Mathematical Problems in Engineering

Mathematical Problems in Engineering / 2011 / Article

Research Article | Open Access

Volume 2011 |Article ID 145638 |

M. Jakomin, F. Kosel, "Stability of the Shallow Axisymmetric Parabolic-Conic Bimetallic Shell by Nonlinear Theory", Mathematical Problems in Engineering, vol. 2011, Article ID 145638, 30 pages, 2011.

Stability of the Shallow Axisymmetric Parabolic-Conic Bimetallic Shell by Nonlinear Theory

Academic Editor: Mohammad Younis
Received13 Jul 2010
Revised16 Feb 2011
Accepted30 May 2011
Published12 Sep 2011


In this contribution, we discuss the stress, deformation, and snap-through conditions of thin, axi-symmetric, shallow bimetallic shells of so-called parabolic-conic and plate-parabolic type shells loaded by thermal loading. According to the theory of the third order that takes into account the balance of forces on a deformed body, we present a model with a mathematical description of the system geometry, displacements, stress, and thermoelastic deformations. The equations are based on the large displacements theory. We numerically calculate the deformation curve and the snap-through temperature using the fourth-order Runge-Kutta method and a nonlinear shooting method. We show how the temperature of both snap-through depends on the point where one type of the rotational curve transforms into another.

1. Introduction

The development of machine sciences in recent centuries has led to the manufacture of various devices from relatively simple mechanisms to the very complex mechanical devices used by mankind in the process of transforming material goods. Although modern equipment comes in very different forms, functions, and structure, owing to the importance of smooth, reliable operation and their value, a demand for protection against a number of overloads is expressed. It is especially necessary to provide reliable protection against thermal overload for machines that convert one form of energy into another and heat up in the process. For this purpose, elements are built into devices to serve as a “thermal fuse” turning the machine off as soon as an individual part reaches the maximum permissible temperature. Due to their operational reliability, both line and plane bimetallic structural elements are used in protection against thermal overload, whose operation is based on the known physical fact that bodies expand with the increase of temperature. With a suitable technical act, we can connect a bimetallic construction element, Figure 1, with electrical contacts and make a so-called “thermal switch”. Displacements created on the bimetallic element due to a combination of temperature and mechanical loads turn the device on and off dependent on the temperature 𝑇. For this, it is of course necessary to know the connection between the displacements and loading of the bimetallic construction element. Apart from material properties, this connection is also dependent on the geometric properties of the bimetal, as the line bimetallic construction elements respond with different stresses and deformational states to temperature loads as compared to plane construction elements. In practice, the difference in the stability conditions is the most important. Thin and shallow bimetallic shells with suitable material and geometric properties have the characteristic of snapping-through into a new equilibrium position at a certain temperature. The result of such a fast snap-through of a bimetallic shell acting as a switching element in a thermal switch is the instantaneous shutdown of electric power and the machine. The snap-through of the bimetallic shell is a dynamic occurrence that lasts a very short time and as such prevents the damaging sparking and melting of electric contacts and extends the life expectancy of the thermal switch.

Panov, Timoshenko, Videgren, Witrick, Aggarwala, Saibel, Huai, Vasudevan, Johnson, Keller, Reiss, Brodland, Cohen, Kosel, Batista, Drole, Jakomin, and some other authors have engaged in the research of bimetallic shell elements in a homogenous temperature field. S. Timoshenko [1] researched the problem of the stability of bimetallic lines and plates. The authors Panov [2] and Wittrick et al. [3] researched the problem of the stability for shallow axi-rotational symmetric spherical shells during heating. The related problem of stability of a spherical shell under normal loads has been treated by Keller and Reiss [4]. The problem of thermal stability of a multimetallic strip has been treated by Vasudevan and Johnson in [5]. Aggarwala and Saibel researched the thermal stability of thin spherical shells [6]. The occurrence of the snap-through of an open bimetallic shell was treated by Ren Huai [7] using approximative methods. The problem of finite axisymmetric deflection and snapping of spherical shells which are point loaded at the apex and simply supported at the boundary is analysed by Brodland and Cohen, in [8]. Kosel et al. researched the stability conditions during the temperature and mechanical loading of rotational axisymmetric [912] and translation shells [13, 14] with and without an opening at the apex of the shell.

Apart from the spherical and parabolic bimetallic shells, the market also offers shells with more complex initial geometries. “Elektronik Werkstatte” the manufacturer of bimetallic shells from Eichgraben in Austria offers several different types of combined axisymmetric shells (Figure 1, the first and the second shell from the left in the top row) that have an advantage over spherical shells in that the temperature range of the snap-through (the difference in temperature of the upper and lower snap-through) can be changed at the constant of the initial bimetallic shell height. Even with a relatively small initial shell height, using a suitable combination of a parabola and cone rotational curve, it is possible to achieve snap-through of the shell only at very high temperature loads. Due to the smaller initial height, it is important that the stresses in these shells are smaller relative to the stresses in parabolic or spherical shells.

So, this time, we are discussing the stability and deformation conditions for a thin axisymmetric shallow bimetallic shell, composed of a parabola and cone and a plane and parabola. Apart from the temperature, the shell is additionally burdened with a force at the apex and with pressure. When executing a nonlinear mathematical model for the snap-through of a bimetallic translation shell, we will assume a small strain and the moderate rotation of the shell element. In the strain tensor, we will also consider nonlinear terms, while placing equilibrium equations on the deformed part of the shell. For the first time, we will show in both table and graphic form how the temperature of both snap-through depends on the point where the parabolic shape of the rotational curve changes into a cone shape. We will explain the effect of the concentrated force at the apex for the example of a bimetallic shell of the plate-parabola type!

The defined thermoelastic problem will be solved with the following steps:(1)defining the geometry of the undeformed shell,(2)deriving the displacement vector as relation between the geometry of the undeformed and the deformed shell,(3)defining the geometry of the deformed shell,(4)deriving the elements of the strain and stress tensor,(5)introducing the forces and moments per unit of length,(6)deriving the equilibrium equations of unit forces and moments acting in the deformed shell element, and(7)calculating the deformation curve and the snap-through temperature using the fourth-order Runge-Kutta method and a nonlinear shooting method.

2. Geometry of the Undeformed Shell

The axisymmetric shape of the undeformed shell is formed by rotation of the curve 𝑦=𝑦(𝑥), about the 𝑦 axis [15], Figure 2. The middle surface of the undeformed axisymmetric shell in the Lagrange Coordinate System is, therefore, defined by the function 𝑦=𝑦(𝑥). Figure 3 shows the middle surface of a thin rotationally symmetric bimetallic shell.

From Figures 2 and 3, we can obtain the geometric properties of the undeformed shell.

Differential of the length in the meridian direction 𝑑𝑠𝜓:𝑑𝑠𝜓=𝑟𝜓𝑑𝜓.(2.1) Differential of the length in the circular direction 𝑑𝑠𝜑 is𝑑𝑠𝜑=𝑟𝜑sin𝜓𝑑𝜑=𝑥𝑑𝜑.(2.2) Meridian angle 𝜓𝜓=arctan𝑑𝑦𝑦𝑑𝑥=arctan𝑦.(2.3) The flexion curvature 1/𝑟𝜓 of the rotational curve 𝑦(𝑥) in the meridian direction is, Figures 2 and 31𝑟𝜓=𝑦1+𝑦23𝑦.(2.4) The flexion curvature 1/𝑟𝜑 of the circle formed by rotation of the curve 𝑦=𝑦(𝑥), in the circular direction is, Figures 2 and 3,1𝑟𝜑=sin𝜓𝑥=𝑦sinarctan𝑥=1𝑥𝑦1+(𝑦)2𝑦𝑥.(2.5) The simplifications in (2.3), (2.4), and (2.5) are justified since we are discussing a shallow shell, where,𝑦(𝑥)21,(2.6) and consequently, sin𝜓𝜓,sin𝜑𝜑,cos𝜓1.(2.7)

3. Displacement Vector and Geometry of Deformed Shell

Due to the temperature change, the shell deforms into a new shape defined by the function 𝑌(𝑋) in the Euler Coordinate System. Since we are discussing a thin double-layered shell, the displacement field is selected to satisfy the Kirchhoff hypothesis [16]:(1)straight lines perpendicular to the shell’s middle surface before deformation, remain straight after deformation,(2)the transverse normals do not experience elongation,(3)the transverse normals rotate, so that they remain perpendicular to the shell’s middle surface after deformation.

