Predicting Young's Modulus of Banana-Epoxy Composite Using MATLAB

In summary, the conversation is about analyzing a composite part made of carbon/epoxy with [+45/-45]2s layup. The material properties for carbon/epoxy are provided from a textbook and the coordinate system for the part is shown. The process of transforming the material properties into the coordinate system is discussed, involving the use of stiffness and compliance matrices. A MATLAB code is also provided for calculating the material properties, but there seems to be an issue with the out-of-plane stiffness being higher than the in-plane stiffness.
  • #1
barbarahowser
3
0
Hi,
I am trying to analyze a composite part which is made of carbon/epoxy and has [+45/-45]2s as the layup. I got the following material properties for carbon/epoxy from the textbook "Engineering Mechanics of Composite Materials", by I.M. Daniel & O. Ishai,
Longitudinal Modulus, E1=147Gpa
Transverse In-plane, E2=10.3Gpa
Transverse out of plane, E3=10.3Gpa
In plane shear modulus, G12=7Gpa
Out of plane shear modulus, G23=3.7Gpa
Out of plane shear modulus, G13=7Gpa
Major in-plane Poisson's ratio, niu12=0.27
Major in-plane Poisson's ratio, niu23=0.54
Major in-plane Poisson's ratio, niu13=0.27

The coordinate system of the part is shown in figure attached with the fiber laid up in the YZ plane. Can someone please tell me how I can transform the material properties given above into the coordinate system shown in (composite part.jpeg)

Thanks,
Barbara
 

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  • #2
Hi Barbara,

you've a reference of lamina & laminate analysis nearby (that textbook might do it although haven't got it myself so can't check)? 1st you derive the properties for different orthotropic lamina (you've the basic elements there which you've collected), like the stiffness or compliance matrix (depending on what you're after), and then you "stack them" in the laminate part (laminate=several lamina) of the analysis (which can then contain for example a stress analysis of some "element" using the laminate in question). The properties are transformed between coordinate systems in the process, typically using so called transformation matrices.

It's somewhat lengthy to present, so if you'd have a book on the subject available with a consistent run through of it all it would help a lot.
 
  • #3
Hi,
Thanks for the reply. Here is what I did,
1. Calculate the compliance matrix using the available material properties.
2. Calculate transformation matrices for +45 and -45. This will be transformation about X-axis (i.e rotation about X-axis) since X-axis is the perpendicular out-of-plane axis.
3. Calculate ABD matrix using lamination theory
4. Calculate inverse of ABD matrix
5. Calculate material properties using the inverse of ABD matrix

The problem is that using this code, I get the out-of plane stiffness EX higher than the in-plane stiffness EY and EZ which I think is wrong since out-of-plane stiffness should always be lower.

Can you tell me whether the procedure I am using is right or not? I would really appreciate any help on this!

Below is the MATLAB code used according to procedure given above,

format long
%Material Properties
E1=147e9
E2=10.3e9
E3=10.3e9
G12=7e9
G23=3.7e9
G13=7e9
niu12=0.27
niu23=0.54
niu13=0.27
tply=6.35e-4
t=0.00508

S=[(1/E1) (-niu12/E1) (-niu13/E1) 0 0 0;(-niu12/E1) 1/E2 (-niu23/E2) 0 0 0;(-niu13/E1) (-niu23/E2) 1/E3 0 0 0;0 0 0 1/G23 0 0;0 0 0 0 1/G13 0;0 0 0 0 0 1/G12]
Q = inv(S)

%Calculation of Qbar matrix for different fibre orientations
m=cos(pi/4)
n=sin(pi/4)
%Roattion about X axis
Tsigma=[1 0 0 0 0 0;0 m^2 n^2 2*m*n 0 0;0 n^2 m^2 -2*m*n 0 0;0 -m*n m*n (m^2-n^2) 0 0;0 0 0 0 m -n;0 0 0 0 n m]
Tepsilon=[1 0 0 0 0 0;0 m^2 n^2 m*n 0 0;0 n^2 m^2 -m*n 0 0;0 -2*m*n 2*m*n (m^2-n^2) 0 0;0 0 0 0 m -n;0 0 0 0 n m]
Qbar45=inv(Tsigma)*Q*Tepsilon

m=cos(-pi/4)
n=sin(-pi/4)
Rotation about X axis
Tsigma=[1 0 0 0 0 0;0 m^2 n^2 2*m*n 0 0;0 n^2 m^2 -2*m*n 0 0;0 -m*n m*n (m^2-n^2) 0 0;0 0 0 0 m -n;0 0 0 0 n m]
Tepsilon=[1 0 0 0 0 0;0 m^2 n^2 m*n 0 0;0 n^2 m^2 -m*n 0 0;0 -2*m*n 2*m*n (m^2-n^2) 0 0;0 0 0 0 m -n;0 0 0 0 n m]

