringer Computed with a semi-empirical skill tool: 1s per unitary calculation (one internal load vector) But multiplied by elements, 100 critical load cases, 10 variables: 2000 hours for one iteration. Surrogate Models To reduce unitary calculation time from 1s to 10-4 s Page 7
8 Rapid sizing Accelerate sizing loops based on -Engineering approaches -IT means: High Performance Computing -Numerical techniques Multi-level decomposition Surrogate models To reduce non-recurring costs in airframe developments. To enable higher level trade-off studies Page 8
9 Summary Introduction Various R&T approaches Gradual industrialization Conclusions & next steps Page 9
10 Design curves Reduction of input variables via optimization We do not approximate RF but local optimization results: (P) is solved at elementary level with generic internal loads inputs. Results (t,a) are approximated as functions of internal loads: <10 inputs t(n), A(N) are used as gauge constraints in global level optimization Super-stringer level N s. t. Min s m( s) RF ( s, N) 1 k (t,a) Surrogate models: t(n), A(N) Page 10
11 Limitations Mitigated results This approach enables to work with a limited number of inputs and already solves part of the optimization problem. And it gives quite smooth response surfaces (integration effect) that can be used in other contexts (design curves) This approach is acceptable for rough preliminary sizing but does not provide an accurate representation of the feasible space: cross section area of the stringer Sr panel thickness (tp) Moreover: For several internal load components, different external load cases can contribute to the sizing. It is not possible to perform material exchange between panel and stringer Page 11
12 Analysis regression PS3 test-case Definition of a composite wing panel test-case with T stringers and thickness/percentages input for skin Use of PS3 semi-empirical ISAMI analysis tool to address all failure modes of a composite wing cover Approximation of RFs from PS3: tool for flat composite panel analysis (composite wing) 5 geometrical inputs 3 internal loads inputs First applications performed with neural networks ba t 1 tw h ta t 2 Page 12
13 Limitations Accuracy goal not met Approximation results were not as expected: 95% of samples below 5% error This was undersood as linked to Discontinuities in reserve factors: linked to leaps between failure modes, changes of theory Or zones of large variations: high gradients When we try to be more accurate we have a Gibbs effect: oscillations around the singularity Page 13
14 Piecewise approach PhD theses To master these effects a piecewise approach was developed: 1) Manual (A.Merval PhD) Subdivision of the load input space in 20 subdomains Separation of local/global buckling modes with a classifier neural network 2) Fully automated (D.Bettebghor PhD) thanks to an EM classification approach: IMAGE concept Parameters estimated wih an expectation minimization. Database clusterised Approximation per cluster then recombination
15 Consolidation A new partnership: IRIAS/DATADVANCE, MACROS tool Use of gaussian/sigmoïdal approximations and mixture of experts (greedy approach) Application of boosting for high dimensional approximation Page 15
16 Gradual increase of dimensionality Challenge input dimensions %0, %90, length width MACROS step state of the art: detailed report (curves,cpu, accuracy) 2009 statement of work: new design variables, new reserve factors MACROS step 2 16 design variables (v1+8) with 1% accuracy: v1+8: 4 percentages in skin (0 and 90 percentages for left and right shells) 4 percentages in stringer (flange and web) MACROS step3 27 design variables (v2+11) with 1% accuracy: V2+11: Flange width, panel width, panel length UD material coefficients: 4 for skin and 4 for stringers Approximation of the complete set of reserve factors Page 16 July 2010
17 Full surrogate model implementation COMBOX Substitution of PS3 with a surrogate model built from MACROS inside the COMBOX optimization tool used for pre-sizing of all A350 boxes BOSS Quattro Objective Value 2.10E E E+03 Weight 1.80E+03 Objective Value CAESAM 1.70E E E Iteration ISAMI-PS3 NASTRAN Page 17
18 Integration in optimization Optimization results As expected: Good accuracy Smoother convergence Reduced computational times Objective Value Blue: convergence with MACROS 278s instead of 1216s for sensitivity analysis inside one iteration Weight 1.70E E E E E E E+03 MACROS PS3 Green: restart with PS3 1.67E Iteration Page 18
19 Summary Introduction Various R&T approaches Gradual industrialization Conclusions & next steps Page 19
20 PRESTO A new sizing tool A new sizing tool has been implemented for rapid sizing of structures with main application to A fuselage. Particularity: To support thin composite fuselage design and trade-off studies, strength analysis are performed upfront on predefined catalogues: discrete approach Page 20
21 Catalogue concept in PRESTO Catalogues are a way to reduce sizing variables to a thickness and a cross-sectional area: Page 21