The reader should note that the Kirchhoff hypothesis stating that the thickness of the shell before and after deformation remains the same when the shell is subjected to kinematic constraint is not realistic when large strains are admitted in the deformation process [17]. The so-called Zig-Zag theory is known in literature and describes a piecewise continuous displacement field in the direction of the multilayered shell thickness and accomplishes the continuity of transverse stresses at each layer [1820]. However, given the fact that the ratio between the thickness and length of bimetallic shells, used as safety constructional elements against temperature overheating, is about 1/100, we found the Kirchhoff hypothesis is fully acceptable for our mathematical model.

The new shape of the shell in a deformed state is axisymmetric due to the homogeneous temperature field and axisymmetric mechanical load. Therefore, the displacement 𝑣 in the circular direction as well as other shell properties relative to the angle 𝜑 do not change:𝜕𝑣=0,𝜕𝜑()=0.(3.1)

The displacement vector 𝑢 of any point 𝑃 on the middle surface of an undeformed shell defines the point 𝑃 on the middle surface of a deformed shell𝑢=𝑢𝑒𝜓+𝑣𝑒𝜑+𝑤𝑒𝑟,(3.2) and with the supposition (3.1),𝑢=𝑢𝑒𝜓+𝑤𝑒𝑟.(3.3) Unit basis vectors 𝑒𝜓,𝑒𝜑 and 𝑒𝑟 in the Cartesian coordinate system follow directly from the system geometry, Figure 2,𝑒𝜓=(cos𝜓cos𝜑)𝑖+(sin𝜓)𝑗+(cos𝜓sin𝜑)𝑘,𝑒𝜑=(sin𝜑)𝑖+(cos𝜑)𝑘,𝑒𝑟=(sin𝜓cos𝜑)𝑖(cos𝜓)𝑗+(sin𝜓sin𝜑)𝑘.(3.4) These vectors are mutually orthogonal because𝑒𝜓𝑒𝜑=𝑒𝜓𝑒𝑟=𝑒𝜑𝑒𝑟=0.(3.5) Derivatives of these vectors with respect to the curvilinear coordinates 𝜓,𝜑, and 𝑟 are [21]𝜕𝑒𝜓𝜕𝜓=(cos𝜑sin𝜓)𝑖+(cos𝜓)𝑗(sin𝜑sin𝜓)𝑘=𝑒𝑟,𝜕𝑒𝜓𝜕𝜑=(cos𝜓sin𝜑)𝑖+0𝑗+(cos𝜑cos𝜓)𝑘=𝑒𝜑cos𝜓,𝜕𝑒𝜓=𝜕𝑟0,𝜕𝑒𝜑=𝜕𝜓0,𝜕𝑒𝜑𝜕𝜑=(cos𝜑)𝑖+0𝑗+(sin𝜑)𝑘=𝑒𝑟sin𝜓𝑒𝜓cos𝜓,𝜕𝑒𝜑=𝜕𝑟0,𝜕𝑒𝑟=𝜕𝜓(cos𝜑cos𝜓)𝑖+(sin𝜓)𝑗+(cos𝜓sin𝜑)𝑘=𝑒𝜓,𝜕𝑒𝑟𝜕𝜑=(sin𝜑sin𝜓)𝑖+0𝑗+(cos𝜑sin𝜓)𝑘=𝑒𝜑sin𝜓,𝜕𝑒𝑟=𝜕𝑟0,(3) and when simplified due to the supposition(2.7)𝜕𝑒𝜓𝜕𝜓=𝑒𝑟,𝜕𝑒𝜓𝜕𝜑=𝑒𝜑,𝜕𝑒𝜓=𝜕𝑟0,𝜕𝑒𝜑=𝜕𝜓0,𝜕𝑒𝜑𝜕𝜑=𝜓𝑒𝑟𝑒𝜓,𝜕𝑒𝜑=𝜕𝑟0,𝜕𝑒𝑟𝜕𝜓=𝑒𝜓,𝜕𝑒𝑟𝜕𝜑=𝜓𝑒𝜑,𝜕𝑒𝑟=𝜕𝑟0.(3.7) Now, let us observe displacements on a thin shallow axisymmetric bimetallic shell in a homogenous temperature field, Figure 3, which is additionally loaded with the force 𝐹 at its apex.

The point 𝑃 at the position 𝑃(𝑥,𝑦(𝑥)) on the undeformed shell moves into the position 𝑃 on the deformed shell with the coordinates 𝑃(𝑋,𝑌(𝑋)). The reader should note that both the Euler (𝑋,𝑌(𝑋)) and Lagrange (𝑥,𝑦(𝑥)) coordinate system have the same origin at point (0,0). So, when a force or temperature load is exerted on the shell the optional point 𝑃 moves, as we have shown in Figure 3, since the reaction force per unit of length 𝑉𝑒 acts in the opposite direction. The connection between the Euler (𝑋,𝑌(𝑋)) and Lagrange (𝑥,𝑦(𝑥)) Coordinate System is, Figure 3,𝑋=𝑥+𝑢,(3.8) where𝑢𝑤𝑢(𝑥,𝑦)=cos𝜓sin𝜓sin𝜓cos𝜓,(3.9) from which we obtain𝑋=𝑥+𝑤sin𝜓+𝑢cos𝜓𝑥+𝑤𝑦+𝑢,(3.10)𝑌=𝑦𝑤cos𝜓+𝑢sin𝜓𝑦𝑤.(3.11) In (3.10), we also consider that the displacement 𝑢 is small in comparison with the displacement 𝑤, which in turn is small in comparison with the Lagrange coordinates 𝑥 so that the Euler coordinates 𝑋 is approximately𝑋=𝑥+𝑤𝑦+𝑢𝑥.(3.12) From Figure 3, we can also find geometric properties of the deformed shell.

