Study on Dynamic Snap-Through and Nonlinear Vibrations of an Energy Harvester Based on an Asymmetric Bistable Composite Laminated Shell

Abstract

Bistable energy harvesters have been extensively studied. However, theoretical research on the dynamics of bistable energy harvesters based on asymmetric bistable composite laminated plate and shell structures has not been conducted. In this paper, a theoretical model on the dynamics of an energy harvester based on an asymmetric bistable composite laminated shell is established. The dynamic snap-through, the nonlinear vibrations and the voltage output with two potential wells of the bistable energy harvester are studied. The influence of the amplitude and the frequency for the base excitation on the bistable energy harvester is studied. When the frequency for the base excitation with a suitable amplitude in the frequency sweeping is located in a specific range or the amplitude for the base excitation with a suitable frequency in the amplitude sweeping is located in a specific range, the large-amplitude dynamic snap-through, nonlinear vibrations and voltage output with two potential wells can be found to occur. The amplitude and the frequency for the base excitation interact on each other for the specific amplitude or frequency range which migrates due to the softening nonlinearity. The vibration in the process of the dynamic snap-through behaves as the chaotic vibration. The nonlinear vibrations of the bistable system behave as the periodic vibration, the quasi-periodic vibration and the chaotic vibration. This study provides a theoretical reference for the design of energy harvesters based on asymmetric bistable composite laminated plate and shell structures.

1. Introduction

Bistable composite laminated plate and shell structures have two equilibrium configurations, so the large-amplitude dynamic snap-through and nonlinear vibrations may occur in dynamic environments, which greatly promotes the development of energy harvesters. The conventional energy harvesters integrated with bistable composite laminated plate and shell structures are designed as many kinds of bistable energy harvesters. Compared with conventional energy harvesters, bistable energy harvesters produce more strain and thus improve the power generation efficiency due to the large-amplitude dynamic snap-through and nonlinear vibrations with two potential wells. In fact, there have been several types of bistable energy harvesters based on different bistable structures. At present, the bistability of bistable energy harvesters can be realized by many ways. Specific boundary conditions and external forces can make structures buckle and thus obtain bistability [1,2,3]. In the manufacturing process, structures can realize bistability by applying the prestress to the materials [4,5,6,7]. When the plastic deformation or the inelastic deformation is applied to the materials, two or more stable equilibrium configurations can be obtained. The plastic deformation or the inelastic deformation is usually defined as Gaussian curvature effect [8,9,10,11,12,13]. The residual thermal stress formed in the curing process of asymmetric composite laminates can lead to two stable equilibrium configurations [14,15,16,17,18,19,20,21]. The integration of structures and bistable composite laminates can make the structures have two stable equilibrium configurations [22,23,24]. In this paper, an asymmetric bistable composite laminated shell for an energy harvester is adopted. The bistable shell is formed by an asymmetric composite laminated plate containing residual thermal stress which is naturally formed during curing. The greatest advantage of the asymmetric bistable composite laminated shell is that it is naturally formed by an asymmetric composite laminated plate through cooling from high temperature to room temperature without manual operations.

So far, some research on many different kinds of bistable energy harvesters has been carried out. Clamped–clamped buckled beams and cantilever beams for bistable energy harvesters were studied [25,26,27]. The magnetic forces were deployed to generate bistability [28,29]. Arrieta et al. [30] designed a nonlinear broadband energy harvester making use of a bistable plate and its nonlinearity. Lee and Inman [31] designed an asymmetric bistable composite laminated plate and shell structure by using two orthogonal MFCs (macro-fiber composites) for broadband energy harvesting. Syta et al. [32] utilized cross-well dynamics with snap-through of an asymmetric bistable composite laminated plate to enhance power generation capacity. Emam et al. [33] studied the snap-through and the period-doubling bifurcation of a bistable energy harvester based on an antisymmetric bistable composite laminated plate. Emam and Inman [34] summarized the developments and the principles of many different kinds of bistable energy harvesters. Pellegrini et al. [35] utilized the duffing oscillator to describe dynamics of all kinds of bistable energy harvesters. Lu et al. [36] performed research on energy harvesting during the passive vibration isolation. Single-well vibrations and the snap-through of bistable energy harvesters were also exhibited [37].

Above all, although there has been much research on many different kinds of bistable energy harvesters, the research on energy harvesters based on asymmetric bistable composite laminated plate and shell structures were focused on experiments. As the asymmetric bistable composite laminated plate and shell structures are naturally formed by asymmetric composite laminates through cooling from high temperature to room temperature without manual operations, it is very necessary and meaningful to study energy harvesters based on asymmetric bistable composite laminated plate and shell structures theoretically.

In this paper, a dynamic model of an energy harvester based on an asymmetric bistable composite laminated shell is established. The influence of the base excitation amplitude and frequency on the bistable energy harvester is studied. The frequency sweeping with a constant amplitude and the amplitude sweeping with a constant frequency are carried out respectively. The dynamic snap-through, the nonlinear vibrations and the voltage output with two potential wells of the bistable energy harvester are given. When the frequency for the base excitation with a suitable amplitude is located in a specific range in the frequency sweeping or the amplitude for the base excitation with a suitable frequency is located in a specific range in the amplitude sweeping, the large-amplitude dynamic snap-through, nonlinear vibrations and voltage output with two potential wells can be found to occur. That is to say, deploying only one parameter amplitude or frequency for the base excitation cannot maximize the optimization of the bistable energy harvester. When the amplitude and the frequency for the base excitation jointly achieve the maximum optimization, the large-amplitude dynamic snap-through and voltage output can be realized in a very ideal amplitude or frequency range for the base excitation.

2. Dynamic Model

In order to determine the two stable equilibrium configurations formed after curing of the asymmetric composite laminated plate shown in Figure 1, the displacement field can be written based on the classical plate theory in Ref. [38] as follows

$$u\left(x,y,z,t\right)=u_0\left(x,y,t\right)-z\frac{\partial w}{\partial x},$$

(1)

$$v\left(x,y,z,t\right)=v_0\left(x,y,t\right)-z\frac{\partial w}{\partial y},$$

(2)

$$w\left(x,y,t\right)=w_0\left(x,y,t\right).$$

(3)

Figure 1. The asymmetric composite laminated plate [0/0/0/0/90/90/90/90] before curing.

