*Heading Compression Test using Axisymmetric model with analytical rigid surface as load. *Preprint, echo=NO, model=NO, history=NO, contact=NO ** ** ** ************************************************************************** ** UNITS: mm - MPa - N - kg ************************************************************************** ** ************************************************************************** ** MODEL DEFINITION **Include for each part: Node ** Elements ** Nset and Elset (Including Ref Point) ** Constraint equations ** Section Type (Solid, Rigid, etc.) ************************************************************************** *Part, name=Cylinder *Node 1, 0., 0. 2, 2.125, 0. 3, 4.25, 0. 4, 0., 2.53999996 5, 2.125, 2.53999996 6, 4.25, 2.53999996 7, 0., 5.07999992 8, 2.125, 5.07999992 9, 4.25, 5.07999992 10, 0., 7.61999989 11, 2.125, 7.61999989 12, 4.25, 7.61999989 13, 0., 10.1599998 14, 2.125, 10.1599998 15, 4.25, 10.1599998 16, 0., 12.6999998 17, 2.125, 12.6999998 18, 4.25, 12.6999998 19, 0., 15.2399998 20, 2.125, 15.2399998 21, 4.25, 15.2399998 22, 0., 17.7800007 23, 2.125, 17.7800007 24, 4.25, 17.7800007 25, 0., 20.3199997 26, 2.125, 20.3199997 27, 4.25, 20.3199997 28, 0., 22.8600006 29, 2.125, 22.8600006 30, 4.25, 22.8600006 31, 0., 25.3999996 32, 2.125, 25.3999996 33, 4.25, 25.3999996 *Element, type=CAX4R 1, 1, 2, 5, 4 2, 2, 3, 6, 5 3, 4, 5, 8, 7 4, 5, 6, 9, 8 5, 7, 8, 11, 10 6, 8, 9, 12, 11 7, 10, 11, 14, 13 8, 11, 12, 15, 14 9, 13, 14, 17, 16 10, 14, 15, 18, 17 11, 16, 17, 20, 19 12, 17, 18, 21, 20 13, 19, 20, 23, 22 14, 20, 21, 24, 23 15, 22, 23, 26, 25 16, 23, 24, 27, 26 17, 25, 26, 29, 28 18, 26, 27, 30, 29 19, 28, 29, 32, 31 20, 29, 30, 33, 32 ** ** Reference Point for the top part *Node, nset=CylRef 9999,0,0,0 ** *Nset, nset=Bottom, generate ** First N, Last N, Increment 1, 3, 1 *Nset, nset=Nall, generate 1, 33,1 *Nset, nset=Top, generate 31, 33, 1 *Nset, nset=Axis, generate 1, 31, 3 *Elset, elset=Nall, generate 1, 20, 1 *Elset, elset=Top, generate 19,20,1 **Constraint Equations for cylinder *Equation 2 Top,2,1.0,CylRef,2,-1.0 ** **Section Type *Solid Section, elset=Nall, material=Material_Whole *End Part ** *Part, name=Plana *Node, nset=PlRef 9999,0,0,0 **Specifying the analytical surface ** Contact face is defined depending on the start ** point. For this start line, the contact surface is below. If, instead, it was ** Start 0.,0. with Line 10.,0., then the contact surface would be above. (Use type=segments for analytical surface) *Surface, Type=segments, name=Plane_Surface Start, 10.,0. Line, 0.,0. *Rigid Body, Ref Node=PlRef, Analytical Surface=Plane_Surface *End Part ************************************************************************** ** ASSEMBLY ** Include : Part instance and positionning ** Surface Definitions ************************************************************************** *Assembly, name=Sample ** *Instance, name=Cylinder-1, part=Cylinder *End Instance ** *Instance, name=Plana-1, part=Plana **Translation from original position to place the plane 0.,25.4,0. *End Instance ** ** Surface definitions for the assembly. *Surface, Type=Element, name=Cylinder_Top Cylinder-1.Top,S3 ** *End Assembly *************************************************************************** ** ************************************************************************** ** MATERIAL DEFINITION ************************************************************************** *Material, name=Material_Whole *Elastic, Type=isotropic **Young, Poisson, 42E3, 0.33 ** *Plastic, Hardening=isotropic **Yield Stress, Plastic strain (Give at least 2 points) 320.8719, 0.0 338.7911, 0.0030 345.2682, 0.0049 349.2022, 0.0068 352.1135, 0.0087 354.6137, 0.0106 356.8812, 0.0125 359.0374, 0.0144 361.0348, 0.0163 363.0197, 0.0183 364.9139, 0.0202 366.8312, 0.0221 368.7173, 0.0239 370.4824, 0.0258 372.2715, 0.0277 373.9894, 0.0295 375.7299, 0.0314 377.3489, 0.0333 378.8942, 0.0351 380.6240, 0.0370 382.1343, 0.0388 383.5124, 0.0407 385.0787, 0.0425 386.3263, 0.0444 387.5978, 0.0462 388.9174, 0.0480 390.0584, 0.0499 391.1194, 0.0517 392.0746, 0.0535 393.0372, 0.0554 393.7202, 0.0572 394.3218, 0.0590 394.8415, 0.0609 395.0000, 0.0627 395.1104, 0.0645 *************************************************************************** ** Interaction properties and Interactions ************************************************************************** ** INTERACTION PROPERTIES *Surface Interaction, Name=Frictioneless **Offplane thickness (See reference manual) 1. ** Define the friction parameters such as friction coefficient. Must be used with Surface Interaction *Friction 0. ** INTERACTIONS *Contact Pair, Interaction=Frictioneless, Type= surface to surface, Tracking=state **Slave surface, Master surface Cylinder_Top, Plana-1.Plane_Surface ** ************************************************************************** ** Boundary Conditions ************************************************************************** **Symmetry Condition *Boundary Sample.Cylinder-1.Bottom, YSYMM **Rigid Body Motion *Boundary ** Node, First D, Last D Sample.Cylinder-1.Axis,1,1 ** **Initialize the plane *Boundary Sample.Plana-1.PlRef,1,2 *Boundary Sample.Plana-1.PlRef,6,6 ** ************************************************************************** ** Step 1 - Plane moving down ************************************************************************** *Step, Name=loading, Amplitude=ramp, Inc=100 *Static **Initial, Total, Min, Max 1E-1,5,1e-3,5e-1 ** *Boundary, Type=displacement Sample.Plana-1.PlRef,2,2,-1.5 *************************************************************************** *Output, Field *Node Output, nset=Cylinder-1.Nall u *Element Output, elset=Cylinder-1.Nall S, E *Element Output, elset=Cylinder-1.Top S, E ** *Output, History ** The individual components are extracted in the History Output *Node Output, nset=Cylinder-1.CylRef u2,rf2 *Node Output, nset=Plana-1.PlRef u2,rf2 ** *Element Output, elset=Cylinder-1.Top S22,E22 ** *End Step **