The differential of the length 𝑑𝑠𝜓 in the meridian direction𝑑𝑠𝜓=𝑟𝜓𝑑𝜓=𝑑𝑋2+𝑑𝑌2=𝑑𝑥𝑋2+𝑌2.(3.13) Meridian angle 𝜓 is𝜓=arctan𝑑𝑌𝑑𝑋𝑑𝑌𝑑𝑋𝑑𝑌𝑑𝑥=𝑌𝑑𝑋𝑑𝑥𝑋𝑌.(3.14) Flexion curvature 1/𝑟𝜓 in the meridian direction is1𝑟𝜓=||𝑋𝑋𝑌𝑌||𝑋2+𝑌23𝑌.(3.15) Flexion curvature 1/𝑟𝜑 in the circular direction1𝑟𝜑=sin𝜓𝑋𝜓𝑋𝑑𝑌1𝑑𝑋𝑋𝑌𝑋.(3.16) With (3.11) and (3.12) for Euler’s coordinates 𝑌 and 𝑋, we finally obtain𝜓=𝑦𝑤,1𝑟𝜓=𝑦𝑤,1𝑟𝜑=𝑦𝑤𝑥.(3.17)

4. Strain and Stress Tensor

A shell’s deformation state is shown by the displacement vector 𝑢 in the middle, that is, reference surface. This vector has two components: the displacement 𝑢 in the meridian direction and the displacement 𝑤 in the radial direction. The elements of the strain tensor 𝐄 in the curvilinear orthogonal coordinate system are determined by the Green-Lagrange strain tensor 𝐄 for the middle surface of the shell [16]𝐄=𝐄𝑇=12𝑢+𝑢𝑇+𝑢𝑢𝑇,(4.1) where the displacement vector 𝑢 is of the form (3.3). The vector operator is by definition =𝑒𝜓𝜕𝜕𝑠𝜓+𝑒𝜑𝜕𝜕𝑠𝜑+𝑒𝑟𝜕𝜕𝑧=𝑒𝜓1𝑟𝜓𝜕𝜕𝜓+𝑒𝜑1𝑥𝜕𝜕𝜑+𝑒𝑟𝜕𝜕𝑧.(4.2) The gradient of the displacement vector 𝑢, while keeping in mind the derivatives of the unit basis vectors (3.7) and supposition (3.1), in the Green-Lagrange strain tensor (4.1) is𝑝grad𝑢=𝑢=11,𝑝12,𝑝13𝑝21,𝑝22,𝑝23𝑝31,𝑝32,𝑝33=1𝑟𝜓𝜕𝑢1𝜕𝜓+𝑤,0,𝑟𝜓𝜕𝑤1𝜕𝜓𝑢0,𝑟𝜑𝜓(𝑢+𝑤𝜓),0𝜕𝑢𝜕𝑧,0,𝜕𝑤𝜕𝑧.(4.3) All nine tensor elements are obtained once (4.3) is inserted into (4.1):1𝐄=22𝑝11+𝑝211+𝑝212+𝑝213,𝑝12+𝑝21+𝑝11𝑝21+𝑝12𝑝22+𝑝13𝑝23,𝑝12+𝑝21+𝑝11𝑝21+𝑝12𝑝22+𝑝13𝑝23,2𝑝22+𝑝221+𝑝222+𝑝223,𝑝13+𝑝31+𝑝11𝑝31+𝑝12𝑝32+𝑝13𝑝33,𝑝23+𝑝32+𝑝21𝑝31+𝑝22𝑝32+𝑝23𝑝33,𝑝13+𝑝31+𝑝11𝑝31+𝑝12𝑝32+𝑝13𝑝33𝑝23+𝑝32+𝑝21𝑝31+𝑝22𝑝32+𝑝23𝑝332𝑝33+𝑝231+𝑝232+𝑝233,(4.4) or in explicit form𝜀𝜓=1𝑟𝜓𝜕𝑢+1𝜕𝜓+𝑤2𝑟2𝜓𝑢2+𝑤2+2𝑤𝜕𝑢𝜕𝜓2𝑢𝜕𝑤+𝜕𝜓𝜕𝑢𝜕𝜓2+𝜕𝑤𝜕𝜓2,𝜀𝜑=1𝑟𝜑1𝜓+1𝑢+𝑤2𝑟𝜑2𝑤2+2𝑢𝑤𝜓+1𝜓2𝑢2+𝑣2,𝜀𝜓𝑟=𝜀𝑟𝜓=12𝜕𝑢+1𝜕𝑧2𝑟𝜓𝜕𝑤+1𝜕𝜓𝑢2𝑟𝜓𝑤𝜕𝑢𝜕𝑧𝑢𝜕𝑤+𝜕𝑧𝜕𝑢𝜕𝑧𝜕𝑢+𝜕𝜓𝜕𝑤𝜕𝑧𝜕𝑤,𝜀𝜕𝜓𝑟𝑟=𝜕𝑤+1𝜕𝑧2𝜕𝑢𝜕𝑧2+𝜕𝑤𝜕𝑧2,𝜀𝜓𝜑=0,𝜀𝜑𝜓=0,𝜀𝜑𝑟=𝜀𝑟𝜑=0.(4.5) However, the strains in (4.4) and (4.5) are still cumbersome and can hardly be used in practical computation. On the other hand, some nonlinear terms are relatively small and can be neglected without any significant effect on the accuracy of the results. Let us find the terms to be neglected.

In the case of rotation 𝝎 of the shell element with the length 𝐝𝐬𝝍 in the direction of the unit vector 𝐞𝝍, Figure 4, we can express the differential of the displacement vector 𝐝𝐮 with||||𝑑𝑢=𝑑𝑢cos𝜃𝑒𝜓+sin𝜃𝑒𝑟=𝑑𝑥grad𝑢=𝑑𝑠𝜓𝑝11𝑒𝜓+𝑝13𝑒𝑟,(4.6) where 𝜃 is angle that the vector 𝑑𝑢 forms with the basis unit vector 𝑒𝜓, Figure 4.

In the case of small strains |𝜺𝝍|𝟏, we have||𝑑𝑋||=||||𝑑𝑥1+𝜀𝜓||||,||||||||𝑑𝑥𝑑𝑢𝑑𝑥𝜔𝑟𝜓𝑑𝜓𝜔=𝑑𝑠𝜓𝜔,(4.7) where 𝜔 as the rotation of the shell element is expressed in radians. It is also further evident by comparing the coefficients in (4.6) that𝑝11||||=𝑑𝑢𝑑𝑠𝜓cos𝜃=𝜔cos𝜃𝑝13=||||𝑑𝑢||||𝑑𝜓sin𝜃=𝜔sin𝜃.(4.8) If the shell element with the length 𝑑𝑠𝜓 in the direction of the unit vector 𝑒𝜓 completes the rotation for the angle 𝜔=20 around the vector 𝑒𝜑, it follows that:𝑝11𝜋9cos800.06𝑝13𝜋9sin800.34.(4.9) A similar calculation can be performed for the rotation of the shell element with the length 𝑑𝑠𝜑 in the direction of the unit vector 𝑒𝜑.

In case of small strains and moderate shell rotations approximately up to 20, the components of the displacement gradient are||𝑝11||,||𝑝22||,||𝑝33||||𝑝1,(4.10)13||<1,(4.11) due to which we ignore all nonlinear terms in Green-Lagrange strain tensor (4.4) except the term 𝑝213.