22 PRESTO & surrogate models A step by step approach Surrogate models are progressively being integrated: Step1: Surrogate models with respect to internal loads have been introduced to compress look-up tables of Reserve Factors: Compression of RF databases by a factor 10 obtained! First step and PRESTO and MACROS are now linked for future steps: Step2 is to approximate with respect to catalogue inputs: t,a, to link PRESTO to continuous optimization approaches. IRT MDA-MDO Step3: see conclusion Page 22
23 Summary Introduction Various R&T approaches Gradual industrialization Conclusions & next steps Page 23
24 Conclusion and next steps Surrogate models identified as a very valuable technology for rapid sizing of structures Also linked to the kind of targeted tool with limited computational time and limited inputs Next step is to provide surrogate models from PRESTO and to deliver these surrogate models for: structure optimization tools detailed sizing in operational teams Idea is also to use them in a kind of stress cockpit to have quick sensitivity/curves plots for the designer in order to improve his knowledge of the strength analysis tool. Page 24
25 This document and all information contained herein is the sole property of AIRBUS Operations S.A.S. No intellectual property rights are granted by the delivery of this document or the disclosure of its content. This document shall not be reproduced or disclosed to a third party without the express written consent of AIRBUS Operations S.A.S. This document and its content shall not be used for any purpose other than that for which it is supplied. The statements made herein do not constitute an offer. They are based on the mentioned assumptions and are expressed in good faith. Where the supporting grounds for these statements are not shown, AIRBUS Operations S.A.S will be pleased to explain the basis thereof. AIRBUS, its logo, A300, A310, A318, A319, A320, A321, A330, A340, A350, A380, A400M are registered trademarks. Page 25
Surrogate Modeling of Buckling Analysis in Support of Composite Structure Optimization
Surrogate Modeling of Buckling Analysis in Support of Composite Structure Optimization S. GRIHON a, S. ALESTRA b, 1 E. BURNAEV c,d,e, 1 P. PRIKHODKO c,d,e a. ESAZO, Airbus Operations SAS, 316, Route de
More informationMulti-Objective Design Exploration (MODE) Applied to a Regional Jet Design. Shigeru Obayashi Institute of Fluid Science Tohoku University
Multi-Objective Design Exploration (MODE) Applied to a Regional Jet Design Shigeru Obayashi Institute of Fluid Science Tohoku University n Introduction Outline n Multi-Objective Design Exploration (MODE)
More informationMélange d experts pour l approximation des calculs de flambage pour les matériaux composites
Mélange d experts pour l approximation des calculs de flambage pour les matériaux composites D. BETTEBGHOR 1, N. BARTOLI 2 1 Onera, The French Aerospace Lab, 1 Dpt. Dynamique des Structures et Aéroélasticité,
More informationApplications of structural optimisation to AIRBUS A380 powerplant configuration and pylon design
Applications of structural optimisation to AIRBUS A380 powerplant configuration and pylon design ABSTRACT 2001-122 Stéphane GRIHON AIRBUS 316, Route de Bayonne 31060 Toulouse CEDEX France stephane.grihon@airbus.aeromatra.com
More informationOPTIMIZATION OF STIFFENED LAMINATED COMPOSITE CYLINDRICAL PANELS IN THE BUCKLING AND POSTBUCKLING ANALYSIS.
OPTIMIZATION OF STIFFENED LAMINATED COMPOSITE CYLINDRICAL PANELS IN THE BUCKLING AND POSTBUCKLING ANALYSIS. A. Korjakin, A.Ivahskov, A. Kovalev Stiffened plates and curved panels are widely used as primary
More informationSIZE OPTIMIZATION OF AIRCRAFT STRUCTURES
26 TH INTERNATIONAL CONGRESS OF THE AERONAUTICAL SCIENCES SIZE OPTIMIZATION OF AIRCRAFT STRUCTURES S. Hernandez, A. Baldomir and J. Mendez Structural Engineering Department, University of Coruna Campus
More informationAPPLICATION OF STRUCTURAL OPTIMISATION WITH BOSS QUATTRO TO A380 RIB1 OPTIMISATION
December 2003 FENet Presented by Ghislaine MALHERBE (SAMTECH France) Collaboration with Stéphane Grihon ESANT - (AIRBUS France) Cesare CRUCCAS (SAMTECH France) APPLICATION OF STRUCTURAL OPTIMISATION WITH
More informationFuselage Structure Optimisation
Fuselage Structure Optimisation Stéphane Grihon AIRBUS, Toulouse, France Manuel Samuelides, Antoine Merval ONERA, Toulouse, France Alain Remouchamps, Michael Bruyneel, Benoit Colson SAMTECH, Liège, Belgium
More informationTargeting Composite Wing Performance Optimising the Composite Lay-Up Design
Targeting Composite Wing Performance Optimising the Composite Lay-Up Design Sam Patten Optimisation Specialist, Altair Engineering Ltd Imperial House, Holly Walk, Royal Leamington Spa, CV32 4JG sam.patten@uk.altair.com
More informationSDA Webinar Introduction to NX Nastran SOL 200 Design Optimization
SDA Webinar Introduction to NX Nastran SOL 200 Design Optimization David Cross Senior Stress Analyst at SDA david@structures.aero July 23, 2015 Page 1 Webinar Overview About SDA What is Design Optimization?
