Sandwich theory
In the engineering theory of sandwich beams, the axial strain is assumed to vary linearly over the cross-section of the beam as in Euler-Bernoulli theory, i.e.,
formula_1
Therefore, the axial stress in the sandwich beam is given by
formula_2
where formula_3 is the Young's modulus which is a function of the location along the thickness of the beam. The bending moment in the beam is then given by
formula_4
The quantity formula_5 is called the flexural stiffness of the sandwich beam. The shear force formula_6 is defined as
formula_7
Using these relations, we can show that the stresses in a sandwich beam with a core of thickness formula_8 and modulus formula_9 and two facesheets each of thickness formula_10 and modulus formula_11, are given by
formula_12
For a sandwich beam with identical facesheets and unit width, the value of formula_5 is 
formula_14
If formula_15, then formula_5 can be approximated as
formula_17
and the stresses in the sandwich beam can be approximated as
formula_18
If, in addition, formula_19, then
formula_20
and the approximate stresses in the beam are
formula_21
If we assume that the facesheets are thin enough that the stresses may be assumed to be constant through the thickness, we have the approximation
formula_22
Hence the problem can be split into two parts, one involving only core shear and the other involving only bending stresses in the facesheets. The main assumptions of linear sandwich theories of beams with thin facesheets are:

However, the xz shear-stresses in the core are not neglected. The constitutive relations for two-dimensional orthotropic linear elastic materials are
formula_23
The assumptions of sandwich theory lead to the simplified relations
formula_24
and
formula_25
The equilibrium equations in two dimensions are
formula_26
The assumptions for a sandwich beam and the equilibrium equation imply that
formula_27
Therefore, for homogeneous facesheets and core, the strains also have the form
formula_28 Let the sandwich beam be subjected to a bending moment formula_29 and a shear force formula_30. Let the total deflection of the beam due to these loads be formula_31. The adjacent figure shows that, for small displacements, the total deflection of the mid-surface of the beam can be expressed as the sum of two deflections, a pure bending deflection formula_32 and a pure shear deflection formula_33, i.e.,
formula_34
From the geometry of the deformation we observe that the engineering shear strain (formula_35) in the core is related the effective shear strain in the composite by the relation
formula_36
Note the shear strain in the core is larger than the effective shear strain in the composite and that small deformations (formula_37) are assumed in deriving the above relation. The effective shear strain in the beam is related to the shear displacement by the relation
formula_38
The facesheets are assumed to deform in accordance with the assumptions of Euler-Bernoulli beam theory. The total deflection of the facesheets is assumed to be the superposition of the deflections due to bending and that due to core shear. The formula_39-direction displacements of the facesheets due to bending are given by
formula_40
The displacement of the top facesheet due to shear in the core is
formula_41
and that of the bottom facesheet is
formula_42
The normal strains in the two facesheets are given by
formula_43
Therefore,
formula_44 The shear stress in the core is given by
formula_45
or,
formula_46
The normal stresses in the facesheets are given by
formula_47
Hence,
formula_48 The resultant normal force in a face sheet is defined as
formula_49
and the resultant moments are defined as
formula_50
where
formula_51
Using the expressions for the normal stress in the two facesheets gives
formula_52
In the core, the resultant moment is
formula_53
The total bending moment in the beam is
formula_54
or,
formula_55
The shear force formula_6 in the core is defined as
formula_57
where formula_58 is a shear correction coefficient. The shear force in the facesheets can be computed from the bending moments using the relation
formula_59
or,
formula_60
For thin facesheets, the shear force in the facesheets is usually ignored. The bending stiffness of the sandwich beam is given by
formula_61
From the expression for the total bending moment in the beam, we have
formula_55
For small shear deformations, the above expression can be written as
formula_63
Therefore, the bending stiffness of the sandwich beam (with formula_19) is given by
formula_65
and that of the facesheets is
formula_66
The shear stiffness of the beam is given by
formula_67
Therefore, the shear stiffness of the beam, which is equal to the shear stiffness of the core, is
formula_68 A relation can be obtained between the bending and shear deflections by using the continuity of tractions between the core and the facesheets. If we equate the tractions directly we get
formula_69
