A quasi-zero stiffness vibration isolator based on bistable composite hybrid laminates
By using a bistable composite hybrid layer structure, the problem of insufficient adaptability of existing quasi-zero stiffness vibration isolators under different working conditions is solved, achieving stable vibration isolation effect over a larger stroke range and enhancing the system's adaptability.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- NINGBO UNIV
- Filing Date
- 2023-09-26
- Publication Date
- 2026-07-24
AI Technical Summary
Existing quasi-zero stiffness vibration isolators have poor adaptability to vibration and overload conditions under different working conditions, and their effective vibration isolation working range is relatively short.
A structure based on a bistable composite hybrid plate is adopted to replace the complex spring mechanism. By combining positive and negative stiffness structures, a stable quasi-zero stiffness system is formed. The symmetry and stable configuration of the bistable composite hybrid plate are utilized to enhance the adaptability of the system.
Maintaining near-zero stiffness over a wider travel range enhances the system's adaptability to vibration and overload conditions under different operating conditions, and improves the effective vibration isolation range of the vibration isolation system.
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Figure CN117515089B_ABST
Abstract
Description
Technical Field
[0001] This invention relates to the field of vibration isolator technology, and more specifically, to a quasi-zero stiffness vibration isolator based on a bistable composite hybrid laminate. Background Technology
[0002] With increasingly stringent requirements for the operational precision and stability of mechanical equipment, the concept of nonlinear vibration isolation has garnered widespread attention. As a typical nonlinear vibration isolation technology, quasi-zero stiffness vibration isolation combines high static stiffness with low dynamic stiffness. To adapt to the vibration isolation needs of different environments, existing technologies include: Chinese Patent No. CN116292738A, which discloses a quasi-zero stiffness vibration isolator suitable for ultra-low power environments in cryogenic environments, where nonlinearity is controlled by magnetic force; Chinese Patent No. CN114321260A, which discloses an electrically active quasi-zero stiffness vibration isolator with a low vibration isolation initiation frequency, adjusting equipment stiffness through electrically active materials to adapt to load changes; and Chinese Patent No. CN114688201A, which discloses a quasi-zero stiffness vibration isolator using a diaphragm disc spring connected in series with an air suspension, where the diaphragm disc spring itself has a nonlinear load characteristic curve, and different heights and thicknesses can be selected... In comparison, the diaphragm disc spring can exhibit negative stiffness characteristics when flattened. Chinese patent number CN216242018U discloses a quasi-zero stiffness vibration isolator with a mechanical frequency-modulated dynamic vibration absorber, which broadens the excitation frequency adaptation range and realizes excitation frequency adaptability. However, the above-mentioned existing vibration isolators are all formed by parallel connection of nonlinear negative stiffness structure and linear positive stiffness spring. The equivalent stiffness of the linear positive stiffness spring matched with the nonlinear negative stiffness structure can only form quasi-zero stiffness characteristics within a very small vibration isolation system stroke range. The effective vibration isolation working section of the vibration isolation system is relatively short, that is, the zero stiffness section is relatively short, and the adaptability to vibration, overload or underload conditions under different working conditions is poor. Summary of the Invention
[0003] The problem solved by this invention is to provide a quasi-zero stiffness vibration isolator based on a bistable composite hybrid plate, which does not require a complex spring mechanism, can increase the effective vibration isolation working section of the vibration isolation system, and enhance the adaptability to vibration, overload or underload conditions under different working conditions.
