MATLAB Answers

Issues with plotting/best method

조회 수: 1(최근 30일)
Eddy Ramirez
Eddy Ramirez 2021년 4월 17일
편집: per isakson 2021년 4월 17일
Greetings,
I would like to plot the following, but I get a blank graph and I am not sure if it is the way I am inputting the values
any recommendations? or a different approach?
close all
clear all
clc
%%%FIBER
Ef=220e9;%[N/m] GPA to Newton/square meter
Vf=.63; %fiber volume fraction
vf=.33;%fiber poissions ratio
%%MATRIX
Em=10e9;%[N/m] GPA to Newton/square meter
Vm=1-Vf; %%matrix volume fraction
vm=.33;%%matrix poissons ratio
Em2=Em/(1-vm^2); %equation 3.31
%%Lamina's Thickness
h=1e-3;%[N/m] mm to Newton/square meter
%%Shear modulus
Gf=Ef/(2*(1+vf));
Gm=Em/(2*(1+vm));
%%Lamina Properties
E1=(Vf*Ef)+(Vm*Em);
E2=(Ef*Em)/(Vf*Gm+Vm*Gf);
E_2=Ef*Em2/(Vf*Em2+Vm*Ef); %equation 3.32
v12=(Vf*vf)+(Vm*vm);
v21=(E2/E1)*v12;
G12=(Gf*Gm)/((Vf*Gm)+(Vm*Gf));
% Reduced local in plane stiffness Q
Q11=E1/(1-v12*v21);
Q12=(v21*E1)/(1-v12*v21);
Q22=E2/(1-v12*v21);
Q66=G12;
Q=[Q11,Q12,0;
Q12,Q22,0;
0,0,Q66];
%%Laminate rotations in degrees
theta=[0,45,-45,90,30,60,-30,-60,-60,-30,60,30,90,-45,45,0];
%%Laminate rotations in radians
% theta=pi/180*[0;45;-45;90;30;60;-30;-60]';%%DEGREES TO RADIANS
% theta=[theta;theta(end:-1:1)];
z=(-length(theta)/2+(0:length(theta)))'*h;
% Global Q matrix:
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
for i=1:length(theta)
m=cosd(theta(i));
n=sind(theta(i));
T=[m.^2,n.^2,2.*m.*n;
n.^2,m.^2,-2.*m.*n;
-m.*n,m.*n,m.^2-n.^2];
% Global transformed reduced stiffness coefficients Q_bar
Q_bar{i}=inv(T).*Q.*T;
end
Aij=0;
Bij=0;
Dij=0;
for j=1:length(theta)
A_j=Q_bar{j}*(z(j+1)-z(j));
Aj{j}=A_j;
Aij=Aij+Aj{j};
B_j=Q_bar{j}*((z(j+1))^2-(z(j))^2);
Bj{j}=B_j;
Bij=Bij+Bj{j};
D_j=Q_bar{j}*((z(j+1))^3-(z(j))^3);
Dj{j}=D_j;
Dij=Dij+Dj{j};
end
A=Aij;
B=(1/2)*Bij;
D=(1/3)*Dij;
%%Forces
Nx=2e6;
Ny=4.6e6;
Ns=0;
N=[Nx;Ny;Ns];
%%Moments
Mx=3e3;
My=0;
Ms=-1e-3;
M=[Mx;My;Ms];
%%Shear
e_x=sym('Epsilonx');
e_y=sym('Epsilony');
gamma_xy=sym('Gammaxy');
shear=[e_x;e_y; gamma_xy];
%%Bending Twist
k_x=sym('Kx');
k_y=sym('Ky');
k_xy=sym('Kxy');
bending=[k_x;k_y;k_xy];
%%Shear Extension Coupling
SEC=N==A*shear;
SEC_F=solve(SEC);
e_xf=vpa(SEC_F.Epsilonx);
e_yf=vpa(SEC_F.Epsilony);
gamma_xyf=(SEC_F.Gammaxy);
shearf=[e_xf;e_yf; gamma_xyf];
%%Bending
BEC=M==D*bending;
BEC_F=solve(BEC);
k_xf=vpa(BEC_F.Kx);
k_yf=vpa(BEC_F.Ky);
k_xyf=vpa(BEC_F.Kxy);
bendingf=[k_xf;k_yf;k_xyf];
test=Q_bar{1}*shearf+z(1,1)*Q_bar{1}*bendingf;
test1=Q_bar{1}.*shearf+z(2,1)*Q_bar{1}.*bendingf;
