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Lab 2 Experiment No ALLLab 2 Experiment No ALL
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Experiment No. 1
Problem Definition: Analysis of Inertia Force in Slider Crank Mechanism Using Computer Software.
% Programme For Slider Crank Mechanismfunction slidercrank1()clc;
fprintf('\nINPUT\n');
N=input('Engine Speed, N (rpm) : ');l=input('Length between centres, l (mm): ');l2=input('Dist between centres of mass, l2 (mm): ');m=input('Mass of connecting rod, m (kg): ');mr=input('Mass of reciprocating parts, mr (kg): ');r=input('Crank length, r (mm): ');theta=input('Crank angle, Theta (Deg) : ');k=input('Radius of Gyration, k (mm) : ');
fprintf('\nOUTPUT');
% Angular Velocityw=2*pi*N/60;fprintf('\nAngular Velocity, w = %f rad/s\n',w);
% Mass at Crank Pinl1=l-l2;mi=m*l2/(l1+l2);Mr=mr+mi;fprintf('\nMass at Crank Pin, Mr = %d kg',Mr);
theta_rad=theta*pi/180;
% l/r Ration=l/r;fprintf('\nl/r Ratio, n = %f',n);
%Acceleration of Reciprocating Partsf=r/1000*w^2*(cos(theta_rad)+cos(2*theta_rad)/n);fprintf('\nAcceleration of Reciprocating Parts, f = %f m/s^2',f);
% Inertia ForceFi=Mr*f;fprintf('\nInertia Force, Fi = %f N',Fi);
% Inertia TorqueTi=Fi*r/1000*(sin(theta_rad)+sin(2*theta_rad)/(2*(n^2-(sin(theta_rad))^2)^(1/2)));fprintf('\nInertia Torque Due to Reciprocating Parts, Ti = %f N.m\n',Ti);
L=l1+(k^2)/l1;alpha=(-1)*w^2*sin(theta_rad)*((n^2-1)/((n^2-(sin(theta_rad))^2)^(3/2)));
fprintf('\nl1 = %d mm',l1);fprintf('\nL = %f mm\n',L);fprintf('\nalpha = %f rad/s^2\n',alpha);
% Correction CoupledT=m*alpha*l1/1000*(l-L)/1000;fprintf('\nCorrection Couple, dT = %f N.m/n',dT);
% Correction Torque on CrankshaftTc=dT*cos(theta_rad)/(n^2-(sin(theta_rad))^2)^(1/2);fprintf('\nCorrection Torque on Crankshaft, Tc = %f N.m',Tc);
% Torque due to Weight of Mass at Crank Ping=9.81;m2=m-mi;Ta=m2*g*r*cos(theta_rad)/1000;fprintf('\nTorque Due to Weight of Mass at Crank Pin, Ta = %f N.m',Ta);
% Total Inertia Torque on CrankshaftT=Ti-Tc+Ta;fprintf('\nTotal Inertia Torque on Crankshaft, T = %f N.m\n\n',T);
for theta=0:20*pi/180:2*pi; f=r/1000*w^2*(cos(theta)+cos(2*theta)/n); Fi=Mr*f; Ti=Fi*r/1000*(sin(theta)+sin(2*theta)/(2*(n^2-(sin(theta))^2)^(1/2))); L=l1+(k^2)/l1; alpha=(-1)*w^2*sin(theta)*((n^2-1)/((n^2-(sin(theta))^2)^(3/2))); dT=m*alpha*l1/1000*(l-L)/1000; Tc=dT*cos(theta)/(n^2-(sin(theta))^2)^(1/2); g=9.81; m2=m-mi; Ta=m2*g*r*cos(theta)/1000; T=Ti-Tc+Ta; thetad= theta*180/pi; fprintf('\nTheta = %f Deg',thetad); fprintf('\tT = %f N.m',T); end for theta=0:0.001:2*pi; f=r/1000*w^2*(cos(theta)+cos(2*theta)/n); Fi=Mr*f; Ti=Fi*r/1000*(sin(theta)+sin(2*theta)/(2*(n^2-(sin(theta))^2)^(1/2))); L=l1+(k^2)/l1; alpha=(-1)*w^2*sin(theta)*((n^2-1)/((n^2-(sin(theta))^2)^(3/2))); dT=m*alpha*l1/1000*(l-L)/1000; Tc=dT*cos(theta)/(n^2-(sin(theta))^2)^(1/2); g=9.81; m2=m-mi; Ta=m2*g*r*cos(theta)/1000; T=Ti-Tc+Ta; thetad= theta*180/pi; hold on plot (thetad,T,'r'); hold offend title('T-\theta Diagram');xlabel ('\theta [Deg]');ylabel ('T(N.m)');gridendINPUTEngine Speed, N (rpm) : 600Length between centres, l (mm): 450Dist between centres of mass, l2 (mm): 180Mass of connecting rod, m (kg): 90Mass of reciprocating parts, mr (kg): 120Crank length, r (mm): 90Crank angle, Theta (Deg) : 80Radius of Gyration, k (mm) : 150
OUTPUTAngular Velocity, w = 62.831853 rad/s
Mass at Crank Pin, Mr = 156 kgl/r Ratio, n = 5.000000Acceleration of Reciprocating Parts, f = -5.077442 m/s^2Inertia Force, Fi = -792.081014 NInertia Torque Due to Reciprocating Parts, Ti = -72.691161 N.m
l1 = 270 mmL = 353.333333 mm
alpha = -792.113864 rad/s^2
Correction Couple, dT = -1860.675467 N.m/nCorrection Torque on Crankshaft, Tc = -65.911711 N.mTorque Due to Weight of Mass at Crank Pin, Ta = 8.278955 N.mTotal Inertia Torque on Crankshaft, T = 1.499505 N.m
Theta = 0.000000 DegT = 47.676600 N.mTheta = 20.000000 DegT = 2376.265323 N.mTheta = 40.000000 DegT = 3182.214761 N.mTheta = 60.000000 DegT = 2091.243250 N.mTheta = 80.000000 DegT = 1.499505 N.mTheta = 100.000000 DegT = -1787.634693 N.mTheta = 120.000000 DegT = -2516.629612 N.mTheta = 140.000000 DegT = -2200.522564 N.mTheta = 160.000000 DegT = -1249.418507 N.mTheta = 180.000000 DegT = -47.676600 N.mTheta = 200.000000 DegT = 1159.815809 N.mTheta = 220.000000 DegT = 2127.477775 N.mTheta = 240.000000 DegT = 2468.953012 N.mTheta = 260.000000 DegT = 1771.076784 N.mTheta = 280.000000 DegT = 15.058405 N.mTheta = 300.000000 DegT = -2043.566650 N.mTheta = 320.000000 DegT = -3109.169972 N.mTheta = 340.000000 DegT = -2286.662625 N.mTheta = 360.000000 DegT = 47.676600 N.m>>
Result :-
Experiment No. 2
Problem Definition: Coupler Curve Synthesis for A Mechanism Using Computer Software.
