Mathematical Problems in Engineering

Volume 2011 (2011), Article ID 145638, 30 pages

http://dx.doi.org/10.1155/2011/145638

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

^{1}Faculty of Maritime Studies and Transport, University of Ljubljana, Pot Pomorščakov 4, 6320 Portorož, Slovenia^{2}Faculty of Mechanical Engineering, University of Ljubljana, Aškerčeva 6, 1000 Ljubljana, Slovenia

Received 13 July 2010; Revised 16 February 2011; Accepted 30 May 2011

Academic Editor: Mohammad Younis

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.

#### Abstract

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 . 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 [9–12] 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 , about the axis [15], Figure 2. The middle surface of the undeformed axisymmetric shell in the Lagrange Coordinate System is, therefore, defined by the function . 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 : Differential of the length in the circular direction is Meridian angle The flexion curvature of the rotational curve in the meridian direction is, Figures 2 and 3 The flexion curvature of the circle formed by rotation of the curve , in the circular direction is, Figures 2 and 3, The simplifications in (2.3), (2.4), and (2.5) are justified since we are discussing a shallow shell, where, and consequently,

#### 3. Displacement Vector and Geometry of Deformed Shell

Due to the temperature change, the shell deforms into a new shape defined by the function 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 [18–20]. 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 in the circular direction as well as other shell properties relative to the angle do not change:

The displacement vector of any point on the middle surface of an undeformed shell defines the point on the middle surface of a deformed shell and with the supposition (3.1), Unit basis vectors and in the Cartesian coordinate system follow directly from the system geometry, Figure 2, These vectors are mutually orthogonal because Derivatives of these vectors with respect to the curvilinear coordinates , and are [21] and when simplified due to the supposition(2.7) 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 at its apex.

The point at the position on the undeformed shell moves into the position on the deformed shell with the coordinates . The reader should note that both the Euler and Lagrange coordinate system have the same origin at point . So, when a force or temperature load is exerted on the shell the optional point moves, as we have shown in Figure 3, since the reaction force per unit of length acts in the opposite direction. The connection between the Euler and Lagrange Coordinate System is, Figure 3, where from which we obtain In (3.10), we also consider that the displacement is small in comparison with the displacement , which in turn is small in comparison with the Lagrange coordinates so that the Euler coordinates is approximately From Figure 3, we can also find geometric properties of the deformed shell.

The differential of the length in the meridian direction Meridian angle is Flexion curvature in the meridian direction is Flexion curvature in the circular direction With (3.11) and (3.12) for Euler’s coordinates and , we finally obtain

#### 4. Strain and Stress Tensor

A shell’s deformation state is shown by the displacement vector in the middle, that is, reference surface. This vector has two components: the displacement in the meridian direction and the displacement in the radial direction. The elements of the strain tensor in the curvilinear orthogonal coordinate system are determined by the Green-Lagrange strain tensor for the middle surface of the shell [16] where the displacement vector is of the form (3.3). The vector operator is by definition The gradient of the displacement vector , 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) is All nine tensor elements are obtained once (4.3) is inserted into (4.1): or in explicit form 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 of the shell element with the length in the direction of the unit vector , Figure 4, we can express the differential of the displacement vector with where is angle that the vector forms with the basis unit vector , Figure 4.

In the case of small strains , we have where as the rotation of the shell element is expressed in radians. It is also further evident by comparing the coefficients in (4.6) that If the shell element with the length in the direction of the unit vector completes the rotation for the angle around the vector , it follows that: A similar calculation can be performed for the rotation of the shell element with the length in the direction of the unit vector .

In case of small strains and moderate shell rotations approximately up to , the components of the displacement gradient are due to which we ignore all nonlinear terms in Green-Lagrange strain tensor (4.4) except the term .

Thus, the displacement of the point due to load is the largest in the direction of the unit vector , while the displacement in the direction of the unit vectors is by absolute value smaller Further, we consider that the flexion curvature of the shallow shell in the meridian direction is very small due to which it is true that So, the tensor elements (4.4) and (4.5) are finally or With the introduction of the local coordinate with the centre of origin on the middle surface of the shell, Figure 4, the elements of the strain tensor are, due to the shell’s curvature, also the function of the coordinate . The relation between the displacement on the local coordinate and displacement on the middle surface of the bimetallic shell, Figure 4, can be found from the strain tensor element , 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 is zero The solution to this equation with respect to the element of the displacement vector is: The normal strain in the transversal direction is equal to zero according to the second assumption of Kirchhoff’s hypothesis: Now, two nonzero elements of the Green-Lagrange strain tensor (4.15) for the middle surface of the shell can be recorded by means of relation (4.13) as Note again that when we form the strain tensor , we retain the nonlinear term for strain in 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 and at distance from the middle surface of the bimetallic shell in the direction of the unit vector with (4.15), where we replace the displacement with the displacement .

Since we are working on a thin shell, where , we obtain

The relation between the strain and stress tensor is determined by Hooke’s law [22] The symbol denotes the Young’s modulus, the symbol denotes the Poisson’s ratio and is the thermal expansion coefficient. The symbol denotes the shell’s relative temperature relevant to the reference for which the stress state in the shell is equal to zero:

#### 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 , and and the bending moments , which act upon the planes are With and 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 form The reader should note that the transversal shear force in (5.1) cannot be expressed by a definite integral since the transversal shear strain is disregarded according to the Kirchhoff hypothesis. However, this assumption does not exclude the full consideration of the shear force , 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 can be replaced by its argument , while the cosine of the same angle is very close to one Equilibrium of the forces in the meridian direction is Equilibrium of the forces in the radial direction The equilibrium equation of forces in the circular direction cannot be considered due to the axisymmetric deformation. We write the moment equilibrium as where

After arranging and using (3.17), the equilibrium equations are

#### 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 , , , , , , , , , , , and and can be reduced further in a following way: first, we insert (4.20) into (5.2). After integration, we have where , and are constants as follows [13, 14]: We now multiply (5.8) with and add (5.9). So, we obtain We disregard the last nonlinear term of magnitude order, since

In this way, we obtain the relation and after integration where is a constant that depends exclusively on the external force acting on the shell.

