Avionics vibration reduction structure

Abstract

The application provides an avionics vibration reduction structure, and belongs to the technical field of electronic equipment mechanical structures, and specifically comprises a bottom mounting plate, a middle shock absorption layer structure and a top mounting plate, the middle shock absorption layer structure comprises a plurality of parallel arranged layer plates, gaps are arranged between the plurality of layer plates, between the layer plates and the bottom mounting plate and between the layer plates and the top mounting plate, a connecting strip for closing any side edge of each gap is arranged on each gap, the bottom mounting plate comprises a first area covered by the middle shock absorption layer structure and a second area exposed from the coverage range of the middle shock absorption layer structure; the connecting strip is connected to the bottommost layer plate on the side of the first area away from the second area as the basis; on the side of the first area away from the second area, the side edges of all the gap intervals are closed by the connecting strip; on the side of the first area close to the second area, the side edges of all the gap intervals are closed by the connecting strip. The application has effective vibration isolation efficiency under the condition of meeting the strength life requirement.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of electronic equipment mechanical structure, and particularly to an avionics equipment damping structure. BACKGROUND

[0002] The vibration environment of avionics equipment is complex and severe, and the vibration frequency band is relatively wide, generally 10-2000Hz. The inherent frequency of the equipment cannot avoid the vibration frequency band range, so the equipment will certainly resonate. When the vibration energy is large, the avionics equipment is generally installed with a damper to reduce the vibration response. However, the conventional damper has a large size and a service life limit, and cannot meet the long-term life requirement and installation space requirement of the aircraft. SUMMARY

[0003] Therefore, the present application provides an avionics equipment damping structure, which solves the problems in the prior art and has effective damping efficiency under the condition of meeting the strength and life requirements.

[0004] The avionics equipment damping structure provided by the present application adopts the following technical scheme:

[0005] An avionics equipment damping structure includes a bottom mounting plate, a middle damping layer structure and a top mounting plate distributed in sequence, the middle damping layer includes a plurality of parallel arranged layer plates, gaps are arranged between the layer plates, between the layer plates and the bottom mounting plate, and between the layer plates and the top mounting plate, a connecting strip closing any side edge of the gap is arranged on each gap, the bottom mounting plate includes a first area covered by the middle damping layer structure and a second area exposed from the coverage range of the middle damping layer structure;

[0006] Wherein, the connecting strip is connected to the layer plate closest to the bottom mounting plate on the side edge of the first area away from the second area;

[0007] On the side of the first area away from the second area, the side edges of all the gaps are closed by the connecting strips;

[0008] On the side of the first area close to the second area, the side edges of all the gaps are closed by the connecting strips.

[0009] Optionally, the distance from the bottom surface of the bottom mounting plate to the top surface of the top mounting plate is 15-20mm, and the thickness of the bottom mounting plate, the layer plate and the top mounting plate ranges from 2-4mm.

[0010] Optionally, the side length of the layer plate and the top mounting plate is 30-40mm.

[0011] Optionally, the top mounting plate is provided with a mounting hole for connecting the equipment, or;

[0012] The top is mounted on the device integrally.

[0013] Optionally, the second region is connected to the external body by screws or rivets.

[0014] Optionally, the gap spacing is greater than the maximum amplitude of the device divided by the number of gaps.

[0015] Optionally, the gap is filled with damping material, and the damping coefficient of the damping material is greater than 0.1.

[0016] Optionally, the top mounting plate, several layers of plates and the bottom mounting plate are integrally formed by multiple bending of the plate material.

[0017] Optionally, the shock absorbing device is symmetrically mounted on the device at four points, and the direction from the second region to the first region is towards the center of mass of the device.

[0018] Optionally, the first natural frequency of the damping structure is less than half of the natural frequency of the device, and the first natural frequency of the shock absorbing device is:

[0019] Where E is the elastic modulus of the material, I is the sectional moment of inertia of the single layer of plates, m is the mass borne by each damping structure, n is the number of layers of plates, and L is the length of the plates in the direction from the second region to the first region.

[0020] In summary, the present application has the following beneficial technical effects:

[0021] The folding hairpin structure is used in a limited space, which can effectively isolate vibration. The damping structure has low space requirements for installation, has effective vibration isolation efficiency under the condition of meeting the strength and service life requirements, and can meet the long-term use in harsh vibration environments such as aircraft engines.

[0022] Meanwhile, the symmetric center-of-mass mounting method is used to ensure that the natural frequencies of the device in three directions are close and the vibration isolation efficiency is equivalent. BRIEF DESCRIPTION OF DRAWINGS

[0023] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the following will briefly introduce the drawings needed in the embodiments. Obviously, the drawings described below are only some embodiments of the present application, and other drawings can be obtained by those skilled in the art without creative labor.

[0024] Figure 1 The overall structure of the shock absorbing device of the present application is shown in the figure.

[0025] Reference numerals: 1, bottom mounting plate; 11, second area; 12, first area; 2, layer plate; 3, top mounting plate; 4, gap; 5, connecting strip. DETAILED DESCRIPTION

[0026] The embodiments of the present application will be described in detail below with reference to the drawings.