Based on the von Kármán′s large deformation theory in Ref. [38], the nonlinear strain-displacement relationship can be determined:

$$\left\{\begin{array}{c}{\epsilon }_x\\ {\epsilon }_y\\ {\gamma }_{xy}\end{array}\right\}=\left\{\begin{array}{c}{\epsilon }_x^{(0)}\\ {\epsilon }_y^{(0)}\\ {\gamma }_{xy}^{(0)}\end{array}\right\}+z\left\{\begin{array}{c}{\epsilon }_{xx}^{\left(1\right)}\\ {\epsilon }_{yy}^{\left(1\right)}\\ {\gamma }_{xy}^{\left(1\right)}\end{array}\right\},$$

(4)

$$\left\{\begin{array}{c}{\epsilon }_{xx}^{\left(0\right)}\\ {\epsilon }_{yy}^{\left(0\right)}\\ {\gamma }_{xy}^{\left(0\right)}\end{array}\right\}=\left\{\begin{array}{c}\frac{\partial u_0}{\partial x}+\frac{1}{2}{\left(\frac{\partial w_0}{\partial x}\right)}^2\\ \frac{\partial v_0}{\partial y}+\frac{1}{2}{\left(\frac{\partial w_0}{\partial y}\right)}^2\\ \frac{\partial u_0}{\partial y}+\frac{\partial v_0}{\partial x}+\frac{\partial w_0}{\partial x}\frac{\partial w_0}{\partial y}\end{array}\right\}, \left\{\begin{array}{c}{\epsilon }_{xx}^{\left(1\right)}\\ {\epsilon }_{yy}^{\left(1\right)}\\ {\gamma }_{xy}^{\left(1\right)}\end{array}\right\}=\left\{\begin{array}{c}-\frac{{\partial }^2{w}_0}{\partial x^2}\\ -\frac{{\partial }^2{w}_0}{\partial y^2}\\ -2\frac{{\partial }^2{w}_0}{\partial x\partial y}\end{array}\right\}.$$

(5)

The constitutive relation of the asymmetric composite laminated plate is

$$\left\{\begin{array}{c}{\sigma }_x\\ {\sigma }_y\\ {\sigma }_{xy}\end{array}\right\}=\left[\begin{array}{ccc}{\overline{Q}}_{11}& {\overline{Q}}_{12}& {\overline{Q}}_{16}\\ {\overline{Q}}_{12}& {\overline{Q}}_{22}& {\overline{Q}}_{26}\\ {\overline{Q}}_{16}& {\overline{Q}}_{26}& {\overline{Q}}_{66}\end{array}\right]\left\{\left\{\begin{array}{c}{\epsilon }_x\\ {\epsilon }_y\\ {\epsilon }_{xy}\end{array}\right\}-\left\{\begin{array}{c}{\overline{\alpha }}_{xx}\\ {\overline{\alpha }}_{yy}\\ {\overline{\alpha }}_{xy}\end{array}\right\}\Delta T\right\},$$

(6)

where ΔΤ denotes the difference between the room temperature and the manufacturing temperature, and

$$\begin{gathered} {\overline{Q}}_{11}=Q_{11}{\cos }^4\theta +2\left(Q_{12}+2Q_{66}\right){\sin }^2\theta {\cos }^2\theta +Q_{22}{\sin }^4\theta , \\ {\overline{Q}}_{12}=\left(Q_{11}+Q_{22}-4Q_{66}\right){\sin }^2\theta {\cos }^2\theta +Q_{12}\left({\sin }^4\theta +{\cos }^4\theta \right), \\ {\overline{Q}}_{22}=Q_{11}{\sin }^4\theta +2\left(Q_{12}+2Q_{66}\right){\sin }^2\theta {\cos }^2\theta +Q_{22}{\cos }^4\theta , \\ {\overline{Q}}_{16}=\left(Q_{11}-Q_{12}-2Q_{66}\right)\sin \theta {\cos }^3\theta +\left(Q_{12}-Q_{22}+2Q_{66}\right){\sin }^3\theta \cos \theta , \\ {\overline{Q}}_{26}=\left(Q_{11}-Q_{12}-2Q_{66}\right){\sin }^3\theta \cos \theta +\left(Q_{12}-Q_{22}+2Q_{66}\right)\sin \theta {\cos }^3\theta , \\ {\overline{Q}}_{66}=\left(Q_{11}+Q_{22}-2Q_{12}-2Q_{66}\right){\sin }^2\theta {\cos }^2\theta +Q_{66}\left({\sin }^4\theta +{\cos }^4\theta \right), \\ {\overline{\alpha }}_{xx}={\alpha }_{xx}{\cos }^2\theta +{\alpha }_{yy}{\sin }^2\theta , {\overline{\alpha }}_{yy}={\alpha }_{xx}{\sin }^2\theta +{\alpha }_{yy}{\cos }^2\theta , \\ {\overline{\alpha }}_{xy}=\left({\alpha }_{xx}-{\alpha }_{yy}\right)\sin \theta \cos \theta , \end{gathered}$$

(7)

where

$$\begin{gathered} Q_{11}=\frac{E_{11}}{1-v_{12}{v}_{21}}, Q_{22}=\frac{E_{22}}{1-v_{12}{v}_{21}}, Q_{12}=\frac{E_{22}{v}_{12}}{1-v_{12}{v}_{21}}, Q_{16}=Q_{26}=0, \\ {Q}_{45}=0, Q_{44}=Q_{55}=G_{13}, Q_{66}=G_{12} \end{gathered}$$

(8)

Based on Equations (1)–(8), the potential energy of the asymmetric composite laminated plate can be determined

$$U_{\mathrm{Lam}1}=\frac{1}{2}{\displaystyle \underset{V_{\mathrm{Lam}}}{\int }\left({\sigma }_{xx}{\epsilon }_{xx}+{\sigma }_{yy}{\epsilon }_{yy}+{\sigma }_{xy}{\gamma }_{xy}\right)}d{V}_{\mathrm{Lam}},$$

(9)

where the V_Lam denotes the volume of the asymmetric composite laminated plate.

In order to determine the static equilibrium configurations, u₀, v₀ and w₀ in Equations (1)–(5) are replaced by static displacements $u_s^{\mathrm{I}}$, $v_s^{\mathrm{I}}$ and $w_s^{\mathrm{I}}$.

