1. CE 529a
FINITE ELEMENT ANALYSIS
COURSE PROJECT
AYUSHI SRIVASTAVA
9664835820

2. Contents
1. Theory
2. Shear wall – node and element label plots
2.1Shear wall – node and element labels
For Shear loading
2.2 shear wall – node and element labels
For thermal loading
3. Shell model – node and element
Label plots
4. Shear wall – deformation plot under
Shear loading
5. Shear wall – deformation plot under thermal
Loading
6. Shell model – deformation plot
Under pressure loading
7. Discussion of results
7.1Shear wall
7.1.1 Static Shear loading case
7.1.2 Static thermal loading case
7.2Shell model
8. Shear wall – stress plots
8.1Stress plots for Shear force case
8.2Stress plots for thermal load case
9. Shell model – stress plots
9.1Stress plots for bottom surface
9.2Stress plots for top surface

3. 10.List of codes
10.1 Shear wall
10.1.1Shear wall – concentrated force case
10.1.2Shear wall – thermal load case

4. 1. THEORY
This project is basically a computer implementation of finite element method using ABAQUS
and MATLAB. In this project, a particular class of finite element models were considered, the
3D plate/ shell elements. These elements are a special type of shell element created from plate
elements that are essentially flat except for a small amount of warpage. Two elements are used
for the assembly of this element – a membrane component to model the in-plane performance of
the structure and a bending component to model the out-of-plane bending and torsion. Each
component has its own stiffness matrix, and these components are combined or assembled to
obtain the stiffness matrix for the entire plate/ shell element.
For analysis purposes, we use Gauss quadrature on a 4 noded Lagrange Isoparametric
element. For the shell problem, we use Flat element approximation. A shell element can be
subdivided into three parts, viz., membrane element, plate element and a drilling element. These
three parts each have a stiffness matrix which has to be calculated and assembled together.For
the membrane part, firstly, we define the material properties, for eg, E matrix, etc and A matrix,
shape function and its derivatives. After this, we create Jacobian matrix and its inverse. Then,
we create the B matrix and C matrix. We use 2x2 Gauss points to generate the stiffness matrix
for the membrane part.
Similarly for the plate part, we calculate each of the above for bending and transverse
shear. For bending we are using 2X2 Gauss points, whereas for the transverse shear we use 1X1
Gauss point to avoid shear lock.
 Gauss quadrature
These points are chosen so as to integrate cetain degree polynomials exactly.

5.  Shear Force Calculation
The Shear Force on the wall can be calculated by the formula
F=P/L
Where, P= The force which is applied on the wall
L=The length of the side of the wall to which force is applied.
 Pressure force calculation
The pressure force used in the bending part is shown below

6.  Thermal force calculation
Thermal loading is applied to the shear wall for analysis. Thermal loading is applied to
the shear wall for analysis.
{GFther}8x1 = =
Where; t: Thickness
[D]8x3=[A][B][C]
 Stress calculation
ϭ=εE where ϭ – stress
E – Young’s Modulus
For thermal stress calculation,
ϭthermal = E(ε-εthermal)
For Von-mises stress calculation,

12. 3. Shear wall – Node and element label plots
3.1 Shear wall – Node and element labels for concentrated force
Node Labels – Shear Load(Top Edge)
Element Labels – Shear Load

13. 3.2 Shear wall – Node and element labels for thermal load case
Node Labels – Thermal load case
Element Labels – Thermal load case

14. 4. Shell intersection model – Node and element label plots
Node Labels
Element Labels

15. 5. Shear wall – Deformation plot under concentrated force loading
Shear wall deformation plot (concentrated load) from Abaqus
Shear wall deformation plot (concentrated load) from Matlab

16. 6. Shear wall – Deformation plot under thermal loading
Shear wall deformation plot (Thermal load) from Abaqus
Shear wall deformation plot (Thermal load) from Matlab