Qbar_45=inv(Tsigma)*Q*Tepsilon

h0=-2.54e-3
h1=-1.905e-3
h2=-1.27e-3
h3=-6.35e-4
h4=0
h5=6.35e-4
h6=1.27e-3
h7=1.905e-3
h8=2.54e-3

%ABD matirx
A=Qbar45*(h1-h0)+Qbar_45*(h2-h1)+Qbar45*(h3-h2)+Qbar_45*(h4-h3)+Qbar_45*(h5-h4)+Qbar45*(h6-h5)+Qbar_45*(h7-h6)+Qbar45*(h8-h7)
B=(1/2)*(Qbar45*(h1^2-h0^2)+Qbar_45*(h2^2-h1^2)+Qbar45*(h3^2-h2^2)+Qbar_45*(h4^2-h3^2)+Qbar_45*(h5^2-h4^2)+Qbar45*(h6^2-h5^2)+Qbar_45*(h7^2-h6^2)+Qbar45*(h8^2-h7^2))
D=(1/3)*(Qbar45*(h1^3-h0^3)+Qbar_45*(h2^3-h1^3)+Qbar45*(h3^3-h2^3)+Qbar_45*(h4^3-h3^3)+Qbar_45*(h5^3-h4^3)+Qbar45*(h6^3-h5^3)+Qbar_45*(h7^3-h6^3)+Qbar45*(h8^3-h7^3))

ABD=[A B;B D]
abd=inv(ABD)

%Calculate material properties
EZ=1/((abd(1,1))*t)
Ey=1/((abd(2,2))*t)
EX=1/((abd(3,3))*t)

niuzy=-(abd(2,1)/abd(1,1))
niuxy=-(abd(3,2)/abd(2,2))
niuxz=-(abd(3,1)/abd(1,1))

Gzy=1/((abd(6,6))*t)
Gxz=1/((abd(5,5))*t)
Gxy=1/((abd(4,4))*t)



Thanks,
Barbara
 
  • #4
Im sorry there was a probelm in the last part of the code. Here is the correct one,

format long
%Material Properties
E1=147e9
E2=10.3e9
E3=10.3e9
G12=7e9
G23=3.7e9
G13=7e9
niu12=0.27
niu23=0.54
niu13=0.27
tply=6.35e-4
t=0.00508

S=[(1/E1) (-niu12/E1) (-niu13/E1) 0 0 0;(-niu12/E1) 1/E2 (-niu23/E2) 0 0 0;(-niu13/E1) (-niu23/E2) 1/E3 0 0 0;0 0 0 1/G23 0 0;0 0 0 0 1/G13 0;0 0 0 0 0 1/G12]
Q = inv(S)

%Calculation of Qbar matrix for different fibre orientations
m=cos(pi/4)
n=sin(pi/4)
%Roattion about X axis
Tsigma=[1 0 0 0 0 0;0 m^2 n^2 2*m*n 0 0;0 n^2 m^2 -2*m*n 0 0;0 -m*n m*n (m^2-n^2) 0 0;0 0 0 0 m -n;0 0 0 0 n m]
Tepsilon=[1 0 0 0 0 0;0 m^2 n^2 m*n 0 0;0 n^2 m^2 -m*n 0 0;0 -2*m*n 2*m*n (m^2-n^2) 0 0;0 0 0 0 m -n;0 0 0 0 n m]
Qbar45=inv(Tsigma)*Q*Tepsilon

m=cos(-pi/4)
n=sin(-pi/4)
%Rotation about X axis
Tsigma=[1 0 0 0 0 0;0 m^2 n^2 2*m*n 0 0;0 n^2 m^2 -2*m*n 0 0;0 -m*n m*n (m^2-n^2) 0 0;0 0 0 0 m -n;0 0 0 0 n m]
Tepsilon=[1 0 0 0 0 0;0 m^2 n^2 m*n 0 0;0 n^2 m^2 -m*n 0 0;0 -2*m*n 2*m*n (m^2-n^2) 0 0;0 0 0 0 m -n;0 0 0 0 n m]