According to Refs. [38,39], the static displacement field can be set as

$$u_s^{\mathrm{I}}={\displaystyle \sum _{m=0}^M{\displaystyle \sum _{n=0}^m{u}_{n,m-n}}}{x}^n{y}^{m-n},$$

(10)

$$v_s^{\mathrm{I}}={\displaystyle \sum _{m=0}^M{\displaystyle \sum _{n=0}^m{v}_{n,m-n}}}{x}^n{y}^{m-n},$$

(11)

$$w_s^{\mathrm{I}}={\displaystyle \sum _{m=0}^M{\displaystyle \sum _{n=0}^m{w}_{n,m-n}}}{x}^n{y}^{m-n}.$$

(12)

The principle of minimum potential energy can be expressed in the following form

$$f_i=\frac{\partial U_{\mathrm{Lam}1}}{\partial X_i}, \left(i=1,2,3\right),$$

(13)

where the U_Lam1 denotes the potential energy of the asymmetric composite laminated plate, and $X_1=u_s^{\mathrm{I}}$, $X_2=v_s^{\mathrm{I}}$ and $X_3=w_s^{\mathrm{I}}$.

Setting the absolute value of the temperature difference |ΔΤ| as the control parameter and solving f₁, f₂ and f₃ by Equations (9)–(13), the static bifurcation diagram Figure 2 can be graphically presented as below.

Figure 2. The static bifurcation diagram for the asymmetric composite laminated plate.

When ΔΤ is set to −90 °C, the asymmetric composite laminated plate generates two stable equilibrium states with large deformation. However, when ΔΤ is too small, the deformation is not obvious, and when ΔΤ is too large, the manufacturing cost is increased.

Making ΔΤ = −90 °C, $u_{s1}^{\mathrm{I}}$, $v_{s1}^{\mathrm{I}}$ and $w_{s1}^{\mathrm{I}}$ corresponding to the lower stable equilibrium configuration and $u_{s2}^{\mathrm{I}}$, $v_{s2}^{\mathrm{I}}$ and $w_{s2}^{\mathrm{I}}$ corresponding to the upper stable equilibrium configuration can be determined shown in Figure 3.

Figure 3. The two stable cylindrical shells after curing, (a) the cylindrical Shell I, (b) the cylindrical Shell II.

Compared to a simple piezoelectric layer, the energy approach based on the MFC is similar. Since the two stable states of the bistable structure behave as cylindrical shells, the simple piezoelectric layer may significantly reduce the curvature and weaken the bistability of the bistable structure, while the MFC can guarantee the bistability of the bistable structure. Moreover, the MFC can be used to actuate the snap-through, which will be introduced in the next stage.

Since the MFC is to be attached to the surface of the shell, the plate model above must be transformed into a shell model.

Due to the stiffness of the MFC itself, new deformations can occur in the process of attaching the MFC to the surface of the bistable shell, which produces new equilibrium positions.

Setting $u_{s1}^{\mathrm{I}}$, $v_{s1}^{\mathrm{I}}$ and $w_{s1}^{\mathrm{I}}$ as initial equilibrium positions and combining with Equations (1)–(3), the displacement field of the bistable shell can be obtained:

$$u\left(x,y,z,t\right)=u_0\left(x,y,t\right)+u_{s1}^{\mathrm{I}}-z\frac{\partial \left(w_0+w_{s1}^{\mathrm{I}}\right)}{\partial x},$$

(14)

$$v\left(x,y,z,t\right)=v_0\left(x,y,t\right)+v_{s1}^{\mathrm{I}}-z\frac{\partial \left(w_0+w_{s1}^{\mathrm{I}}\right)}{\partial y},$$

(15)

$$w\left(x,y,t\right)=w_0\left(x,y,t\right)+w_{s1}^{\mathrm{I}}.$$

(16)

The new nonlinear strain-displacement relationship can be determined

$$\left\{\begin{array}{c}{\epsilon }_x\\ {\epsilon }_y\\ {\gamma }_{xy}\end{array}\right\}=\left\{\begin{array}{c}{\epsilon }_x^{(0)}\\ {\epsilon }_y^{(0)}\\ {\gamma }_{xy}^{(0)}\end{array}\right\}+z\left\{\begin{array}{c}{\epsilon }_{xx}^{\left(1\right)}\\ {\epsilon }_{yy}^{\left(1\right)}\\ {\gamma }_{xy}^{\left(1\right)}\end{array}\right\},$$

(17)

$$\left\{\begin{array}{c}{\epsilon }_{xx}^{\left(0\right)}\\ {\epsilon }_{yy}^{\left(0\right)}\\ {\gamma }_{xy}^{\left(0\right)}\end{array}\right\}=\left\{\begin{array}{c}\frac{\partial \left(u_0+u_{s1}^{\mathrm{I}}\right)}{\partial x}+\frac{1}{2}{\left(\frac{\partial \left(w_0+w_{s1}^{\mathrm{I}}\right)}{\partial x}\right)}^2\\ \frac{\partial \left(v_0+v_{s1}^{\mathrm{I}}\right)}{\partial y}+\frac{1}{2}{\left(\frac{\partial \left(w_0+w_{s1}^{\mathrm{I}}\right)}{\partial y}\right)}^2\\ \frac{\partial \left(u_0+u_{s1}^{\mathrm{I}}\right)}{\partial y}+\frac{\partial \left(v_0+v_{s1}^{\mathrm{I}}\right)}{\partial x}+\left(\frac{\partial \left(w_0+w_{s1}^{\mathrm{I}}\right)}{\partial x}\right)\left(\frac{\partial \left(w_0+w_{s1}^{\mathrm{I}}\right)}{\partial y}\right)\end{array}\right\},$$

(18)

$$\left\{\begin{array}{c}{\epsilon }_{xx}^{\left(1\right)}\\ {\epsilon }_{yy}^{\left(1\right)}\\ {\gamma }_{xy}^{\left(1\right)}\end{array}\right\}=\left\{\begin{array}{c}-\frac{{\partial }^2\left(w_0+w_{s1}^{\mathrm{I}}\right)}{\partial x^2}\\ -\frac{{\partial }^2\left(w_0+w_{s1}^{\mathrm{I}}\right)}{\partial y^2}\\ -2\frac{{\partial }^2\left(w_0+w_{s1}^{\mathrm{I}}\right)}{\partial x\partial y}\end{array}\right\}.$$

(19)

To determine the new equilibrium positions, the potential energy must be recalculated, and the principle of minimum potential energy must be carried out again.