More informationDISTRIBUTED LOADS DISCRETIZATION IN COMPOSITE MATERIALS STRUCTURES TESTS
DISTRIBUTED LOADS DISCRETIZATION IN COMPOSITE MATERIALS STRUCTURES TESTS C. Arellano 1 1 Structural Laboratory, TEAMS, Wilbur y Orville Wright N1 AEROPOLIS 41309 La Rinconada, Espana Corresponding Author:
More informationSimulation of Discrete-source Damage Growth in Aircraft Structures: A 3D Finite Element Modeling Approach
Simulation of Discrete-source Damage Growth in Aircraft Structures: A 3D Finite Element Modeling Approach A.D. Spear 1, J.D. Hochhalter 1, A.R. Ingraffea 1, E.H. Glaessgen 2 1 Cornell Fracture Group, Cornell
More informationModule 1 Lecture Notes 2. Optimization Problem and Model Formulation
Optimization Methods: Introduction and Basic concepts 1 Module 1 Lecture Notes 2 Optimization Problem and Model Formulation Introduction In the previous lecture we studied the evolution of optimization
More informationUser guide - VIM plus AOG & RG - V1. New VIM plus AOG & RG. User guide
New VIM plus AOG & RG User guide What is it? (1/2) The Vendor Information Manual plus Aircraft On Ground and Repair Guide is a web-based tool enabling relevant Supplier Support contact details, including
More informationReducing overdesign with predictive performance and producibility simulation
American Society of Composites 29 th technical Conf., 16 th US-Japan Conf. on Composite Materials, San Diego, USA, September 10, 2014 Reducing overdesign with predictive performance and producibility simulation
More informationComputer Aided Drafting, Design and Manufacturing Volume 26, Number 4, December 2016, Page 30
Computer Aided Drafting, Design and Manufacturing Volume 26, Number 4, December 2016, Page 30 CADDM Aircraft wing box rapid modeling based on skeleton model Zhang Chao, Xi Ping School of Mechanical Engineering
More informationMultidisciplinary design optimization (MDO) of a typical low aspect ratio wing using Isight
Multidisciplinary design optimization (MDO) of a typical low aspect ratio wing using Isight Mahadesh Kumar A 1 and Ravishankar Mariayyah 2 1 Aeronautical Development Agency and 2 Dassault Systemes India
More informationSeven Techniques For Finding FEA Errors
Seven Techniques For Finding FEA Errors by Hanson Chang, Engineering Manager, MSC.Software Corporation Design engineers today routinely perform preliminary first-pass finite element analysis (FEA) on new
More informationFinite Element Buckling Analysis Of Stiffened Plates
International Journal of Engineering Research and Development e-issn: 2278-067X, p-issn: 2278-800X, www.ijerd.com Volume 10, Issue 2 (February 2014), PP.79-83 Finite Element Buckling Analysis Of Stiffened
More informationTOPOLOGY OPTIMIZATION OF WING RIBS IN CESSNA CITATION
TOPOLOGY OPTIMIZATION OF WING RIBS IN CESSNA CITATION [1],Sathiyavani S [2], Arun K K [3] 1,2 student, 3 Assistant professor Kumaraguru College of technology, Coimbatore Abstract Structural design optimization
More informationVIRTUAL TESTING OF AIRCRAFT FUSELAGE STIFFENED PANELS
4 TH INTERNATIONAL CONGRESS OF THE AERONAUTICAL SCIENCES VIRTUAL TESTING OF AIRCRAFT FUSELAGE STIFFENED PANELS Peter Linde*, Jürgen Pleitner*, Wilhelm Rust** *Airbus, Hamburg, Germany, **CAD-FE GmbH, Burgdorf
More informationAXIAL OF OF THE. M. W. Hyer. To mitigate the. Virginia. SUMMARY. the buckling. circumference, Because of their. could.