[0004] To solve the above problems, the present invention provides a quasi-zero stiffness isolator based on bistable composite hybridization, comprising: a base, with a groove formed thereon; a connecting block, disposed within the groove; a positive stiffness structure, which includes a pair of thin shells that are symmetrically arranged left and right and spaced apart; the lower ends of both thin shells are fixedly connected to the bottom of the groove, and the upper ends are fixedly connected to the lower end of the connecting block, such that a first cavity is formed between the two thin shells; the middle parts of the two thin shells protrude away from each other to form a pair of convex parts with a curvature; a negative stiffness structure, which includes a plurality of bistable composite hybrid laminates symmetrically arranged on the left and right sides of the connecting block; the lengths of the laminates on the same side are parallel to each other and spaced apart, and the laminates on the same side are located in the same plane; the plate surfaces of the laminates are all bent; one end of each laminate is fixed to the connecting block, and the other end is fixedly connected to the groove wall, such that a second cavity is formed between the upper and lower adjacent laminates on the same side; a support member for bearing an external force is further fixed to the upper end of the connecting block.
[0005] The beneficial effects of the present invention are as follows. The bistable composite hybrid laminate structure can be used to replace the complex spring structure as the negative stiffness structure to construct a quasi-zero stiffness system. Due to the stable configuration and symmetry of the laminate structure, it is easier to assemble. The two ends can be used as connection points to form a fixed support, making it easier to be connected in series or parallel with other structures to form a more functional deformable structure. Compared with the quasi-zero stiffness vibration isolation system formed by the parallel connection of a non-linear negative stiffness structure and a linear spring, the quasi-zero stiffness system constructed by this laminate structure has the structural advantage of maintaining the quasi-zero stiffness of the system within a larger stroke range. Compared with the linear spring structure, the vibration isolation working section of the vibration isolation system is increased, and the adaptability of the system to vibrations and overload states under different working conditions is enhanced.
[0006] Furthermore, both thin shells are in a "U" - shaped structure, and the plate surfaces of both thin shells are bent.
[0007] The beneficial effect of this setting is that the positive stiffness can be changed by adjusting geometric parameters such as the curvature of the bend to better match the negative stiffness structure.
[0008] Furthermore, the bistable composite hybrid layer includes a first metal composite hybrid layup, a composite material layup, and a second metal composite hybrid layup arranged sequentially from front to back; the first metal composite hybrid layup includes a first 90° composite fiber material layer, a first aluminum layer, and a second 90° composite fiber material layer arranged sequentially from bottom to top; the composite material layup includes a third 90° composite fiber material layer, a 0° composite fiber layer, and a fourth 90° composite fiber layer arranged sequentially from bottom to top; the second metal composite hybrid layup includes a fifth 90° composite fiber material layer, a second aluminum layer, and a sixth 90° composite fiber layer arranged sequentially from bottom to top; the 0° composite fiber material layer, the first aluminum layer, and the second aluminum layer all have the same thickness.
[0009] The beneficial effect of this setup is that the mismatch in the coefficients of thermal expansion between aluminum and composite materials introduces residual thermal stress, which results in the laminate having two stable curved configurations after heat treatment during manufacturing. The curvature directions of these two stable configurations are parallel to each other, thereby improving the load-bearing capacity of the laminate.
[0010] Furthermore, there are four bistable composite hybrid layers: a first layer, a second layer, a third layer, and a fourth layer. The first and second layers are symmetrically arranged vertically and spaced apart. The third and fourth layers are also symmetrically arranged vertically and spaced apart. The first and second layers are both positioned above one of the thin shells, with one end of each layer fixed to a connecting block and the other end fixed to the groove wall. The third and fourth layers are both positioned above another thin shell, with one end of each layer fixed to a connecting block and the other end fixed to the groove wall.
[0011] The beneficial effect of this arrangement is that it allows the stress to be evenly distributed on both sides: the first layer plate, the second layer plate and the thin shell below them, the third layer plate, the fourth layer plate and the thin shell below them, resulting in better load-bearing capacity and vibration isolation effect.
[0012] Furthermore, both the first cavity and the second cavity are filled with high-damping rubber.
[0013] The beneficial effect of this setting is that it effectively improves energy dissipation capacity, thereby improving vibration isolation performance.
[0014] Furthermore, the high-damping rubber is butyl rubber.
[0015] The beneficial effects of this design are that butyl rubber has good airtightness, heat resistance, ozone resistance, aging resistance, chemical resistance, and good shock absorption and electrical insulation properties.