The constitutive relationship for the shell of the MFC–bistable composite laminated shell structure is

$$\left\{\begin{array}{c}{\sigma }_x\\ {\sigma }_y\\ {\sigma }_{xy}\end{array}\right\}=\left[\begin{array}{ccc}{\overline{Q}}_{11}& {\overline{Q}}_{12}& {\overline{Q}}_{16}\\ {\overline{Q}}_{12}& {\overline{Q}}_{22}& {\overline{Q}}_{26}\\ {\overline{Q}}_{16}& {\overline{Q}}_{26}& {\overline{Q}}_{66}\end{array}\right]\left\{\left\{\begin{array}{c}{\epsilon }_x\\ {\epsilon }_y\\ {\epsilon }_{xy}\end{array}\right\}-\left\{\begin{array}{c}{\overline{\alpha }}_{xx}\\ {\overline{\alpha }}_{yy}\\ {\overline{\alpha }}_{xy}\end{array}\right\}\Delta T\right\},$$

(20)

where ΔΤ denotes the difference between the room temperature and the manufacturing temperature, and

$$\begin{gathered} {\overline{Q}}_{11}=Q_{11}{\cos }^4\theta +2\left(Q_{12}+2Q_{66}\right){\sin }^2\theta {\cos }^2\theta +Q_{22}{\sin }^4\theta , \\ {\overline{Q}}_{12}=\left(Q_{11}+Q_{22}-4Q_{66}\right){\sin }^2\theta {\cos }^2\theta +Q_{12}\left({\sin }^4\theta +{\cos }^4\theta \right), \\ {\overline{Q}}_{22}=Q_{11}{\sin }^4\theta +2\left(Q_{12}+2Q_{66}\right){\sin }^2\theta {\cos }^2\theta +Q_{22}{\cos }^4\theta , \\ {\overline{Q}}_{16}=\left(Q_{11}-Q_{12}-2Q_{66}\right)\sin \theta {\cos }^3\theta +\left(Q_{12}-Q_{22}+2Q_{66}\right){\sin }^3\theta \cos \theta , \\ {\overline{Q}}_{26}=\left(Q_{11}-Q_{12}-2Q_{66}\right){\sin }^3\theta \cos \theta +\left(Q_{12}-Q_{22}+2Q_{66}\right)\sin \theta {\cos }^3\theta , \\ {\overline{Q}}_{66}=\left(Q_{11}+Q_{22}-2Q_{12}-2Q_{66}\right){\sin }^2\theta {\cos }^2\theta +Q_{66}\left({\sin }^4\theta +{\cos }^4\theta \right), \\ {\overline{\alpha }}_{xx}={\alpha }_{xx}{\cos }^2\theta +{\alpha }_{yy}{\sin }^2\theta , {\overline{\alpha }}_{yy}={\alpha }_{xx}{\sin }^2\theta +{\alpha }_{yy}{\cos }^2\theta , \\ {\overline{\alpha }}_{xy}=\left({\alpha }_{xx}-{\alpha }_{yy}\right)\sin \theta \cos \theta , \end{gathered}$$

(21)

where

$$\begin{gathered} Q_{11}=\frac{E_{11}}{1-v_{12}{v}_{21}}, Q_{22}=\frac{E_{22}}{1-v_{12}{v}_{21}}, Q_{12}=\frac{E_{22}{v}_{12}}{1-v_{12}{v}_{21}}, Q_{16}=Q_{26}=0, \\ {Q}_{45}=0, Q_{44}=Q_{55}=G_{13}, Q_{66}=G_{12}. \end{gathered}$$

(22)

Equations (6), (7), (20) and (21) are the same in form but different in content. Equations (6) and (7) denote the plate, while Equations (20) and (21) denote the shell.

The constitutive relationship for the MFC of the MFC–bistable composite laminated shell structure is

$$\left\{\begin{array}{c}{\sigma }_{xx}^E\\ {\sigma }_{yy}^E\\ {\sigma }_{xy}^E\\ D_z\end{array}\right\}=\left[\begin{array}{cccc}{c}_{11}^E& c_{12}^E& 0& -e_{31}\\ c_{12}^E& c_{22}^E& 0& -e_{32}\\ 0& 0& c_{66}^E& 0\\ e_{31}& e_{32}& 0& {\epsilon }_{33}^s\end{array}\right]\left\{\begin{array}{c}{\epsilon }_x\\ {\epsilon }_y\\ {\epsilon }_{xy}\\ E_z\end{array}\right\}.$$

(23)

Based on Equations (14)–(22), the potential energy of the bistable shell in the structure is recalculated as

$$U_{\mathrm{Lam}2}=\frac{1}{2}{\displaystyle \underset{V_{\mathrm{Lam}}}{\int }\left({\sigma }_{xx}{\epsilon }_{xx}+{\sigma }_{yy}{\epsilon }_{yy}+{\sigma }_{xy}{\gamma }_{xy}\right)}d{V}_{\mathrm{Lam}}.$$

(24)

Based on Equations (14)–(19) and (23), the potential energy of the MFC in the structure is

$${\left(U_{\mathrm{pie}}\right)}_{\mathrm{m}}=\frac{1}{2}{\displaystyle \underset{V_{\mathrm{pie}}}{\int }\left({\sigma }_{xx}^E{\epsilon }_{xx}^E+{\sigma }_{yy}^E{\epsilon }_{yy}^E+{\sigma }_{xy}^E{\gamma }_{xy}^E\right)}d{V}_{\mathrm{pie}}.$$

(25)

The total potential energy of the MFC–bistable composite laminated shell structure is

$$U_{\mathrm{total}}=U_{\mathrm{Lam}2}+{\left(U_{\mathrm{pie}}\right)}_{\mathrm{m}}.$$

(26)

The principle of minimum potential energy is re-expressed as follows

$$\delta U_{\mathrm{total}}={\displaystyle \sum _{i=1}^3\frac{\partial U_{\mathrm{total}}}{\partial Y_i}}\delta Y_i, \left(i=1,2,3\right).$$

(27)

By solving Equation (27), the deformations $\Delta u_{s1}^{\mathrm{I}}$, $\Delta v_{s1}^{\mathrm{I}}$ and $\Delta w_{s1}^{\mathrm{I}}$ in the process of attaching the MFC to the surface of the bistable shell can be determined.

