Mechanical properties of materials in the principle material coordinate .
In the past years, many studies have been conducted on behaviors of adhesive tubular joints subjected to various loading conditions, such as torsion, axial, and internal and external pressure. However, the previous models are conceptually distinct, since they were developed to analyze only for each type of load. Mostly, homogeneous isotropic or orthotropic material were considered and thin-walled joint structures were examined. Therefore, the aim of this chapter is to present for the first time a generalized mathematical formulation and modeling of adhesive-bonded cylindrical coupler joints taking into account all loading scenarios. The inner and outer adherends can be made of isotropic, orthotropic, or laminated composite materials, and they are modeled as three-dimensional elastic body, so adherends with any thickness can be analyzed. Assumptions of an axisymmetric joint with linearly elastic adherends and adhesive materials are employed. Thin adhesive layer is considered so that only the out-of-plane adhesive stresses are concerned, and they are treated to be uniform through its thickness. Using elasticity theory and the newly developed finite-segmented method, stress distributions in both adherends and adhesive can be evaluated. Calculation examples of laminated composite joints are given. This model provides the unified analysis of adhesive-bonded cylindrical coupler joints.
- coupler joint
- lap joint
- finite-segment method
Structures usually need to have joints connecting each part together due to the limitation of manufacturing, transportation, and installation. These structures are generally vulnerable at the joints because of the stress concentrations from material discontinuity. There are many types of joint, such as mechanical joints, welding joints, and adhesive-bonded joints. Over the other kinds of joints, adhesive-bonded joints have advantages due to less stress concentration, higher capability of joining dissimilar materials, lighter weight, and better corrosion resistance. Nonetheless, stress concentration in the adhesive layer is still existing. The adhesive stress distribution is locally nonuniform and always highest at the edges of the bonding region. Thus, in order to use an adhesive-bonded joint safely, it is important to predict the developed adhesive stress accurately. A good analysis also provides the understanding of the joint behavior, yielding a design for improving the joint performance by decreasing the joint stress concentration.
There are lots of literature dealing with the stresses in lap joints and coupler joints between two tubular adherends. Among several types of adhesive-bonded joint, cylindrical or tubular joints subjected to axial, torsional, and external as well as internal pressure loads have been one of the main focus of mechanics of adhesion research for a half century due to their popular usage in many engineering applications. The analytical modeling and finite-element analysis are the two popular approaches for predicting the stresses developed in adhesive and adherends. In order to recognize the progress in this field, some examples of important work in mathematical modeling are given below.
For axial loads, the early investigation was conducted by Lubkin and Reissner  who analyzed the tubular lap joints. Axial shear stresses and radial normal stresses in the adhesive layer were predicted under the assumption of approximating the layer as an infinite number of tensile and shear springs. However, disappearance of axial shear stress on the free surfaces at the ends of the adhesive was not considered. Adam and Peppiatt  performed axisymmetric finite-element analysis (FEA) of tubular lap joints subjected to stretching and twisting loads. The effects of an adhesive filet and partial tapering adherends on stress distribution were also reported. Using a minimum strain energy, Allman  proposed two-dimensional analytical solution for lap joints that ensure the traction-free boundary condition. Bending, stretching, and shearing of the adherends and shearing and tearing of the adhesive layer were taken into account. Shi and Cheng  formulated closed-form solutions for tubular lap joints utilizing the variational principle of complementary energy. Boundary conditions and assumptions of Allman were adopted in their model development. Nemes et al.  further developed the stress analysis of adhesive in a cylindrical assembly of two tubes. Variational method of the potential energy was also employed. Nonetheless, Nemes et al. neglected radial stress component in the joint. Kumar  presented a theoretical framework for the stress analysis of shaft-tube adhesive joints subjected to tensile loads. The joint assembly was considered to consist of similar or dissimilar isotropic or orthotropic adherends. The principle of minimum complementary energy and a stress function approach were used to establish the governing equations in order to determine the stress state in each constituent. To reduce the stress concentration, Kumar  also studied the use of functionally graded adhesive in a tubular lap joint with an isotropic adherend under tension. In his model, the adhesive was divided into annular rings to take into account the gradient property of shear modulus.
