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Mechanics of Composite Materials
Constitutive Relationships for Composite Materials
Ⅰ. Material Behavior in Principal Material Axes• Isotropic materials
– uniaxial loading
12
1
E G
12
EG
– 2-D loading
S
G
EE
EE
xy
y
x
xy
y
x
1 , 0 , 0
0 ,1
,
0 ,, 1
Where [ S ]: compliance matrix
Q
G
EE
EE
xy
y
x
xy
y
x
, 0 , 0
0 ,1 ,
1
0 ,1
, 1
22
22
Where [Q]: stiffness matrix
Isotropic Materials
Note:1. Only two independent material constants in the
constitutive equation.2. No normal stress and shear strain coupling, or no
shear stress and normal strain coupling.
Examples: polycrystalline metals,PolymersRandomly oriented fiber-reinforced
compositesParticulate-reinforced composites
Transversely isotropic materials
Principal material axesL: longitudinal directionT: transverse direction
In L–T plane
LT
T
L
LT
TT
TL
L
LT
L
LT
T
L
G
EE
EE
1 , 0 , 0
0 ,1
,
0 ,, 1
LT
T
L
LT
TLLT
T
TLLT
TLT
TLLT
LTL
TLLT
L
LT
T
L
G
EE
EE
, 0 , 0
0 ,1 ,
1
0 ,1
, 1
Transversely isotropic materials
Principal material axesL: longitudinal directionT: transverse direction
In T1, T2 plane
21
2
1
21
2
1
1 , 0 , 0
0 ,1
,
0 ,, 1
TT
T
T
TT
TT
TT
T
TT
T
TT
T
T
G
EE
EE
Same as those for isotropic materials:
TT
TTT
EG
12
Transversely isotropic materials
Where EL: elastic modulus in longitudinal direction
ET: elastic modulus in transverse direction
GLT: shear modulus in L – T plane
GTT: shear modulus in transverse plane
LT: major Poisson’s ratio
(strain in T – direction caused by stress in L – direction)
TL : minor Poisson’s ratio
And
Note: 1. 4 independent material constants (EL, ET, GLT, LT ) in L – T plane while 5 (EL, ET, GLT, LT, GTT) for 3-D state.
2. No normal stress and shear strain coupling in L – T axes or no shear stress and normal strain coupling in L – T axes
T
TL
L
LT
EE
Orthotropic materials
1.2.3: principal material axes
For example in 1-2 plane
12
2
1
12
22
21
1
12
1
12
2
1
1 , 0 , 0
0 ,1
,
0 ,, 1
G
EE
EE
12
2
1
12
2112
2
2112
212
2112
121
2112
1
12
2
1
, 0 , 0
0 ,1 ,
1
0 ,1
, 1
G
EE
EE
2
21
1
12
EE
Orthotropic Materials
Note:
1. 4 independent constants in 2-D state (e.g. 1-2 plane, E1,
E2, G12, 12 )while 9 in 3-D state (E1, E2, E3, G12, G13, G23, 12 ,
13 , 23 )
2. No coupling between normal stress and shear strain or no coupling between shear stress and normal strain
Question
Ex. Find the deformed shape of the following composite:
Possible answers?
Off-axis loading of unidirectional composite
For orthotropic material in principal material axes (1-2 axes)
12
2
1
66
2221
1211
12
2
1
0 0
0
0
Q
By coordinate transformation
12
2
11
12
2
1
22
22
22
sin-cos ,sincos- ,sinos
sin2cos cos sin
sin2cos- sin cos
T
cxy
y
x
12
2
11
T
xy
y
x
, xyxy are tensorial shear strains
Let
12
2
1
12
2
1
12
2
1
2 0 0
0 1 0
0 0 1
R
Then
xy
y
x
xy
y
x
xy
y
x
xy
y
x
RTRQTTRQT
RQTQTT
Q
111
12
2
11
12
2
11
12
2
11
Transformed stiffness matrix
Where 11 RTRQTQ = transformed stiffness matrix
sin ,cos
22
22
22
4
22
22
3662212
366121126
3662212
366121116
4466
226612221166
4412
2266221112
422
226612
41122
422
226612
41111
nm
nmQQQmnQQQQ
mnQQQnmQQQQ
nmQnmQQQQQ
nmQnmQQQQ
mQnmQQnQQ
nQnmQQmQQ
Transformed compliance matrix
xy
y
x
xy
y
x
xy
y
x
SQ
1
S : transformed compliance matrix
Off-axis loading - deformation
xy
y
x
xy
y
x
QQQ
QQQ
QQQ
662616
262212
161211
1. 4 material constants in 1-2 plane.2. There is normal stress and shear strain coupling (forθ≠0, 90˚ ), or
shear stress and normal strain coupling.