The new equilibrium positions can be expressed

$$u_s^{\mathrm{II}}=u_{s1}^{\mathrm{I}}+\Delta u_{s1}^{\mathrm{I}},$$

(28)

$$v_s^{\mathrm{II}}=v_{s1}^{\mathrm{I}}+\Delta v_{s1}^{\mathrm{I}},$$

(29)

$$w_s^{\mathrm{II}}=w_{s1}^{\mathrm{I}}+\Delta w_{s1}^{\mathrm{I}}.$$

(30)

Finally, the energy harvester based on the asymmetric bistable composite laminated shell is determined shown in Figure 4.

Figure 4. The two new stable cylindrical shells with a piezoelectric patch on the surface, (a) the cylindrical Shell I, (b) the cylindrical Shell II.

In order to establish the dynamic model shown in Figure 5 for the bistable energy harvester, the displacement field must be written as follows

$$u\left(x,y,z,t\right)=u_0\left(x,y,t\right)+u_s^{\mathrm{II}}-z\frac{\partial \left(w_0+w_s^{\mathrm{II}}\right)}{\partial x},$$

(31)

$$v\left(x,y,z,t\right)=v_0\left(x,y,t\right)+v_s^{\mathrm{II}}-z\frac{\partial \left(w_0+w_s^{\mathrm{II}}\right)}{\partial y},$$

(32)

$$w\left(x,y,t\right)=w_0\left(x,y,t\right)+w_s^{\mathrm{II}}+Y,$$

(33)

where Y is the base excitation.

Figure 5. The dynamic model for the bistable energy harvester based on the asymmetric bistable composite laminated shell.

The nonlinear strain-displacement relationship of the MFC–bistable shell structure is rewritten as

$$\left\{\begin{array}{c}{\epsilon }_x\\ {\epsilon }_y\\ {\gamma }_{xy}\end{array}\right\}=\left\{\begin{array}{c}{\epsilon }_x^{(0)}\\ {\epsilon }_y^{(0)}\\ {\gamma }_{xy}^{(0)}\end{array}\right\}+z\left\{\begin{array}{c}{\epsilon }_{xx}^{\left(1\right)}\\ {\epsilon }_{yy}^{\left(1\right)}\\ {\gamma }_{xy}^{\left(1\right)}\end{array}\right\}$$

(34)

$$\left\{\begin{array}{c}{\epsilon }_{xx}^{\left(0\right)}\\ {\epsilon }_{yy}^{\left(0\right)}\\ {\gamma }_{xy}^{\left(0\right)}\end{array}\right\}=\left\{\begin{array}{c}\frac{\partial \left(u_0+u_s^{\mathrm{II}}\right)}{\partial x}+\frac{1}{2}{\left(\frac{\partial \left(w_0+w_s^{\mathrm{II}}\right)}{\partial x}\right)}^2\\ \frac{\partial \left(v_0+v_s^{\mathrm{II}}\right)}{\partial y}+\frac{1}{2}{\left(\frac{\partial \left(w_0+w_s^{\mathrm{II}}\right)}{\partial y}\right)}^2\\ \frac{\partial \left(u_0+u_s^{\mathrm{II}}\right)}{\partial y}+\frac{\partial \left(v_0+v_s^{\mathrm{II}}\right)}{\partial x}+\left(\frac{\partial \left(w_0+w_s^{\mathrm{II}}\right)}{\partial x}\right)\left(\frac{\partial \left(w_0+w_s^{\mathrm{II}}\right)}{\partial y}\right)\end{array}\right\}$$

(35)

$$\left\{\begin{array}{c}{\epsilon }_{xx}^{\left(1\right)}\\ {\epsilon }_{yy}^{\left(1\right)}\\ {\gamma }_{xy}^{\left(1\right)}\end{array}\right\}=\left\{\begin{array}{c}-\frac{{\partial }^2\left(w_0+w_s^{\mathrm{II}}\right)}{\partial x^2}\\ -\frac{{\partial }^2\left(w_0+w_s^{\mathrm{II}}\right)}{\partial y^2}\\ -2\frac{{\partial }^2\left(w_0+w_s^{\mathrm{II}}\right)}{\partial x\partial y}\end{array}\right\}$$

(36)

Based on Equations (20)–(22) and (28)–(36), the potential energy of the bistable shell in the structure is redefined as

$$U_{\mathrm{Lam}3}=\frac{1}{2}{\displaystyle \underset{V_{\mathrm{Lam}}}{\int }\left({\sigma }_{xx}{\epsilon }_{xx}+{\sigma }_{yy}{\epsilon }_{yy}+{\sigma }_{xy}{\gamma }_{xy}\right)}d{V}_{\mathrm{Lam}}.$$

(37)

Based on Equations (23) and (28)–(36), the potential energy of the MFC in the structure is the sum of its own strain energy and the electric potential energy after energization.

$$U_{\mathrm{pie}}=\frac{1}{2}{\displaystyle \underset{V_{\mathrm{pie}}}{\int }\left({\sigma }_{xx}^E{\epsilon }_{xx}^E+{\sigma }_{yy}^E{\epsilon }_{yy}^E+{\sigma }_{xy}^E{\epsilon }_{xy}^E\right)}d{V}_{\mathrm{pie}}-{\displaystyle \underset{V_{\mathrm{pie}}}{\int }\left(E_z{e}_{31}{\epsilon }_{xx}^E+E_z{e}_{32}{\epsilon }_{yy}^E\right)}d{V}_{\mathrm{pie}}.$$

(38)

The kinetic energy of the bistable shell in the structure is defined as

$$T_{\mathrm{Lam}}=\frac{1}{2}{\rho }_{\mathrm{Lam}}{\displaystyle \underset{V_{\mathrm{Lam}}}{\int }\left({\dot{u}}^2+{\dot{v}}^2+{\dot{w}}^2\right)}d{V}_{\mathrm{Lam}}$$

(39)

The kinetic energy of the MFC in the structure is defined as

$$T_{\mathrm{pie}}=\frac{1}{2}{\rho }_{\mathrm{pie}}{\displaystyle \underset{V_{\mathrm{pie}}}{\int }\left({\dot{u}}^2+{\dot{v}}^2+{\dot{w}}^2\right)}d{V}_{\mathrm{pie}}$$

(40)

The work performed by the electric field in the direction of potential shift is

$$W_{ie}=\frac{1}{2}{\displaystyle \underset{V_{\mathrm{pie}}}{\int }\left(E_z{D}_z\right)}d{V}_{\mathrm{pie}}$$

(41)

The potential shift D_z is homogenized in the thickness direction

$${\tilde{D}}_z=\frac{{\displaystyle {\int }_H^{H+h_p}\left(e_{31}{\epsilon }_x+e_{32}{\epsilon }_y+{\epsilon }_{33}^s{E}_z\right)}}{h_p}$$

(42)

The electric charge quantity is calculated

$$Q\left(t\right)=-{\displaystyle \underset{{\Omega }_{\mathrm{pie}}}{\iint }{\tilde{D}}_z}dxdy$$

(43)

An energy balance is introduced

$${\displaystyle \int V\left(t\right)I\left(t\right)dt}=V\left(t\right)Q\left(t\right),$$

(44)

where V(t) is the voltage and Q(t) is the electric quantity.