Thus, the displacement of the point 𝑃 due to load is the largest in the direction of the unit vector 𝑒𝑟, while the displacement in the direction of the unit vectors 𝑒𝜓 is by absolute value smaller |𝑢|<|𝑤|.(4.12) Further, we consider that the flexion curvature of the shallow shell in the meridian direction is very small due to which it is true that1𝑟𝜓𝑢𝑦1𝑢𝑟𝜓𝑑𝑤=𝑑𝜓𝑑𝑤𝑑𝑠𝜓𝑑𝑤𝑑𝑥=𝑤.(4.13) So, the tensor elements (4.4) and (4.5) are finally1𝐄=22𝑝11+𝑝213,0,𝑝13+𝑝310,2𝑝22,0𝑝13+𝑝31,0,2𝑝33,(4.14) or𝜀𝜓=1𝑟𝜓𝜕𝑢+1𝜕𝜓+𝑤2𝑟2𝜓𝜕𝑤𝜕𝜓2,𝜀𝜑=1𝑟𝜑1𝜓,𝜀𝑢+𝑤𝜓𝑟=𝜀𝑟𝜓=12𝜕𝑢+1𝜕𝑧2𝑟𝜓𝜕𝑤𝜕𝜓,𝜀𝑟=𝜕𝑤,𝜀𝜕𝑧𝜓𝜑=0,𝜀𝜑𝜓=0,𝜀𝜑𝑟=𝜀𝑟𝜑=0.(4.15) With the introduction of the local coordinate 𝑧 with the centre of origin on the middle surface of the shell, Figure 4, the elements of the strain tensor 𝐄 are, due to the shell’s curvature, also the function of the coordinate 𝑧. The relation between the displacement 𝑢𝑧 on the local coordinate 𝑧 and displacement 𝑢 on the middle surface of the bimetallic shell, Figure 4, can be found from the strain tensor element 𝜀𝜓𝑟, since Kirchhoff hypothesis states that the strait lines perpendicular to the shell’s middle surface before deformation remain straight also after deformation. In other words, the hypothesis declares that the shear strain 𝜀𝜓𝑟 is zero𝜀𝜓𝑟=12𝜕𝑢+1𝜕𝑧2𝑟𝜓𝜕𝑤𝜕𝜓=0.(4.16) The solution to this equation with respect to the element 𝑢 of the displacement vector 𝑢 is:𝑢(𝑧)=𝑢𝑧𝑧=𝑢𝑟𝜓𝜕𝑤𝜕𝜓.(4.17) The normal strain 𝜀𝑟 in the transversal direction is equal to zero according to the second assumption of Kirchhoff’s hypothesis:𝜀𝑟=0.(4.18) Now, two nonzero elements of the Green-Lagrange strain tensor 𝐄 (4.15) for the middle surface of the shell can be recorded by means of relation (4.13) as𝜀𝜓=𝑢+𝑤𝑦+12𝑤2,𝜀𝜑=𝑢+𝑦𝑤𝑥.(4.19) Note again that when we form the strain tensor 𝐄, we retain the nonlinear term for strain 𝜀𝜓 in 𝑢𝑧 the meridian direction according to the third order of the large displacements theory. Namely, it has been confirmed that taking into account this nonlinear term is crucial for the accuracy of the results.

We calculate the strains 𝜀𝑧𝜓 and 𝜀𝑧𝜑 at distance 𝑧 from the middle surface of the bimetallic shell in the direction of the unit vector 𝑒𝑟 with (4.15), where we replace the displacement 𝑢 with the displacement 𝑢𝑧.

Since we are working on a thin shell, where 𝑧{𝑟𝜓,𝑟𝜑}, we obtain𝜀𝑧𝜓=(𝑢𝑧)+𝑤𝑟𝜓+1+𝑧2𝑤2=𝑢𝑧𝑤+𝑤𝑟𝜓+1+𝑧2𝑤2𝜀𝜓𝑧𝑤,𝜀𝑧𝜑=1𝑟𝜑𝑢+𝑧𝑧𝜓=1+𝑤𝑟𝜑+𝑧𝑢𝑧𝑤𝜓+𝑤𝜀𝜑𝑧𝑤𝑥.(4.20)

The relation between the strain and stress tensor is determined by Hooke’s law [22]𝜎𝑧𝜓=𝐸1𝜇2𝜇𝜀𝑧𝜑+𝜀𝑧𝜓,𝜎(1+𝜇)𝛼𝑇𝑧𝜑=𝐸1𝜇2𝜇𝜀𝑧𝜓+𝜀𝑧𝜑.(1+𝜇)𝛼𝑇(4.21) The symbol 𝐸 denotes the Young’s modulus, the symbol 𝜇 denotes the Poisson’s ratio and 𝛼 is the thermal expansion coefficient. The symbol 𝑇 denotes the shell’s relative temperature relevant to the reference 𝑇0 for which the stress state in the shell is equal to zero:𝜎𝑧𝜓𝑥,𝑧,𝑇0=𝜎𝑧𝜑𝑥,𝑧,𝑇0=𝜏𝑧𝜓𝑟𝑥,𝑧,𝑇0=0.(4.22)

5. Equilibrium of the Forces and Moments

Figure 5 shows an elementary small part of the bimetallic shell with the stresses that arise on the cross-section planes of the shell. The forces 𝑑𝑁𝜓,𝑑𝑁𝜑, and 𝑑𝑇𝜓𝑟 and the bending moments 𝑑𝑀𝜓, 𝑑𝑀𝜑 which act upon the 𝐴𝐵𝐶𝐷 planes are𝑑𝑁𝜓=𝑛𝜓𝑋𝑑𝜑,𝑑𝑁𝜑=𝑛𝜑𝑟𝜓𝑑𝜓,𝑑𝑇𝜓𝑟=𝑡𝜓𝑟𝑋𝑑𝜑,𝑑𝑀𝜓=𝑚𝜓𝑋𝑑𝜑,𝑑𝑀𝜑=𝑚𝜑𝑟𝜓𝑑𝜓.(5.1) With 𝑛𝜓,𝑛𝜑,𝑡𝜓𝑟 and 𝑚𝜓,𝑚𝜑 in (5.1) the unit forces and unit moments, respectively, are denoted. Since we are dealing with a thin bimetallic shell, these forces and moments have the form𝑛𝜓=𝛿/2𝛿/2𝜎𝑧𝜓𝑑𝑧,𝑛𝜑=𝛿/2𝛿/2𝜎𝑧𝜑𝑚𝑑𝑧,𝜓=𝛿/2𝛿/2𝑧𝜎𝑧𝜓𝑑𝑧,𝑚𝜑=𝛿/2𝛿/2𝑧𝜎𝑧𝜑𝑑𝑧.(5.2) The reader should note that the transversal shear force 𝑑𝑇𝜓𝑟 in (5.1) cannot be expressed by a definite integral since the transversal shear strain 𝜀𝜓𝑟 is disregarded according to the Kirchhoff hypothesis. However, this assumption does not exclude the full consideration of the shear force 𝑇𝜓𝑟, which, in continuation, will be expressed with the equilibrium equations. According to the Euler-Bernoulli beam theory assumptions, a similar example occurs for a clamped thin beam when loaded with a transversal shear force.

As the shell element in Figure 6 is in equilibrium, we can write three equations for the equilibrium of forces and moments in the meridian, circular and radial directions of the shell. In doing so, let us also remember that we are discussing a shallow shell, where the sinus function of the meridian angle 𝜓 can be replaced by its argument 𝜓, while the cosine of the same angle is very close to onesin𝜓𝜓,cos𝜓1.(5.3) Equilibrium of the forces in the meridian direction is𝑑𝑁𝜓+𝑑𝑑𝑁𝜓𝑑𝑁𝜓𝑑𝑇𝜓𝑟𝑑𝜓+𝑝𝑟𝜓𝑑𝑑𝜓𝑋𝑑𝜑𝜓2𝑑𝑁𝜑𝑑𝜑=0.(5.4) Equilibrium of the forces in the radial direction𝑑𝑇𝜓𝑟+𝑑𝑑𝑇𝜓𝑟𝑑𝑇𝜓𝑟+𝑝𝑟𝜓𝑑𝜓𝑋𝑑𝜑+𝑑𝑁𝜓𝑑𝜓+𝑑𝑁𝜑𝑑𝜑𝑑𝜓+𝜓2=0.(5.5) The equilibrium equation of forces in the circular direction cannot be considered due to the axisymmetric deformation. We write the moment equilibrium as𝑑𝑀𝜓+𝑑𝑑𝑀𝜓𝑑𝑀𝜓2𝑑𝑀𝜑𝑑𝜑2𝑑𝑇𝜓𝑟𝑑𝑋𝑑𝑇𝜓𝑟𝜓𝑑𝑌+𝑝𝑟𝜓𝑑𝜓𝑋𝑑𝜑𝑑𝑋2+𝑑𝜓+𝜓2𝑑𝑌2𝑑𝑁𝜓𝜓𝑑𝑋+𝑑𝑁𝜓𝑑𝑌+2𝑑𝑁𝜑𝑑𝜑2𝑑𝑌2=0,(5.6) where𝑑𝑑𝑁𝜓=𝜕𝑑𝑁𝜓𝜕𝜓𝑑𝜓=𝑑𝑛𝜓𝑋𝑑𝜑+𝑛𝜓𝑑𝑑𝑋𝑑𝜑,𝑑𝑇𝜓𝑟=𝜕𝑑𝑇𝜓𝑟𝜕𝜓𝑑𝜓=𝑑𝑡𝜓𝑟𝑋𝑑𝜑+𝑡𝜓𝑟𝑑𝑑𝑋𝑑𝜑,𝑑𝑀𝜓=𝜕𝑑𝑀𝜓𝜕𝜓𝑑𝜓=𝑑𝑚𝜓𝑋𝑑𝜑+𝑚𝜓𝑑𝑋𝑑𝜑.(5.7)