Regarding the case of the tubular joint subjected to torsion, Volkersen  provided a closed-form solution for circumferential shear stresses at the interface of tubular lap joint exerted by a torque. Pugno and Surace  investigated the analysis of the joint subjected to torsion. They utilized the common function of resultant torques in adherends and achieved the uniform adhesive hoop shear stress by tapering adherend surfaces. Xu and Li  investigated the full three-dimensional stress analysis of a bonded tubular-coupler joint subjected to torsion. Their purpose was to investigate all of the adherend and adhesive stress components without the assumption of through-thickness constant stresses across the adhesive layer. Oh  performed an analysis of the bonded tubular lap joint of laminated tubes with softening adhesive’s stiffness properties under torsion using an elasticity model. Oh concluded that the load capacity in the linear analysis can be quite underestimated when compared to the nonlinear modeling. Spaggiari and Dragoni  investigated the joint studied in the Kumar’s work in , but the joint is subjected to torsion instead. They developed the closed-form function of the adhesive shear modulus in order to minimize adhesive shear stress over the bonding region and addressed the limitation of shear modulus and thicknesses ratio for joint manufacturing with functionally graded adhesives. Recently, Aimmanee and Hongpimolmas  formulated a mathematical model of an adhesive-bonded tubular joint with a variable-stiffness composite coupler. The optimal variable fiber orientation in the coupler was determined to minimize the adhesive hoop shear stress.
Stresses in cylindrical joints under pressure have also been studied, even though investigation of this type of load was comparatively scarce compared to the above two loadings. Terekhova and Skoryi  provided a close-form solution for the stresses in tubular lap joints under external and internal pressures and axial forces. Their model neglected the effect of adherend bending. Baishya et al.  conducted research in individual and combined effect of internal pressure and torsional loading on stress and failure characteristics of tubular single lap joints made of composite materials. The onset of different joint fracture modes was investigated in their work. Strength analysis of adhesive joints of riser pipes in deep sea environment loadings was performed by Zhang et al.  External pressure, internal pressure, tension, torsion, and bending were examined to understand singular stress fields existing around end of the interface. Apalak  investigated elastic stresses in the adhesive layer and tubes of an adhesively bonded tubular joint with functionally graded tubes subjected to an internal pressure. Finite-element method was used to model the tubes having gradient layer between a ceramic layer and a metal layer.
According to the former analytical research work presented in the literature, the problems can be mathematically complicated even though the joint is made of simple conventional isotropic adherends. In addition, the previous models usually are distinct for each type of load, since they were developed to analyze only for a specific loading case. Therefore, this chapter aims to present a mathematical modeling of adhesive-bonded cylindrical coupler joints taking into account all loading scenarios, i.e., torsion, axial, and pressure loadings. The inner and outer adherends can be made of isotropic, orthotropic, or laminated composite materials, and they are modeled as three-dimensional elastic body, so a thick or solid cylinder adherend can also be analyzed. Stresses in adhesive layer and adherends can be evaluated by newly developed finite-segment method. The unified formulation of the model will be discussed in the next section.
2. Elasticity theory of a laminated cylindrical structure
A bonded-coupler joint is illustrated in Figure 1(a). The joint consists of two inner tubes (adherend part 1), a coupler of length 2
For the sake of generality, this section discusses the elasticity theory of a laminated cylindrical tube . A sketch of a general open-ended, cylindrical, laminated
denote normal and shear strains, respectively.
According to the prescribed loading conditions and constant fiber orientation, the normal stresses,
, and the shear stresses,
, are independent of
The stresses and strains in the
are tensorial stress and tensorial strain components, respectively.
is transformation matrix of the
The constitutive relation in the
In the above, is the transformed stiffness matrix, and is engineering strain components in the global cylindrical coordinate system. The transformed stiffness matrix can be evaluated as
, as shown in Eq. (9), is the stiffness matrix in the principle material coordinate system in the
and are Young’s modulus and shear modulus, respectively. is the Reuter’s matrix, which is defined as
With the strains defined in Eq. (1), three out of six equations of the compatibility in the cylindrical coordinates described in  are automatically satisfied. Solving the equilibrium equations in Eqs. (2)–(4) and using the strain–displacement relations in Eq. (1), the constitutive relation in Eq. (7), the remaining three compatibility equations, as well as the displacement continuity between each layer yield the displacement expressions in the
In the above,
are axial strain and angle of twist per unit length constants, respectively.
are the integration constants in the
Note that when a layer is made of 0o fiber orientation, the stiffness coefficients , , and are zero and as well as . As such, Eq. (13) is degenerated to become .