The work performed by external forces is

$$W={\displaystyle \underset{V_{\mathrm{total}}}{\int }\left(-c\dot{w}w\right)}d{V}_{\mathrm{total}}-V\left(t\right)Q\left(t\right),$$

(45)

where c is the damping coefficient.

The relationship between the current and the voltage is as follows

$$V\left(t\right)=I\left(t\right)R=-R\dot{Q}\left(t\right),$$

(46)

where R is the external electrical resistance, and I(t) is the current.

The Hamilton’s principle according to Ref. [38] is given as

$$\delta {\displaystyle {\int }_{t_1}^{t_2}L}=0,$$

(47)

where

$$L=T_{\mathrm{Lam}}+T_{\mathrm{pie}}-U_{\mathrm{Lam}3}-U_{\mathrm{pie}}+W_{ie}+W.$$

(48)

In order to study the dynamic snap-through, the nonlinear vibrations and the voltage output with two potential wells of the bistable energy harvester, the dynamic displacements according to Ref. [39] are set as

$$u_0\left(x,y,t\right)={\displaystyle \sum _{m=0}^N{\displaystyle \sum _{n=0}^m{u}_{n,m-n}\left(t\right)}}{x}^n{y}^{n-m},$$

(49)

$$v_0\left(x,y,t\right)={\displaystyle \sum _{m=0}^N{\displaystyle \sum _{n=0}^m{v}_{n,m-n}\left(t\right)}}{x}^n{y}^{n-m},$$

(50)

$$w_0\left(x,y,t\right)={\displaystyle \sum _{m=0}^N{\displaystyle \sum _{n=0}^m{w}_{n,m-n}\left(t\right)}}{x}^n{y}^{n-m}.$$

(51)

Substituting Equations (37)–(46) and (49)–(51) into Equation (47), integrating on plane (x∈[−L_x, L_x] and y∈[−L_y, L_y]), selecting the first three degrees of freedom and introducing dimensionless parameters,

$$\begin{gathered} {\overline{u}}_1=u_1, {\overline{u}}_2=L_y^2{u}_2, {\overline{u}}_3=L_x^2{u}_3, {\overline{v}}_1=v_1, {\overline{v}}_2=L_x^2{v}_2, {\overline{v}}_3=L_y^2{v}_3, \\ {\overline{w}}_1=L_x{w}_1, {\overline{w}}_2=L_y{w}_2 \end{gathered}$$

(52)

dimensionless ordinary differential equations can be obtained

$$\begin{gathered} {\ddot{\overline{w}}}_1+{\overline{c}}_1{\dot{\overline{w}}}_1+{\overline{k}}_1{\overline{w}}_1+{\overline{k}}_2{\overline{w}}_2+{\overline{N}}_1{\overline{w}}_1+{\overline{N}}_2{\overline{w}}_2+{\overline{N}}_3+{\overline{V}}_1{\overline{w}}_1+{\overline{V}}_2{\overline{w}}_2+{\overline{V}}_3+{\overline{a}}_{11}{\overline{w}}_1^2+{\overline{a}}_{12}{\overline{w}}_2^2 \\ +{\overline{a}}_{13}{\overline{w}}_1{\overline{w}}_2+{\overline{a}}_{14}{\overline{w}}_1^3+{\overline{a}}_{15}{\overline{w}}_2^3+{\overline{a}}_{16}{\overline{w}}_1^2{\overline{w}}_2+{\overline{a}}_{17}{\overline{w}}_1{\overline{w}}_2^2=\overline{f}\cos \left(\overline{\Omega }\overline{t}\right), \end{gathered}$$

(53)

$$\begin{gathered} {\ddot{\overline{w}}}_2+{\overline{c}}_2{\dot{\overline{w}}}_2+{\overline{k}}_3{\overline{w}}_1+{\overline{k}}_4{\overline{w}}_2+{\overline{N}}_4{\overline{w}}_1+{\overline{N}}_5{\overline{w}}_2+{\overline{N}}_6+{\overline{V}}_4{\overline{w}}_1+{\overline{V}}_5{\overline{w}}_2+{\overline{V}}_6+{\overline{a}}_{21}{\overline{w}}_1^2+{\overline{a}}_{22}{\overline{w}}_2^2 \\ +{\overline{a}}_{23}{\overline{w}}_1{\overline{w}}_2+{\overline{a}}_{24}{\overline{w}}_1^3+{\overline{a}}_{25}{\overline{w}}_2^3+{\overline{a}}_{26}{\overline{w}}_1^2{\overline{w}}_2+{\overline{a}}_{27}{\overline{w}}_1{\overline{w}}_2^2=\overline{f}\cos \left(\overline{\Omega }\overline{t}\right), \end{gathered}$$

(54)

$$\dot{\overline{V}}+{\overline{a}}_{31}\overline{V}+{\overline{a}}_{32}{\overline{w}}_1{\dot{\overline{w}}}_1+{\overline{a}}_{33}{\overline{w}}_2{\dot{\overline{w}}}_1+{\overline{a}}_{34}{\dot{\overline{w}}}_1+{\overline{a}}_{35}{\overline{w}}_1{\dot{\overline{w}}}_2+{\overline{a}}_{36}{\overline{w}}_2{\dot{\overline{w}}}_2+{\overline{a}}_{37}{\dot{\overline{w}}}_2=0$$

(55)

The coefficients in Equations (53)–(55) can be determined by material properties shown in Table 1 and Table 2 and step-by-step numerical calculations from Equation (1) to Equation (55). Based on Ref. [40], the Table 1 and Table 2 take the following form.

Table 1. Material properties of the bistable asymmetric composite laminated shell.