[0016] Furthermore, the positive stiffness structure is made of nylon-carbon fiber.
[0017] The advantages of this design are that it has good rigidity and strength, is lightweight, and is convenient for 3D printing production. Attached Figure Description
[0018] Figure 1 This is a three-dimensional schematic diagram of the present invention;
[0019] Figure 2 This is a three-dimensional view of the layer division of the present invention;
[0020] Figure 3 This is a schematic diagram of the laminated structure of the present invention;
[0021] Figure 4 This is a schematic diagram of an embodiment of the invention in use;
[0022] Figure 5 This is a schematic diagram of the present invention when used in conjunction with external components;
[0023] Figure 6 This is a schematic diagram of the force-displacement curves of the positive and negative stiffness structure in this invention;
[0024] Explanation of reference numerals in the attached figures:
[0025] 1-Base, 2-Connecting block, 3-Thin shell, 4-Layer plate, 4.1-First metal composite hybrid layup, 4.11-First 90° composite fiber material layer, 4.12-First aluminum layer, 4.13-Second 90° composite fiber material layer, 4.2-Composite material layup, 4.21-Third 90° composite fiber material layer, 4.22-0° composite fiber material layer, 4.23-Fourth 90° composite fiber material layer, 4.3-Second metal composite hybrid layup, 4.31-Fifth 90° composite fiber material layer, 4.32-Fifth 90° composite fiber material layer, 4.33-Sixth 90° composite fiber material layer, 5-Supporting member, 11-Groove, 30-First cavity, 31-Protrusion, 40-Second cavity, 41-First layer plate, 42-Second layer plate, 43-Third layer plate, 44-Fourth layer plate. Detailed Implementation
[0026] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, specific embodiments of the present invention will be described in detail below with reference to the accompanying drawings.
[0027] In the description of this invention, it should be noted that the terms "upper," "lower," "left," "right," "front," "rear," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, or the orientation or positional relationship in which the product of this invention is usually placed when in use. They are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limiting this invention.
[0028] It should also be noted that, in actual use, the ends of the base 1 along its length can be connected end-to-end to form a series connection, or the bottom surface of the base 1 can be fixed to the upper surface of the support member 5 and stacked sequentially to form a series connection. Alternatively, both methods can be combined, i.e., series and parallel connections can be used together, ultimately forming the connection shown in the attached figure. Figure 4 The multi-layered structure shown; attached Figure 5 For single-layer applications, those skilled in the art can flexibly adjust the use of the present invention according to the actual situation. All such changes and modifications will fall within the protection scope of the present invention and therefore should not be construed as limitations on the present invention.
[0029] This embodiment provides a quasi-zero stiffness vibration isolator based on a bistable composite hybrid laminate, comprising: a base 1 with a groove 11 formed thereon; a connecting block 2 disposed within the groove 11; a positive stiffness structure, comprising a pair of thin shells 3 symmetrically arranged and spaced apart; the lower ends of both thin shells 3 are fixedly connected to the bottom of the groove 11, and the upper ends of both are fixedly connected to the lower end of the connecting block 2, thereby forming a first cavity 30 between the two thin shells 3; the middle portions of the two thin shells 3 protrude in opposite directions to form a pair of arc-shaped protrusions 31; a negative stiffness structure... The negative stiffness structure includes multiple bistable composite hybrid plates 4 arranged symmetrically on the left and right sides of the connecting block 2; the plates 4 on the same side are parallel to each other in the length direction and are spaced apart, and the plates 4 on the same side are located on the same plane; the surfaces of the plates 4 are all bent; one end of each plate 4 is fixed to the connecting block 2, and the other end is fixed to the groove wall of the groove 11, so that a second cavity 40 is formed between two adjacent plates 4 on the same side; a support member 5 for bearing external force is also fixed at the upper end of the connecting block 2.