17. 7. Shell intersection model – Deformation plot under pressure loading
Shell Intersection model deformation plot from Abaqus
8. Discussion of results
8.1 Shear wall
8.1.1 Static pressure loading case
PROGRAM Dx Dy
MATLAB 15.5324 -5.54696
ABAQUS 15.76 -5.58588
PERCENTAGE ERROR 1.44 0.69
8.1.2 Static thermal loading case
PROGRAM Dx Dy
MATLAB 0.29413 0.84120
ABAQUS 0.302049 0.838056
PERCENTAGE ERROR 2.62 0.375

18. 9. Shear wall – Stress Plots
9.1 Stress plots for concentrated force case
Von Mises from Abaqus
Von Mises from Matlab

19. Principal Stress 1 from Abaqus
Principal Stress 1 from Matlab

20. Principal Stress 2 from Abaqus
Principal Stress 2 from Matlab

21. 9.2 Stress plots for thermal load case
Von Mises from Abaqus
Von Mises from Matlab

22. Principal Stress 1 from Abaqus
Principal Stress 1 from Matlab

23. Principal Stress 2 from Abaqus
Principal Stress 2 from Matlab

24. 10. Shell Intersection Model – Stress Plots
10.1 Stress plots for bottom surface
Von Mises @ bottom from Abaqus
Principal Stress 1 @ bottom from Abaqus

25. Principal Stress 2 @ bottom from Abaqus
10.2 Stress plots for top surface
Von Mises @ top from Abaqus

26. Principal Stress 1 @ top from Abaqus
Principal Stress 2 @ top from Abaqus

27. 12. List of Codes
12.1 Shear Wall
12.1.1 Shear Wall – Concentrated Force Case
 CreateBCmatrix_membrane
%This code creates (4X4)B and (4X8)C Matrices
function [B,C] =
CreateBCmatrix_membrane(dhdr,dhdn,ajacinv,x_loc,y_loc,dkdr,dkdn)
B =
[ajacinv(1,1),ajacinv(1,2),0,0;ajacinv(2,1),ajacinv(2,2),0,0;0,0,ajacinv(1,1),a
jacinv(1,2);0,0,ajacinv(2,1),ajacinv(2,2)];
for i = 1:4,
if i < 4
j=i+1;
xlocal(i,1) = x_loc(j,1)-x_loc(i,1);
ylocal(i,1) = y_loc(j,1)-y_loc(i,1);
else if i==4
j=1;
xlocal(i,1) = x_loc(j,1)- x_loc(i,1);
ylocal(i,1) = y_loc(j,1)- y_loc(i,1);
end
end
end;
for i=1:4,
if i<4
j=i+1;
l(i,1) = sqrt(xlocal(i,1)^2+ylocal(i,1)^2);
else if i==4
j=1;
l(i,1) = sqrt(xlocal(i,1)^2+ylocal(i,1)^2);
end
end
end
for i=1:4,
if i<4
j=i+1;
c(i,1) = ylocal(i,1)/l(i,1);
s(i,1) = -xlocal(i,1)/l(i,1);
else if i==4
j=1;
c(i,1)=ylocal(i,1)/l(i,1);
s(i,1)=-xlocal(i,1)/l(i,1);
end
end
end;
C = zeros(4,12);
C=[dhdr(1,1),0,1/8*(-
dkdr(1,1)*l(1,1)*c(1,1)+dkdr(4,1)*l(4,1)*c(4,1)),dhdr(2,1),0,1/8*(-
dkdr(2,1)*l(2,1)*c(2,1)+dkdr(1,1)*l(1,1)*c(1,1)),dhdr(3,1),0,1/8*(-