Qbar_45=inv(Tsigma)*Q*Tepsilon

h0=-2.54e-3
h1=-1.905e-3
h2=-1.27e-3
h3=-6.35e-4
h4=0
h5=6.35e-4
h6=1.27e-3
h7=1.905e-3
h8=2.54e-3

%ABD matirx
A=Qbar45*(h1-h0)+Qbar_45*(h2-h1)+Qbar45*(h3-h2)+Qbar_45*(h4-h3)+Qbar_45*(h5-h4)+Qbar45*(h6-h5)+Qbar_45*(h7-h6)+Qbar45*(h8-h7)
B=(1/2)*(Qbar45*(h1^2-h0^2)+Qbar_45*(h2^2-h1^2)+Qbar45*(h3^2-h2^2)+Qbar_45*(h4^2-h3^2)+Qbar_45*(h5^2-h4^2)+Qbar45*(h6^2-h5^2)+Qbar_45*(h7^2-h6^2)+Qbar45*(h8^2-h7^2))
D=(1/3)*(Qbar45*(h1^3-h0^3)+Qbar_45*(h2^3-h1^3)+Qbar45*(h3^3-h2^3)+Qbar_45*(h4^3-h3^3)+Qbar_45*(h5^3-h4^3)+Qbar45*(h6^3-h5^3)+Qbar_45*(h7^3-h6^3)+Qbar45*(h8^3-h7^3))

ABD=[A B;B D]
abd=inv(ABD)

%Calculate material properties
EX=1/((abd(1,1))*t)
Ey=1/((abd(2,2))*t)
EZ=1/((abd(3,3))*t)

niuxy=-(abd(2,1)/abd(1,1))
niuyz=-(abd(3,2)/abd(2,2))
niuxz=-(abd(3,1)/abd(1,1))

Gxy=1/((abd(6,6))*t)
Gyz=1/((abd(5,5))*t)
Gxz=1/((abd(4,4))*t)

And here are the results,
EX = 1.470000000000000e+011 Pa

Ey = 1.112375948628138e+010 Pa

EZ = 1.112375948628138e+010 Pa

niuxy = 0.27000000000000

niuyz = 0.50321074138938

niuxz = 0.27000000000000

Gxy = 7.000000000000000e+009 Pa

Gyz = 7.000000000000000e+009 Pa

Gxz = 3.344155844155844e+009 Pa


Thanks,
Barbara
 
  • #5
Hi anyone help me to predict youngs modulus of banana-epoxy composite using matlab
 

What are composite materials?

Composite materials are materials made up of two or more components with different physical and chemical properties. These components are combined to create a material with unique properties that are different from the individual components.

What are the advantages of using composite materials?

Composite materials have a high strength-to-weight ratio, making them lighter and stronger than traditional materials. They can also be designed to have specific properties, such as high strength, flexibility, or heat resistance. Additionally, composite materials can be resistant to corrosion and have a longer lifespan than some traditional materials.

What are the most common types of composite materials?

The most common types of composite materials include fiber-reinforced composites, particulate composites, and structural composites. Fiber-reinforced composites, such as carbon fiber, are made up of fibers embedded in a matrix material, while particulate composites, like concrete, have particles dispersed in a matrix. Structural composites, such as plywood, are made up of layers of different materials bonded together.

What factors affect the properties of composite materials?

The properties of composite materials can be affected by various factors, including the type of components used, the ratio of components, the method of fabrication, and the environmental conditions the material will be exposed to. The orientation and distribution of fibers or particles within the matrix can also greatly impact the properties of the composite material.

What are the applications of composite materials?

Composite materials have a wide range of applications in industries such as aerospace, automotive, construction, and sports equipment. They are used to make lightweight and strong structures, such as aircraft parts, car bodies, and building materials. They are also used in high-performance sports equipment, such as tennis rackets and golf clubs, due to their strength and flexibility.

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