IMPROVEMENT OF THE AXIAL BUCKLING CAPACITY OF COMPOSITE ELLIPTICAL CYLINDRICAL SHELLS M. W. Hyer Department of Engineering Science and Mechanics (0219) Virginia Polytechnic Institute and State University
More informationIntroduction to Nastran SOL 200 Design Sensitivity and Optimization
Introduction to Nastran SOL 200 Design Sensitivity and Optimization PRESENTED BY: CHRISTIAN APARICIO The Nastran Engineering SOL 200 questions? Lab Email me: christian@ the-engineering-lab.com Motivation
More informationConnecting Rod Shape Optimization Tutorial (AutoDesign)
Connecting Rod Shape Optimization Tutorial (AutoDesign) Copyright 2018 FunctionBay, Inc. All rights reserved. User and training documentation from FunctionBay, Inc. is subjected to the copyright laws of
More informationA Sequential, Multi-Complexity Topology Optimization Process for Aeroelastic Wing Structure Design
A Sequential, Multi-Complexity Topology Optimization Process for Aeroelastic Wing Structure Design Bill Crossley, crossley@purdue.edu Significant content from graduate student Mark Guiles and input from
More informationMSC.Nastran Structural Optimization Applications for Aerospace Structures
MSC.Nastran Structural Optimization Applications for Aerospace Structures Jack Castro Sr. Technical Representative/Boeing Technical manager Jack Castro Sr. Technical Representative/Boeing Technical manager
More informationEXACT BUCKLING SOLUTION OF COMPOSITE WEB/FLANGE ASSEMBLY
EXACT BUCKLING SOLUTION OF COMPOSITE WEB/FLANGE ASSEMBLY J. Sauvé 1*, M. Dubé 1, F. Dervault 2, G. Corriveau 2 1 Ecole de technologie superieure, Montreal, Canada 2 Airframe stress, Advanced Structures,
More informationThe Methods of Automated Synthesis of Finite Element Models of Bearing Elements of the Joint Area of the Center Wing with Cargo Aircraft Fuselage
Engineering and Technology 2015; 2(4): 192-201 Published online June 10, 2015 (http://www.aascit.org/journal/et) The Methods of Automated Synthesis of Finite Element Models of Bearing Elements of the Joint
More informationStructural Design Optimization of the SAR Plate Assembly Through Genetic Algorithm
Structural Design Optimization of the SAR Plate Assembly Through Genetic Algorithm Ezgi KIRMAN 1, Sergio RICCI 2, Giuseppe TORRACO 3, Claudio CAVALLERO 4 and Luca FATTORE 4 1 Politecnico di Milano - kirman.ezgi@gmail.com
More informationISSN: ISO 9001:2008 Certified International Journal of Engineering and Innovative Technology (IJEIT) Volume 2, Issue 3, September 2012
Mitigation Curves for Determination of Relief Holes to Mitigate Concentration Factor in Thin Plates Loaded Axially for Different Discontinuities Shubhrata Nagpal, S.Sanyal, Nitin Jain Abstract In many
More informationCost Functions in Machine Learning
Cost Functions in Machine Learning Kevin Swingler Motivation Given some data that reflects measurements from the environment We want to build a model that reflects certain statistics about that data Something
More informationIndustrial stakes and state of the art of aircraft broadband noise prediction
X-noise workshop N. Molin, T. Nodé-Langlois, A. Sengissen, Industrial stakes and state of the art of aircraft broadband noise prediction Outline Stakes of aircraft broadband noise prediction Airframe noise
More informationA sizing method for cylindrical grid-stiffened structures in composite material
A sizing method for cylindrical grid-stiffened structures in composite material G. Gatta & F. Romano Structural Design & Aeroelasticity Laboratory CIRA - Italian Aerospace Research Center, Italy Abstract
More informationDevelopment of an Object Oriented Data Model ADDAM for Applications in Aircraft Design
Development of an Object Oriented Data Model ADDAM for Applications in Aircraft Design MATLAB EXPO 2014 9 th July, Munich Fellow of Munich Aerospace e.v. Research Associate, Technical University of Munich
More informationBackward facing step Homework. Department of Fluid Mechanics. For Personal Use. Budapest University of Technology and Economics. Budapest, 2010 autumn
Backward facing step Homework Department of Fluid Mechanics Budapest University of Technology and Economics Budapest, 2010 autumn Updated: October 26, 2010 CONTENTS i Contents 1 Introduction 1 2 The problem
More informationLOCAL STRESS ANALYSIS OF STIFFENED SHELLS USING MSC/NASTRAN S SHELL AND BEAM p-elements
LOCAL STRESS ANALYSIS OF STIFFENED SHELLS USING MSC/NASTRAN S SHELL AND BEAM p-elements Sanjay Patel, Claus Hoff, Mark Gwillim The MacNeal-Schwendler Corporation Abstract In large finite element models
More informationModeling and Simulation for Aircraft Structural Repair Using Modern FEA Tools
Modeling and Simulation for Aircraft Structural Repair Using Modern FEA Tools December 19-22, 2011 and January 9-12, 2012 Kuang-Hua Chang, Ph.D. Williams Presidential Professor School of Aerospace and
More informationCNC Milling Machines Advanced Cutting Strategies for Forging Die Manufacturing
CNC Milling Machines Advanced Cutting Strategies for Forging Die Manufacturing Bansuwada Prashanth Reddy (AMS ) Department of Mechanical Engineering, Malla Reddy Engineering College-Autonomous, Maisammaguda,
More informationADVANCED ULTRASOUND WAVEFORM ANALYSIS PACKAGE FOR MANUFACTURING AND IN-SERVICE USE R. A Smith, QinetiQ Ltd, Farnborough, GU14 0LX, UK.