Eqs. (15)–(20) give the system of algebraic equations written in matrix form as
where are the coefficients obtained from the equations above. By solving Eq. (21), the constants and can be obtained. Subsequently, all displacements, strains, and stresses are calculated by using Eqs. (11)–(13), (1), and (7), respectively.
3. Formulation of an equivalent lap joint model
3.1. Derivation of governing equations
All geometric parameters of a perfectly bonded tubular lap joint are shown in Figure 1(b). The adhesive is assumed to be isotropic and linearly elastic. The adhesive thickness
is considered to be very thin compared to the adherend thicknesses, and thus, the outer radius of part 1
is approximately the same as the inner radius of part 2,
. In addition, there are only three out-of-plane stress components mainly contributed in the adhesive: hoop shear stress
longitudinal shear stress
, and radial normal stress
. These stresses in the adhesive are treated to be uniform through the adhesive thickness. Applied torque
In order to derive the governing equations, let us initially consider the torque transmission through a coupler joint. The applied torque
To determine the variation of the
along the bonding length, the adherend 2 is divided into elements with an infinitesimal length
In Eq. (23), is shear modulus of adhesive. By considering the deformation of an adhesive element on a cross-sectional plane in the overlap region of the perfectly bonded joint, the kinematic condition in the adhesive can be written as
and its derivative with respect to
Combining Eqs. (23) and (25) yields the first governing equation:
Next, consider equilibrium of resultant axial force. When the joint is subjected to tension or compression loads, the resultant axial force in the adherend 1, and in adherend 2, are produced at any given cross section in the overlap region, similar to Eq. (22). The force equilibrium is
The variation of the
along the length can be examined by considering an infinitesimal elements in adherend part 2 with the differential length
By considering compatibility of the joint, it can be shown that.
Combining Eqs. (28) and (29) yields the axial force governing equation:
Next, interacting through the adhesive thickness, the resultant normal traction acting on the outer surface of adherend 1, , and that exerting on the inner surface of adherend 2, are generated. Under the assumption of thin adhesive layer, the resultant normal tractions and are related to each other as
Lastly, instead of directly equating adhesive radial normal stress to normal traction in (31), can be more accurately determined by the equilibrium equation in cylindrical coordinates of the adhesive layer showing in Eq. (32):
With the conditions of axisymmetry, the equilibrium equation is reduced to
According to the study conducted in , is observed to have the same distribution as so they are legitimately regarded as being proportional to each other via adhesive normal stress ratio . Their relation can be mathematically expressed in Eq. (34):
As a consequence, the equilibrium equation in Eq. (32) can then be written as
3.2. Implementation of elasticity theory for adherends
The two governing equations Eqs. (26) and (30) have already been formulated to determine resultant loads in adherend part 2 of an adhesive-bonded-coupler joint. The resultant loads in adherend part 1 can be then calculated easily by using Eqs. (22) and (27) after all internal loads in adherend part 2 are evaluated. However, related through Eq. (21), the two equations are coupled and need to be solved altogether. To aptly deal with this complicated condition, the problem is separated into primary and secondary effects. When the joint is subjected to torsion, the hoop shear stress in the adhesive is primary and dominant compared to the other adhesive stresses as discussed in [8, 10, 13], whereas in the case of the joint being under an application of longitudinal force, or external and internal pressure, the adhesive longitudinal shear stress and adhesive radial normal stress are comparatively crucial . By neglecting the secondary stress components and the corresponding resultant internal loads in the early calculation stage, the problem is then uncoupled and can be readily solved for the primary variables. The initially excluded stress components are later recovered by using the obtained solutions in the coupled set of governing equations.