After arranging and using (3.17), the equilibrium equations are𝑛𝜓𝑥𝑛𝜑𝑡𝜓𝑟𝑥(𝑦𝑤)𝑡=0,(5.8)𝜓𝑟𝑥+𝑛𝜑(𝑦𝑤)+𝑛𝜓𝑥(𝑦𝑤)𝑚+𝑝𝑥=0,(5.9)𝜓𝑥𝑚𝜑𝑡𝜓𝑟𝑥=0.(5.10)

6. Solving Equilibrium Equations

The system of thermoelastic equations for a thin shallow axisymmetric bimetallic shell consists of three equilibrium equations (5.8), (5.9), (5.10), the four equations (5.2) for unit forces and moments, two equations (4.21) for stresses in the shell, two equations (4.20) for strains outside the middle plan of the shell, and finally two equations (4.19) which relate strains and displacements. Thus, the system has 13 equations and as many unknowns, namely 𝑛𝜓, 𝑛𝜑, 𝑡𝜓𝑟, 𝑚𝜓, 𝑚𝜑, 𝜎𝑧𝜓, 𝜎𝑧𝜑, 𝜀𝑧𝜓, 𝜀𝑧𝜑, 𝜀𝜓, 𝜀𝜑, 𝑢 and 𝑤 and can be reduced further in a following way: first, we insert (4.20) into (5.2). After integration, we have𝑛𝜓𝜀=𝐴𝜓+𝜇𝜀𝜑𝑛𝑃𝑇,(6.1)𝜑𝜀=𝐴𝜑+𝜇𝜀𝜓𝑚𝑃𝑇,(6.2)𝜓𝑤=𝐵𝑤+𝜇𝑥𝑚𝑄𝑇,(6.3)𝜑𝑤=𝐵𝑥+𝜇𝑤𝑄𝑇,(6.4) where 𝐴,𝐵,𝑃, and 𝑄 are constants as follows [13, 14]:𝐴=𝐸𝛿1𝜇2,𝐵=𝐸𝛿3121𝜇2,𝑃=𝐸𝛿2𝛼(1𝜇)1+𝛼2,𝑄=𝐸𝛿2𝛼2𝛼18(𝜇1).(6.5) We now multiply (5.8) with (𝑦𝑤) and add (5.9). So, we obtain𝑛𝜓𝑥(𝑦𝑤)+𝑛𝜓𝑥(𝑦𝑤)+𝑡𝜓𝑟𝑥+𝑝𝑥𝑡𝜓𝑟𝑥(𝑦𝑤)(𝑦𝑤)=0.(6.6) We disregard the last nonlinear term of 103 magnitude order, since𝑦𝑤𝑦𝑤=𝑌𝑌=12𝑌21031.(6.7)

In this way, we obtain the relation 𝑡𝜓𝑟𝑥𝑛=𝜓𝑥(𝑦𝑤)𝑛𝑝𝑥=𝜓𝑥(𝑦𝑤)+𝑝𝑥𝑑𝑥,(6.8) and after integration𝑡𝜓𝑟=1𝑥𝑐𝑥0𝑝𝑥𝑑𝑥𝑛𝜓(𝑦𝑤),(6.9) where 𝑐 is a constant that depends exclusively on the external force 𝐹 acting on the shell.

The relation (6.9) is inserted into (5.9) and (5.10). 𝑛𝜓𝑥𝑛𝜑𝑚=0,𝜓𝑥𝑚𝜑+𝑛𝜓𝑥(𝑦𝑤)𝑐+𝑥0𝑝𝑥𝑑𝑥=0.(6.10) We now express the unit forces 𝑛𝜓, 𝑛𝜑 and moments 𝑚𝜓, 𝑚𝜑 in the equations above with (6.1), (6.2), (6.3), and (6.4), and the strains 𝜀𝜓, 𝜀𝜑 wit

h the kinematic equations (4.19). Therefore, the dependent unknown variables by which we solve the differential equations (6.10) are the elements 𝑢 and 𝑤 of the displacement vector 𝑢𝑢+𝑤𝑦𝑢=𝑥𝑤+(1𝜇)22+𝑤𝜇𝑦𝑤+𝑥+𝑦+𝑥𝑢𝑦+𝑤+𝑥𝑦,(6.11)𝑐𝑥+𝐵𝑤=𝑥𝑥0𝑝𝑥d𝑥+𝐵𝑤𝑤𝑦×𝑃𝑇𝑥+𝐴𝜇𝑢+𝜇𝑤𝑦𝑢+𝑥+𝑤22+𝑤𝑦+𝐵𝑥𝑤.(6.12) We define the integration constant 𝑐 in (6.12) by taking into account the equilibrium of forces on the edge of the shell.

If a shallow shell is simply supported, the supporting force 𝑡𝜓𝑟 per unit of length at the edge of the shell is directed opposite to and in value equal to the sum of the force 𝐹 and pressure 𝑝 acting on the shell, Figure 7𝑡𝜓𝑟||𝑥=𝑎1=2𝜋𝑎𝐹+2𝜋𝑎0𝑝(𝑥)𝑥𝑑𝑥,(6.13) equation (6.13) is inserted into (6.9) from where the constant 𝑐 is expressed𝑐=𝐹2𝜋.(6.14) If the bimetallic shell serves as a thermal switch shutting down a device in the case of it overheating, then it is necessary to assure that the shell can extend unrestricted in a horizontal direction [10]. In continuation, we will discuss a simply supported shell. At the boundary of the simply supported shell, the force and moment per unit of length are equal to zero𝑛𝜓(𝑎)=𝑛𝜓(𝑎)=𝑚𝜓(𝑎)=𝑚𝜓(𝑎)=0.(6.15) We use (6.1) and(6.3)𝑢𝑃𝑇+𝐴+12𝑤2+𝜇𝑢+𝑤𝑦𝑥+𝑤𝑦|||||𝑥=±𝑎=0,(6.16)𝑄𝑇+𝐵𝜇𝑤𝑥+𝐵𝑤||||𝑥=±𝑎=0.(6.17) The displacement 𝑤 at the apex of the shell is equal to zero in the chosen coordinate system:𝑤(0)=0.(6.18) It is also demonstrated that this system of (6.11), (6.12), (6.16), (6.17), and (6.18) has symmetry. Namely, if the displacement vector 𝑢(𝑥)=𝑢𝑒𝜓+𝑤𝑒𝑟 is the solution to this system, then the solution is also𝑢(𝑥)=𝑢𝑒𝜓+𝑤𝑒𝑟.(6.19) due to which it is sufficient that we solve the system of equations only for positive 𝑥 values in the interval [0𝑥𝑎]. For negative 𝑥, the displacement vector 𝑢 is defined by (6.19). The boundary conditions for the displacement vector 𝑢 also follow from the mentioned symmetry: 𝑢(0)=0,𝑤(0)=0,𝑤(0)=0.(6.20) The remaining conditions on the edges of the shell at 𝑥=𝑎 are defined with unit forces and moments in the equations for boundary conditions (6.16) and (6.17).