Transformation of engineering constants
For uni-axial tensile testing in x-direction 0 ,0 xyyx
∴ stresses in L – T axes
cossin
sin
cos
0
0 2
2
x
x
xx
LT
T
L
T
Strains in L – T axes
LT
LLT
T
TTL
L
x
x
x
x
LT
TT
TL
L
LT
L
LT
T
L
LT
T
L
G
EE
EE
G
EE
EE
S
SS
SS
cossin
cossin
sincos
cossin
sin
cos
1, 0 , 0
0 ,1
,
0 ,, 1
0 0
0
0
22
22
2
2
66
2212
1211
And strains in x – y axes
LT
LLT
T
TTL
L
x
LT
T
L
xy
y
x
G
EE
EE
TT
2
cossin
cossin
sincos
2
1
2
1
22
22
11
LTTL
LT
LLTTL
LT
LTTL
LT
LL
LT
L
LT
LTTL
x
xy
y
x
GEEEGEE
GEEEE
EGEE
1121cos
2
112sin
2
1
2sin1121
4
1
2sin21
4
1sincos
2
1
2
2
244
Recall for uni-axial tensile testing
2sin1121
4
1
and
2sin21
4
1sincos1
2
244
LTTL
LT
LL
LT
x
y
x
xy
xx
y
x
yxy
xxyy
L
LT
LTTLx
x
xx
GEEEEE
E
EGEEE
E
Define cross-coefficient, mx
LT
L
T
LLT
LT
L
T
LLT
x
Lxyx
L
xxxy
G
E
E
E
G
E
E
E
Em
Em
21cos2
2sin
2
Similarly, for uni-axial tensile testing in y-direction
LT
L
T
LLT
LT
L
T
LLTy
x
xy
LTTT
TL
LT
TL
y
yx
L
LT
LTTLy
G
E
E
E
G
E
E
Em
EGEEEEE
EGEEE
21sin2
2sin
2sin1121
4
1
2sin21
4
1cossin1
2
2
244
For simple shear testing in x – y plane
0 ,0 xyyx
stresses in L – T axes
22 sincos
cossin2
cossin2
0
0
xy
xy
xy
xyLT
T
L
T
Strains in L – T axes
22
22
sincos1
1cossin2
1cossin2
sincos
cossin2
cossin2
1, 0 , 0
0 , 1
,
0 ,,1
1, 0 , 0
0 , 1
,
0 , , 1
LT
L
LT
T
T
TL
L
xy
xy
xy
xy
LT
TT
TL
L
LT
L
LT
T
L
LT
TT
TL
L
LT
L
LT
T
L
G
EE
EE
G
EE
EE
G
EE
EE
Strains in x – y axes
2cos1121121
where
22
2
1
LTTL
LT
LTL
LT
Lxyxy
L
xyyy
L
xyxx
LT
T
L
xy
y
x
GEEEEEE
Em
Em
T
2cos11211211
2
LTLL
LT
LTL
LT
Lxy
xy
xyxy
GEEEEEEG
G
In summary, for a general planar loading, by principle of superposition
xy
y
x
xyL
y
L
x
L
y
yy
yx
L
x
x
xy
x
xy
y
x
GE
m
E
m
E
m
EE
E
m
EE
1 ,,
, 1
,
,, 1
Micromechanics of Unidirectional Composites
• Properties of unidirectional lamina is determined by
– volume fraction of constituent materials (fiber, matrix, void, etc.)