INPUT% ProgrammeFor Coupler Curve SynthesisfunctionCoupler_Curve_Synthesis()clc;
%Inputst1=110; t2=77; t3=50;r1=80; r2=90; r3=96;a1=65; a2=56; a3=48;
%Angle Conversionst1=degtorad(t1); t2=degtorad(t2); t3=degtorad(t3);a1=degtorad(a1); a2=degtorad(a2); a3=degtorad(a3);
%Assuming Suitable Value of Angles Gamma=20 Deg, Si=10 Deg, Delta1=150 Deggg=degtorad(20); ss=degtorad(10); d1=degtorad(150);
for j=0:1:1if j==0 tt1=t1; tt2=t2; tt3=t3; dd=gg; sign=1;end
if j==1 a=x; g=y; e=z; b1=(acos((r1*cos(a1)-g*cos(gg)-a*cos(t1))/e)); b2=(acos((r2*cos(a2)-g*cos(gg)-a*cos(t2))/e)); b3=(acos((r3*cos(a3)-g*cos(gg)-a*cos(t3))/e)); d2=d1+(b2-b1); d3=d1+(b3-b1); tt1=d1; tt2=d2; tt3=d3; dd=ss; sign=-1;end
%Matrix For l l0=[2*r1*cos(tt1-a1) 2*r1*cos(a1-dd) 1;2*r2*cos(tt2-a2)... 2*r2*cos(a2-dd) 1;2*r3*cos(tt3-a3) 2*r3*cos(a3-dd) 1]; l1=[r1^2 2*r1*cos(a1-dd) 1;r2^2 2*r2*cos(a2-dd) 1;r3^2 2*r3*cos(a3-dd) 1]; l2=[2*r1*cos(tt1-a1) r1^2 1;2*r2*cos(tt2-a2) r2^2 1;2*r3*cos(tt3-a3) r3^2 1]; l3=[2*r1*cos(tt1-a1) 2*r1*cos(a1-dd) r1^2;2*r2*cos(tt2-a2)... 2*r2*cos(a2-dd) r2^2;2*r3*cos(tt3-a3) 2*r3*cos(a3-dd) r3^2];
%matrix for m m0=[2*r1*cos(tt1-a1) 2*r1*cos(a1-dd) 1;2*r2*cos(tt2-a2)... 2*r2*cos(a2-dd) 1;2*r3*cos(tt3-a3) 2*r3*cos(a3-dd) 1]; m1=[2*cos(tt1-dd) 2*r1*cos(a1-dd) 1;2*cos(tt2-dd)... 2*r2*cos(a2-dd) 1;2*cos(tt3-dd) 2*r3*cos(a3-dd) 1]; m2=[2*r1*cos(tt1-a1) 2*cos(tt1-dd) 1;2*r2*cos(tt2-a2)... 2*cos(tt2-dd) 1;2*r3*cos(tt3-a3) 2*cos(tt3-dd) 1]; m3=[2*r1*cos(tt1-a1) 2*r1*cos(a1-dd) 2*cos(tt1-dd);2*r2*cos(tt2-a2)... 2*r2*cos(a2-dd) 2*cos(tt2-dd);2*r3*cos(tt3-a3) 2*r3*cos(a3-dd)... 2*cos(tt3-dd)];
%Constants Calculationla=det(l1)/det(l0);lg=det(l2)/det(l0);lk=det(l3)/det(l0); ma=det(m1)/det(m0);mg=det(m2)/det(m0);mk=det(m3)/det(m0);
A=ma*mg; B=la*mg+lg*ma-1; C=la*lg;
L=(-B-sign*sqrt(B^2-4*A*C))/(2*A); x=la+L*ma; y=lg+L*mg; k=lk+L*mk; z=sqrt(k+x^2+y^2);end
f=x; h=y; c=z;dx=h*cos(ss)-g*cos(gg);dy=h*sin(ss)-g*sin(gg);d=sqrt(dx^2+dy^2);b=distance(a*cos(t1),a*sin(t1),(a*cos(t1)+e*cos(b1)+f*cos(pi+d1)),... (a*sin(t1)+e*sin(b1)+f*sin(pi+d1)));
%Link Lengthsfprintf('\nOUTPUT');fprintf('\n a b c d e f g h');fprintf('\n%8.2f %8.2f %8.2f %8.2f %8.2f %8.2f %8.2f %8.2f\n',a,b,c,d,e,f,g,h);
%Set Graph Limitsxlim([-60 100])ylim([-10 110])
%Plotting Fixed Linkline([0,dx],[0,dy],'Color','g','DisplayName','Fixed Link','LineWidth',2);
for j=0:1:2if j==0tt=t1; bb=b1; dd=d1;end
if j==1tt=t2; bb=b2; dd=d2;end
if j==2tt=t3; bb=b3; dd=d3;end
%Plotting Moving Linksline([0,a*cos(tt),(a*cos(tt)+e*cos(bb)+f*cos(pi+dd)),dx],... [0,a*sin(tt),(a*sin(tt)+e*sin(bb)+f*sin(pi+dd)),dy],...'DisplayName','Moving Links','LineWidth',2); %Line Properties
%Plotting Coupler Linksline([a*cos(tt),(a*cos(tt)+e*cos(bb)),(a*cos(tt)+e*cos(bb)+f*cos(pi+dd))]... ,[a*sin(tt),(a*sin(tt)+e*sin(bb)),(a*sin(tt)+e*sin(bb)+f*sin(pi+dd))]... ,'Color','r','DisplayName','Coupler Links','LineWidth',2);end
%Plotting Coupler Curve k1=d/a; k2=d/b; k3=(c^2-a^2-b^2-d^2)/(2*a*b); A=(k2+1)*cos(t1)+k3-k1; B=-2*sin(t1); C=k1+k3+(k2-1)*cos(t1);beta=2*atan((-B-sqrt(B^2-4*A*C))/(2*A)); alpha=b1-beta;
for t=0:.001:2*pi; A=(k2+1)*cos(t)+k3-k1; B=-2*sin(t); C=k1+k3+(k2-1)*cos(t);beta=2*atan((-B-sqrt(B^2-4*A*C))/(2*A)); x=real(a*cos(t)+e*cos(alpha+beta)); y=real(a*sin(t)+e*sin(alpha+beta));holdonplot(x,y,'k','DisplayName','Coupler Curve','LineWidth',2);legendshowholdoffend
title('Coupler Curve Plot');xlabel ('X-Axis');ylabel ('Y-Axis');gridend
title('Coupler Curve Plot');xlabel ('X-Axis');ylabel ('Y-Axis');gridend
OUTPUT
a b c d e f g h 17.20 44.63 28.50 27.51 39.40 65.04 54.95 79.91
Experiment No. 3
Problem Definition: Determination of Natural Frequencies & Modal Analysis of A Cantilever Beam Using FFT Analyzer.