ADVANCED ULTRASOUND WAVEFORM ANALYSIS PACKAGE FOR MANUFACTURING AND IN-SERVICE USE R. A Smith, QinetiQ Ltd, Farnborough, GU14 0LX, UK. Abstract: Users of ultrasonic NDT are fundamentally limited by the
More informationBuckling design of axially compressed steel silos on discrete supports
Articles Arne Jansseune* Jan Belis Wouter De Corte DOI: 10.1002/stco.201810007 Buckling design of axially compressed steel silos on discrete supports Comparison between FE-calculated buckling strengths
More informationSingle and multi-point aerodynamic optimizations of a supersonic transport aircraft using strategies involving adjoint equations and genetic algorithm
Single and multi-point aerodynamic optimizations of a supersonic transport aircraft using strategies involving adjoint equations and genetic algorithm Prepared by : G. Carrier (ONERA, Applied Aerodynamics/Civil
More informationSupervised vs. Unsupervised Learning
Clustering Supervised vs. Unsupervised Learning So far we have assumed that the training samples used to design the classifier were labeled by their class membership (supervised learning) We assume now
More informationEN 10211:2007 validation of Therm 6.3. Therm 6.3 validation according to EN ISO 10211:2007
Therm 6.3 validation according to EN ISO 10211:2007 Therm 6.3 validation according to NBN EN ISO 10211:2007 eneral considerations and requirements for validation of calculation methods according to NBN
More informationInternational Journal of Mechanical Civil and Control Engineering. Vol. 1, Issue. 3, June 2015 ISSN (Online):
Design Evolution of a Typical Aircraft Engine Mount Bracket Using FE Based Optimisation Technique Revanasidda Benur 1 and Akshatha H T 2 1 former project trainee, 2 Senior Scientist, Centre for Civil Aircraft
More informationA MODELING METHOD OF CURING DEFORMATION FOR CFRP COMPOSITE STIFFENED PANEL WANG Yang 1, GAO Jubin 1 BO Ma 1 LIU Chuanjun 1
21 st International Conference on Composite Materials Xi an, 20-25 th August 2017 A MODELING METHOD OF CURING DEFORMATION FOR CFRP COMPOSITE STIFFENED PANEL WANG Yang 1, GAO Jubin 1 BO Ma 1 LIU Chuanjun
More informationFOUNDATION IN OVERCONSOLIDATED CLAY
1 FOUNDATION IN OVERCONSOLIDATED CLAY In this chapter a first application of PLAXIS 3D is considered, namely the settlement of a foundation in clay. This is the first step in becoming familiar with the
More informationANALYSIS OF A STRINGER RUN-OUT CONCEPT INCLUDING DAMAGE INITIATION AND EVOLUTION AT THE INTERFACES
ANALYSIS OF A STRINGER RUN-OUT CONCEPT INCLUDING DAMAGE INITIATION AND EVOLUTION AT THE INTERFACES A. Blázquez 1, J. Reinoso 1, F. París 1, A. Estefani 1, E. Arévalo 2, F. Cruz 3 1 Group of Elasticity
More informationinter.noise 2000 The 29th International Congress and Exhibition on Noise Control Engineering August 2000, Nice, FRANCE
Copyright SFA - InterNoise 2000 1 inter.noise 2000 The 29th International Congress and Exhibition on Noise Control Engineering 27-30 August 2000, Nice, FRANCE I-INCE Classification: 2.4 NORD 2000. STATE-OF-THE-ART
More informationSummary of New DARWIN TM Capabilities for Surface Damage Tolerance Assessment and Related Enhancements
Summary of New DARWIN TM Capabilities for Surface Damage Tolerance Assessment and Related Enhancements Mike Enright, Luc Huyse, Yi-Der Lee, Graham Chell, Craig McClung, Gerald Leverant Southwest Research
More informationApplication of shape optimization method to artificial leaf design
Design and Nature VI 157 Application of shape optimization method to artificial leaf design M. Shimoda1 & Y. Nakata2 1 Department of Advanced Science and Technology, Toyota Technological Institute, Japan
More informationModel Set up, Analysis and Results of the Inverse Forming Tool in ANSA
Model Set up, Analysis and Results of the Inverse Forming Tool in ANSA Evlalia Iordanidou, Georgios Mokios BETA CAE Systems SA Abstract With an ongoing aim to reduce the time a model requires to be prepared,
More informationThe new HyperMesh - Samcef interface.
