COPYRIGHT DASSAULT SYSTEMES FEM Surface CATIA Training Exercises Version 5 Release 8 March 2002 EDU-CAT-E-FMS-FX-V5R8
COPYRIGHT DASSAULT SYSTEMES Table of Contents 1. Meshing of Parametric Conceptual Bodyp.3 Creating a mesh according to specificationsp.6 Modify and update an existing meshp.8 Analyze Mesh Qualityp.10 Static Analysis Performancep Floor Meshp Fuselage Door Static Analysisp Spot welding Analysisp.19 Analysis connectionsp.22 Meshingp.24 Boundary conditions and Weld PointsP.26 Analysis and Post-Processingp Meshing of a Wing Structurep.31 Ribs meshingp.34 Spars and central box meshingp.36 Skins meshingp.38 Pressure with Data Mappingp.40 Static Analysis and Post-Processingp.42 Hints and Tipsp.45
COPYRIGHT DASSAULT SYSTEMES Master Exercise Meshing of Parametric Conceptual Body In this exercise you will perform a shell meshing on a conceptual body, update it after design modification and realize a quality analysis. You will use : Mesh Definition Tools Mesh Specification Tools Mesh Modification Tools Quality Analysis Tools Pre-processing Analysis 60 min.
COPYRIGHT DASSAULT SYSTEMES Design Intent: Meshing of Parametric Conceptual Body Visualize Static Pre-Processing Elements on Mesh Create and Name Static Analysis Define meshing specifications Mesh the part Perform geometric modifications and update the mesh Analyse elements quality Modify the mesh Perform a torsional stiffness analysis
COPYRIGHT DASSAULT SYSTEMES Design Process : Meshing of Parametric Conceptual Body Create a mesh according to global parameters and specifications 1 Modify the geometry and update the mesh 2 Perform a mesh modification 3 Quality Analysis 4 Torsionnal Stifness Analysis 5
COPYRIGHT DASSAULT SYSTEMES Master Exercise Meshing of Parametric Conceptual Body: Creating a mesh according to specifications In this step you will : create a new surface mesh object save the analysis document 15 min.
COPYRIGHT DASSAULT SYSTEMES Do It Yourself Visualize how the restraints defined on the assembly are translated onto the mesh Creating a mesh according to specifications : Enter in the Advanced Meshing Tools workbench Create a new static case Create a new surface mesh (use quadrangle frontal method, mesh size = 20mm, maximum sag = 1.5mm and details simplification minimum size = 5mm) Remove the two smallest holes and the two gaps Define edge constraints and node distributions Create the mesh Load: CATFMSParametric_Pillar.CATPart
COPYRIGHT DASSAULT SYSTEMES Master Exercise Meshing of Parametric Conceptual Body: Modify and update an existing mesh In this step you will : modify the geometry update the mesh directly modify it again. 15 min.
COPYRIGHT DASSAULT SYSTEMES Do It Yourself Modify and update an existing mesh : Modify a pillar section (BiW / Detailed / B_Pillar / Section / Sketch.2, replace dimension 17 mm by 19 mm) Update the geometry and the corresponding mesh Remesh a domain Load: CATFMSParametric_Pillar.CATAnalysis
COPYRIGHT DASSAULT SYSTEMES min. Master Exercise Meshing of Parametric Conceptual Body : Analyse Mesh Quality In this step you will : analyze the mesh quality edit an analysis report.
COPYRIGHT DASSAULT SYSTEMES Do It Yourself Analyse Mesh Quality : Analyse the mesh quality Edit an analysis report Modify the mesh in order to increase its quality Load: CATFMSParametric_Pillar.CATAnalysis
COPYRIGHT DASSAULT SYSTEMES Master Exercise Meshing of Parametric Conceptual Body : Static Analysis performance In this step you will perform a torsionnal stiffness analysis. 15 min.
COPYRIGHT DASSAULT SYSTEMES Do It Yourself Static Analysis Performance : Create a surface mesh Perform a torsionnal stiffness analysis by applying Clamps, rigid virtual Part and a moment of 500 N.m on the rigid virtual Part. Enter a thick of 2 mm for elements Compute and display the displacements Load: CATFMSParametric_Pillar.CATPart
COPYRIGHT DASSAULT SYSTEMES Creating a mesh according to specifications Create a new surface mesh object. Remove holes and gaps. Define edge constraints and node distributions. Create the mesh. Modify and update an existing mesh Modify the geometry. Update the geometry and the mesh. Remesh a domain. Analyze Mesh Quality Analyse the mesh quality. Edit an analysis report. Modify the mesh to increase quality. Static Analysis Performance Perform a torsionnal stiffness analysis. Compute and display the displacements. Fundamental Steps
COPYRIGHT DASSAULT SYSTEMES Additional Exercise Step (1): Floor Mesh In this exercise, you will create a surface mesh on a part. 20 min.