[0030] For details, see attached. Figure 1As shown, the base 1 is in the shape of a rectangular plate structure, and a groove 11 extending along the length direction is opened downward at the upper end of the base 1; both thin shells 3 are arranged in the middle position of the bottom of the groove 11, and the upper ends of the two thin shells 3 are fixed to the lower end of the connecting block 2; the plate surfaces of the laminate 4 are both bent and are in an S-shaped structure in the cross-section along the length direction; the two thin shells 3 serve as load-bearing structures. Using this laminate 4 structure can replace a complex spring structure as a negative stiffness structure to construct a quasi-zero stiffness system. Due to the stable configuration and symmetry of this laminate 4 structure, it is easier to assemble. The two ends can be used as connection points to form a fixed support, presenting symmetry about the fixed plane, which makes it easier to be connected in series or in parallel with other structures to form a more functional deformable structure. Moreover, the two S-shaped laminates 4 will deform along the deformation path during the vibration isolation jump process, thereby further improving the bearing capacity. Compared with the quasi-zero stiffness vibration isolation system formed by connecting a non-linear negative stiffness structure and a linear spring in parallel, the quasi-zero stiffness system constructed by this laminate 4 structure has the structural advantage of maintaining the quasi-zero stiffness of the system within a larger stroke range. Compared with the linear spring structure, this extends the vibration isolation working section of the vibration isolation system and enhances the adaptability of the system to vibrations and overload states under different working conditions.
[0031] In a preferred embodiment of the present invention, both thin shells 3 are in a "U" shape structure, and the plate surfaces of the two thin shells 3 are both bent.
[0032] Specifically, as shown in the appendix Figure 1 As shown, the lower ends of the two thin shells 3 can be integrally formed together through a cross beam, and the upper ends of the two thin shells 3 are also integrally formed with the connecting block 2; the two thin shells 3 with this bent structure have stronger elastic ability and can effectively cope with the external force applied on the upper support.
[0033] In a preferred embodiment of the present invention, each bistable composite hybrid laminate 4 includes a first metal composite hybrid ply 4.1, a composite ply 4.2, and a second metal composite hybrid ply 4.3 arranged in sequence from front to back; the first metal composite hybrid ply 4.1 includes a first 90° composite fiber material layer 4.11, a first aluminum layer 4.12, and a second 90° composite fiber material layer 4.13 arranged in sequence from bottom to top; the composite ply 4.2 includes a third 90° composite fiber material layer 4.21, a 0° composite fiber material layer 4.22, and a fourth 90° composite fiber material layer 4.23 arranged in sequence from bottom to top; the second metal composite hybrid ply 4.3 includes a fifth 90° composite fiber material layer 4.31, a second aluminum layer 4.32, and a sixth 90° composite fiber material layer 4.33 arranged in sequence from bottom to top; the 0° composite fiber material layer 4.22, the first aluminum layer 4.12, and the second aluminum layer 4.32 have the same thickness.
[0034] Specifically, as shown in the appendix Figure 2and attached Figure 3 As shown, due to the mismatch in the coefficients of thermal expansion of aluminum and composite materials, residual thermal stress is introduced. This results in the layer 4 having two stable curved configurations after heat treatment during the manufacturing process. The curvature directions of these two stable configurations are parallel to each other, thereby improving the load-bearing capacity of the layer 4.
[0035] In a preferred embodiment of the present invention, there are four bistable composite hybrid plates 4, namely a first plate 41, a second plate 42, a third plate 43, and a fourth plate 44; the first plate 41 and the second plate 42 are arranged symmetrically and spaced apart vertically; the third plate 43 and the fourth plate 44 are arranged symmetrically and spaced apart vertically; the first plate 41 and the second plate 42 are both disposed above one of the thin shells 3, one end of the first plate 41 and the second plate 42 are fixed to the connecting block 2, and the other end is fixed to the groove wall of the groove 11; the third plate 43 and the fourth plate 44 are both disposed above another thin shell 3, one end of the third plate 43 and the fourth plate 44 are both fixed to the connecting block 2, and the other end is fixed to the groove wall of the groove 11.