28. dkdr(3,1)*l(3,1)*c(3,1)+dkdr(2,1)*l(2,1)*c(2,1)),dhdr(4,1),0,1/8*(-
dkdr(4,1)*l(4,1)*c(4,1)+dkdr(3,1)*l(3,1)*c(3,1));dhdn(1,1),0,1/8*(-
dkdn(1,1)*l(1,1)*c(1,1)+dkdn(4,1)*l(4,1)*c(4,1)), dhdn(2,1),0,1/8*(-
dkdn(2,1)*l(2,1)*c(2,1)+dkdn(1,1)*l(1,1)*c(1,1)),dhdn(3,1),0,1/8*(-
dkdn(3,1)*l(3,1)*c(3,1)+dkdn(2,1)*l(2,1)*c(2,1)),dhdn(4,1),0,1/8*(-
dkdn(4,1)*l(4,1)*c(4,1)+dkdn(3,1)*l(3,1)*c(3,1));0,dhdr(1,1),1/8*(-
dkdr(1,1)*l(1,1)*s(1,1)+dkdr(4,1)*l(4,1)*s(4,1)),0,dhdr(2,1),1/8*(-
dkdr(2,1)*l(2,1)*s(2,1)+dkdr(1,1)*l(1,1)*s(1,1)),0,dhdr(3,1),1/8*(-
dkdr(3,1)*l(3,1)*s(3,1)+dkdr(2,1)*l(2,1)*s(2,1)),0,dhdr(4,1),1/8*(-
dkdr(4,1)*l(4,1)*s(4,1)+dkdr(3,1)*l(3,1)*s(3,1));0,dhdn(1,1),1/8*(-
dkdn(1,1)*l(1,1)*s(1,1)+dkdn(4,1)*l(4,1)*s(4,1)),0,dhdn(2,1),1/8*(-
dkdn(2,1)*l(2,1)*s(2,1)+dkdn(1,1)*l(1,1)*s(1,1)),0,dhdn(3,1),1/8*(-
dkdn(3,1)*l(3,1)*s(3,1)+dkdn(2,1)*l(2,1)*s(2,1)),0,dhdn(4,1),1/8*(-
dkdn(4,1)*l(4,1)*s(4,1)+dkdn(3,1)*l(3,1)*s(3,1))];
end
 CreateEA_membrane
%This code creates E (Youngs Modulus) and A Matrices for the membrane element
function [E,A]=CreateEA_membrane(young,poisson)
E=young/(1-poisson^2)*[1,poisson,0;poisson,1,0;0,0,(1-poisson)/2];
A = [1 0 0 0; 0 0 0 1; 0 1 1 0];
end
 CreateJacobian
%Generates the Jacobian Matrix
function [ajac]=CreateJacobian(dhdr,dhdn,x_loc,y_loc)
ajac=zeros(2,2);
ajac=[dhdr'*x_loc,dhdr'*y_loc;dhdn'*x_loc,dhdn'*y_loc];
end
 Jacinv
%Returns the inverse of the Jacobian Matrix
function [ajacinv,det,c]=jacinv(ajac)
c(1,1) = ajac(2,2);
c(1,2) = -ajac(2,1);
c(2,1) = -ajac(1,2);
c(2,2of th = ajac(1,1);
det = 0.0;
for i = 1:2,
det = det + ajac(1,i)*c(1,i);
end;
for i = 1:2,