First, further modification of the torque governing equation of Eq. (26) is performed, adherend in-plane shear strains and must be expanded in terms of the internal resultant loads. It can be seen that they are equal to and , respectively, where and are denoted for of adherend parts 1 and 2. Utilizing Eq. (21) yields the relations:
where quantities and , where , and 4 are the first four elements compliances in the second row of matrix in Eq. (21). Superscripts 1 and 2 are defined for adherend parts 1 and 2, respectively. , , , , , , , and are in-plane shear strains per unit load on the outer interfacial surface of adherend part 1 and inner interfacial surface of adherend part 2, respectively.
By substituting Eqs. (36) and (37) into the governing equation Eq. (26) and utilizing Eqs. (22), (27), and (31), the governing equation in term of becomes
where the parameters , , and are.
Accompanying with the boundary conditions of Eq. (40), which are implied that torque in adherend part 2 is zero at
Second, analogous to Eqs. (36) and (37), adherend in-plane normal strains and must also be written in terms of the internal resultant loads. Again, using the expression in Eq. (21), the following expressions are obtained:
In the above,
and 4 are the first four elements in the first row of matrix
in Eq. (21). Superscripts 1 and 2 are defined for adherend parts 1 and 2, respectively.
are newly denoted to indicate the physical meaning of the parameters. They represent the in-plane normal strains due to unit load on the adhesive-interfacial surface in the adherends. The unit load quantities are distinguished by after-comma subscripts
Combining the governing equations Eqs. (30), (41), and (42), as well as the load equilibriums in Eqs. (22), (27), and (31), yields a new form of the axial force governing equation:
where the parameters , , , and are.
To specify the boundary conditions of Eq. (43), one can consider the disappearance of
Finally, it should be noted that the occurrence of in Eq. (43) is closely related with the existence of because the tensile or compressive loading can induce the peeling traction. Therefore, in the equation is considered as unknown. However, it is possible to find the approximated relation between the two variables by letting and be zero; then can be evaluated and expressed in Eq. (46):
where and are integration constants.
Reinstating the resultant normal traction and substituting Eq. (46) into Eq. (43), it is found that can be simply estimated as
in which, and are unknown parameters. In order to determine these two parameters, two more boundary conditions are required from zero longitudinal shear stress in the adhesive layer at left and right ends as shown in Eq. (48):
Up to this point, the unified formulation of an analysis of adhesive-bonded coupler joint has been developed. The model can be universally used to determine the stresses in the adhesive layer for any particular load case previously mentioned. To elaborate the applicability of the model for each loading condition, i.e., torsion, axial, or external and internal pressure, the pertinent details are given below:
For torsional load, the secondary variables, namely, and are initially neglected in Eq. (38). In addition, . Consequently, and can be evaluated. Subsequently, , , and and can be recovered and computed by employing the full form of Eqs. (43) and (47), (28), and (35), respectively.
For axial load, the secondary variable is initially neglected. Additionally, The primary variables , , and are solved by using the governing equation, Eqs. (43), (47), (28), and (35). and is later calculated from the full form of Eqs. (38) and (23), respectively.
For external and internal pressure, the secondary variable is firstly omitted. In this case If only external pressure is present, , whereas if only internal pressure exists, . The first variables , , and are solved by using the governing equation, Eqs. (43), (47), (28), and (35). and can be later recovered the same way as those for the axial load.
3.3. Finite segment solution for evaluating adherend stresses
As previously discussed, all resultant loads in adherend parts 1 and 2 can be obtained as functions of
Presented in this section are some sample computational results of the model developed. The numerical calculation is performed by using software MATHEMATICA™. The validation of the model is not given herein, since it has already been shown in  and . Adhesive-bonded tubular joints with isotropic inner adherend and symmetric-balanced four-layer stacking sequence couplers are selected for consideration. The reference joint geometry is given with parameters , mm. The adherend part 1 is made of steel, whereas the adherend part 2 is fabricated from carbon fiber-reinforced plastic. Epoxy is used as the adhesive material. The material properties of the joints are listed in Table 1. Adhesive normal stress ratio, , is set to be 20 because it has shown to provide accurate predictions of adhesive radial stresses . In the following computational results, the adhesive stresses in the coupler joint are normalized by the average applied stress in each loading case, because the dimensionless stresses are readily exploited to identify the level of load distribution intensity in the joint.