– form of the reinforcement (fiber, particle, …)– orientation of fibers
Volume fraction & Weight fraction
• Vi=volume, vi=volume fraction=
• Wi=weight, wi=weight fraction=
Where subscripts i = c: composite
f: fiber
m: matrix
c
i
i
i
V
V
V
V
i i
i c
W W
W W
1
1
c f m
f m
c c
f m
W W W
W W
W W
w w
Conservation of mass:
Assume composite is void-free:
1
1
c f m
f m
c c
f m
V V V
V V
V V
v v
Density of composite
m
m
f
f
c
m
m
f
f
c
c
mfc
mmffc
c
mmff
c
mf
c
cc
ww
g
W
g
W
g
W
VVV
vv
gV
gVgV
gV
WW
gV
W
1
or
Generalized equations for n – constituent composite
1
1
1n
c i i ni i
i i
vw
Void content determination
ce f f m m v v
f f m m
v v v
v v
1
t
c f m
ct v f f m m
ct f f m m c v
W W W
v v v
v v v
Experimental result (with voids):
Theoretical calculation (excluding voids):
: ct cev
ct
void content v
In general, void content < 1% Good composite
> 5% Poor composite
Burnout test of glass/epoxy composite Weight of empty crucible = 47.6504 gWeight of crucible +composite = 50.1817 gWeight of crucible +glass fibers = 49.4476 g
33 2.1 ,5.2cmg
cmg
mf
386.1 if cmgv cev Find
3
49.4476 47.65040.71
50.1817 47.6504
1 1 0.71 0.29
1 11.902
0.71 0.292.5 1.2
1.9020.71 0.54
2.5
1.9020.29 0.46
1.2
ff
c
m f
c ctf m
f m
cf f
f
cm m
m
Ww
W
w w
gw cmw
v w
v w
Sol:
1.902 1.86
1.902
0.0221 2.21%
ct cev
ct
v
Longitudinal Stiffness
For linear fiber and matrix:
Lmmffc EvEvEE
Generalized equation for composites with n constituents:
n
iiic vEE
1
Rule-of-mixture
Longitudinal Strength
fmff
mmffc
vv
vv
1
Modes of Failurematrix-controlled failure: 11 fmucu v
fiber-controlled failure:
1
[ ] 2
fu
fu fu
cu fu f m f
fu m f m
v v
v
21 ,max cucucu
Critical fiber volume fractionFor fiber-controlled failure to be valid:
For matrix is to be reinforced:
min
12
1
vv
vv
fu
fu
fufu
mmufu
mmu
f
fmumfmfu
cucu
crit
vv
v
fu
fu
fufu
mfu
mmu
f
mumfmfu
mucu
Factors influencing EL and cu
• mis-orientation of fibers
• fibers of non-uniform strength due to variations in diameter, handling and surface treatment, fiber length
• stress concentration at fiber ends (discontinuous fibers)
• interfacial conditions
• residual stresses
Transverse Stiffness, ET
Assume all constituents are in linear elastic range:
1 f m
c f m
v v
E E E
Generalized equation for n – constituent composite:
modulus) e(transvers 1
or
1
1
1
Tn
i i
i
c
n
i i
i
c
E
E
vE
E
v
E
Transverse Strength
Due to stress (strain) concentration
mucu
Factors influence cu:• properties of fiber and matrix• the interface bond strength• the presence and distribution of voids (flaws)• internal stress and strain distribution (shape of fib
er, arrangement of fibers)
In-plane Shear Modulus
For linearly elastic fiber and matrix: 1
or
f m
c f m
f mc LT
m f f m
v v
G G G
G GG G
G v G v
Major Poisson’s Ratio
LT f f m mv v
Analysis of Laminated Composites
• Classical Laminate Theory (CLT)
yxwzyxw
y
wzyxvzyxv
x
wzyxuzyxu
,,,
,,,
,,,
0
00
00
Displacement field:
Resultant Forces and Moments
2
2
d 1
xx x xh
hy y y y
xy xy xyxy
N k
N z A B k
N k
2
2
d 1
x
y
xy
x x xh
hy y y
xy xy xy
M k
M z z B D k
M k
11 11
d
kk
n
k
h
h
n
kkijkijij hhQzQA k
k
2
d22
1 1
1
1
kkk
k
hhQzzQB
n
k
h
h
n
kkijkijij
3
d
33
1 1
2 1
1
kkk
k
hhQzzQD
n
k
h
h
n
kkijkijij
Resultant forces:
Resultant moments:
[A]: extensional stiffness matrix
[B]: coupling stiffness matrix
[D]: bending stiffness matrix
Laminates of Special Configurations
• Symmetric laminates
• Unidirectional (UD) laminates– specially orthotropic – off-axis
• Cross-ply laminates
• Angle-ply laminates
• Quasi-isotropic laminates
Strength of Laminates
Maximum Stress Criterion
• Lamina fails if one of the following inequalities is satisfied:
LTLT
TcT
TtT
LcL
LtL
ˆ
ˆ
ˆ
ˆ
ˆ
Maximum Strain Criterion
• Lamina fails if one of the following inequalities is satisfied:
LTLT
TcT
TtT
LcL
LtL
ˆ
ˆ
ˆ
ˆ
ˆ
Tsai – Hill Criterion
• Lamina fails if the following inequality is satisfied:
1ˆˆˆˆ
222
LT
LT
T
T
L
TL
L
L
0 if ˆ
0 if ˆˆ
0 if ˆ
0 if ˆˆ
TTc
TTtT
LLc
LLtL
Where :
Comparison among Criteria
• Maximum stress and strain criteria can tell the mode of failure
• Tsai-Hill criterion includes the interaction among stress components
Strength of Off-Axis Lamina in Uni-axial Loading
Maximum stress criterionTsai-Hill criterion
Strength of a Laminate
• First-ply failure
• Last-ply failure