COPYRIGHT DASSAULT SYSTEMES Design Intent: Floor Mesh Create the Surface mesh of this part by using a mesh size of 15 mm and a maximum sag of 1 mm. Modify just the indicated domain and remesh it with Mapped quads mesh method and with a mesh size of 10mm. Load: FMS_AddEx_1. CATPart Remesh this domain
COPYRIGHT DASSAULT SYSTEMES Additional Exercise Step (2): Fuselage door Static Analysis In this exercise, you will create a surfacic mesh on the fuselage and create a static analysis. 30 min.
COPYRIGHT DASSAULT SYSTEMES Design Intent: Fuselage Door Static Analysis Create the Surface mesh of this part by using a mesh size of 35 mm and a maximum sag of 2 mm. Modify the mesh around the door and for each hole by using a thinest surface mesh of 15 mm. Apply Clamps all around the part, apply a pressure of 5000 N/m2 only on the door and then compute all the structure. Display the Von Mises constraints. Change the thickness of the part from 2 mm to 5 mm and display the new Von Mises constraints. Displacements Load: FMS_AddEx_2. CATPart Part Thick
COPYRIGHT DASSAULT SYSTEMES Exercise Spot Welding Analysis In this exercise you will perform a Spot Welding meshing and static analysis. You will use : Analysis connections Mesh Definition Tools Static Analysis Post-processing 60 min.
COPYRIGHT DASSAULT SYSTEMES Load: Soudure.CATProduct Design Intent: Spot Welding Analysis Create analysis welding points connections. Mesh all the structure with FMS tools. Apply boundary conditions and spot welding connections. Perform a static analysis. Post-processing : point force vectors.
COPYRIGHT DASSAULT SYSTEMES Surfacic meshing Apply analysis connections on the assembly 1 2 Apply Boundary conditions and Spot Welding Connections 3 Post-Processing 4 Design Process : Spot Welding Analysis
COPYRIGHT DASSAULT SYSTEMES min. Master Exercise Spot Welding Analysis : Analysis connections In this step you will : Apply analysis welding point connections Save the product document
COPYRIGHT DASSAULT SYSTEMES Load: Soudure.CATPart A set of points must be in a single Open Body ! Fillet.2 and extrude.1 are the two parts welded ( Stiffener and Part1), OpenBody2 and 3 are the two sets of welding spots. Do It Yourself Choose New Welding Point Connection creation. Select Part1 Fillet.2 as first surface. Select OpenBody1 Extrude.1 as second surface. Select OpenBody2 points as welding spots. Repeat the same sequence changing OpenBody2 by OpenBody3.
COPYRIGHT DASSAULT SYSTEMES min. Master Exercise Spot Welding Analysis : Surfacic meshing In this step you will Mesh the assembly surfaces and use FMS mesh tools.
COPYRIGHT DASSAULT SYSTEMES Do It Yourself Enter the Advanced Meshing Tools workbench : static analysis. Mesh Stiffener : Select Surface Mesher icon. Choose the Stiffener part and triangular element shape. Enter a 150 mm Mesh size and a 20 mm Constraint sag. Validate. Select mesh icon and exit. Mesh Part1 : Repeat the sequence for the Part1, but enter a 250 mm Mesh size and choose quadrangle element shape.
COPYRIGHT DASSAULT SYSTEMES min. Master Exercise Spot Welding Analysis : Boundary conditions and Weld points connections In this step you will : Apply clamp and distributed load. Apply Spot Welding connections.
COPYRIGHT DASSAULT SYSTEMES Do It Yourself Enter the Generative Structural Analysis workbench. Apply clamp on a Part1 side. Apply a 500 N distributed force on the opposite middle edge side along Z axis. Select Spot Welding connection icon : Select Spot Welding Analysis Connection.1 in the tree. Repeat with Spot Welding Analysis Connection.2.
COPYRIGHT DASSAULT SYSTEMES min. Master Exercise Spot Welding Analysis : Analysis and Post-Processing In this step you will : Compute a static analysis. Visualize Von Mises Stresses. Show Point force vectors.
COPYRIGHT DASSAULT SYSTEMES Do It Yourself Launch a static analysis. Visualize Von Mises stresses, then deactivate. Contextual menu on Static Case Solution : Choose Generate Image. Choose Point force vector. Double click on Point force vector : Select Weld Spot Connection Mesh 1&2. In Filters, select Node of element. In Symbol, adjust the vectors size.
COPYRIGHT DASSAULT SYSTEMES Fundamental Steps Analysis connections Apply analysis welding point connections. Surfacic meshing Use of FMS mesh definition tools. Boundary conditions and Spot Welding connections Apply clamp and distributed load. Apply Spot Welding connections from Analysis connections. Analysis and Post-Processing Launch a static analysis. Visualize Von Mises Stresses. Visualize Point force vectors.