% plot(test(1,1), z(1,1));
for k=1:length(theta)
stress1=Q_bar{k}*shearf+z(k)*Q_bar{k}*bendingf;%%BOTTOM LAYER
stress2=Q_bar{k}*shearf+z(k+1)*Q_bar{k}*bendingf;%%TOP LAYER
stress1f{k}=stress1; %Bottom
stress2f{k}=stress2; %Top
end
b0=stress1f{1};
b1=stress1f{2};
b2=stress1f{3};
b3=stress1f{4};
b4=stress1f{5};
b5=stress1f{6};
b6=stress1f{1};
b7=stress1f{7};
b8=stress1f{8};
b9=stress1f{9};
b10=stress1f{10};
b11=stress1f{11};
b12=stress1f{12};
b13=stress1f{13};
b14=stress1f{14};
b15=stress1f{15};
t0=stress2f{1};
t1=stress2f{2};
t2=stress2f{3};
t3=stress2f{4};
t4=stress2f{5};
t5=stress2f{6};
t6=stress2f{1};
t7=stress2f{7};
t8=stress2f{8};
t9=stress2f{9};
t10=stress2f{10};
t11=stress2f{11};
t12=stress2f{12};
t13=stress2f{13};
t14=stress2f{14};
t15=stress2f{15};
plot(b0(1,1), z(1,1))
keyboard
hold on
plot(t0(1,1), z(2,1))
plot(b1(1,1), z(2,1))
plot(t1(1,1), z(3,1))
plot(b2(1,1), z(3,1))
plot(t2(1,1), z(4,1))
plot(b3(1,1), z(4,1))
plot(t3(1,1), z(5,1))
plot(b4(1,1), z(5,1))
plot(t4(1,1), z(6,1))
plot(b5(1,1), z(6,1))
plot(t5(1,1), z(7,1))
plot(b6(1,1), z(7,1))
plot(t6(1,1), z(8,1))
plot(b7(1,1), z(8,1))
plot(t7(1,1), z(9,1))
plot(b8(1,1), z(9,1))
plot(t8(1,1), z(10,1))
plot(b9(1,1), z(10,1))
plot(t9(1,1), z(11,1))
plot(b10(1,1), z(11,1))
plot(t10(1,1), z(12,1))
plot(b11(1,1), z(12,1))
plot(t11(1,1), z(13,1))
plot(b12(1,1), z(13,1))
plot(t12(1,1), z(14,1))
plot(b13(1,1), z(14,1))
plot(t13(1,1), z(15,1))
plot(b14(1,1), z(15,1))
plot(t14(1,1), z(16,1))
plot(b15(1,1), z(16,1))
plot(t15(1,1), z(17,1))
hold off
keyboard
  댓글 수: 8
Clayton Gotberg
Clayton Gotberg 2021년 4월 17일
To connect the dots, just plot all of the points at once in the order you want them to be connected, using a line.
If I have three points (x_a, y_a), (x_b,y_b), and (x_c,y_c), I can plot them separately or together:
%Separately
plot(x_a, y_a,'k.')
plot(x_b, y_b,'k.')
plot(x_c, y_c,'k.')
%Together
plot([x_a x_b x_c],[y_a y_b y_c],'k-')
% Or
X = [x_a x_b x_c];
Y = [y_a y_b y_c];
plot(X,Y,'k-')

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답변(2개)

LO
LO 2021년 4월 17일
short answer: you are plotting points singularly so you can't see them
short solution: pool them together in arrays then use the command to plot
arrays can be made using the line
[a,b,c,d,.....,z]
where letters are your values for bottom or top
I am not familiar with the sym data format but I think the issue might be just in the way you plot there. Also comment the keyboard otherwise it gets stuck in debugging.