Properties	Description	Data	Unit
E11	The longitudinal modulus	147	GPa
E22	The transverse modulus	10.7	GPa
G12	The shear modulus	7	GPa
G13	The shear modulus	7	GPa
G23	The shear modulus	7	GPa
ν12	The major Poisson’s ratio	0.3	–
α1	The longitudinal coefficient of thermal expansion	5 × 10−7	[°C]−1
α2	The transversal coefficient of thermal expansion	2.649 × 10−5	[°C]−1
h	The thickness of the fiber	0.122	mm
Lx	The length of the fiber	300	mm
Ly	The width of the fiber	300	mm

Table 2. Material properties of the MFC.

Properties	Description	Data	Unit
E11	The longitudinal modulus	30.336	GPa
E22	The transverse modulus	15.857	GPa
G12	The shear modulus	5.515	GPa
G13	The shear modulus	5.515	GPa
G23	The shear modulus	6.823	GPa
ν12	The major Poisson’s ratio	0.31	–
e31 [10−9 mm/V]	The piezoelectric constant	−210	10−9 mm/V
e32 [10−9 mm/V]	The piezoelectric constant	−210	10−9 mm/V
e33 [10−9 mm/V]	The piezoelectric constant	460	10−9 mm/V
h	The thickness of the MFC	0.3	mm
Lx	The length of the MFC	85	mm
Ly	The width of the MFC	57	mm

The physical parameters in Table 1 are measured directly in the laboratory. The physical parameters in Table 2 are determined according to Ref. [41].

3. Numerical Simulation

In order to study the dynamic snap-through, the nonlinear vibrations and the voltage output with two potential wells of the energy harvester based on the asymmetric bistable composite laminated shell, the Runge–Kutta method is adopted to solve Equations (53)–(55). The bifurcation diagram, the time-history graph, the Poincaré map, the amplitude-frequency curve and the spectrum diagram are demonstrated. Dimensionless symbols are omitted in Equations (53)–(55) for convenience. The influence of the base excitation amplitude f and frequency Ω on the bistable energy harvester is studied.

3.1. Dynamic Snap-Through and Nonlinear Vibrations

The time-history diagrams, the spectrum diagrams and the Poincaré maps are graphically presented in Figure 6, Figure 7, Figure 8, Figure 9, Figure 10 and Figure 11, which represent different vibrations based on different operating conditions. When the insufficient energy is applied, the vibration of the system revolves around either the upper stable state or the lower stable state shown in Figure 6, while when the sufficient energy is applied, the system vibrates between the two stable states, which denotes the dynamic snap-through shown in Figure 7 and Figure 11. The dynamic snap-through is elaborated in Figure 7 and Figure 11 delivering the vibrations around the two stable states respectively and the dynamic snap-through between the two stable states. The vibration in the process of the dynamic snap-through behaves as the chaotic vibration which is the nonlinear vibration with two potential wells due to the two stable equilibrium positions. The nonlinear vibrations of the bistable system in the whole process behave as the periodic vibration, the quasi-periodic vibration and the chaotic vibration based on the Poincaré maps shown in Figure 9, Figure 10 and Figure 11. Similarly, the vibrations of the bistable system can be detected by the spectrum diagrams. The vibration of the system revolves around either the upper stable state or the lower stable state behaves as the periodic vibration or the quasi-periodic vibration according to the spectrum diagrams in Figure 6b,c, where the response of the system is excited only at a certain frequency. Based on the spectrum diagram in Figure 7b, where the responses of the system are excited in a broadband, the vibration in the process of the dynamic snap-through behaves as the chaotic vibration.

Figure 6. The voltage outputs around the two stable states respectively, (a) the time-history graphs around the two stable states respectively, (b) the spectrum diagram for the lower stable state, (c) the spectrum diagram for the upper stable state.

Figure 7. The dynamic snap-through for the voltage output, (a) the time-history graph, (b) the spectrum diagram.

Figure 8. The vibrations of the asymmetric bistable composite laminated shell, (a) the vibrations around the two stable states respectively, (b) the dynamic snap-through between the two stable states.

Figure 9. The periodic vibration, (a) the time-history graph, (b) the Poincaré map.

Figure 10. The quasi-periodic vibration, (a) the time-history graph, (b) the Poincaré map.

Figure 11. The dynamic snap-through and chaotic vibration, (a) the time-history graph, (b) the Poincaré map.

3.2. Frequency Sweeping

The Runge–Kutta method is adopted to solve the dimensionless Equations (53)–(55). Dimensionless symbols are omitted in Equations (53)–(55) for convenience. A series of bifurcation diagrams can be obtained shown in Figure 12, Figure 13 and Figure 14 by sweeping frequency while keeping the amplitude constant. Figure 12 shows the bifurcation diagrams for displacement w and voltage output V by sweeping frequency when f = 0.2. Figure 13 shows the bifurcation diagrams for displacement w and voltage output V by sweeping frequency when f = 0.3. Figure 14 shows the bifurcation diagrams for displacement w and voltage output V by sweeping frequency when f = 0.6.

Figure 12. The bifurcation diagrams for displacement w and voltage V via the base excitation frequency Ω when amplitude f = 0.2, (a) the dynamic displacement, (b) the voltage output of harvester.

Figure 13. The bifurcation diagram for displacement w and voltage V via the base excitation frequency Ω when amplitude f = 0.3, (a) the dynamic displacement, (b) the voltage output of harvester.

Figure 14. The bifurcation diagram for displacement w and voltage V via the base excitation frequency Ω when amplitude f = 0.6, (a) the dynamic displacement, (b) the voltage output of harvester.

The bistable energy harvester has two equilibrium positions shown in Figure 12, Figure 13 and Figure 14 due to the two stable equilibrium states of the asymmetric bistable composite laminated shell. As shown in Figure 12, Figure 13 and Figure 14, when the frequency for the base excitation with an appropriate amplitude is located in a particular range, the bistable system is found to vibrate between the two equilibrium positions, denoting the dynamic snap-through, while when the frequency is outside this particular range, the bistable system is found to vibrate around an equilibrium position.

Deploying an amplitude of 0.3, the frequency range for the base excitation, where the bistable system vibrates violently between the two equilibrium positions, denoting the dynamic snap-through, is 13~15 shown in Figure 13. Nevertheless, when the amplitude varies from 0.3 to 0.6, the frequency range where the dynamic snap-through can be found to occur migrates from 13~15 to 10~12 shown in Figure 14. The major reason why the frequency range migrates with the increase of the amplitude is the softening nonlinearity of the bistable system. The softening characteristics are detected based on the amplitude-frequency curve shown in Figure 15. The bistable system is a softening nonlinear system due to its negative stiffness. When the excitation amplitude increases gradually, the softening nonlinearity of the bistable system is enhanced during frequency sweeping, leading to the migration of the frequency range for the dynamic snap-through.