5mm
600mm 50mm
Fig 3.1 Cantilever beam with loadingTable 3.1 shows the detail of cantilever beam which includes dimension of beam and its material properties.Table 3.1Dimension and material properties of cantilever beam.Length600 mm
Width50 mm
Height5 mm
Youngs modulus (E)210 GPa
Poissons ratio0.3
The beam is clamped to a rigid wall at the left end and Impact load is applied on Specimen by using Impact hammer.
Accelerometer 'C 'Clamp for Holding SpecimenChannel BoardImpact HammerFFT Software SpecimenFig 3.2 Experimental Setup of FFT AnalyzerAs shown in Fig no.3.2 the experimental setup of FFT Analyzer consist of following equipment as.1. Speciman: The Specimen having dimension 600 X 50 X 5 mm, of mild steel is used for testing.2. 'C' Clamp Board: It is used for holding the beam at one end. 3. FFT Channel: This is hardware device which is used for giving input and output to the FFT software. It contains 8 no of channels out of that channel no 2 and channel no 5 are used to take input and output of data. Channel no 2 is connected to accelerometer sensor to take output signals from beam and channel no 5 is connected to impact hammer to excite the beam.4. Impact Hammer: It is used to excite the beam.5. Acclerometer Sensor: It is used for measuring vibration parameters.
Fig 3.3 Channel SetupThe Fig no. 3.3 is shows channel setup window hear we gives channel setup for channel no2 and no5.
Fig 3.4 Channel Setup for channel no 2.
In channel no 2 we give the physical quantity as Acceleration and unit as 'g'. Here Sensitivity of accelerometer sensor is 9.749 mv/g.
Fig 3.5 Channel Setup for channel no 5.
In channel no 5 we give the physical quantity as Force and unit as 'N'. Here sensitivity of Impact hammer which is 2.28 mv/N.
Fig 3.6 Modal Test Window.
The fig no 3.6 shows the model test window in that we selected calculation type as Triggered(FRF) and tick on Roving hammer/acc. In this experiment we excite the specimen at 3 different position (at X= -300,X=0 and X=300mm)
Fig 3.7 Frequency Domain Graph of Model Test
Conclusion: In above fig. Maximum peaks at frequency 332.31 Hz and 546.875 Hz. So,Natural frequency in the first two modes are 332.31 Hz and 546.875 Hz.
Experiment No 44.1 Problem Definition: Stress And Deflection Analysis of Short and Long Beams With Different End Condition and Crass-Section Subjected to Different Loading Condition Using FEA Software.
Fig 4.1 Cantilever beam with loadingTable 4.1 shows the detail of cantilever beam which includes dimension of beam and its material properties.Table 4.1 Dimension and material properties of cantilever beam.Length90 mm
Width10 mm
Height5 mm
Youngs modulus (E)210 GPa
Poissons ratio0.3
The beam is clamped to a rigid wall at the left end and loaded at x =80mm by a point load of P =100 N.
Fig 4.2 Flowchart of the structural analyses by ANSYS.
Modeling: Figure 1.3-1.4 show the ANSYS Main Menu window where we can find layered command options imitating folders and files in the Microsoft Explorer folder window. In order to prepare for creating the beam, the following operations should be made:(1) Preprocessor to open its sub-menus in ANSYS Main Menu window.(2) Modeling to open its sub-menus and select Create menu.(3) Areas to open its sub-menus and select Rectangle menu.(4) Click on By 2 corners menu.
Fig 4.3 ANSYS Main Menu Fig 4.4 Rectangle by 2 Corners window. window.
Fig 4.5 2-D beam created and displayed on the ANSYS Graphics window.
Material Properties: ANSYSMainMenuPreprocessorMaterial PropsMaterial Models. Then the Define Material Model Behavior window opens as shown inFig 4.6-4.7
Fig 4.6 Define Material Model Behavior window.
Fig 4.7 Input of elastic constants through the Linear Isotropic Properties for Material Number 1 window.
Finite-Element Discretization of the Beam Area: Here we will divide the beam area into finite elements. The procedures for finiteelement discretization are firstly to select the element type, secondly to input the element thickness and finally to divide the beam area into elements. ANSYS Main MenuPreprocessorElement TypeAdd/ Edit/Delete
Fig 4.8 Library of Element Types window.
Fig 4.9 PLANE 182 element type options window.
Fig 4.10 Real Constants Set Number 1. for PLANE 183 window.Sizing of the elements: ANSYSMainMenuPreprocessorMeshingSize CntrlsManual SizeGlobalSize
Fig 4.11 Global Element Sizes window.
Meshing: ANSYSMainMenuPreprocessorMeshingMeshAreasFree
Fig 4.12 FE model of beam
Input of Boundary Conditions: Here we will impose constraint and loading conditions on nodes of the beam model. Display the nodes first to define the constraint and loading conditions.ANSYSMainMenuSolutionDefineLoadsApplyStructuralDisplacementOn Nodes
Fig 4.13 Apply U. ROT on Nodes window.
ANSYSMainMenuSolutionDefine LoadsStructuralForce/ MomentOn Nodes
Fig 4.14 Apply F/M on Nodes window.
Fig 4.15 Boundary condition with loading
Solution Procedures: ANSYSMainMenuSolutionSolveCurrent LS
Fig 4.15 Solve Current Load Step window.
Fig 4.16 Note window.
Graphical representation of the results: ANSYSMainMenuGeneral PostprocPlot ResultsContour PlotNodal Solution
Fig 4.17 Contour Nodal Solution Data window for deflection
Fig 4.18 Contour map representation of the distribution of displacement in the y- or vertical direction.
Fig 4.19 Contour Nodal Solution Data window for stress
Fig 4.20 Contour map representation of the distribution of Von Mises stress
Conclusion: The maximum deflection in Y direction is 0.927 mm and maximum Von Mises stress is 190.45 MPa.
4.2 Problem Definition: Stress and Deflection Analysis of Short and Long Beams With Different End Condition and Crass-Section Subjected to Different Loading Condition Using FEA Software .
Fig 4.21 Stepped beam with loadingTable 4.21 shows the detail of stepped beam which includes dimension of beam and its material properties.Table 4.21 Dimension and material properties of cantilever beam.Length100 mm
Width10 mm
Height20 mm
Youngs modulus (E)210GPa
Poissons ratio0.3
The beam is clamped to a rigid wall at the left end and loadedat x =100mm by a point load of P =100 N.