29. for j = 1:2,
ajacinv(i,j) = c(j,i)/det;
end;
end;
end
 CreateShapeFunc
function [shapeF,dhdr,dhdn] = CreateShapeFunc(r,n)
% CREATE THE SHAPE FUNCTION EVALUATED AT (r,n) AND THEIR DERIVATIVES
% r: Ksi n: Eta
shapeF=zeros(4,1);
dhdr=zeros(4,1);
dhdn=zeros(4,1);
% INCLUDE THE 4 SHAPE FUNCTIONS AND DERIVATIVES
% CALCULATE THE SHAPE FUNCTIONS
shapeF(1,1)=((1-r)*(1-n))/4;
shapeF(2,1)=((1+r)*(1-n))/4;
shapeF(3,1)=((1+r)*(1+n))/4;
shapeF(4,1)=((1-r)*(1+n))/4;
% CALCULATE THE DERIVATIVES OF THE SHAPE FUNCTION W.R.T r
dhdr(1,1)=-0.25*(1-n);
dhdr(2,1)=0.25*(1-n);
dhdr(3,1)=0.25*(1+n);
dhdr(4,1)=-0.25*(1+n);
% CALCULATE THE DERIVATIVES OF THE SHAPE FUNCTION W.R.T n
dhdn(1,1)=-0.25*(1-r);
dhdn(2,1)=-0.25*(1+r);
dhdn(3,1)=0.25*(1+r);
dhdn(4,1)=0.25*(1-r);
end
 Stiff_membrane
function [akloc_m,fel_m,amloc_m] =
stiff_membrane(young,poisson,density,x_loc,y_loc,z_loc,dTemp,coefExp,Thickness)
msize = 12;
fel_m = zeros(msize,1);
akloc_m = zeros(msize,msize);
amloc_m = zeros(msize,msize);
% ZERO ELEMENT THERMAL FORCE VECTOR.
felTher = zeros(msize,1);
% CREATE THE [E] Elasticity and [A] MATRIX FOR THE ELEMENT.

30. [E,A]=CreateEA_membrane(young,poisson);
% NUMBER OF GAUSS POINT TO USE FOR THE NUMERICAL INTEGRATION.
nGP=3;
gamma=1e5;
% THERMAL STRAIN.
ThermalStrain=zeros(3,1);
ThermalStrain(1:2,1)=coefExp*dTemp;
% CALCULATE ELEMENT STIFFNESS MATRIX, MASS MATRIX AND FORCE VECTOR.
for i=1:nGP,
[r,wr]=GaussPoint(nGP,i);
for j=1:nGP,
[n,wn]=GaussPoint(nGP,j);
% Create the Shape functions and their derivatives
[shapeF,dhdr,dhdn]=CreateShapeFunc(r,n);
[dkdr,dkdn]=CreateMidSideShapeFunc(r,n);
% Create the jacobian and its inverse
[ajac]=CreateJacobian(dhdr,dhdn,x_loc,y_loc);
[ajacinv,det,c]=jacinv(ajac);
% Create B and C of membrane
[B,C]=CreateBCmatrix_membrane(dhdr,dhdn,ajacinv,x_loc,y_loc,dkdr,dkdn);
% Create extra stiffness matrix for constraint
G=RotDispCoupling(dhdr,dhdn,dkdr,dkdn,B,C,ajacinv,x_loc,y_loc,shapeF);
% Local Stiffness Matrix
Kms=Thickness*wr*wn*C'*B'*A'*E*A*B*C*det;
Kmc=gamma*Thickness*wr*wn*G*det;
akloc_m=akloc_m+Kms+Kmc;
end
end
 Loc2GlobTrans
function [akglob,felglob] = Loc2GlobTrans(akloc,felloc,lambda,amloc)
% [L] 24x24 TRANSFORMATION MATRIX
L = eye(24,24);
L = blkdiag(lambda,lambda,lambda,lambda,lambda,lambda,lambda,lambda);
% CALCULATE ELEMENT STIFFNESS MATRIX IN GLOBAL COORDINATE SYSTEM
akglob = L'*akloc*L;
% CALCULATE ELEMENT MASS MATRIX IN GLOBAL COORDINATE SYSTEM
%amglob = L'*amloc*L;
% CALCULATE ELEMENT FORCE VECTOR IN GLOBAL COORDINATE SYSTEM
felglob = L'*felloc;