see your code with scatter instead of plot (scatter can plot single points, plot can too but if you plot a single points one by one you will not see them, they have to be organized in arrays)
close all
clear all
clc
%%%FIBER
Ef=220e9;%[N/m] GPA to Newton/square meter
Vf=.63; %fiber volume fraction
vf=.33;%fiber poissions ratio
%%MATRIX
Em=10e9;%[N/m] GPA to Newton/square meter
Vm=1-Vf; %%matrix volume fraction
vm=.33;%%matrix poissons ratio
Em2=Em/(1-vm^2); %equation 3.31
%%Lamina's Thickness
h=1e-3;%[N/m] mm to Newton/square meter
%%Shear modulus
Gf=Ef/(2*(1+vf));
Gm=Em/(2*(1+vm));
%%Lamina Properties
E1=(Vf*Ef)+(Vm*Em);
E2=(Ef*Em)/(Vf*Gm+Vm*Gf);
E_2=Ef*Em2/(Vf*Em2+Vm*Ef); %equation 3.32
v12=(Vf*vf)+(Vm*vm);
v21=(E2/E1)*v12;
G12=(Gf*Gm)/((Vf*Gm)+(Vm*Gf));
% Reduced local in plane stiffness Q
Q11=E1/(1-v12*v21);
Q12=(v21*E1)/(1-v12*v21);
Q22=E2/(1-v12*v21);
Q66=G12;
Q=[Q11,Q12,0;
Q12,Q22,0;
0,0,Q66];
%%Laminate rotations in degrees
theta=[0,45,-45,90,30,60,-30,-60,-60,-30,60,30,90,-45,45,0];
%%Laminate rotations in radians
% theta=pi/180*[0;45;-45;90;30;60;-30;-60]';%%DEGREES TO RADIANS
% theta=[theta;theta(end:-1:1)];
z=(-length(theta)/2+(0:length(theta)))'*h;
% Global Q matrix:
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
for i=1:length(theta)
m=cosd(theta(i));
n=sind(theta(i));
T=[m.^2,n.^2,2.*m.*n;
n.^2,m.^2,-2.*m.*n;
-m.*n,m.*n,m.^2-n.^2];
% Global transformed reduced stiffness coefficients Q_bar
Q_bar{i}=inv(T).*Q.*T;
end
Aij=0;
Bij=0;
Dij=0;
for j=1:length(theta)
A_j=Q_bar{j}*(z(j+1)-z(j));
Aj{j}=A_j;
Aij=Aij+Aj{j};
B_j=Q_bar{j}*((z(j+1))^2-(z(j))^2);
Bj{j}=B_j;
Bij=Bij+Bj{j};
D_j=Q_bar{j}*((z(j+1))^3-(z(j))^3);
Dj{j}=D_j;
Dij=Dij+Dj{j};
end
A=Aij;
B=(1/2)*Bij;
D=(1/3)*Dij;
%%Forces
Nx=2e6;
Ny=4.6e6;
Ns=0;
N=[Nx;Ny;Ns];
%%Moments
Mx=3e3;
My=0;
Ms=-1e-3;
M=[Mx;My;Ms];
%%Shear
e_x=sym('Epsilonx');
e_y=sym('Epsilony');
gamma_xy=sym('Gammaxy');
shear=[e_x;e_y; gamma_xy];
%%Bending Twist
k_x=sym('Kx');
k_y=sym('Ky');
k_xy=sym('Kxy');
bending=[k_x;k_y;k_xy];
%%Shear Extension Coupling
SEC=N==A*shear;
SEC_F=solve(SEC);
e_xf=vpa(SEC_F.Epsilonx);
e_yf=vpa(SEC_F.Epsilony);
gamma_xyf=(SEC_F.Gammaxy);
shearf=[e_xf;e_yf; gamma_xyf];
%%Bending
BEC=M==D*bending;
BEC_F=solve(BEC);
k_xf=vpa(BEC_F.Kx);
k_yf=vpa(BEC_F.Ky);
k_xyf=vpa(BEC_F.Kxy);
bendingf=[k_xf;k_yf;k_xyf];
test=Q_bar{1}*shearf+z(1,1)*Q_bar{1}*bendingf;
test1=Q_bar{1}.*shearf+z(2,1)*Q_bar{1}.*bendingf;
% scatter(test(1,1), z(1,1));
for k=1:length(theta)