Modeling: Figure 4.20 -4.21 show the ANSYS Main Menu window where we can find layered command options imitating folders and files in the Microsoft Explorer folder window.In order to prepare for creating the beam, the following operations should be made:(1) Preprocessor to open its sub-menus in ANSYS Main Menu window.(2) Modeling to open its sub-menus and select Create menu.(3) Areas to open its sub-menus and select Rectangle menu.(4) Click on By 2 corners menu.(5)ModelingOperateBooleansSubtractArea.(6) Areas to open its sub-menus and select Circle menu.(7) Click onSolid circle menu.(8)ModelingOperateBooleansSubtractArea.
Fig 4.22ANSYS main menu Fig 4.23Rectangle by 2 corners window. window.
Fig 4.24Solid circle Area window.
Fig 4.25 2-D beam created and displayed on the ANSYS Graphics window.
Material Properties: ANSYSMainMenuPreprocessorMaterialPropsMaterialModels. Then the Define Material Model Behavior window opens as shown inFigure 4.22.-4.22.3
Fig 4.26 Define Material Model Behavior window.
Fig 4.27 Input of elastic constants through the Linear Isotropic Properties for Material Number 1 window.
Finite-Element Discretization of the Beam Area:Here we will divide the beam area into finite elements. The procedures for finiteelement discretization are firstly to select the element type, secondly to input the element thickness and finally to divide the beam area into elements.ANSYS Main MenuPreprocessorElement TypeAdd/ Edit/Delete
Fig 4.28 Library of Element Types window.
Fig 4.29 PLANE 182 element type options window.
Fig 4.30 Real Constants Set Number 1. for PLANE 183 window.Sizing of the elements: ANSYSMainMenuPreprocessorMeshingSizeCntrlsManualSizeGlobalSize
Fig 4.31Global Element Sizes window.
Meshing: ANSYSMainMenuPreprocessorMeshingMeshAreasFree
Fig 4.32 FE model of beam
Input of Boundary Conditions: Here we will impose constraint and loading conditions on nodes of the beam model. Display the nodes first to define the constraint and loading conditions.ANSYSMainMenuSolutionDefineLoadsApplyStructuralDisplacementOn Nodes
Fig 4.33 Apply U. ROT on Nodes window.
ANSYSMainMenuSolutionDefineLoadsStructuralForce/MomentOn Nodes
Fig 4.34 Apply F/M on Nodes window.
Fig 4.35 Boundary condition with loading
Solution Procedures: ANSYSMainMenuSolutionSolveCurrent LS
Fig 4.36 Solve Current Load Step window.
Fig 4.37 Note window.
Graphical representation of the results:ANSYSMainMenuGeneralPostprocPlotResultsContourPlotNodal Solution
Fig 4.38 Contour Nodal Solution Data window for deflection
Fig 4.39 Contour map representation of the distribution of displacement in the y- or vertical direction.
Fig 4.40 Contour Nodal Solution Data window for stress
Fig 4.41 Contour map representation of the distribution of Von Mises stress
Conclusion: The maximum deflection in Y direction is 0.044 mm and maximum Von Mises stress is 30.36MPa.
Experiment No 5 5.1 Problem Definition: Stress and Deflection Analysis of Rectangular Plates Using FEA Software.
Fig 5.1 rectangular plate having one holeTable 5.1 shows the detail of rectangular plate which includes dimension of plate and its material properties.Table 5.1 Dimension and material properties of cantilever beam.Width1000 mm
Height500 mm
Thickness10 mm
Radius of circle25 mm
Youngs modulus (E)210GPa
Poissons ratio0.3
Fig 5.2 Flowchart of the structural analyses by ANSYS.
Modeling:Figure 5.3-5.4 show the ANSYS Main Menu window where we can find layeredcommand options imitating folders and files in the Microsoft Explorer folderwindow.In order to prepare for creating the plate, the following operations shouldbe made:(1) Preprocessor to open its sub-menus in ANSYSMainMenu window.(2) Modeling to open its sub-menus and select Create menu.(3) Areas to open its sub-menus and select Rectangle menu.(4) Click on By 2 corners menu.(5) Areas to open its sub-menus and select Circle menu.(6) Click onSolid circle menu.(7)ModelingOperateBooleansSubtractArea.
Fig 5.3ANSYS Main Menu Fig 5.4Rectangle By 2 Corners window. Window.
Fig 5.5Solid Circular Area window
Fig 5.6 2-D plate created and displayed on the ANSYS Graphics window.
Material Properties: ANSYSMainMenuPreprocessorMaterialPropsMaterialModels. Then the Define Material Model Behavior window opens as shown inFigure 5.6-5.7
Fig 5.7 Define Material Model Behavior window.
Fig 5.8 Input of elastic constants through the Linear Isotropic Properties for Material Number 1 window.
Finite-Element Discretization of the Rectangular plate Area:Here we will divide the plate area into finite elements. The procedures for finiteelement discretization are firstly to select the element type, secondly to input the element thickness and finally to divide the plate area into elements.ANSYS Main MenuPreprocessorElement TypeAdd/ Edit/Delete
Fig 5.9 Library of Element Types window.
Fig 5.10PLANE 183 element type options window.
Fig 5.11 Real Constants Set Number 1. for PLANE 183 window.
Meshing: ANSYSMainMenuPreprocessorMeshingMeshAreasFree
Fig 5.12: FE model of plate
Input of Boundary Conditions: Here we will impose constraint and loading conditions on nodes of the plate model. Display the nodes first to define the constraint and loading conditions.ANSYSMainMenuSolutionDefineLoadsApplyStructuralDisplacementOn Nodes
Fig 5.13 Apply U. ROT on Nodes window.
ANSYSMainMenuSolutionDefineLoads ApplyStructuralForce/MomentOn Nodes
Fig 5.14 Apply F/M on Nodes window.
Fig 5.15 Boundary condition with loading
Solution Procedures: ANSYSMainMenuSolutionSolveCurrent LS
Fig 5.16 Solve Current Load Step window.
Fig 5.17 Note window.
Graphical representation of the results: ANSYSMainMenuGeneralPostprocPlotResultsContourPlotNodal Solution
Fig 5.18 Contour Nodal Solution Data window for stress
Fig 5.19 Contour map representation of the distribution of Von Mises stress
Result: The maximum Von Mises stress in the plate having one hole is 7.35489MPa.
5.2 Problem Definition: Find The Stress Analysis of Rectangular Plate Having Three Holes As Shown In Fig.
Fig 5.20 rectangular plate having three holesTable 5.2 shows the detail of rectangular plate which includes dimension of plate and its material properties.Table 5.2 Dimension and material properties of plateWidth1000 mm
Height500 mm
Thickness10 mm
Radius of middle circle25 mm
Radius of outside circle12.5 mm
Youngs modulus (E)210GPa
Poissons ratio0.3
Fig 5.21 2-D plate created and displayed on the ANSYS Graphics window.
