EML 4230 Introduction to Composite Materials
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Transcript EML 4230 Introduction to Composite Materials
Chapter 4 Macromechanical Analysis of a Laminate
Classical Lamination Theory
Dr. Autar Kaw
Department of Mechanical Engineering
University of South Florida, Tampa, FL 33620
Courtesy of the Textbook
Mechanics of Composite Materials by Kaw
Fiber Direction
x
y
z
• elastic moduli
• the stacking position
• thickness
• angles of orientation
• coefficients of thermal expansion
• coefficients of moisture expansion
xx =
P
z
(a)
M
M
x
xx =
Mz
I
xx =
z
1
z
=
P
+
M
xx
AE
EI
z
(b)
M
M
x
P
x
P
z
(c)
(4.1)
P
xx =
AE
x
P
P
A
1
= 0 + z
= 0 + z
x
x
z
z
Mxy
Myx
Nx
y
Nyx
Nxy
My
y
Ny
(a)
(b)
Nx = normal force resultant in the x direction (per unit length)
Ny = normal force resultant in the y direction (per unit length)
Nxy = shear force resultant (per unit length)
Mx
x
x
z
z
Mxy
Myx
Nx
y
Nyx
Nxy
My
y
Ny
(a)
(b)
Mx = bending moment resultant in the yz plane (per unit length)
My = bending moment resultant in the xz plane (per unit length)
Mxy = twisting moment resultant (per unit length)
Mx
Each lamina is orthotropic.
Each lamina is homogeneous.
A line straight and perpendicular to the middle surface remains
straight and perpendicular to the middle surface during
deformation. ( γxz = γyz = 0 ) .
The laminate is thin and is loaded only in its plane (plane stress)
(σz = τxz = τyz = 0 ) .
Displacements are continuous and small throughout the laminate
(| u |, | v |, | w | | h |) , where h is the laminate thickness.
Each lamina is elastic.
No slip occurs between the lamina interfaces.
u0
h/2
Mid-Plane
h/2
x
z
A
z
A
z
Cross-Section
Before Loading
Cross-Section
after Loading
wo
2
w0
u0
2
x
x
ε x
2
v0
w0
ε y =
+ z
2
y
y
γ xy
u0
2
v0
+
2 w0
x
xy
y
0
κx
ε
x
0
ε y + z κ y .
κ xy
γ0xy
Mid-Plane
z
Laminate
Strain Variation
Stress Variation