Boundary value problem (BVP) for the snap-through of the system of a shallow axisymmetric bimetallic shell is therefore composed of equilibrium equations (6.11) and (6.12), boundary conditions (6.16) and (6.17) at the point 𝑥=𝑎, and boundary conditions (6.20) at the point 𝑥=0𝑢+𝑤𝑦𝑢=𝑥𝑤+(1𝜇)22+𝑤𝜇𝑦𝑤+𝑥+𝑦+𝑥𝑢𝑦+𝑤+𝑥𝑦,𝑐𝑥+𝐵𝑤=𝑥𝑥0𝑝𝑥d𝑥+𝐵𝑤𝑤𝑦×𝑃𝑇𝑥+𝐴𝜇𝑢+𝜇𝑤𝑦𝑢+𝑥+𝑤22+𝑤𝑦+𝐵𝑥𝑤,𝑢𝑃𝑇=𝐴+12𝑤2+𝜇𝑢+𝑤𝑦𝑥+𝑤𝑦|||||𝑥=𝑎,𝑄𝑇=𝐵𝜇𝑤𝑥+𝐵𝑤||||𝑥=𝑎,𝑢(0)=𝑤(0)=𝑤(0)=0.(6.21)

7. Analysis of Stability Conditions in a Spherical-Conic Type Bimetallic Shell

In continuation, we will discuss the snap-through and stability conditions during the loading of a parabolic-conic shell composed of a parabola near the apex and of a cone for the rest, Figures 8 and 9, where the rotational curve is determined by the function 𝑦𝑦(𝑥)=𝑘𝑥2,𝑥𝑏,𝑘(𝑎+𝑏)𝑥𝑎𝑏𝑘,𝑥>𝑏,(7.1) with the following material and geometric properties:1𝑘=1521mm,𝑎=15mm,𝛿=0.3mm,𝜇=3,𝑎1=3.41105K,𝑎2=1.41105K.(7.2)

7.1. Analytic Solution in the Case of Flattened Parabolic Shell

The parameter 𝑏 in the rotational curve function (7.1) defines the point at which the parabola translates into a straight line. If in (7.1) the parameter 𝑏 is equal to the horizontal radius of the shell 𝑎, therefore, 𝑏=𝑎, we obtain a parabolic shell with the rotational curve 𝑦(𝑥)=𝑘𝑥2, Figure 10. Let this parabolic shell be loaded only with the temperature 𝑇. Suppose also that the shell at a certain temperature 𝑇=𝑇𝑚 is completely flattened, Figure 11.The displacement function 𝑤(𝑥) is in that case𝑤(𝑥)=𝑦(𝑥)=𝑘𝑥2.(7.3) We insert (7.3) into the boundary condition (6.17) and express the temperature 𝑇𝑚 at which the shell is flattened𝑇𝑚=4𝑘𝛿3𝛼1𝛼2.(7.4) With the displacement 𝑤 as defined by (7.3), the moment equilibrium equation (6.12) is identically satisfied𝐵𝑤𝑥𝐵𝑤𝑤𝑦𝑃𝑇𝑥+𝐴𝜇𝑢+𝜇𝑤𝑦𝑢+𝑥+𝑤22+𝑤𝑦+𝐵𝑥𝑤0,(7.5) and the equation for the equilibrium of forces becomes2𝑘2𝑥3𝜇𝑢+𝑥𝑢+𝑥2𝑢=10𝑘2𝑥3,(7.6) with the solution with respect to displacement 𝑢𝑢8𝛼(𝑥)=𝑘𝑥1+𝛼2𝛿+3𝑎2𝑘𝛼1𝛼2(𝜇1)3𝑘𝑥2𝛼1𝛼2(5+𝜇)𝛼121𝛼2,(7.7) that at the same time also satisfies the boundary condition (6.16) at the point 𝑥=𝑎 and the boundary condition (6.20) for the displacement 𝑢 at the point 𝑥=0. Therefore, at the temperature 𝑇=𝑇𝑚 the parabolic shell is completely flattened. The reader should also note that such a state of the shell is only stable with shells that are shallow enough!

7.2. Numeric Solution of the BVP

We solved the system of (6.21) using the nonlinear shooting method. First, the BVP (6.21) was converted into the system of ordinary differential equations of the first order 𝑦1=𝑦2𝑦3=𝑦4𝑦4=𝑦5,𝑦2=12𝑥22𝑦12𝑥𝑦2𝑥𝑦242𝑥2𝑦4𝑦5+𝑥𝑦34𝜇+2𝑦3𝑦2𝑥𝑦4𝜇𝑦2𝑥𝑦3𝑦2𝑥2𝑦4𝑦2𝑥2𝑦3𝑦,𝑦5=12𝐵𝑥22𝑐𝑥+2𝐵𝑦42𝑃𝑇𝑥2𝑦4+2𝐴𝑥2𝑦2𝑦4+𝐴𝑥2𝑦342𝐵𝑥𝑦5+2𝐴𝑥𝑦1𝑦4𝜇2𝑥𝑥0𝑥𝑝d𝑥2𝐴𝑥𝑦3𝜇𝑦2+2𝐴𝑥2𝑦3𝑦4𝑦+𝑥𝑦2𝑃𝑇𝑥𝐴2𝑥𝑦2+𝑥𝑦24+2𝑦1𝜇2𝑦3𝑦4𝜇2𝐴𝑥𝑦3𝑦𝑦1(0)=0,𝑦3(0)=0,𝑦4𝑦(0)=0,𝑃𝑇=𝐴2+12𝑦42+𝜇𝑦1+𝑦3𝑦𝑥+𝑦3𝑦|||||𝑥=𝑎,𝑄𝑇=𝐵𝜇𝑦4𝑥+𝐵𝑦5||||𝑥=𝑎,(7.8) when the substitution is introduced𝑢(𝑥)=𝑦1,𝑢(𝑥)=𝑦2,𝑤(𝑥)=𝑦3,𝑤(𝑥)=𝑦4,𝑤(𝑥)=𝑦5.(7.9) We chose the approximate values for 𝑦2(0) and 𝑦5(0) and calculated the approximate values for the displacements 𝑢 and 𝑤 by the classic one-step fourth-order Runge-Kutta method [23]. Defining more exact values for 𝑦2(0) and 𝑦5(0) was carried out by the Newton method [24] for solving nonlinear equations. We wrote the shell deformation with the ratio 𝜉 between the current height of the deformed shell and the initial height 0 of the undeformed shell𝜉=0=𝑦(𝑎)𝑤(𝑎)𝑦(𝑎).(7.10) The program code was written in Mathematica package 7.01.0.

As the components 𝑢 and 𝑤 of the displacement vector 𝑢 at the temperature 𝑇𝑚 for a totally flattened parabolic shell are defined by (7.3) and (7.7), it is possible to calculate how much the numeric results differ from the actual ones. In this manner, we can estimate the accuracy of the chosen numeric method.

7.3. Temperature Loading of a Parabolic Shell

Let us first observe the stability conditions at temperature loading of a parabolic bimetallic shell with 𝑏=𝑎 in (7.1). For this special example of a parabolic-conic shell, we calculated, with the earlier mentioned method, the stability conditions at temperature loading. The obtained results are identical to the results calculated by Wittrick et al. [3] for the parabolic shell.