Finite-Element Discretization of the Rectangular plate Area: Here we will divide the plate area into finite elements. The procedures for finiteelement discretization are firstly to select the element type, secondly to input the element thickness and finally to divide the plate area into elements.ANSYS Main MenuPreprocessorElementTypeAdd/ Edit/Delete
Meshing: ANSYSMainMenuPreprocessorMeshingMeshAreasFree
Fig 5.22 FE model of plate
Input of Boundary Conditions: Here we will impose constraint and loading conditions on nodes of the plate model. Display the nodes first to define the constraint and loading conditions.
ANSYSMainMenuSolutionDefineLoads ApplyStructuralForce/MomentOn Nodes
Fig 5.23 Boundary condition with loading
Solution Procedures: ANSYSMainMenuSolutionSolveCurrent LS
Fig 5.24 Note window.
Graphical representation of the results: ANSYS MainMenuGeneralPostprocPlotResultsContourPlotNodal Solution
Fig 5.25 Contour Nodal Solution Data window for stress
Fig 5.26Contour map representation of the distribution of Von Mises stress
Result: The maximum Von Mises stress in the plate having three hole is 7.30891MPa.
Conclusion: The maximum Von Mises stress in the plate having three holes is less as compared to the plate having one hole.
Experiment No 6Problem Definition: Stress Analysis of Rotating Disk Using FEA Software.
Fig 6.1 3-D model of disk
Experiment No 7
Problem Definition: Direct/Model Frequency Response Analysis of a Beam/Plate Under a Single-Point Cycle Load/Base Excitation With and Without Damping Using FEA Software.
Fig 8.1 linear buckling on 1st node
Fig 8.2 linear buckling on 2nd node
Fig 8.3 linear buckling on 3rd node
Structural Steel > Isotropic Secant Coefficient of Thermal Expansion
Experiment No 8Problem Definition: Direct /Model Frequency Response Analysis of A Plate Under A Single Point Cycle Load/ Base Excitation With and Without Damping Using FEA Software.
UnitsUnit SystemMetric (mm, kg, N, s, mV, mA) Degrees rad/s Celsius
AngleDegrees
Rotational Velocityrad/s
TemperatureCelsius
Geometry
Model (A4, B4, C4) > GeometryObject NameGeometry
StateFully Defined
Definition
SourceC:\Users\mi747\AppData\Local\Temp\WB_W3-A46012_mi747_5480_2\unsaved_project_files\dp0\SYS\DM\SYS.agdb
TypeDesignModeler
Length UnitMeters
Element ControlProgram Controlled
Display StyleBody Color
Bounding Box
Length X50. mm
Length Y5. mm
Length Z400. mm
Properties
Volume100000 mm
Mass0.785 kg
Scale Factor Value1.
Statistics
Bodies1
Active Bodies1
Nodes6053
Elements800
Mesh MetricNone
Basic Geometry Options
ParametersYes
Parameter KeyDS
AttributesNo
Named SelectionsNo
Material PropertiesNo
Advanced Geometry Options
Use AssociativityYes
Coordinate SystemsNo
Reader Mode Saves Updated FileNo
Use InstancesYes
Smart CAD UpdateNo
Compare Parts On UpdateNo
Attach File Via Temp FileYes
Temporary DirectoryC:\Users\mi747\AppData\Local\Temp
Analysis Type3-D
Decompose Disjoint GeometryYes
Enclosure and Symmetry ProcessingYes
Model (A4, B4, C4) > Geometry > PartsObject NameSolid
StateMeshed
Graphics Properties
VisibleYes
Transparency1
Definition
SuppressedNo
Stiffness BehaviorFlexible
Coordinate SystemDefault Coordinate System
Reference TemperatureBy Environment
Material
AssignmentStructural Steel
Nonlinear EffectsYes
Thermal Strain EffectsYes
Bounding Box
Length X50. mm
Length Y5. mm
Length Z400. mm
Properties
Volume100000 mm
Mass0.785 kg
Centroid X-3.5293e-016 mm
Centroid Y2.5 mm
Centroid Z200. mm
Moment of Inertia Ip110468 kgmm
Moment of Inertia Ip210630 kgmm
Moment of Inertia Ip3165.18 kgmm
Statistics
Nodes6053
Elements800
Mesh MetricNone
Model (A4, B4, C4) > Geometry > Image
Coordinate Systems
Model (A4, B4, C4) > Coordinate Systems > Coordinate SystemObject NameGlobal Coordinate System
StateFully Defined
Definition
TypeCartesian
Coordinate System ID0.
Origin
Origin X0. mm
Origin Y0. mm
Origin Z0. mm
Directional Vectors
X Axis Data[ 1. 0. 0. ]
Y Axis Data[ 0. 1. 0. ]
Z Axis Data[ 0. 0. 1. ]
Mesh
Model (A4, B4, C4) > MeshObject NameMesh
StateSolved
Defaults
Physics PreferenceMechanical
Relevance0
Sizing
Use Advanced Size FunctionOff
Relevance CenterCoarse
Element Size5.0 mm
Initial Size SeedActive Assembly
SmoothingMedium
TransitionFast
Span Angle CenterCoarse
Minimum Edge Length5.0 mm
Inflation
Use Automatic InflationNone
Inflation OptionSmooth Transition
Transition Ratio0.272
Maximum Layers5
Growth Rate1.2
Inflation AlgorithmPre
View Advanced OptionsNo
Patch Conforming Options
Triangle Surface MesherProgram Controlled
Patch Independent Options
Topology CheckingYes
Advanced
Number of CPUs for Parallel Part MeshingProgram Controlled
Shape CheckingStandard Mechanical
Element Midside NodesProgram Controlled
Straight Sided ElementsNo
Number of RetriesDefault (4)
Extra Retries For AssemblyYes
Rigid Body BehaviorDimensionally Reduced
Mesh MorphingDisabled
Defeaturing
Pinch TolerancePlease Define
Generate Pinch on RefreshNo
Automatic Mesh Based DefeaturingOn
Defeaturing ToleranceDefault
Statistics
Nodes6053
Elements800
Mesh MetricNone
Model (A4, B4, C4) > Mesh > Image
Modal (A5)
Model (A4, B4, C4) > AnalysisObject NameModal (A5)
StateSolved
Definition
Physics TypeStructural
Analysis TypeModal
Solver TargetMechanical APDL
Options
Environment Temperature22. C
Generate Input OnlyNo
Model (A4, B4, C4) > Modal (A5) > Initial ConditionObject NamePre-Stress (None)
StateFully Defined
Definition
Pre-Stress EnvironmentNone
Model (A4, B4, C4) > Modal (A5) > Analysis SettingsObject NameAnalysis Settings
StateFully Defined
Options
Max Modes to Find10
Limit Search to RangeNo
Solver Controls
DampedNo
Solver TypeProgram Controlled
Rotordynamics Controls
Coriolis EffectOff
Campbell DiagramOff
Output Controls
StressYes
StrainYes
Nodal ForcesNo
Calculate ReactionsYes
Store Modal ResultsProgram Controlled
General MiscellaneousNo
Analysis Data Management
Solver Files DirectoryC:\Users\mi747\AppData\Local\Temp\WB_W3-A46012_mi747_5480_2\unsaved_project_files\dp0\SYS\MECH\
Future AnalysisMSUP Analyses
Scratch Solver Files Directory
Save MAPDL dbYes
Delete Unneeded FilesYes
Solver UnitsActive System
Solver Unit SystemNmm
Model (A4, B4, C4) > Modal (A5) > LoadsObject NameFixed Support
StateFully Defined
Scope
Scoping MethodGeometry Selection
Geometry1 Face
Definition
TypeFixed Support
SuppressedNo
Solution (A6)
Model (A4, B4, C4) > Modal (A5) > SolutionObject NameSolution (A6)
StateSolved
Adaptive Mesh Refinement
Max Refinement Loops1.