The relation (6.9) is inserted into (5.9) and (5.10). We now express the unit forces , and moments , in the equations above with (6.1), (6.2), (6.3), and (6.4), and the strains , wit

h the kinematic equations (4.19). Therefore, the dependent unknown variables by which we solve the differential equations (6.10) are the elements and of the displacement vector We define the integration constant 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 per unit of length at the edge of the shell is directed opposite to and in value equal to the sum of the force and pressure acting on the shell, Figure 7 equation (6.13) is inserted into (6.9) from where the constant is expressed 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 zero We use (6.1) and(6.3) The displacement at the apex of the shell is equal to zero in the chosen coordinate system: 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 is the solution to this system, then the solution is also due to which it is sufficient that we solve the system of equations only for positive values in the interval . For negative , the displacement vector is defined by (6.19). The boundary conditions for the displacement vector also follow from the mentioned symmetry: The remaining conditions on the edges of the shell at 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 , and boundary conditions (6.20) at the point

#### 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 with the following material and geometric properties:

##### 7.1. Analytic Solution in the Case of Flattened Parabolic Shell

The parameter 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 is equal to the horizontal radius of the shell , therefore, , we obtain a parabolic shell with the rotational curve , Figure 10. Let this parabolic shell be loaded only with the temperature . Suppose also that the shell at a certain temperature is completely flattened, Figure 11.The displacement function is in that case We insert (7.3) into the boundary condition (6.17) and express the temperature at which the shell is flattened With the displacement as defined by (7.3), the moment equilibrium equation (6.12) is identically satisfied and the equation for the equilibrium of forces becomes with the solution with respect to displacement that at the same time also satisfies the boundary condition (6.16) at the point and the boundary condition (6.20) for the displacement at the point . Therefore, at the temperature 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 when the substitution is introduced We chose the approximate values for and and calculated the approximate values for the displacements and by the classic one-step fourth-order Runge-Kutta method [23]. Defining more exact values for and was carried out by the Newton method [24] for solving nonlinear equations. We wrote the shell deformation with the ratio between the current height of the deformed shell and the initial height of the undeformed shell The program code was written in Mathematica package 7.01.0.

As the components and of the displacement vector at the temperature 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 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 depending on the ratio of heights represents the stability circumstances during the shell’s temperature load.

During the initial state of no temperature load , at point , the ratio of heights is equal to one. By increasing the dimensionless temperature , this ratio decreases. As is clear in Figure 12, the segment on the curve between the point and the point , where the function has a local maximum, is the region of stable equilibrium. The upper snap-through of the shell will, therefore, occur at point at the temperature of , because the segment between the points and , 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 at the temperature . With further heating of the shell, the ratio continues to decrease.

During the cooling of the shell, we have the opposite phenomenon and at point at the temperature another lower snap-through. This time the shell snaps-through into the stable equilibrium position at point at the temperature . By reheating the shell to the temperature of the upper snap-through , 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 , the shell cannot endure as the point belongs in unstable region between the points and . Equation (7.4) determines the temperature at which the shell flattens, Figure 11. If at the temperature the flattened shell deflects downwards so that the ratio of heights is , then the temperature of the shell is too high for an equilibrium state of the shell at the ratio of heights . The apex of the shell accelerates downwards so that a new stable equilibrium state is established in the position . It is quite similar if the shell deflects upwards except that in this case, the temperature for the ratio of heights 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 , Figure 12.

##### 7.4. Temperature Loading of a Conic Shell

If in (7.1) , 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 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 and at the height ratio , 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 and at the height ratio , 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 . It is verified that it is not possible to identically satisfy (6.12) with the displacement , thus a flattened state of a conic bimetallic shell is not possible. The shape of the deformed conic shell at the ratio of heights is shown in Figure 17.

##### 7.5. Temperature Loading of a Parabolic-Conic Shell

We gradually increased the value of the parameter 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 and at the parameter values between are shown in Table 1.

We ascertained that the snap-through temperature is dependent from point , 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 , an example of the conic shell is shown, and on the right at , 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 °C at mm. The lowest temperature of the return (lower) snap-through is 25°C at mm. The difference in the temperature of the upper and lower snap-through relevant to the parameter 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: We will again numerically discuss the example of a shell with material and geometric properties in (7.2). The parameter where the shell translates from a plane into a parabola should have a value of mm. At first, the shell should be loaded only with temperature . The upper snap-through of such a shell occurs at the temperature °C and the height ratio of , 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 °C, when it snaps-through into a new stable equilibrium position. Therefore, with an equal initial height , 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 , 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 °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 , and the same Poisson’s ratio . Two parabolic shells of different rotational curves and have at the same temperature load equal relative displacements If Conic shells with different functions of rotational curves and have equal relative displacements (8.1) if the geometry parameters are such that 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 and lower 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 if the shell translates from a conic shape to a parabolic approximately at the middle of the horizontal radius . Therefore, for this type of shell, it is possible to influence the upper and lower temperature snap-through by changing the parameter , 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.

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