The new HyperMesh - Samcef interface. Deployment and industrial applications at Eurocopter. Ronan PITOIS Dynamic systems dpt. Presentation plan Eurocopter overview Stress computation performed in Eurocopter
More informationStatus of Gradient-based Airframe MDO at DLR The VicToria Project
DLR.de Chart 1 Status of Gradient-based Airframe MDO at DLR The VicToria Project M. Abu-Zurayk, C. Ilic, A. Merle, A. Stück, S. Keye, A. Rempke (Institute of Aerodynamics and Flow Technology) T. Klimmek,
More information[1] involuteσ(spur and Helical Gear Design)
[1] involuteσ(spur and Helical Gear Design) 1.3 Software Content 1.3.1 Icon Button There are 12 icon buttons: [Dimension], [Tooth Form], [Accuracy], [Strength], [Sliding Graph], [Hertz Stress Graph], [FEM],
More informationDigital-X. Towards Virtual Aircraft Design and Testing based on High-Fidelity Methods - Recent Developments at DLR -
Digital-X Towards Virtual Aircraft Design and Testing based on High-Fidelity Methods - Recent Developments at DLR - O. Brodersen, C.-C. Rossow, N. Kroll DLR Institute of Aerodynamics and Flow Technology
More informationTopology and Topometry Optimization of Crash Applications with the Equivalent Static Load Method
Topology and Topometry Optimization of Crash Applications with the Equivalent Static Load Method Katharina Witowski*, Heiner Müllerschön, Andrea Erhart, Peter Schumacher, Krassen Anakiev DYNAmore GmbH
More informationStress Concentration Factors
CONSEIL INTERNATIONAL DES MACHINES A COMBUSTION INTERNATIONAL COUNCIL ON COMBUSTION ENGINES CO-ORDINATING WORKING GROUP "CLASSIFICATION SOCIETIES DIESEL" (WG2) Proposal by CIMAC WG4 11th May 2012 IACS
More informationOPTICAL TOOL FOR IMPACT DAMAGE CHARACTERIZATION ON AIRCRAFT FUSELAGE
OPTICAL TOOL FOR IMPACT DAMAGE CHARACTERIZATION ON AIRCRAFT FUSELAGE N.Fournier 1 F. Santos 1 - C.Brousset 2 J.L.Arnaud 2 J.A.Quiroga 3 1 NDT EXPERT, 2 AIRBUS France, 3 Universidad Cmplutense de Madrid
More informationBUCKLING AND POSTBUCKLING ANALYSIS OF A CFRP STIFFENED PANEL FOR A BETTER MATERIAL EXPLOITATION
BUCKLING AND POSTBUCKLING ANALYSIS OF A CFRP STIFFENED PANEL FOR A BETTER MATERIAL EXPLOITATION Richard DEGENHARDT 1 Jean-Pierre DELSEMME 2 1 DLR, Institute of Structural Mechanics, Braunschweig, Germany
More informationExample 24 Spring-back
Example 24 Spring-back Summary The spring-back simulation of sheet metal bent into a hat-shape is studied. The problem is one of the famous tests from the Numisheet 93. As spring-back is generally a quasi-static
More informationModeling Strategies for Dynamic Finite Element Cask Analyses
Session A Package Analysis: Structural Analysis - Modeling Modeling Strategies for Dynamic Finite Element Cask Analyses Uwe Zencker, Günter Wieser, Linan Qiao, Christian Protz BAM Federal Institute for
More informationIntegrated FEM-based. package for Fatigue and Damage Tolerance - SAFE
Integrated FEM-based package for Fatigue and Damage Tolerance - SAFE Emmanuelle ALIOS Jean-Pascal KLEINERMANN 1 Content Introduction Airbus France tool : SAFE General overview Assessment of initiation
More informationLS-OPT : New Developments and Outlook
13 th International LS-DYNA Users Conference Session: Optimization LS-OPT : New Developments and Outlook Nielen Stander and Anirban Basudhar Livermore Software Technology Corporation Livermore, CA 94588
More informationThe Role of Finite Element Analysis in Light Aircraft Design and Certification
The Role of Finite Element Analysis in Light Aircraft Design and Certification Nigel Bamber Wey Valley Aeronautics Ltd www.weyvalleyaero.co.uk Engineering Consultancy Civil and Military Aerospace and Motorsport
More informationMetal 3D Printing. - Design for Metal 3D Printing - 10th October 2018
Metal 3D Printing - Design for Metal 3D Printing - 10th October 2018 Agenda 1. Short Introduction Materialise 2. Design for Manufacturing / M3DP 3. General Design Process 4. Topology Optimization 5. Example
More information1. Introduction. performance of numerical methods. complexity bounds. structural convex optimization. course goals and topics
1. Introduction EE 546, Univ of Washington, Spring 2016 performance of numerical methods complexity bounds structural convex optimization course goals and topics 1 1 Some course info Welcome to EE 546!