Refinement Depth2.
Information
StatusDone
The following bar chart indicates the frequency at each calculated mode.
Model (A4, B4, C4) > Modal (A5) > Solution (A6)
Model (A4, B4, C4) > Modal (A5) > Solution (A6)ModeFrequency [Hz]
1.25.701
2.160.9
3.252.26
4.390.12
5.450.48
6.882.99
7.1179.7
8.1460.
9.1479.8
10.1996.7
Model (A4, B4, C4) > Modal (A5) > Solution (A6) > Solution InformationObject NameSolution Information
StateSolved
Solution Information
Solution OutputSolver Output
Newton-Raphson Residuals0
Update Interval2.5 s
Display PointsAll
FE Connection Visibility
Activate VisibilityYes
DisplayAll FE Connectors
Draw Connections Attached ToAll Nodes
Line ColorConnection Type
Visible on ResultsNo
Line ThicknessSingle
Display TypeLines
Model (A4, B4, C4) > Modal (A5) > Solution (A6) > ResultsObject NameTotal DeformationTotal Deformation 2Total Deformation 3Total Deformation 4Total Deformation 5Total Deformation 6Total Deformation 7Total Deformation 8Total Deformation 9Total Deformation 10
StateSolved
Scope
Scoping MethodGeometry Selection
GeometryAll Bodies
Definition
TypeTotal Deformation
Mode1.2.3.4.5.6.7.8.9.10.
Identifier
SuppressedNo
Results
Minimum0. mm
Maximum71.526 mm71.524 mm71.163 mm88.984 mm71.633 mm71.878 mm90.584 mm72.274 mm70.678 mm93.557 mm
Minimum Value Over Time
Minimum0. mm
Maximum0. mm
Maximum Value Over Time
Minimum71.526 mm71.524 mm71.163 mm88.984 mm71.633 mm71.878 mm90.584 mm72.274 mm70.678 mm93.557 mm
Maximum71.526 mm71.524 mm71.163 mm88.984 mm71.633 mm71.878 mm90.584 mm72.274 mm70.678 mm93.557 mm
Information
Frequency25.701 Hz160.9 Hz252.26 Hz390.12 Hz450.48 Hz882.99 Hz1179.7 Hz1460. Hz1479.8 Hz1996.7 Hz
Model (A4, B4, C4) > Modal (A5) > Solution (A6) > Total DeformationModeFrequency [Hz]
1.25.701
2.160.9
3.252.26
4.390.12
5.450.48
6.882.99
7.1179.7
8.1460.
9.1479.8
10.1996.7
Model (A4, B4, C4) > Modal (A5) > Solution (A6) > Total Deformation > Image
Model (A4, B4, C4) > Modal (A5) > Solution (A6) > Total Deformation 2ModeFrequency [Hz]
1.25.701
2.160.9
3.252.26
4.390.12
5.450.48
6.882.99
7.1179.7
8.1460.
9.1479.8
10.1996.7
Model (A4, B4, C4) > Modal (A5) > Solution (A6) > Total Deformation 2 > Image
Model (A4, B4, C4) > Modal (A5) > Solution (A6) > Total Deformation 3ModeFrequency [Hz]
1.25.701
2.160.9
3.252.26
4.390.12
5.450.48
6.882.99
7.1179.7
8.1460.
9.1479.8
10.1996.7
Model (A4, B4, C4) > Modal (A5) > Solution (A6) > Total Deformation 3 > Image
Model (A4, B4, C4) > Modal (A5) > Solution (A6) > Total Deformation 4ModeFrequency [Hz]
1.25.701
2.160.9
3.252.26
4.390.12
5.450.48
6.882.99
7.1179.7
8.1460.
9.1479.8
10.1996.7
Model (A4, B4, C4) > Modal (A5) > Solution (A6) > Total Deformation 4 > Image
Model (A4, B4, C4) > Modal (A5) > Solution (A6) > Total Deformation 5ModeFrequency [Hz]
1.25.701
2.160.9
3.252.26
4.390.12
5.450.48
6.882.99
7.1179.7
8.1460.
9.1479.8
10.1996.7
Model (A4, B4, C4) > Modal (A5) > Solution (A6) > Total Deformation 5 > Image
Model (A4, B4, C4) > Modal (A5) > Solution (A6) > Total Deformation 6ModeFrequency [Hz]
1.25.701
2.160.9
3.252.26
4.390.12
5.450.48
6.882.99
7.1179.7
8.1460.
9.1479.8
10.1996.7
Model (A4, B4, C4) > Modal (A5) > Solution (A6) > Total Deformation 7ModeFrequency [Hz]
1.25.701
2.160.9
3.252.26
4.390.12
5.450.48
6.882.99
7.1179.7
8.1460.
9.1479.8
10.1996.7
Model (A4, B4, C4) > Modal (A5) > Solution (A6) > Total Deformation 8ModeFrequency [Hz]
1.25.701
2.160.9
3.252.26
4.390.12
5.450.48
6.882.99
7.1179.7
8.1460.
9.1479.8
10.1996.7
Model (A4, B4, C4) > Modal (A5) > Solution (A6) > Total Deformation 9ModeFrequency [Hz]
1.25.701
2.160.9
3.252.26
4.390.12
5.450.48
6.882.99
7.1179.7
8.1460.
9.1479.8
10.1996.7
Model (A4, B4, C4) > Modal (A5) > Solution (A6) > Total Deformation 10ModeFrequency [Hz]
1.25.701
2.160.9
3.252.26
4.390.12
5.450.48
6.882.99
7.1179.7
8.1460.