[0036] For details, see attached. Figure 1 As shown, the length directions of the first layer plate 41, the second layer plate 42, the third layer plate 43, and the fourth layer plate 44 are all parallel to the length direction of the base 1 and located on the same vertical plane. This allows the force to be evenly distributed on both sides, namely the first layer plate 41, the second layer plate 42 and the thin shell 3 below them, the third layer plate 43, the fourth layer plate 44 and the thin shell 3 below them, resulting in better load-bearing capacity and vibration isolation effect.
[0037] In a preferred embodiment of the present invention, both the first cavity 30 and the second cavity 40 are filled with high-damping rubber. This effectively improves energy dissipation capacity, thereby enhancing vibration isolation performance.
[0038] In a preferred embodiment of the present invention, the high-damping rubber is butyl rubber. Butyl rubber has good airtightness, heat resistance, ozone resistance, aging resistance, chemical resistance, and good shock absorption and electrical insulation properties.
[0039] In a preferred embodiment of the invention, the positive stiffness structure is made of nylon-carbon fiber. It has good rigidity and strength, is lightweight, and is convenient for 3D printing production.
[0040] The above-mentioned method for fabricating the bistable composite hybrid laminate 4 includes the following steps:
[0041] Step 1: Prepare two 90° composite fiber material layers with equal length and width, and one 0° composite fiber material layer 4.22. Use two aluminum plates as the first aluminum layer 4.12 and the second aluminum layer 4.32, respectively. The thickness of the 0° composite fiber material layer 4.22 is equal to that of the first aluminum layer 4.12 and the second aluminum layer 4.32.
[0042] Step 2: Stack the first aluminum layer 4.12, the 0° composite fiber material layer 4.22 and the second aluminum layer 4.32 in the transverse direction, and lay two 90° composite fiber material layers on the upper and lower surfaces of the first aluminum layer 4.12, the 0° composite fiber material layer 4.22 and the second aluminum layer 4.32 respectively to obtain a layer plate sample;
[0043] Step 3: Curing the laminate sample at the curing temperature and curing pressure of the composite fiber material.
[0044] Specifically, in step 1, sandpaper is used to polish the surface of each aluminum plate to roughen it, and then ethanol liquid is used to clean the surface of each aluminum plate. The composite fiber material is a carbon fiber resin composite material. Since the first 90° composite fiber material layer 4.11, the third 90° composite fiber material layer 4.21, and the fifth 90° composite fiber material layer 4.31 are all the first layers of the layer 4, they can be completed by a single 90° composite fiber material layer. The second 90° composite fiber material layer 4.13, the fourth 90° composite fiber material layer 4.23, and the sixth 90° composite fiber material layer 4.33 are similar. Due to the difference in the coefficient of thermal expansion between aluminum and the composite material, thermally induced strain, i.e., bending, will occur during the heating process, which will cause these layers to directly produce a bistable effect. The thicknesses of the first aluminum layer 4.12, the second aluminum layer 4.32, and the 0° composite fiber material layer 4.22 are all 0.25 mm, while the thicknesses of the first 90° composite fiber material layer 4.11, the second 90° composite fiber material layer 4.13, the third 90° composite fiber material layer 4.21, the fourth 90° composite fiber material layer 4.23, the fifth 90° composite fiber material layer 4.31, the sixth 90° composite fiber material layer 4.33, and the 0° composite fiber material layer 4.22 are all 0.125 mm. It should also be noted that each layup can be represented as [902 / Al / 902]. T ∪[902 / 02 / 902] T ∪[902 / AI / 902] T Specifically, the first 90° composite fiber material layer 4.11, the second 90° composite fiber material layer 4.13, the third 90° composite fiber material layer 4.21, the fourth 90° composite fiber material layer 4.23, the fifth 90° composite fiber material layer 4.31, the sixth 90° composite fiber material layer 4.33, and the 0° composite fiber material layer 4.22 are each formed by stacking two layers into one layer. The specific number of layers can be flexibly adjusted by those skilled in the art. The carbon fiber resin composite material needs to be cured in a high-pressure reactor at a temperature of 150°C and a pressure of 0.2MPa for 1 hour, and then cooled to room temperature of 30°C to complete the curing.