More informationSIZE PRESERVING MESH GENERATION IN ADAPTIVITY PROCESSES
Congreso de Métodos Numéricos en Ingeniería 25-28 junio 2013, Bilbao, España c SEMNI, 2013 SIZE PRESERVING MESH GENERATION IN ADAPTIVITY PROCESSES Eloi Ruiz-Gironés 1, Xevi Roca 2 and Josep Sarrate 1 1:
More informationFree-Form Shape Optimization using CAD Models
Free-Form Shape Optimization using CAD Models D. Baumgärtner 1, M. Breitenberger 1, K.-U. Bletzinger 1 1 Lehrstuhl für Statik, Technische Universität München (TUM), Arcisstraße 21, D-80333 München 1 Motivation
More information4-2 Quasi-Static Fatigue
1 4-2 Quasi-Static Fatigue Case Description: Example Location: Composite coupon subject to tensile cyclic loading Tutorials > Fatigue > Quasi Static Fatigue Model Description: Nodes: 261; Elements: 224
More informationSIMULATION CAPABILITIES IN CREO. Enhance Your Product Design with Simulation & Analysis
SIMULATION CAPABILITIES IN CREO Enhance Your Product Design with Simulation & Using digital prototypes to understand how your designs perform in real-world conditions is vital to your product development
More informationComposite Optimisation of an F1 Front Wing
Composite Optimisation of an F1 Front Wing Jonathan Heal Senior Stress Engineer, McLaren Racing Ltd McLaren Technology Centre, Chertsey Rd, Woking. GU21 4YH Jonathan.heal@mclaren.com Abstract Formula one
More informationINTERPRETATION OF CROP CIRCLE PATTERNS
ERIC INTERPRETATION OF CROP CIRCLE PATTERNS Brian Tunstall Key words: Perfield Abstract Diagrams and images of selected crop circle patterns are interpreted in relation knowledge of design requirements
More informationECS289: Scalable Machine Learning
ECS289: Scalable Machine Learning Cho-Jui Hsieh UC Davis Sept 22, 2016 Course Information Website: http://www.stat.ucdavis.edu/~chohsieh/teaching/ ECS289G_Fall2016/main.html My office: Mathematical Sciences
More informationOPTIMIZATION OF STIFFENED PANEL WITH THE HELP OF MATHEMATICAL PROGRAMMING EXPERIMENTAL VERIFICATION
6 TH INTERNATIONAL CONGRESS OF THE AERONAUTICAL SCIENCES OPTIMIZATION OF STIFFENED PANEL WITH THE HELP OF MATHEMATICAL PROGRAMMING Prof. Ing. Antonín Píštěk, CSc. *, Ing. Miroslav Pešák* * Brno University
More informationThe optimisation of shot peen forming processes
The optimisation of shot peen forming processes T. Wang a, M.J. Platts b, J. Wu c a School of Engineering and Design, Brunel University, Uxbridge UB8 3PH, U. b Department of Engineering, University of
More informationLearning and Inferring Depth from Monocular Images. Jiyan Pan April 1, 2009
Learning and Inferring Depth from Monocular Images Jiyan Pan April 1, 2009 Traditional ways of inferring depth Binocular disparity Structure from motion Defocus Given a single monocular image, how to infer
More informationFinite Element Method. Chapter 7. Practical considerations in FEM modeling
Finite Element Method Chapter 7 Practical considerations in FEM modeling Finite Element Modeling General Consideration The following are some of the difficult tasks (or decisions) that face the engineer
More informationLoads Analysis and Structural Optimization - A Parameterized and Integrated Process
DLR.de Chart 1 Loads Analysis and Structural Optimization - A Parameterized and Integrated Process Thomas Klimmek (AE), Thiemo Kier (SR), Andreas Schuster (FA), Tobias Bach (FA), and Dieter Kohlgrüber
More informationVisualization of errors of finite element solutions P. Beckers, H.G. Zhong, Ph. Andry Aerospace Department, University of Liege, B-4000 Liege, Belgium
Visualization of errors of finite element solutions P. Beckers, H.G. Zhong, Ph. Andry Aerospace Department, University of Liege, B-4000 Liege, Belgium Abstract The aim of this paper is to show how to use
More informationVisual Analysis of Lagrangian Particle Data from Combustion Simulations
Visual Analysis of Lagrangian Particle Data from Combustion Simulations Hongfeng Yu Sandia National Laboratories, CA Ultrascale Visualization Workshop, SC11 Nov 13 2011, Seattle, WA Joint work with Jishang
More informationIntroduction to the Finite Element Method (3)
Introduction to the Finite Element Method (3) Petr Kabele Czech Technical University in Prague Faculty of Civil Engineering Czech Republic petr.kabele@fsv.cvut.cz people.fsv.cvut.cz/~pkabele 1 Outline
More informationNUMERICAL DESIGN OPTIMISATION OF A COMPOSITE REACTION LINK
THE 19 TH INTERNATIONAL CONFERENCE ON COMPOSITE MATERIALS NUMERICAL DESIGN OPTIMISATION OF A COMPOSITE REACTION LINK Y. Yang*, C. Schuhler, T. London, C. Worrall TWI Ltd, Granta Park, Cambridge CB21 6AL
More informationDesign and optimisation of an Ariane 5 LOX line cover Mode-tracking in B2000
Design and optimisation of an Ariane 5 LOX line cover Mode-tracking in B2000 R.J.C. Creemers Nationaal Lucht- en Ruimtevaartlaboratorium National Aerospace Laboratory NLR Design and optimisation of an