9.1479.8
10.1996.7
Harmonic Response (B5)
Model (A4, B4, C4) > AnalysisObject NameHarmonic Response (B5)
StateSolved
Definition
Physics TypeStructural
Analysis TypeHarmonic Response
Solver TargetMechanical APDL
Options
Environment Temperature22. C
Generate Input OnlyNo
Model (A4, B4, C4) > Harmonic Response (B5) > Initial ConditionObject NameModal (Modal)
StateFully Defined
Definition
Modal EnvironmentModal
Pre-Stress EnvironmentNone
Model (A4, B4, C4) > Harmonic Response (B5) > Analysis SettingsObject NameAnalysis Settings
StateFully Defined
Options
Range Minimum0. Hz
Range Maximum500. Hz
Solution Intervals50
Solution MethodMode Superposition
Include Residual VectorNo
Cluster ResultsNo
Store Results At All FrequenciesYes
Output Controls
StressYes
StrainYes
Nodal ForcesNo
Calculate ReactionsYes
Expand Results FromProgram Controlled
-- ExpansionModal Solution
General MiscellaneousNo
Damping Controls
Constant Damping Ratio0.
Stiffness Coefficient Define ByDirect Input
Stiffness Coefficient0.
Mass Coefficient0.
Analysis Data Management
Solver Files DirectoryC:\Users\mi747\AppData\Local\Temp\WB_W3-A46012_mi747_5480_2\unsaved_project_files\dp0\SYS-1\MECH\
Future AnalysisNone
Scratch Solver Files Directory
Save MAPDL dbNo
Delete Unneeded FilesYes
Solver UnitsActive System
Solver Unit SystemNmm
Model (A4, B4, C4) > Harmonic Response (B5) > LoadsObject NameForce
StateFully Defined
Scope
Scoping MethodGeometry Selection
Geometry1 Face
Definition
TypeForce
Define ByComponents
Coordinate SystemGlobal Coordinate System
X Component0. N
Y Component150. N
Z Component0. N
Phase Angle0.
SuppressedNo
Solution (B6)
Model (A4, B4, C4) > Harmonic Response (B5) > SolutionObject NameSolution (B6)
StateSolved
Information
StatusDone
Model (A4, B4, C4) > Harmonic Response (B5) > Solution (B6)
Model (A4, B4, C4) > Harmonic Response (B5) > Solution (B6) > Solution InformationObject NameSolution Information
StateSolved
Solution Information
Solution OutputSolver Output
Newton-Raphson Residuals0
Update Interval2.5 s
Display PointsAll
FE Connection Visibility
Activate VisibilityYes
DisplayAll FE Connectors
Draw Connections Attached ToAll Nodes
Line ColorConnection Type
Visible on ResultsNo
Line ThicknessSingle
Display TypeLines
Model (A4, B4, C4) > Harmonic Response (B5) > Solution (B6) > Result ChartsObject NameFrequency ResponseFrequency Response 2Frequency Response 3
StateSolved
Scope
Scoping MethodGeometry Selection
Geometry1 Face1 Vertex
Spatial ResolutionUse Average
Definition
TypeShear StressDirectional DeformationDirectional Velocity
OrientationXY PlaneY Axis
SuppressedNo
Options
Frequency RangeUse Parent
Minimum Frequency0. Hz
Maximum Frequency500. Hz
DisplayBode
Results
Maximum Amplitude1.0311e-009 MPa80.258 mm1.2675e+005 mm/s
Frequency30. Hz450. Hz
Phase Angle180. 90.
Real-1.0311e-009 MPa-80.258 mm0. mm/s
Imaginary0. MPa0. mm1.2675e+005 mm/s
Model (A4, B4, C4) > Harmonic Response (B5) > Solution (B6) > Frequency Response
Model (A4, B4, C4) > Harmonic Response (B5) > Solution (B6) > Frequency Response 2
Model (A4, B4, C4) > Harmonic Response (B5) > Solution (B6) > Frequency Response 3
Model (A4, B4, C4) > Harmonic Response (B5) > Solution (B6) > ResultsObject NameEquivalent Stress
StateSolved
Scope
Scoping MethodGeometry Selection
GeometryAll Bodies
Definition
TypeEquivalent (von-Mises) Stress
ByFrequency
Frequency50. Hz
Sweeping Phase0.
Identifier
SuppressedNo
Integration Point Results
Display OptionAveraged
Average Across BodiesNo
Results
Minimum8.0601e-003 MPa
Maximum171.71 MPa
Minimum Value Over Time
Minimum8.0601e-003 MPa
Maximum8.0601e-003 MPa
Maximum Value Over Time
Minimum171.71 MPa
Maximum171.71 MPa
Information
Reported Frequency50. Hz
Model (A4, B4, C4) > Harmonic Response (B5) > Solution (B6) > Equivalent Stress
Model (A4, B4, C4) > Harmonic Response (B5) > Solution (B6) > Equivalent StressSetFrequency [Hz]
1.10.
2.20.
3.30.
4.40.
5.50.
6.60.
7.70.
8.80.
9.90.
10.100.
11.110.
12.120.
13.130.
14.140.
15.150.
16.160.
17.170.
18.180.
19.190.
20.200.
21.210.
22.220.
23.230.
24.240.
25.250.
26.260.
27.270.
28.280.
29.290.
30.300.
31.310.
32.320.
33.330.
34.340.
35.350.
36.360.
37.370.
38.380.
39.390.
40.400.
41.410.
42.420.
43.430.
44.440.
45.450.
46.460.
47.470.
48.480.
49.490.
50.500.
Model (A4, B4, C4) > Harmonic Response (B5) > Solution (B6) > Equivalent Stress > Image
Harmonic Response 2 (C5)
Model (A4, B4, C4) > AnalysisObject NameHarmonic Response 2 (C5)
StateSolved
Definition
Physics TypeStructural
Analysis TypeHarmonic Response
Solver TargetMechanical APDL
Options
Environment Temperature22. C
Generate Input OnlyNo
Model (A4, B4, C4) > Harmonic Response 2 (C5) > Initial ConditionObject NameModal (Modal)
StateFully Defined
Definition
Modal EnvironmentModal
Pre-Stress EnvironmentNone
Model (A4, B4, C4) > Harmonic Response 2 (C5) > Analysis SettingsObject NameAnalysis Settings
StateFully Defined
Options
Range Minimum0. Hz
Range Maximum500. Hz
Solution Intervals50
Solution MethodMode Superposition
Include Residual VectorNo
Cluster ResultsNo
Store Results At All FrequenciesYes
Output Controls
StressYes
StrainYes
Nodal ForcesNo
Calculate ReactionsYes
Expand Results FromProgram Controlled
-- ExpansionModal Solution
General MiscellaneousNo
Damping Controls
Constant Damping Ratio0.2
Stiffness Coefficient Define ByDirect Input
Stiffness Coefficient0.