31. end
 RotDispCoupling
function [ G ]
=RotDispCoupling(dhdr,dhdn,dkdr,dkdn,B,C,ajacinv,x_loc,y_loc,shapeF)
G1 =[0,0,shapeF(1),0,0,shapeF(2),0,0,shapeF(3),0,0,shapeF(4)];
A1= [0,-1/2,1/2,0];
G = ((A1*B*C)-G1)'*((A1*B*C)-G1);
 FEA3DDKQ_create_input
function FEA3DDKQ_create_input
node=load('FEA3DDKQ_node.txt');
element=load('FEA3DDKQ_element.txt');
num_ele = size(element,1);
coord = node(:,2:4);
lotogo = zeros(num_ele,4);
% Load Local Node Numbering Connectivity Data
% from Abaqus to FEA
lotogo(:,1) = element(:,2);
lotogo(:,2) = element(:,3);
lotogo(:,3) = element(:,4);
lotogo(:,4) = element(:,5);
% Adding the Boundary Restraint Conditions
% ----------------------------------------
% jj = 1 means that DOF is free to move
% jj = 0 means the DOF is fixed or restrained
%
jj = ones(size(coord,1),6);
jj(:,3:5)=0;
jj(23,1:6)=0;
jj(164,1:6)=0;
jj(165,1:6)=0;
jj(166,1:6)=0;
jj(167,1:6)=0;
jj(168,1:6)=0;
jj(169,1:6)=0;
jj(16,1:6)=0;
jj(93,1:6)=0;
jj(94,1:6)=0;
jj(95,1:6)=0;
jj(96,1:6)=0;
jj(97,1:6)=0;
jj(7,1:6)=0;
jj(44,1:6)=0;
jj(45,1:6)=0;
jj(1,1:6)=0;

32. jj(24,1:6)=0;
jj(25,1:6)=0;
jj(2,1:6)=0;
%
% Set Restraints to Zero for Nodes at the "offset"
% offset = -25;
% ind = (abs(coord(:,1)-offset)<1e-6);
% %
% jj(ind,:) = 0;
% Material Properties
%young = 2.9E+7;
young =4.2E+6;
poisson = 0.3;
density = .0003;
coefExp = 7.6E-6;
% Dynamic Analysis Parameters
ntimeStep = 200;
dt = .005;
AlfaDamp = 0.08;
BetaDamp = 0.002;
% Temperature Variation
dTemp = 60;
% Thickness of the Shell
Thickness = 6;
Pressure = 4500;
ifornod = [20 150 149 148 147 146 145 144 143 142 141 21]; ifordir = [1 1 1 1 1 1
1 1 1 1 1 1]; forval = [727272.727 1454545.45 1454545.45 1454545.45 1454545.45
1454545.45 1454545.45 1454545.45 1454545.45 1454545.45 1454545.45 727272.727];
save FEA_input_data.mat coord lotogo jj young poisson density ifornod ifordir
forval ntimeStep dt AlfaDamp BetaDamp dTemp coefExp Thickness Pressure;
clear
12.1.2 Shear Wall – Thermal Load Case
 Stiff_membrane
function [akloc_m,fel_m,amloc_m] =
stiff_membrane(young,poisson,density,x_loc,y_loc,z_loc,dTemp,coefExp,Thickness)
msize = 12;
fel_m = zeros(msize,1);
akloc_m = zeros(msize,msize);
amloc_m = zeros(msize,msize);
% ZERO ELEMENT THERMAL FORCE VECTOR.