More informationDevelopment of Lightweight Engine Mounting Cross Member
Development of Lightweight Engine Mounting Cross Member Nitin Babaso Bodhale Team Lead Tata Technologies Ltd Pimpri Pune-411018, India. nitin.bodhale@tatatechnologies.com Jayeshkumar Raghuvanshi Sr. Team
More informationModelling Flat Spring Performance Using FEA
Modelling Flat Spring Performance Using FEA Blessing O Fatola, Patrick Keogh and Ben Hicks Department of Mechanical Engineering, University of Corresponding author bf223@bath.ac.uk Abstract. This paper
More informationMarch 5-8, 2017 Hilton Phoenix / Mesa Hotel Mesa, Arizona Archive Session 7
March 5-8, 2017 Hilton Phoenix / Mesa Hotel Mesa, Arizona Archive Session 7 2017 BiTS Workshop Image: tonda / istock Copyright Notice The presentation(s)/poster(s) in this publication comprise the Proceedings
More informationRecent Developments in the Design and Optimization of Constant Force Electrical Contacts
Recent Developments in the Design and Optimization of Constant orce Electrical Contacts John C. Meaders * Stephen P. Harston Christopher A. Mattson Brigham Young University Provo, UT, 84602, USA Abstract
More informationKeywords: Multi-level optimization, BLISS, least-squares, mixture of experts
27 TH INTERNATIONAL CONGRESS OF THE AERONAUTICAL SCIENCES SURROGATE MODELLING FOR EFFICIENT DESIGN OPTIMIZATION OF COMPOSITE AIRCRAFT FUSELAGE PANELS W.J. Vankan*, R. Maas* * National Aerospace Laboratory
More informationCHAPTER 1. Introduction
ME 475: Computer-Aided Design of Structures 1-1 CHAPTER 1 Introduction 1.1 Analysis versus Design 1.2 Basic Steps in Analysis 1.3 What is the Finite Element Method? 1.4 Geometrical Representation, Discretization
More informationAn Optimization Method Based On B-spline Shape Functions & the Knot Insertion Algorithm
An Optimization Method Based On B-spline Shape Functions & the Knot Insertion Algorithm P.A. Sherar, C.P. Thompson, B. Xu, B. Zhong Abstract A new method is presented to deal with shape optimization problems.
More informationThermal Design Guide for Socket SP3 Processors
Thermal Design Guide for Socket SP3 Processors Publication # 55423 Rev: 3.00 Issue Date: November 2017 2017 Advanced Micro Devices, Inc. All rights reserved. The information contained herein is for informational
More information"The real world is nonlinear"... 7 main Advantages using Abaqus
"The real world is nonlinear"... 7 main Advantages using Abaqus FEA SERVICES LLC 6000 FAIRVIEW ROAD, SUITE 1200 CHARLOTTE, NC 28210 704.552.3841 WWW.FEASERVICES.NET AN OFFICIAL DASSAULT SYSTÈMES VALUE
More information1.2 Numerical Solutions of Flow Problems
1.2 Numerical Solutions of Flow Problems DIFFERENTIAL EQUATIONS OF MOTION FOR A SIMPLIFIED FLOW PROBLEM Continuity equation for incompressible flow: 0 Momentum (Navier-Stokes) equations for a Newtonian
More informationInfluence of geometric imperfections on tapered roller bearings life and performance
Influence of geometric imperfections on tapered roller bearings life and performance Rodríguez R a, Calvo S a, Nadal I b and Santo Domingo S c a Computational Simulation Centre, Instituto Tecnológico de
More informationPlasticity Bending Machine Tutorial (FFlex)
Plasticity Bending Machine Tutorial (FFlex) Copyright 2018 FunctionBay, Inc. All rights reserved. User and training documentation from FunctionBay, Inc. is subjected to the copyright laws of the Republic
More informationAISIBEAM User's Manual (Version 3.0)
AISIBEAM User's Manual (Version 3.0) Shabin Taavoni, Ph.D., PE, title Structural Software Inc. location John C. Huang Ph.D., PE, Principal CHC Engineering, LLC Herndon, VA Scope of Software The software
More informationKeywords: Aerospace, Structures, Modelling, Verification, Validation, Guided Waves.
8th European Workshop On Structural Health Monitoring (EWSHM 2016), 5-8 July 2016, Spain, Bilbao www.ndt.net/app.ewshm2016 More info about this article: http://www.ndt.net/?id=20062 Elastic Waves Simulation
More informationKEYWORDS non-linear FE analysis, pre-processing, decohesion, buckling.
NON-LINEAR MULTI-SCALE ANALYSIS OF AEROSPACE STRUCTURES Orlin Mintchev, Reinhard Diez LASSO Ingenieurgesellschaft, Leinfelden-Echterdingen, Germany KEYWORDS non-linear FE analysis, pre-processing, decohesion,
More informationSecond-order shape optimization of a steel bridge
Computer Aided Optimum Design of Structures 67 Second-order shape optimization of a steel bridge A.F.M. Azevedo, A. Adao da Fonseca Faculty of Engineering, University of Porto, Porto, Portugal Email: alvaro@fe.up.pt,
More informationIntroduction to Abaqus. About this Course
Introduction to Abaqus R 6.12 About this Course Course objectives Upon completion of this course you will be able to: Use Abaqus/CAE to create complete finite element models. Use Abaqus/CAE to submit and
More information