Figure 15. The amplitude-frequency curve for the voltage output.

The voltage output can also be elucidated in Figure 12, Figure 13 and Figure 14. With an amplitude of 0.2, the small-amplitude voltage revolves round the upper equilibrium position during frequency sweeping shown in Figure 12, which is similar to that of conventional nonlinear energy harvesters with a single potential well. At an amplitude of 0.3, the bistability is exhibited in the process of frequency sweeping. Due to the two equilibrium positions, the voltage output of the bistable energy harvester behaves as the large-amplitude dynamic snap-through and nonlinear vibrations with two potential wells shown in Figure 13 and Figure 14. Comparing Figure 12 and Figure 13, the amplitude of the latter voltage is three times that of the former voltage. Due to the large-amplitude dynamic snap-through and nonlinear vibrations with two potential wells, the bistable energy harvester produces large strains and in turn generates large power.

3.3. Amplitude Sweeping

Analogy to the previous section, the Runge–Kutta method is adopted to solve the dimensionless Equations (53)–(55) and dimensionless symbols are omitted in Equations (53)–(55) for convenience. A series of bifurcation diagrams can be obtained shown in Figure 16, Figure 17, Figure 18, Figure 19 and Figure 20 by sweeping amplitude while keeping the frequency constant. When the amplitude for the base excitation with an appropriate frequency is located in a particular range shown in Figure 17, Figure 18 and Figure 19, the bistable system is found to vibrate between the two equilibrium positions, denoting the dynamic snap-through, while when the amplitude is outside this particular range, the bistable system is found to vibrate around an equilibrium position. During amplitude sweeping with the too small excitation frequency shown in Figure 16 and the too large excitation frequency shown in Figure 20, the bistable system is found to vibrate around an equilibrium position.

Figure 16. The bifurcation diagram for displacement w and voltage V via the base excitation amplitude f when frequency Ω = 8, (a) the dynamic displacement, (b) the voltage output of harvester.

Figure 17. The bifurcation diagram for displacement w and voltage V via the base excitation amplitude f when frequency Ω = 10, (a) the dynamic displacement, (b) the voltage output of harvester.

Figure 18. The bifurcation diagram for displacement w and voltage V via the base excitation amplitude f when frequency Ω = 13, (a) the dynamic displacement, (b) the voltage output of harvester.

Figure 19. The bifurcation diagram for displacement w and voltage V via the base excitation amplitude f when frequency Ω = 15, (a) the dynamic displacement, (b) the voltage output of harvester.

Figure 20. The bifurcation diagram for displacement w and voltage V via the base excitation amplitude f when frequency Ω = 16, (a) the dynamic displacement, (b) the voltage output of harvester.

With a frequency of 8, the bistable system vibrates slightly around the lower equilibrium position during amplitude sweeping, which is similar to that of conventional nonlinear energy harvesters with a single potential well. With a slight increase in the frequency, a very narrow amplitude range for the base excitation, where the large-amplitude dynamic snap-through and nonlinear vibrations with two potential wells can be induced, is identified. As the frequency continues to increase, the amplitude range for the base excitation where the dynamic snap-through can be found to occur widens first, then narrows, and finally disappears.

Deploying a frequency of 10, the amplitude range for the base excitation, where the bistable system vibrates violently between the two equilibrium positions, denoting the dynamic snap-through, is 0.6~0.7 shown in Figure 17. Nevertheless, when the frequency varies from 10 to 13, the amplitude range where the dynamic snap-through can be found to occur migrates from 0.6~0.7 to 0.3~0.6 shown in Figure 18. Continuing to increase the frequency to 15, the amplitude range for the base excitation migrates to 0.25~0.35. The major reason why the amplitude range migrates with the increase of the frequency is the softening nonlinearity of the bistable system. The bistable system is a softening nonlinear system due to its negative stiffness. When the excitation frequency increases gradually, the softening nonlinearity of the bistable system is enhanced during amplitude sweeping, leading to the migration of the amplitude range for the dynamic snap-through.

The voltage output can also be elucidated in Figure 16, Figure 17, Figure 18, Figure 19 and Figure 20. With a frequency of 8, the small-amplitude voltage revolves round the upper equilibrium position during amplitude sweeping shown in Figure 16, which is similar to that of conventional nonlinear energy harvesters with a single potential well. At a frequency of 10, the bistability is exhibited in the process of amplitude sweeping shown in Figure 17. Due to the two equilibrium positions, the voltage output of the bistable energy harvester behaves as the large-amplitude dynamic snap-through and nonlinear vibrations with two potential wells shown in Figure 17, Figure 18 and Figure 19. Comparing Figure 19 and Figure 20, the amplitude of the former voltage is five times that of the latter voltage. Due to the large-amplitude dynamic snap-through and nonlinear vibrations with two potential wells, the bistable energy harvester produces large strains and in turn generates large power.

4. Conclusions

In this paper, the theoretical model on the dynamics of the energy harvester based on the asymmetric bistable composite laminated shell is established. The influence of the amplitude and the frequency for the base excitation on the bistable energy harvester is studied. The frequency sweeping with a constant amplitude and the amplitude sweeping with a constant frequency are carried out respectively.

When the frequency for the base excitation with a suitable amplitude is located in a specific range in the frequency sweeping or the amplitude for the base excitation with a suitable frequency is located in a specific range in the amplitude sweeping, the large-amplitude dynamic snap-through, nonlinear vibrations and voltage output with two potential wells can be found to occur. The amplitude and the frequency for the base excitation interact on each other for the specific frequency or amplitude range, that is to say, for the base excitation with different constant amplitudes in the frequency sweeping, the specific frequency ranges are different while for the base excitation with different constant frequencies in the amplitude sweeping, the specific frequency ranges are different.

The specific frequency or amplitude range for the base excitation, where the large-amplitude dynamic snap-through, nonlinear vibrations and voltage output with two potential wells can be found to occur, migrates due to the softening nonlinearity. The vibration in the process of the dynamic snap-through of the bistable system behaves as the chaotic vibration. The nonlinear vibrations of the bistable system behave as the periodic vibration, the quasi-periodic vibration and the chaotic vibration.