Figure 12 shows stability conditions for a parabolic shell with the material and geometric properties in (7.2). The graph of the function of dimensionless temperature 𝜏=𝑇/𝑇𝑚 depending on the ratio of heights 𝜉 represents the stability circumstances during the shell’s temperature load.

During the initial state of no temperature load 𝜏=0, at point 𝑂(1,0), the ratio of heights is equal to one. By increasing the dimensionless temperature 𝜏, this ratio decreases. As is clear in Figure 12, the segment on the curve between the point 𝑂 and the point 𝐴(𝜉𝑢,𝜏𝑢)=𝐴(0.44,1.51), where the function 𝜏(𝜉) has a local maximum, is the region of stable equilibrium. The upper snap-through of the shell will, therefore, occur at point 𝐴 at the temperature of 𝜏𝑢=1.51, because the segment between the points 𝐴 and 𝐶(𝜉𝑙,𝜏𝑙)=𝐶(0.44,0.49), where the function has a local minimum, is the region of unstable equilibrium.

After the snap-through, the shell will occupy a new position of stable equilibrium in point 𝐵(0.91,1.51) at the temperature 𝜏=1,51. With further heating of the shell, the ratio 𝜉 continues to decrease.

During the cooling of the shell, we have the opposite phenomenon and at point 𝐶 at the temperature 𝜏𝑙=0.49 another lower snap-through. This time the shell snaps-through into the stable equilibrium position at point 𝐷(0.91,0.49) at the temperature 𝜏=0.49. By reheating the shell to the temperature of the upper snap-through 𝜏𝑢=1.51, we can repeat the complete cycle of the snap-through of the shell. The shape of the shell in the characteristic stages of temperature loading is clear in Figures 13 and 14.

From Figure 12, it follows that in a flattened state at the ratio of heights 𝜉=0, the shell cannot endure as the point (0,1) belongs in unstable region between the points 𝐴 and 𝐶. Equation (7.4) determines the temperature 𝑇𝑚 at which the shell flattens, Figure 11. If at the temperature 𝑇=𝑇𝑚 the flattened shell deflects downwards so that the ratio of heights is 𝜉<0, then the temperature 𝑇𝑚 of the shell is too high for an equilibrium state of the shell at the ratio of heights 𝜉<0. The apex of the shell accelerates downwards so that a new stable equilibrium state is established in the position (0.78,1). It is quite similar if the shell deflects upwards 𝜉>0 except that in this case, the temperature 𝑇=𝑇𝑚 for the ratio of heights 𝜉>0 is too low to satisfy the conditions for equilibrium and consequently the apex of the shell accelerates upwards so that the new stable equilibrium state is established in the position (0.78,1), Figure 12.

7.4. Temperature Loading of a Conic Shell

If in (7.1) 𝑏=0, then the shell translates into a conic shape, Figure 15. We present an example of a temperature loaded conic shell with material and geometric properties in (7.2) and a rotational curve 𝑦(𝑥)1𝑦(𝑥)=𝑘𝑥=15mm𝑥.(7.11) In comparison with the earlier described parabolic shell, the conic shell has a snap-through at a lower temperature. The upper snap-through occurs at temperature 𝜏=1.00 and at the height ratio 𝜉=0.41, Figure 16(b). The shape of the shell after the snap-through is in Figure 16(c). The repeated (lower) snap-through occurs at temperature 𝜏=0.98 and at the height ratio 𝜉=0.09, Figure 16(d). The shell snaps-through into a new stabile equilibrium position and assumes the shape on the diagram, Figure 16(e).

We would expect, like in the case of a flattened parabolic shell, Figure 11, that at a certain temperature the conic shell would also flatten with the function 𝑦(𝑥)=𝑘𝑥. It is verified that it is not possible to identically satisfy (6.12) with the displacement 𝑤(𝑥)=𝑦(𝑥)=𝑘𝑥, thus a flattened state of a conic bimetallic shell is not possible. The shape of the deformed conic shell at the ratio of heights 𝜉=0 is shown in Figure 17.

7.5. Temperature Loading of a Parabolic-Conic Shell

We gradually increased the value of the parameter 𝑏 in the equation system (6.21) and calculated the temperature of both snap-throughs for a parabolic-conic type bimetallic shell. The snap-through temperatures 𝑇𝑢 and 𝑇𝑙 at the parameter 𝑏 values between 0𝑏𝑎 are shown in Table 1.

𝑏 (mm)012.54567.51012.515
𝑇 𝑢 ( C ) 8996109122130137143141137134
𝜉 𝑢 0.410.400.380.380.390.400.430.490.470.49
𝑇 𝑙 ( C ) 87 92 82 31 25 28 39 43 44 44
𝜉 𝑙 −0.09 −0.21 −0.54 −0.59 −0.60 −0.57 −0.49 −0.49 −0.5 0.48

We ascertained that the snap-through temperature is dependent from point 𝑏, where the parabolic rotational curve translates into a conic one, Figure 18.

Figure 18 shows how both snap-through temperatures are relative to parameter b. At the extreme point on the left at 𝑏=0, an example of the conic shell is shown, and on the right at 𝑏=15, an example of parabolic shell is shown.

Both curves for the snap-through temperature have a local extreme. The highest temperature at which the shell snaps-through for the first time (upper snap-through) is 𝑇𝑢=143°C at 𝑏=8.1 mm. The lowest temperature of the return (lower) snap-through is 25°C at 𝑏=5.0 mm. The difference in the temperature of the upper and lower snap-through relevant to the parameter 𝑏 is evident in Figure 19.

7.6. Temperature and Force Loading of a Circular Plane-Parabolic Shell

In practice, a shell composed of a circular plane near the apex and a parabola at the edge is frequent, Figure 20. Such a shell occurs with the curve rotation:1𝑦(𝑥)=0,𝑥𝑏,𝑎2𝑏2𝑥2+𝑏2𝑏2𝑎2,𝑥>𝑏.(7.12) We will again numerically discuss the example of a shell with material and geometric properties in (7.2). The parameter 𝑏 where the shell translates from a plane into a parabola should have a value of 𝑏=7.5 mm. At first, the shell should be loaded only with temperature 𝑇. The upper snap-through of such a shell occurs at the temperature 𝑇=180°C and the height ratio of 𝜉=0.48, Figure 21.

In comparison with a parabolic shell of equal material and geometric properties, Figure 10, this shell has a snap-through at a much higher temperature. A parabolic shell already translates into an unstable equilibrium state at the temperature 𝑇𝑢=𝜏𝑢𝑇𝑚=134°C, when it snaps-through into a new stable equilibrium position. Therefore, with an equal initial height 0, the combined shell has a higher temperature of the upper snap-through by 46°C or by 34%. Consequently, with an appropriate combination of a circular plate and parabola it is possible to construct a shell with a low initial height that, despite this, will still have a snap-through at a high temperature. Therefore, this is an important advantage of combined shells in comparison with parabolic shells.

The effect of the concentrated force 𝐹[𝑁], exerted at the apex of the shell is clear from Figures 22 and 23. Due to the force, the shell already bends, even when not loaded with temperature, into the shape shown in Figure 23. The concavity is most distinct near the apex. The deformation curve is shown in Figure 22 in blue.

If such a shell is to snap-through it should be additionally heated a bit. The instability and snap-through occurs at temperature 𝑇𝑢=65°C. The shape of the shell at the moment of snap-through is shown in Figure 24, its deformation curve is shown in Figure 22 in red.