[0045] The present invention also provides, as attached Figure 4 In the illustrated application embodiment, the two ends of the base 1 of the vibration isolator are connected end to end to form a single-layer planar structure, and then the base 1 of the vibration isolator is stacked vertically. In this embodiment, the vibration isolators located in the middle and bottom can have their support members 5 removed and are fixed together by connecting blocks 2. In this embodiment, the vibration isolators located in the middle and top can have their base 1 removed. Thus, only the support members 5 need to be set on the connecting blocks 2 of the top layer of vibration isolators and the base 1 needs to be set on the bottom layer of vibration isolators, which can simplify the structure to the greatest extent. In the application process, it is necessary to first calculate the force that needs to be borne, and then set the corresponding number of vibration isolators based on the force to be borne. This makes the weight distributed on each unit vibration isolator approximately equal to the external force corresponding to the quasi-zero stiffness in a single quasi-zero stiffness system. Under this premise, the vibration isolator can play the role of vibration isolation. Those skilled in the art can flexibly adjust the use of the vibration isolator according to the actual situation. These changes and modifications will fall within the protection scope of this invention and should not be construed as limitations on this invention.
[0046] The present invention also provides, as attached Figure 5 In the illustrated application embodiment, the two ends of the base 1 of the vibration isolator are connected end to end to form a single-layer planar structure, with the component to be protected placed on top and the vibration source below. In the application process, it is necessary to first calculate the force to be borne, and then set the corresponding number of vibration isolators based on the force to be borne. This makes the weight distributed on each unit vibration isolator approximately equal to the external force corresponding to the quasi-zero stiffness in a single quasi-zero stiffness system. Under this premise, the vibration isolator can play the role of vibration isolation. Those skilled in the art can flexibly adjust the use of the vibration isolator according to the actual situation. These changes and modifications will fall within the protection scope of this invention and should not be construed as limiting this invention.
[0047] As attached Figure 6 As shown, Figure A is the force-displacement curve of the negative stiffness structure, Figure B is the force-displacement curve of the positive stiffness structure, and Figure C is a schematic diagram combining the force-displacement curves of the positive and negative stiffness structures. The initial state of the bistable hybrid symmetric laminate is... Figure 6The point on the left of Figure A in the middle diagram has a force of 0. As the upper displacement increases, the support reaction force also increases, reaching the critical value of the jump, i.e., the highest point on the left. The force-displacement curve in this stage is positive stiffness. The subsequent force-displacement curve begins to show negative stiffness, i.e., the slope of the curve is negative. This region provides negative stiffness in a quasi-zero stiffness vibration isolator based on a bistable composite hybrid plate. During the assembly of the positive stiffness structure, the positive stiffness needs to be designed according to the force-displacement curve of the negative stiffness. That is, the magnitude of the positive stiffness is approximately the same as the absolute value of the negative stiffness. However, to prevent instability due to negative stiffness, the stiffness of the positive stiffness structure should be slightly greater than the negative stiffness during the design to achieve the effect of quasi-zero stiffness vibration isolation. When designing a quasi-zero stiffness vibration isolator based on a bistable composite hybrid plate, the weight of the protected component plus the weight of the support should be considered. That is, the sum of the two should be equal to the force value corresponding to the interval where the slope of the force-displacement curve of the quasi-zero stiffness system is close to 0.
[0048] It can be seen that the stiffness is almost zero within a certain displacement range. The flat area in Figure C shows that the present invention significantly increases the vibration isolation working section of the vibration isolation system, indicating that the present invention can effectively isolate vibration. In addition, the force corresponding to the flat line in Figure C is equal to the load-bearing capacity of the vibration isolator in the present invention.