|Properties||Epoxy (adhesive)||Steel (adherend 1)||Carbon/epoxy (adherend 2)|
4.1. Torsional loading
In the case of torsional loading, the joints are assumed to have a torque of 1 N.m as an input without loss of generality. Also, the adhesive mean shear stress in Eq. (49) is utilized to normalize the induced adhesive hoop shear stress in the coupler joint:
The resultant torque of the adherend part 2 and normalized adhesive hoop shear stress can be calculated and plotted in Figures 4 and 5, respectively. It can be noticed that the joints considered develop the nonconstant slopes in Figure 4 with relatively high torque gradients at both ends. This is equivalent to the peak adhesive hoop shear stresses at
Stress distributions in the composite coupler are illustrated in Figure 6 for the case of
= 30o. The normal stress in the fiber direction
in Figure 6(a) is the dominant stress component compared to those in the other directions. The radial normal stress
illustrated in Figure 6(b) is relatively small at
4.2. Axial loading
When the coupler joints are subjected to an axial loading, a tension force with the magnitude of 1 N is used in calculation. For this particular case, the adhesive mean shear stress in Eq. (50) is adopted to normalize the induced longitudinal shear stress and radial normal stress in the adhesive. Same as above, the normalized stresses can be utilized to indicate the distribution intensity of load transfer within the joints:
Figures 7 and 8 show the effect of fiber orientation on the distributions of
along the overlap region, respectively. Observation in Figure 8 reveals that by adjusting fiber orientation, the composite coupler can generate mostly uniform load transmission in the central bonding region. The internal forces
of Figure 7 in that region concomitantly reveal linear relationships with the spatial coordinate
Figure 10 shows the normal stresses and of adherend part 2 in the principal material coordinate system, when the fiber orientation is equal to 30o. It can be seen from the figure that under the application of the axial force, is vanished at the left of the bonding region due to the traction-free surface, while is disappeared on the outermost area of the coupler. The stress in the fiber direction steadily attains the same maximum value along the bond length in all laminae of composite coupler. The radial normal stress , which is induced from the resultant axial force, is highest at the adhesive-coupler interface.
4.3. Pressure loading
Lastly, for the case of pressure loads, 1 MPa internal pressure is exerted inside the adherend part 1, but no external pressure is present on the outer surface of the adherend part 2. The adhesive longitudinal shear stress and adhesive radial normal stress can then be normalized by the internal pressure to form the dimensionless variables.
Figures 11 and 12 show the effect of fiber orientation on the distributions of and along the overlap region, respectively. Figure 11 indicates that peak values of are generated in the central region of the composite couplers, but their values are null at both ends. The longitudinal shear stresses in adhesive in Figure 12 illustrate the antisymmetric characteristic along the bond length. It can be seen that the optimum fiber angle is 90°. This fiber orientation delivers the lowest maximum of 0.6. Figure 13 shows the radial normal stress in the adhesive. Interestingly, the values of are reduced by four to five times compared to the internal pressure applied over the whole range of the fiber angles considered.
The normal stresses
of adherend part 2 in the principal material coordinate system, when the fiber orientation are equal to 30°, are displayed in Figure 14. It can be noticed that under the application of the uniform internal pressure with 1 MPa magnitude,
is maximum at the mid-length of bonding region, whereas
is peak at
A unified mathematical model for predicting the joint stresses of the adhesive-bonded tubular-coupler joints or the equivalent bonded-lap joints under several types of load is formulated. The inner and outer adherends can be considered as an isotropic material, orthotropic material, or a laminated composite, whose fiber angle is constant along the tube axis. They are modeled as three-dimensional body and satisfied the equilibrium, kinematic, and constitutive equations in theory of elasticity. The adhesive is only treated to be a very thin isotropic elastic material with relative low modulus, and thus, merely three out-of-plane stress components are present. The finite-segment method is developed to compute adherend stresses in each small portion of the coupler. The analytical results obtained indicate the viability of the model for many joint conditions and configurations. The model can be used conveniently in the preliminary process of the joint design, which is usually critical in huge, complex, or integrated structures.
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