8. Conclusion

Simply supported, thin-walled, shallow bimetallic shells of mixed (combined) type have the property to snap-through at a certain temperature into a new equilibrium position. The temperature of the snap-through depends on the material and geometric properties of the shell. As a special example, we analysed the conditions for parabolic, conic, parabolic-conic and plate-parabolic type of shell that have both layers equally thick 𝛿1=𝛿2=𝛿/2, and the same Poisson’s ratio 𝜇1=𝜇2=𝜇. Two parabolic shells of different rotational curves 𝑦1=𝑘1𝑥2 and 𝑦2=𝑘2𝑥2 have at the same temperature load 𝑇 equal relative displacements𝑢1𝑎1=𝑢2𝑎2,𝑤1𝑎1=𝑤2𝑎2.(8.1) If 𝑘1𝑎1=𝑘2𝑎2,𝛿1𝑎1=𝛿2𝑎2.(8.2) Conic shells with different functions of rotational curves 𝑦1=𝑘1𝑥 and 𝑦2=𝑘2𝑥 have equal relative displacements (8.1) if the geometry parameters are such that𝑘1=𝑘2,𝛿1𝑎1=𝛿2𝑎2.(8.3) A conic shell in comparison with a parabolic shell with equal material and geometric properties snaps-through at lower temperatures, Table 1. With a suitable initial shape of a parabolic-conic type bimetallic shell, we can change the upper 𝑇𝑢 and lower 𝑇𝑙 temperature values at which snap-through occurs. By reducing the conic part of the shell at the expense of the parabolic, the temperature of the upper snap-through increases. It is possible to achieve the highest snap-through temperature 𝑇𝑢 if the shell translates from a conic shape to a parabolic approximately at the middle of the horizontal radius 𝑎. Therefore, for this type of shell, it is possible to influence the upper and lower temperature snap-through by changing the parameter 𝑏, and consequently with it the temperature at which a device would at first shutdown, then after cooling sufficiently start up again. We have ascertained a similar property of changing the temperature of both snap-throughs in parabolic shells with a circular opening in the apex [9]. It is also possible to influence the snap-through temperature by changing the force at the apex of the shell. At a certain force, the shell can snap-through without heating.


  1. S. P. Timoshenko and J. M. Gere, Theory of Elastic Stability, McGraw–Hill, New York, NY, USA, 1961.
  2. D. V. C. Panov, “Prikladnaja matematika i mehanika,” Journal of Applied Mathematics and Mechanics, vol. 11, pp. 603–610, 1947 (Russian). View at: Google Scholar
  3. W. H. Wittrick, W. H. Wittrick, D. M. Myers, and W. R. Blunden, “Stability of a bimetallic disk,” Quarterly Journal of Mechanics and Applied Mathematics, vol. 6, no. 1, pp. 15–31, 1953. View at: Publisher Site | Google Scholar | Zentralblatt MATH
  4. H. B. Keller and E. L. Reiss, “Spherical cap snapping,” Journal of the Aero/Space Sciences, vol. 26, pp. 643–652, 1959. View at: Google Scholar | Zentralblatt MATH
  5. M. Vasudevan and W. Johnson, “On multi-metal thermostats,” Applied Scientific Research, Section B, vol. 9, no. 6, pp. 420–430, 1963. View at: Publisher Site | Google Scholar
  6. B. D. Aggarwala and E. Saibel, “Thermal stability of bimetallic shallow spherical shells,” International Journal of Non-Linear Mechanics, vol. 5, no. 1, pp. 49–62, 1970. View at: Publisher Site | Google Scholar
  7. L. Ren-Huai, “Non-linear thermal stability of bimetallic shallow shells of revolution,” International Journal of Non-Linear Mechanics, vol. 18, no. 5, pp. 409–429, 1983. View at: Publisher Site | Google Scholar
  8. G. W. Brodland and H. Cohen, “Deflection and snapping of spherical caps,” International Journal of Solids and Structures, vol. 23, no. 10, pp. 1341–1356, 1987. View at: Google Scholar | Zentralblatt MATH
  9. F. Kosel, M. Jakomin, M. Batista, and T. Kosel, “Snap-through of the system of open shallow axi-symmetric bimetallic shell by non-linear theory,” Thin-Walled Structures, vol. 44, no. 2, pp. 170–183, 2006. View at: Publisher Site | Google Scholar
  10. F. Kosel and M. Jakomin, “Snap-through of the axi-symmetric bimetallic shell,” in Proceedings of the 3rd International Conference on Structural Engineering, Mechanics and Computation, Cape Town, South Africa, September 2007. View at: Publisher Site | Google Scholar
  11. M. Batista and F. Kosel, “Thermoelastic stability of bimetallic shallow shells of revolution,” International Journal of Solids and Structures, vol. 44, no. 2, pp. 447–464, 2007. View at: Publisher Site | Google Scholar | Zentralblatt MATH
  12. M. Batista and F. Kosel, “Thermoelastic stability of a double-layered spherical shell,” International Journal of Non-Linear Mechanics, vol. 41, no. 9, pp. 1024–1035, 2006. View at: Publisher Site | Google Scholar | Zentralblatt MATH
  13. M. Jakomin, F. Kosel, and T. Kosel, “Thin double curved shallow bimetallic shell of translation in a homogenous temperature field by non-linear theory,” Thin-Walled Structures, vol. 48, no. 3, pp. 243–259, 2010. View at: Publisher Site | Google Scholar
  14. M. Jakomin, F. Kosel, and T. Kosel, “Buckling of a shallow rectangular bimetallic shell subjected to outer loads and temperature and supported at four opposite points,” Advances in Mechanical Engineering, vol. 2009, Article ID 767648, 17 pages, 2009. View at: Publisher Site | Google Scholar
  15. P. L. Gould, Analysis of Plates and Shells, Prentice Hall, Upper Saddle River, NJ, USA, 1999.
  16. J. N. Reddy, Theory and Analysis of Elastic Plates, Taylor & Francis, London, UK, 1999.
  17. V. Biricikoglu and A. Kalnins, “Large elastic deformations of shells with the inclusion of transverse normal strain,” International Journal of Solids and Structures, vol. 7, no. 5, pp. 431–444, 1971. View at: Publisher Site | Google Scholar | Zentralblatt MATH
  18. E. Carrera, “Historical review of Zig-Zag theories for multilayered plates and shells,” Applied Mechanics Reviews, vol. 56, no. 3, pp. 287–308, 2003. View at: Publisher Site | Google Scholar
  19. U. Icardi and L. Ferrero, “Multilayered shell model with variable representation of displacements across the thickness,” Composites Part B: Engineering, vol. 42, no. 1, pp. 18–26, 2011. View at: Publisher Site | Google Scholar
  20. M. Shariyat, “Thermal buckling analysis of rectangular composite plates with temperature-dependent properties based on a layerwise theory,” Thin-Walled Structures, vol. 45, no. 4, pp. 439–452, 2007. View at: Publisher Site | Google Scholar
  21. V. V. Novozhilov, The Theory of Thin Shells, P. Noordhoff, Groningen, The Netherlands, 1959.
  22. A. E. H. Love, A Treatise on the Mathematical Theory of Elasticity, Dover, New York, NY, USA, 1944.
  23. W. H. Press, S. A. Teukolsky, W. T. Vetterling, and B. P. Flannery, Numerical Recipes, Cambridge University Press, New York, NY, USA, 3rd edition, 2007.
  24. D. J. Hoffman, Numerical Methods for Engineers and Scientists, McGraw-Hill, New York, NY, USA, 2001.

Copyright © 2011 M. Jakomin and F. Kosel. This is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.

Related articles

No related content is available yet for this article.
 PDF Download Citation Citation
 Download other formatsMore
 Order printed copiesOrder

Related articles

No related content is available yet for this article.

Article of the Year Award: Outstanding research contributions of 2021, as selected by our Chief Editors. Read the winning articles.