33. felTher = zeros(msize,1);
% CREATE THE [E] Elasticity and [A] MATRIX FOR THE ELEMENT.
[E,A]=CreateEA_membrane(young,poisson);
% NUMBER OF GAUSS POINT TO USE FOR THE NUMERICAL INTEGRATION.
nGP=3;
gamma=1e5;
% THERMAL STRAIN.
ThermalStrain=zeros(3,1);
ThermalStrain=[(coefExp*dTemp);(coefExp*dTemp);0];
% CALCULATE ELEMENT STIFFNESS MATRIX, MASS MATRIX AND FORCE VECTOR.
for i=1:nGP,
[r,wr]=GaussPoint(nGP,i);
for j=1:nGP,
[n,wn]=GaussPoint(nGP,j);
% Create the Shape functions and their derivatives
[shapeF,dhdr,dhdn]=CreateShapeFunc(r,n);
[dkdr,dkdn]=CreateMidSideShapeFunc(r,n);
% Create the jacobian and its inverse
[ajac]=CreateJacobian(dhdr,dhdn,x_loc,y_loc);
[ajacinv,det,c]=jacinv(ajac);
% Create B and C of membrane
[B,C] =
CreateBCmatrix_membrane(dhdr,dhdn,ajacinv,x_loc,y_loc,dkdr,dkdn);
G=RotDispCoupling(dhdr,dhdn,dkdr,dkdn,B,C,ajacinv,x_loc,y_loc,shapeF);
% Local Stiffness Matrix
Kms=Thickness*wr*wn*C'*B'*A'*E*A*B*C*det;
Kmc=gamma*Thickness*wr*wn*G*det;
akloc_m=akloc_m+Kms+Kmc;
% Thermal Force Vector
D = [A*B*C];
fel_m=fel_m+Thickness*[D'*E*ThermalStrain*wr*wn*det];
end
end
 Stress
function
[sig]=stress(young,poisson,x_loc,y_loc,z_loc,disp,r,n,dTemp,coefExp,Thickness)
sig = zeros(3,3); % 1st column @ bottom surface (z=-h/2),
% 2nd column @ midsurface (z=0), and
% 3rd column @ top surface (z=h/2)
sig_m = zeros(3,1);
sig_b = zeros(3,1);
% ZERO STRESSES - SIGMA_Von_Mises, SIGMA_1, SIGMA_2.
sig_out = zeros(3,3); % 1st column @ bottom surface (z=-h/2),
% 2nd column @ midsurface (z=0), and

34. % 3rd column @ top surface (z=h/2)
sigVon = zeros(1,3); % Von-Mises Stress
sig_P = zeros(2,3); % Principal Stresses, 1st row is SIGMA_1, 2nd row is
SIGMA_2
% ZERO DISPLACEMENT VECTORS
disp_m = zeros(12,1);
disp_p = zeros(12,1);
%
%Thermal Strain
ThermalStrain = zeros(3,1);
%COMPUTE STRESSES OF MEMBRANE
%CREATE THE [E] Elasticity and [A] MATRIX FOR THE ELEMENT
[E,A]=CreateEA_membrane(young,poisson);
% Create the Shape functions and their derivatives
[shapeF,dhdr,dhdn]=CreateShapeFunc(r,n);
[dkdr,dkdn]=CreateMidSideShapeFunc(r,n);
% CREATE JACOBIAN AND ITS INVERSE
[ajac]=CreateJacobian(dhdr,dhdn,x_loc,y_loc);
[ajacinv,det,c]=jacinv(ajac);
% CREATE B AND C MATRICES
[B,C]=CreateBCmatrix_membrane(dhdr,dhdn,ajacinv,x_loc,y_loc,dkdr,dkdn);
%CREATE ELEMENT DISPLACEMENT VECTOR OF MEMBRANE
disp_m=[disp(1,1);disp(2,1);disp(6,1);disp(7,1);disp(8,1);disp(12,1);disp(13,1);d
isp(14,1);disp(18,1);disp(19,1);disp(20,1);disp(24,1)];
%CALCULATE THE 3x1 STRESS VECTOR
sig_m=E*(A*B*C*disp_m-ThermalStrain);
%COMPUTE STRESSES OF BENDING
%CREATE THE [E] Elasticity and [A] MATRIX FOR THE ELEMENT
%CALL THE FUNCTION THAT CREATE THE DERIVATIVES OF SHAPE FUNCTIONS
%CREATE THE INVERSE OF JACOBIAN TO FORMULATE B_b
%CREATE THE B AND C MATRICES
%CREATE ELEMENT DISPLACEMENT VECTOR OF BENDING
%Calculate the 3*1 stress vector @ z = h/2 (h: shell thickness)
% use E not E_b (E_b is for stiff calc.)