stress1=Q_bar{k}*shearf+z(k)*Q_bar{k}*bendingf; %%BOTTOM LAYER
stress2=Q_bar{k}*shearf+z(k+1)*Q_bar{k}*bendingf; %%TOP LAYER
stress1f{k}=stress1; %Bottom
stress2f{k}=stress2; %Top
end
b0=stress1f{1};
b1=stress1f{2};
b2=stress1f{3};
b3=stress1f{4};
b4=stress1f{5};
b5=stress1f{6};
b6=stress1f{1};
b7=stress1f{7};
b8=stress1f{8};
b9=stress1f{9};
b10=stress1f{10};
b11=stress1f{11};
b12=stress1f{12};
b13=stress1f{13};
b14=stress1f{14};
b15=stress1f{15};
t0=stress2f{1};
t1=stress2f{2};
t2=stress2f{3};
t3=stress2f{4};
t4=stress2f{5};
t5=stress2f{6};
t6=stress2f{1};
t7=stress2f{7};
t8=stress2f{8};
t9=stress2f{9};
t10=stress2f{10};
t11=stress2f{11};
t12=stress2f{12};
t13=stress2f{13};
t14=stress2f{14};
t15=stress2f{15};
scatter(b0(1,1), z(1,1))
% keyboard
hold on
scatter(t0(1,1), z(2,1))
scatter(b1(1,1), z(2,1))
scatter(t1(1,1), z(3,1))
scatter(b2(1,1), z(3,1))
scatter(t2(1,1), z(4,1))
scatter(b3(1,1), z(4,1))
scatter(t3(1,1), z(5,1))
scatter(b4(1,1), z(5,1))
scatter(t4(1,1), z(6,1))
scatter(b5(1,1), z(6,1))
scatter(t5(1,1), z(7,1))
scatter(b6(1,1), z(7,1))
scatter(t6(1,1), z(8,1))
scatter(b7(1,1), z(8,1))
scatter(t7(1,1), z(9,1))
scatter(b8(1,1), z(9,1))
scatter(t8(1,1), z(10,1))
scatter(b9(1,1), z(10,1))
scatter(t9(1,1), z(11,1))
scatter(b10(1,1), z(11,1))
scatter(t10(1,1), z(12,1))
scatter(b11(1,1), z(12,1))
scatter(t11(1,1), z(13,1))
scatter(b12(1,1), z(13,1))
scatter(t12(1,1), z(14,1))
scatter(b13(1,1), z(14,1))
scatter(t13(1,1), z(15,1))
scatter(b14(1,1), z(15,1))
scatter(t14(1,1), z(16,1))
scatter(b15(1,1), z(16,1))
scatter(t15(1,1), z(17,1))
hold off
% keyboard

per isakson
per isakson 2021년 4월 17일
I added 'd' to all your plot-commands
plot(b0(1,1), z(1,1), 'd' )
keyboard
hold on
plot(t0(1,1), z(2,1), 'd' )
plot(b1(1,1), z(2,1), 'd' )
plot(t1(1,1), z(3,1), 'd' )
plot(b2(1,1), z(3,1), 'd' )
etc.
Now the script outputs
  댓글 수: 3
per isakson
per isakson 2021년 4월 17일
To draw a line you need a vector of at least two elements. That's true for both plot and stairs. I joined only a subset of your points.
x = [t0(1,1),b1(1,1),t1(1,1),b2(1,1),t2(1,1),b3(1,1),t3(1,1),b4(1,1),t4(1,1),b5(1,1),t5(1,1),b6(1,1),t6(1,1),b7(1,1),t7(1,1)];
y = [z(2,1),z(2,1),z(3,1),z(3,1),z(4,1),z(4,1),z(5,1),z(5,1),z(6,1),z(6,1),z(7,1),z(7,1),z(8,1),z(8,1),z(9,1)];
stairs( x, y, '-dk' )
outputs
and replace '-dk' by '-k' to remove the markers
Not all of the lines of unnamed.png are vertical or horizontal. plot( x, y, '-dk' ) produces

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