[0049] While the disclosure is as stated above, its scope of protection is not limited thereto. Those skilled in the art can make various changes and modifications without departing from the spirit and scope of this disclosure, and all such changes and modifications will fall within the protection scope of this invention.
Claims
1. A quasi-zero stiffness vibration isolator based on a bistable composite hybrid laminate, characterized in that, Comprising: A base (1) with a groove (11) formed thereon; A connecting block (2) disposed within the groove (11); A positive stiffness structure, the positive stiffness structure comprising a pair of thin shells (3) that are symmetric about the left and right and spaced apart; The lower ends of both of the thin shells (3) are fixedly connected to the bottom of the groove (11), and the upper ends are fixedly connected to the lower end of the connecting block (2), such that a first cavity (30) is formed between the two thin shells (3); The middle portions of the two thin shells (3) protrude away from each other to form a pair of convex portions (31) with a curvature; A negative stiffness structure, the negative stiffness structure comprising a plurality of laminates (4) disposed symmetrically on the left and right sides of the connecting block (2); The laminates (4) on the same side are parallel to each other in the length direction and spaced apart; The plate surfaces of the laminates (4) are all bent; One end of each of the laminates (4) is fixedly connected to the connecting block (2), and the other end is fixedly connected to the groove wall of the groove (11), such that a second cavity (40) is formed between the upper and lower adjacent laminates (4) on the same side; A support member (5) for bearing an external force is further fixedly connected to the upper end of the connecting block (2); Both of the thin shells (3) have a "U" - shaped structure, and the plate surfaces of the two thin shells (3) are both bent; Each of the laminates (4) comprises a first metal - composite hybrid ply (4.1), a composite ply (4.2), and a second metal - composite hybrid ply (4.3) arranged in sequence along the width direction; The first metal - composite hybrid ply (4.1) comprises a first 90° composite fiber material layer (4.11), a first aluminum layer (4.12), and a second 90° composite fiber material layer (4.13) arranged in sequence from bottom to top; The composite ply (4.2) comprises a third 90° composite fiber material layer (4.21), a 0° composite fiber material layer (4.22), and a fourth 90° composite fiber material layer (4.23) arranged in sequence from bottom to top; The second metal - composite hybrid ply (4.3) comprises a fifth 90° composite fiber material layer (4.31), a second aluminum layer (4.32), and a sixth 90° composite fiber material layer (4.33) arranged in sequence from bottom to top; The 0° composite fiber material layer (4.22), the first aluminum layer (4.12), and the second aluminum layer (4.32) have the same thickness.
2. The quasi-zero stiffness vibration isolator based on a bistable composite hybrid plate according to claim 1, characterized in that, There are four layers (4), namely a first layer (41), a second layer (42), a third layer (43), and a fourth layer (44); the first layer (41) and the second layer (42) are arranged symmetrically and alternately; the third layer (43) and the fourth layer (44) are arranged symmetrically and alternately; the first layer (41) and the second layer (42) are both located above one of the thin shells (3), one end of the first layer (41) and the second layer (42) are fixed to the connecting block (2), and the other end is fixed to the groove wall (11); the third layer (43) and the fourth layer (44) are both located above the other thin shell (3), one end of the third layer (43) and the fourth layer (44) are both fixed to the connecting block (2), and the other end is fixed to the groove wall (11).
3. The quasi-zero stiffness vibration isolator based on a bistable composite hybrid plate according to claim 1, characterized in that, Both the first cavity (30) and the second cavity (40) are filled with high-damping rubber.
4. A quasi-zero stiffness vibration isolator based on a bistable composite hybrid plate according to claim 3, characterized in that, The high-damping rubber is butyl rubber.
5. A quasi-zero stiffness vibration isolator based on a bistable composite hybrid plate according to claim 4, characterized in that, The positive stiffness structure is made of nylon-carbon fiber.