35. % CALCULATE THE STRESS VECTOR AT BOTTOM, MID, AND TOP SURFACE OF THE SHELL
ELEMENT THICKNESS.
sig_out(:,1) = sig_m - sig_b; % Stress @ z = -h/2
sig_out(:,2) = sig_m; % Stress @ z = 0
sig_out(:,3) = sig_m + sig_b; % Stress @ z = +h/2
%
%
% % CALCULATE THE VON-MISES STRESS COMPONENT (IF REQUIRED).
for i=1:3
sig(1,:)=sqrt(0.5*((sig_out(1,i)-
sig_out(2,i))^2+(sig_out(1,i))^2+(sig_out(2,i))^2)+3*(sig_out(3,i))^2);
end
% % CALCULATE THE PRINCIPAL STRESS COMPONENTS (IF REQUIRED).
for i =1:3
sig(2,:)=0.5*(sig_out(1,i)+sig_out(2,i))+sqrt(((sig_out(1,i)-
sig_out(2,i))/2)^2+sig_out(3,i)^2);
end
for i=1:3
sig(3,:)=0.5*(sig_out(1,i)+sig_out(2,i))-sqrt(((sig_out(1,i)-
sig_out(2,i))/2)^2+sig_out(3,i)^2);
end
% % RETURN THE VON-MISES STRESS AND PRINCIPAL STRESSES (IF REQUIRED).
%sig= [sigVon;sig_P];
end
 FEA3DDKQ_create_input
function FEA3DDKQ_create_input
node = load('FEA3DDKQ_node.txt');
element = load('FEA3DDKQ_element.txt');
num_ele = size(element,1);
coord = node(:,2:4);
lotogo = zeros(num_ele,4);
% Load Local Node Numbering Connectivity Data
% from Abaqus to FEA
lotogo(:,1) = element(:,2);
lotogo(:,2) = element(:,3);
lotogo(:,3) = element(:,4);
lotogo(:,4) = element(:,5);
% Adding the Boundary Restraint Conditions
% ----------------------------------------
% jj = 1 means that DOF is free to move
% jj = 0 means the DOF is fixed or restrained
%
jj = ones(size(coord,1),6);

36. jj(:,3:5)=0;
jj(23,1:6)=0;
jj(164,1:6)=0;
jj(165,1:6)=0;
jj(166,1:6)=0;
jj(167,1:6)=0;
jj(168,1:6)=0;
jj(169,1:6)=0;
jj(16,1:6)=0;
jj(93,1:6)=0;
jj(94,1:6)=0;
jj(95,1:6)=0;
jj(96,1:6)=0;
jj(97,1:6)=0;
jj(7,1:6)=0;
jj(44,1:6)=0;
jj(45,1:6)=0;
jj(1,1:6)=0;
jj(24,1:6)=0;
jj(25,1:6)=0;
jj(2,1:6)=0;
%
% Set Restraints to Zero for Nodes at the "offset"
% offset = -25;
% ind = (abs(coord(:,1)-offset)<1e-6);
% %
% jj(ind,:) = 0;
% Material Properties
%young = 2.9E+7;
young =4.2E+6;
poisson = 0.3;
density = .0003;
coefExp = 7.6E-6;
% Dynamic Analysis Parameters
ntimeStep = 200;
dt = .005;
AlfaDamp = 0.08;
BetaDamp = 0.002;
% Temperature Variation
dTemp = 60;
% Thickness of the Shell
Thickness = 6;
Pressure = 4500;
% ----------------------------------------
% Concentrated Forces
% ----------------------------------------
% force directions (1 - x, 2 - y, 3 - z)
% ifornod - Global nodes at which forces are applied
% ifordir - Direction of forces

37. % forval - Force values
% end
ifornod = [20]; ifordir = [1]; forval = [0];
% ----------------------------------------
save FEA_input_data.mat coord lotogo jj young poisson density ifornod ifordir
forval ntimeStep dt AlfaDamp BetaDamp dTemp coefExp Thickness Pressure;
clear