Serr calculation

Copyright c 2007 ICCES ICCES, vol.1, no.2, pp.61-67, 2007
Calculation of Energy Release Rate in Mode I
Delamination of Angle Ply Laminated Composites
K. Gordnian1, H. Hadavinia1, G. Simpson1 and A. Aboutorabi1
Summary
The compliance equation is used to calculate the energy release rate for angle
ply laminated double cantilever composite beam specimen. Instead of the tradi-
tional approach of a beam on an elastic foundation, a second order shear thickness
deformation beam theory (SSTDBT) has been considered.
keywords: Double Cantilever Beam, Energy Release Rate, Fracture Energy
Introduction
Fiber-reinforced composite materials are widely used in all kinds of engineer-
ing structures owing to their high strengths and low densities. Laminated com-
posite structures are made up of layers of orthotropic materials that are bonded
together. The layers may be of different materials, or of the same orthotropic mate-
rial, with the principal material directions of each layer oriented at different angles
to the reference axes. By altering material or orientation, or both, of each layer,
a structural designer can tailor the strength and other properties of a laminate to
the requirements of a given application. Because of the low stiffness in the trans-
verse direction, when out-of-plane loading exists, separation between plies occurs,
i.e. delamination. The presence and growth of delamination under static or fatigue
loadings will lead to safety problems by reduction of structural stiffness or initiating
catastrophic fracture [1–4]. Hence in any engineering design of laminated compos-
ite structures, the delamination mode of failure should be taken into account [5,6].
Usually the delamination modes in composite laminates contain Mode I (opening),
Mode II (in plane shearing) and Mode III (out of plane tearing) fractures. There-
fore, it is important to characterize these fracture modes to prevent delamination
damage.
The overwhelming literature on delamination is mainly related to unidirectional
composites. A feature that complicates the analysis of delamination growth in an-
gle ply laminates is that delamination exists between angle-plies (e.g.±θ). In an
optimum laminate design, the objective will be to minimize the crack driving force
and/or the crack-induced interfacial principal tensile stress in the angle-ply lam-
inate under transverse shear loading. This problem is cast as a single- or multi-
criterion optimization problem. The design variables are the ply angle θ and the
relative ply thicknesses of the sublaminates. It is recognized that a delamination
between angle-plies has the feature of a crack between dissimilar anisotropic ma-
terials which substantially complicates the fracture mechanics analysis.
1Faculty of Engineering, Kingston University, UK. Corresponding author:
h.hadavinia@kingston.ac.uk

62 Copyright c 2007 ICCES ICCES, vol.1, no.2, pp.61-67, 2007
The double cantilever beam (DCB) test [7] is the most widely used method
for determining the Mode I toughness of composite materials. The test specimen,
the applied load, P, to the two arms and the corresponding load line displacement,
δ, are schematically illustrated in Fig. 1. A model based on an Euler-Bernoulli
beam on an elastic Winkler foundation for analysing the DCB specimen was orig-
inally developed by Kanninen [8,9] for isotropic materials and by Williams [10]
for transversely isotropic materials. This model is extended to angle-ply laminates
by Ozdil and Carlsson [11]. The beam displacements derived from this model are
used to calculate the compliance and strain energy release rate of the DCB spec-
imen. Recently, Hamed et al. [12], introduced an improved analytical model for
delamination in composite beams under general edge loading which also takes into
account the shear-thickness deformation.
In the present study, Hamed model together with the compliance equation has
been used to develop a method of determining the Mode I interlaminar fracture
toughness in thick angle ply laminated composites.
Figure 1: Angle ply DCB specimen divided into three regions
Theoretical Analysis
Consider the DCB specimen in Fig. 1 made of an angle ply laminate and
divided into three regions I, II and III. Assuming a second order shear thickness
deformation beam theory (SSTDBT), the displacement ﬁeld is
u1(x,y,z) = u(x)+zψx(x)+z2
ηx(x),
u2(x,y,z) = 0,
u3(x,y,z) = w(x)+zψz(x),
(1)
in all three regions, where u1, u2 and u3 are the displacement components of a point
in the x−, y− and z−directions, respectively. Note that the superscripts I, II and III
will be given to all of the displacement components to distinct them for the regions
I, II and III. Substituting Eq. 1 into the strain-displacement relations of elasticity
we obtain
εx = ε0
1 +zκ1
0 +z2
κ1
1 , εy = 0, εz = ε0
3 , γyz = 0, γxz = ε0
5 +zκ0
5 , γxy = 0
(2)