At both the facesheet-core interfaces formula_70 but at the top of the core formula_71 and at the bottom of the core formula_72. Therefore, traction continuity at formula_73 leads to
formula_74
The above relation is rarely used because of the presence of second derivatives of the shear deflection. Instead it is assumed that 
formula_75
which implies that
formula_76 Using the above definitions, the governing balance equations for the bending moment and shear force are
formula_77
We can alternatively express the above as two equations that can be solved for formula_31 and formula_33 as
formula_80
Using the approximations
formula_81
where formula_82 is the intensity of the applied load on the beam, we have
formula_83
Several techniques may be used to solve this system of two coupled ordinary differential equations given the applied load and the applied bending moment and displacement boundary conditions. Assuming that each partial cross section fulfills Bernoulli's hypothesis, the balance of forces and moments on the deformed sandwich beam element can be used to deduce the bending equation for the sandwich beam. The stress resultants and the corresponding deformations of the beam and of the cross section can be seen in Figure 1. The following relationships can be derived using the theory of linear elasticity:
formula_84
where
Superposition of the equations for the facesheets and the core leads to the following equations for the total shear force formula_30 and the total bending moment formula_29:
formula_87
We can alternatively express the above as two equations that can be solved for formula_31 and formula_35, i.e.,
formula_90 The bending behavior and stresses in a continuous sandwich beam can be computed by solving the two governing differential equations. For simple geometries such as double span beams under uniformly distributed loads, the governing equations can be solved by using appropriate boundary conditions and using the superposition principle. Such results are listed in the standard DIN EN 14509:2006(Table E10.1). Energy methods may also be used to compute solutions directly. The differential equation of sandwich continuous beams can be solved by the use of numerical methods such as finite differences and finite elements. For finite differences Berner recommends a two-stage approach. After solving the differential equation for the normal forces in the cover sheets for a single span beam under a given load, the energy method can be used to expand the approach for the calculation of multi-span beams. Sandwich continuous beam with flexible cover sheets can also be laid on top of each other when using this technique. However, the cross-section of the beam has to be constant across the spans. A more specialized approach recommended by Schwarze involves solving for the homogeneous part of the governing equation exactly and for the particular part approximately. Recall that the governing equation for a sandwich beam is
formula_91
If we define
formula_92
we get
formula_93
Schwarze uses the general solution for the homogeneous part of the above equation and a polynomial approximation for the particular solution for sections of a sandwich beam. Interfaces between sections are tied together by matching boundary conditions. This approach has been used in the open source code swe2. Results predicted by linear sandwich theory correlate well with the experimentally determined results. The theory is used as a basis for the structural report which is needed for the construction of large industrial and commercial buildings which are clad with sandwich panels . Its use is explicitly demanded for approvals and in the relevant engineering standards. Mohammed Rahif Hakmi and others conducted researches into numerical, experimental behavior of materials and fire and blast behavior of Composite material. He published multiple research articles:



Hakmi developed a design method, which had been recommended by the CIB Working Commission W056 Sandwich Panels, ECCS/CIB Joint Committee and has been used in the European recommendations for the design of sandwich panels (CIB, 2000).
Linear sandwich theory ; Bending of a sandwich beam with thin facesheets
The most commonly used sandwich theory is linear and is an extension of first order beam theory. They usually consist of a low to moderate stiffness core which is connected with two stiff exterior facesheets. The high stiffness of the facesheet leads to a high bending stiffness to weight ratio for the composite. If the radius of curvature during bending is large compared to the thickness of the sandwich beam and the strains in the component materials are small, the deformation of a sandwich composite beam can be separated into two parts
* deformations due to bending moments or bending deformation, and
* deformations due to transverse forces, also called shear deformation. These temperature differences, coupled with different linear expansions of the facesheets, can lead to a bending of the sandwich beam in the direction of the warmer facesheet.