COPYRIGHT DASSAULT SYSTEMES min. Master Exercise Meshing of a Wing Structure In this exercise you will perform a Wing Structure meshing and static analysis. You will use : Mesh definition Mesh specifications Pressure with Data Mapping Static Analysis Post-processing
COPYRIGHT DASSAULT SYSTEMES Load: Simplified_wing_R8. CATProduct Design Intent: Meshing of a Wing Structure Ribs meshing. Spars and central box meshing. Skins meshing. Apply Pressure with Data mapping. Static Analysis and Post-Processing.
COPYRIGHT DASSAULT SYSTEMES Ribs meshing 1 Spars and central box meshing 2 Skins meshing 3 Pressure with Data Mapping 4 Static Analysis & Post-processing 5 Design Process : Meshing of a Wing Structure
COPYRIGHT DASSAULT SYSTEMES min. Master Exercise Meshing of a Wing Structure : Ribs Meshing In this step you will mesh the ribs parts.
COPYRIGHT DASSAULT SYSTEMES Do It Yourself Enter the Advanced Meshing Tools workbench. Put the skins in No Show mode. Select Surface Mesher icon : Select rib surface and choose quadrangle elements shape. Enter a 40mm Mesh size, and a 4mm Constraint sag. Select Mesh the part icon, then exit. Repeat the sequence for the second rib.
COPYRIGHT DASSAULT SYSTEMES min. Master Exercise Meshing of a Wing Structure : Spars and central box Meshing In this step you will : Mesh the spars surfaces. Remove constraints. Apply imposed nodes.
COPYRIGHT DASSAULT SYSTEMES First, select Surface Mesher icon. Select the spar surface. Enter a 40mm Mesh size, and a 4mm Constraint sag. 2.Then, select add/remove constraints icon. Select the connected rib edge. 3. Select Distribution nodes icon. Select Capture. Select the meshed rib edge. Set the Coincidence and Condensation options. Enter a sufficient tolerance (here 5 mm). 4. Select Mesh the part icon Exit. 5. Repeat for the others spars (just the capture step twice on each spar side). Good compatibility Do It Yourself
COPYRIGHT DASSAULT SYSTEMES min. Master Exercise Meshing of a Wing Structure : Skins Mesh In this step you will : Mesh the skins surfaces. Remove constraints. Apply imposed nodes.
COPYRIGHT DASSAULT SYSTEMES As for the ribs, you must select in the Capture window Coincidence and Condensation, and enter a sufficient tolerance (offset between edges) to ensure a compatible mesh. Do It Yourself Put the skins in Show mode. Select Surface Mesher and a Skin. Select Add/remove constraints icon, then select ribs and spars curves. Select Imposed nodes icon, then select capture and all edges in contact. Select Mesh the part, and exit. Repeat for the other skin.
COPYRIGHT DASSAULT SYSTEMES min. Master Exercise Meshing of a Wing Structure : Pressure with Data Mapping In this step you will : Apply clamps. Apply pressure with Data Mapping.
COPYRIGHT DASSAULT SYSTEMES Space coordinates of pressure experimental points. Amplification coefficient : at this point, the pressure value is 0.3*100 Pa. With Data Mapping, we are able to apply an un-uniform loading, closer to reality. Do It Yourself Enter the Generative Structural Analysis workbench. Put clamps on the fuselage connection edges. Apply a 100 Pa pressure on the skin and select Data mapping. Choose the Datamapping.xls file. After computation, Select Pressure Visualization on mesh with contextual menu on Pressure icon. Apply an opposite 35 Pa pressure on the second skin.
COPYRIGHT DASSAULT SYSTEMES min. Master Exercise Meshing of a Wing Structure : Static Analysis and Post- Processing In this step you will : Compute a static analysis. Visualize displacements and Von Mises stresses. Animate results.
COPYRIGHT DASSAULT SYSTEMES The maximum displacement is localized to the end of the wing, and the maximum Von Mises stress is near the clamp. Do It Yourself Compute a static analysis. Show displacements results. Animate the results. Show Von Mises stresses.
COPYRIGHT DASSAULT SYSTEMES Fundamental Steps Meshing Remove constraints. Imposed nodes / Capture. Coincidence, condensation and tolerance options. Mesh a part. Apply Pressure with Data Mapping Apply clamps. Apply a pressure. Enter Data Mapping. Static Analysis and Post-Processing Compute a static analysis. Visualize displacements and animation. Visualize Von Mises stresses.
COPYRIGHT DASSAULT SYSTEMES Hints and Tips Select applies customized view to visualize elements edges.