Calculation of Energy Release Rate 63
where
ε0
1 = u , κ1
0 = ψx, κ1
1 = ηx, ε0
3 = ψz, ε0
5 = ψx +w , κ0
5 = 2ηx +ψz (3)
and a prime denotes differentiation with respect to x. Since we are developing a
beam theory, a state of plane stress is presented and therefore
σy = σyz = 0. (4)
Next by imposing Eq. 4 on three dimensional Hooke’s law of elasticity, the plane
stress constitutive law for the kth layer of each region is
⎧
⎨
⎩
σx
σz
σxy
⎫
⎬
⎭
(k)
=
⎡
⎢
⎣
C11 C13 C16
C13 C33 C36
C16 C36 C66
⎤
⎥
⎦
(k) ⎧
⎨
⎩
εx
εz
γxy
⎫
⎬
⎭
(k)
, σ
(k)
xz = C
(k)
55 γ
(k)
xz , (5)
where
Cij = Cij −
Ci2Cj2
C22
i, j = 1,3,6 and C55 = C55 −
C
2
45
C44
. (6)
In Eq. 6, Cij denote off-axis stiffness coefficients of the kth layer [13]. Using
the principle of minimum total potential energy, and considering the displacement
field in Eq. 1, the equilibrium equations together with the boundary conditions
(B.C.’s) at boundaries and continuity conditions (C.C.’s) and the equilibrium con-
ditions (E.C.’s) at the intersection of three regions will be obtained. Further by
substituting the laminate constitutive relations into the equilibrium equations, the
governing equilibrium equations in terms of displacement components for the three
regions will be found as
−A11u −A13ψz −B11ψx −D11ηx = 0,
−B11u −B13ψz −D11ψx −E11ηx +A55(ψx +w ) +B55(2ηx +ψz) = 0,
−D11u −D13ψz −E11ψx −F11ηx +2B55(ψx +w )+2D55(2ηx +ψz) = 0,
−A55(ψx +w )−B55(2ηx +ψz ) = 0,
A13u +A33ψz +B13ψx +D13ηx −B55(ψx +w ) −D55(2ηx +ψz ) = 0,
(7)
where Aij, Bij, Dij, Eij and Fij are laminate stiffness coefficients [12]. Giving the
superscripts I, II and III to all of the displacement components and also the stiffness
coefficients in Eq. 7, a system of ordinary differential equations (ODE) of order
30 will be resulted. This system of ODEs together with the B.C.’s, C.C.’s and
E.C.’s can be solved and all displacement components for the three regions can be
obtained.

Hamed [12] calculated the energy release rate using the J-integral. Here the
classical Irwin-Kies expressions [14] will be used to obtain the strain energy release
rate (SERR) from the beam theory solution, i.e.,
G =
P2
2b
δC
δa
. (8)
where in Eq. 8, P is the load, b is the specimen width, a is the crack length and C
the compliance is defined as
C =
δ
P
, (9)
To obtain the G, we must first express C in terms of the crack length a. From Fig.
1, it is obvious that
δ = uI
3 x = −a
z = 0
− uII
3 x = −a
z = 0
(10)
Because of complicated computations, however, the problem cannot be solved ex-
plicitly in terms of a. Therefore the DCB problem has been solved for a range of
crack length and then a least-square regression was fitted to obtain C as a function
of crack length, a
C(a) = C3a3
+C2a2
+C1a+C0 (11)
The above equation can be differentiated with respect to crack length a and G is
calculated from Eq. 8.
Numerical Examples and Discussions
Glass/polyester DCB specimens consisting of anti-symmetric angle ply lami-
nates of the form [±30◦]5 and [±45◦]5 was chosen as those in [11] where h=7.3 mm,
b=20 mm, a=35 mm and l=100 mm. Also E1 = 34.7GPa, E2 = 8.5GPa, ν12 =
ν13 = 0.27, ν23 = 0.5, G12 = G13 = 4.34GPa, G23 = 2.83GPa. Further for
θ = 45◦
, E3 = 9.85GPa and for θ = 30◦
, E3 = 9.37GPa. Considering these
properties, the corresponding Ci are presented in Table 1.
Table 1: Polynomial coefficients of compliance in Eq. 11.
Lay
up
C0 C1 C2 C3
[±30◦]5 0.1525402534e-7 0.0000108485 0.0027207675 0.3901954340
[±45◦]5 -0.1547188457e-7 -0.0001224524 0.0036116202 0.6069910987
Fig. 2a compares SERR obtained from the compliance equation with those
obtained from J-Integral [12] for two anti-symmetric angle ply laminates of θ = 30◦
and θ = 45◦
,and for various values of crack length at constant applied load of P=40
N. The results are in good agreement with each other. In similar crack lengths,