Mass Coefficient0.
Analysis Data Management
Solver Files DirectoryC:\Users\mi747\AppData\Local\Temp\WB_W3-A46012_mi747_5480_2\unsaved_project_files\dp0\SYS-2\MECH\
Future AnalysisNone
Scratch Solver Files Directory
Save MAPDL dbNo
Delete Unneeded FilesYes
Solver UnitsActive System
Solver Unit SystemNmm
Model (A4, B4, C4) > Harmonic Response 2 (C5) > LoadsObject NameForce
StateFully Defined
Scope
Scoping MethodGeometry Selection
Geometry1 Face
Definition
TypeForce
Define ByComponents
Coordinate SystemGlobal Coordinate System
X Component0. N
Y Component150. N
Z Component0. N
Phase Angle0.
SuppressedNo
Solution (C6)
Model (A4, B4, C4) > Harmonic Response 2 (C5) > SolutionObject NameSolution (C6)
StateSolved
Information
StatusDone
Model (A4, B4, C4) > Harmonic Response 2 (C5) > Solution (C6)
Model (A4, B4, C4) > Harmonic Response 2 (C5) > Solution (C6) > Solution InformationObject NameSolution Information
StateSolved
Solution Information
Solution OutputSolver Output
Newton-Raphson Residuals0
Update Interval2.5 s
Display PointsAll
FE Connection Visibility
Activate VisibilityYes
DisplayAll FE Connectors
Draw Connections Attached ToAll Nodes
Line ColorConnection Type
Visible on ResultsNo
Line ThicknessSingle
Display TypeLines
Model (A4, B4, C4) > Harmonic Response 2 (C5) > Solution (C6) > Result ChartsObject NameFrequency ResponseFrequency Response 2Frequency Response 3
StateSolved
Scope
Scoping MethodGeometry Selection
Geometry1 Face1 Vertex
Spatial ResolutionUse Average
Definition
TypeShear StressDirectional DeformationDirectional Velocity
OrientationXY PlaneY Axis
SuppressedNo
Options
Frequency RangeUse Parent
Minimum Frequency0. Hz
Maximum Frequency500. Hz
DisplayBode
Results
Maximum Amplitude6.338e-010 MPa59.288 mm9289. mm/s
Frequency20. Hz30. Hz
Phase Angle-36.946 -37.779 -36.956
Real5.0653e-010 MPa46.86 mm7422.9 mm/s
Imaginary-3.8096e-010 MPa-36.32 mm-5584.5 mm/s
Model (A4, B4, C4) > Harmonic Response 2 (C5) > Solution (C6) > Frequency Response
Model (A4, B4, C4) > Harmonic Response 2 (C5) > Solution (C6) > Frequency Response 2
Model (A4, B4, C4) > Harmonic Response 2 (C5) > Solution (C6) > Frequency Response 3
Model (A4, B4, C4) > Harmonic Response 2 (C5) > Solution (C6) > ResultsObject NameEquivalent Stress
StateSolved
Scope
Scoping MethodGeometry Selection
GeometryAll Bodies
Definition
TypeEquivalent (von-Mises) Stress
ByFrequency
Frequency50. Hz
Sweeping Phase0.
Identifier
SuppressedNo
Integration Point Results
Display OptionAveraged
Average Across BodiesNo
Results
Minimum8.0803e-003 MPa
Maximum161.44 MPa
Minimum Value Over Time
Minimum8.0803e-003 MPa
Maximum8.0803e-003 MPa
Maximum Value Over Time
Minimum161.44 MPa
Maximum161.44 MPa
Information
Reported Frequency50. Hz
Model (A4, B4, C4) > Harmonic Response 2 (C5) > Solution (C6) > Equivalent Stress
Model (A4, B4, C4) > Harmonic Response 2 (C5) > Solution (C6) > Equivalent Stress
SetFrequency [Hz]
1.10.
2.20.
3.30.
4.40.
5.50.
6.60.
7.70.
8.80.
9.90.
10.100.
11.110.
12.120.
13.130.
14.140.
15.150.
16.160.
17.170.
18.180.
19.190.
20.200.
21.210.
22.220.
23.230.
24.240.
25.250.
26.260.
27.270.
28.280.
29.290.
30.300.
31.310.
32.320.
33.330.
34.340.
35.350.
36.360.
37.370.
38.380.
39.390.
40.400.
41.410.
42.420.
43.430.
44.440.
45.450.
46.460.
47.470.
48.480.
49.490.
50.500.
Model (A4, B4, C4) > Harmonic Response 2 (C5) > Solution (C6) > Equivalent Stress > Image
Material DataStructural Steel Structural Steel > ConstantsDensity7.85e-006 kg mm^-3
Coefficient of Thermal Expansion1.2e-005 C^-1
Specific Heat4.34e+005 mJ kg^-1 C^-1
Thermal Conductivity6.05e-002 W mm^-1 C^-1
Resistivity1.7e-004 ohm mm
Structural Steel > Compressive Ultimate StrengthCompressive Ultimate Strength MPa
0
Structural Steel > Compressive Yield StrengthCompressive Yield Strength MPa
250
Structural Steel > Tensile Yield StrengthTensile Yield Strength MPa
250
Structural Steel > Tensile Ultimate StrengthTensile Ultimate Strength MPa
460
Structural Steel > Isotropic Secant Coefficient of Thermal ExpansionReference Temperature C
22
Structural Steel > Alternating Stress Mean StressAlternating Stress MPaCycles Mean Stress MPa
3999100
2827200
1896500
14131000
10692000
44120000
262100000
214200000
1381.e+0050
1142.e+0050
86.21.e+0060
Structural Steel > Strain-Life ParametersStrength Coefficient MPaStrength Exponent Ductility Coefficient Ductility Exponent Cyclic Strength Coefficient MPaCyclic Strain Hardening Exponent
920-0.1060.213-0.4710000.2
Structural Steel > Isotropic ElasticityTemperature CYoung's Modulus MPaPoisson's Ratio Bulk Modulus MPaShear Modulus MPa
2.e+0050.31.6667e+00576923
Structural Steel > Isotropic Relative PermeabilityRelative Permeability
10000
Problem Definition: Modal Analysis of Beam.Rectangular cross-section set time/freq load step sub-step cumulative 1 12.378 1 1 1 2 77.570 1 2 2 3 82.392 1 3 3 4 217.22 1 4 4 5 425.73 1 5 5
Problem Definition: Modal Analysis of Beam.Square cross-section: Set Time/Freq Load Step Sub-step Cumulative 1 31.953 1 1 1 2 31.953 1 2 2 3 200.01 1 3 3 4 200.01 1 4 4 5 559.00 1 5 5
DCOER ,PunePage 1