30 40 50 60 70 80
0
50
100
150
200
250
300
350
q = 30
o
- Compliance Equation
q = 45
o
- Compliance Equation
q = 30
o
- J Integral
q = 45
o
- J Integral
G[J/m
2
]
Crack Length [mm]
(a)
0 10 20 30 40 50 60
0
50
100
150
200
250
300
θ = 30
ο
-Com plianceEquation
θ = 45
ο
-Com plianceEquation
θ = 30
ο
-JIntegral
θ = 45
ο
-JIntegral
G[J/m
2
]
P [N]
(b)
Figure 2: Comparison of pure mode I strain energy release rate, G, obtained from
J-Integral and compliance equation for [±θ]5 specimens versus (a) Crack length at
constant applied load of P=40 N, (b) Applied load P at constant crack length of
a=40 mm.
30 40 50 60 70 80
0
20
40
60
80
100
SSTDBT
Experiment
Compliance[m/N]
Crack Length [mm]
= 30
30 40 50 60 70 80
0
20
40
60
80
100
120
140
160
SSTDBT
Experiment
Compliance[m/N]
Crack Length [mm]
= 45
Figure 3: Comparison of Calculated and measured Compliance
30 40 50 60 70
100
200
300
400
500
SSTDBT
EFM
Gc
[J/m
2
]
Crack Length [mm]
= 30
30 40 50 60 70 80
100
200
300
SSTDBT
EFM
Gc
[J/m
2
]
Crack Length [mm]
= 45
(a) (b)
Figure 4: Comparison of pure mode I fracture energy, Gc, obtained from elastic
foundation model, EFM [11] and SSTDBT using compliance equation for [±θ]5
specimens (a) θ = 30◦ (b) θ = 45◦.
SERR for θ = 45◦
are greater than when θ = 30◦
. In Fig. 2b, SERR are plotted
versus applied load for two angle ply lay-ups at constant crack length of a=40 mm.

Similar to Fig. 2a, the results obtained from compliance equation are in accordance
with the results from J-Integral.
In Figs. 3 the calculated compliances from SSTDBT theory are compared with
the experimental results obtained by Ozdil and Carlsson [11]. It is observed that
when θ = 30◦
, SSTDBT underestimates the compliance value but for θ = 45◦
the
results are very close. In Figs. 4 pure mode I fracture energy, Gc, obtained from
elastic foundation model, EFM [11] and SSTDBT using compliance equation for
[±θ]5 specimens at two angle-plies of θ = 30◦ and θ = 45◦ are compared.
It is shown and veriﬁed that the second order shear thickness deformation
beam theory (SSTDBT) together with compliance equation accurately estimates
the mode I fracture toughness and strain energy release rate for any angle-ply lami-
nates. The method is robust and general and other mode of fracture can be modelled
using this method.
References
1. Nicholls DJ, Gallagher JP. Determination of GIC in angle-ply composites
using a cantilever beam test method. J. Reinf. Plast. Compos. 1983;2:2–17.
2. Chai H. The characterization of mode I delamination failure in nonwoven,
multidirectional laminates. Composites 1984;15: 277–90.
3. Laksimi A, Benzeggagh ML, Jing G, Hecini M, Roelandt JM. Mode I inter-
laminar fracture of symmetrical cross-ply composites. Compos. Sci. Tech-
nol. 1991;41:147–64.
4. Robinson P, Song DQ. A modiﬁed DCB specimen for mode-I testing of mul-
tidirectional laminates. J. Compos. Mater. 1992;26:1554–77.
5. Johnson WS, editor. Delamination and debonding of materials, ASTM STP
876, Philadelphia, PA, 1985.
6. Prel VJ, Davies P, Benzeggagh ML, de Charentenay FX. Mode I and Mode
II delamination of thermosetting and thermoplastic composites. ASTM STP
1012, Philadelphia, PA, 1989, pp. 251–69.
7. ASTM Test Method D 5528-94a “Mode I Interlaminar Fracture Toughness
of Unidirectional Continuous Fiber Reinforced Composite Materials,” An-
nual Book of ASTM Standards, Vol 15.03, American Society for Testing and
Materials, West Conshohocken, PA.
8. Kanninen MF. An augmented double cantilever beam model for studying
crack propagation and arrest. Int J Fracture 1973; 9(1):83–92.
9. Kanninen MF. A dynamic analysis of unstable crack propagation and arrest
in the DCB test specimen. Int J Fracture 1974;10(3):415.

10. Williams JG. End corrections for orthotropic DCB specimens. Compos Sci
Tech 1989;35:367.
11. Ozdil F, Carlsson LA. Beam analysis of angle-ply laminate DCB specimens.
Compos Sci Technol 1999; 59:305–15.
12. Hamed MA, Nosier A, Farrahi GH. Separation of delamination modes in
composite beams with symmetric delaminations. J. Materials & Design,
2006;27(10):900-10.
13. Herakovich, Carl T. Mechanics of ﬁbrous composites. NewYork: Wiley;
1998.
14. Irwin GR, Kies JA. Critical energy release rate analysis of fracture strength.
Weld J Res Suppl 1954; 33:193–8.

Serr calculation

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