[0027] The above and other aspects of the present application will become more apparent by describing in detail exemplary embodiments thereof with reference to the attached drawings in which:

[0028] It is to be understood that the foregoing description is that of certain examples of the application and that numerous changes in the details of construction and the combination and arrangement of parts can be made by those skilled in the art without departing from the scope of the application.

[0029] It is also to be understood that the following description is only illustrative of the aspects of the application and that changes can be made in the details and arrangement of parts by those skilled in the art without departing from the scope of the application as encompassed by the appended claims.

[0030] Furthermore, in the following description, numerous specific details are set forth in order to provide a thorough understanding of the examples. However, it will be recognized by those skilled in the art that the aspects can be practiced without these specific details.

[0031] Embodiments of the present application provide an avionics device damping structure.

[0032] As Figure 1As shown, an avionics vibration damping structure, characterized in that it comprises a bottom mounting plate 1, a middle damping layer structure and a top mounting plate 3 arranged in sequence, the middle damping layer structure comprises a plurality of parallel arranged layer plates 2, gaps 4 are arranged between the layer plates 2, between the layer plates 2 and the bottom mounting plate 1, and between the layer plates 2 and the top mounting plate 3, a connecting strip 5 is arranged on each of the gaps 4 to close any side of the gap 4, and the bottom mounting plate 1 comprises a first area 12 covered by the middle damping layer structure and a second area 11 exposed from the coverage of the middle damping layer structure.

[0033] Wherein, based on the connecting strip 5 connecting the layer plate 2 closest to the bottom mounting plate 1 on the side of the first area 12 away from the second area 11; on the side of the first area 12 away from the second area 11, the side intervals of all the gaps 4 are closed by the connecting strip 5; on the side of the first area 12 close to the second area 11, the side intervals of all the gaps 4 are closed by the connecting strip 5.

[0034] The distance from the bottom surface of the bottom mounting plate 1 to the top surface of the top mounting plate 3 is 15-20mm, and the thickness of the bottom mounting plate 1, the layer plates 2 and the top mounting plate 3 ranges from 2-4mm.

[0035] The side length of the layer plates 2 and the top mounting plate 3 ranges from 30-40mm.

[0036] The top mounting plate 3 is provided with mounting holes for connecting devices, or the top mounting plate is integrally arranged with the device.

[0037] The second area 11 is connected to the external body by screws or rivets.

[0038] The interval of the gaps 4 is greater than the maximum amplitude of the device divided by the number of gaps 4.

[0039] The gaps 4 are filled with damping materials, and the damping coefficient of the damping materials is greater than 0.1. The damping materials can be rubber.

[0040] The top mounting plate 3, the layer plates 2 and the bottom mounting plate 1 are formed by multiple bending of a plate material. In an embodiment, the layer plates 2, the top mounting plate 3 and the bottom mounting plate 1 can also be formed by cutting gaps in a whole piece of material, and finally forming the damping device of the present application.

[0041] The damping device is symmetrically mounted on the device at four points, and the direction from the second area 11 to the first area 12 is towards the center of mass of the device.

[0042] The first order natural frequency of the vibration damping structure is less than half of the natural frequency of the device, and the first order natural frequency of the damping device is:

[0043] Wherein, E is the modulus of elasticity of the material, I is the section modulus of the single-layered plate 2, m is the mass borne by each damping structure, n is the number of layers of the plate 2, and L is the length of the plate 2 along the direction from the second region 11 to the first region 12.

[0044] The folding hairpin structure is used in the limited space, and the high-damping material (elastic material: rubber) is filled in the folding gap, so that the first-order natural frequency of the damping system is more than half of the natural frequency of the equipment, and the vibration isolation can be effectively achieved. Meanwhile, the symmetric surface is used to face the mass center installation mode, so that the natural frequencies of the equipment in three directions (x, y, z) are close, and the vibration isolation efficiency is equivalent. The damping structure has low demand for the installation space, has effective vibration isolation efficiency under the condition of meeting the strength and service life requirements, and can meet the long-term use in the harsh vibration environment of the aircraft engine.

[0045] The above merely provides a specific implementation of the present application, but the protection scope of the present application is not limited to this. Any person skilled in the art can easily think of changes or replacements within the technical scope disclosed in the present application, and all the changes or replacements should be covered in the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the protection scope of the claims.

Claims

1. A vibration reduction structure for avionics equipment, characterized in that, It includes a bottom mounting plate, a middle damping layer structure and a top mounting plate arranged in sequence. The middle damping layer includes several parallel layers. Gaps are provided between the layers, between the layers and the bottom mounting plate and between the layers and the top mounting plate. Each gap is provided with a connecting strip that closes any side of the gap. The bottom mounting plate includes a first area covered by the middle damping layer structure and a second area exposed within the coverage area of ​​the middle damping layer structure. The connection between the first region and the shelf closest to the bottom mounting plate is made by means of the connecting strip. On the side of the first region away from the second region, the sides of all the gaps are closed by the connecting strip at intervals; On the side of the first region closest to the second region, the sides of all the gaps are closed by the connecting strip at intervals; The vibration damping structure is symmetrically installed on the equipment at four points, with the direction from the second region to the first region facing the center of mass of the equipment; The first natural frequency of the vibration damping structure is lower than half the natural frequency of the equipment. The first natural frequency of the vibration damping structure is: Where E is the elastic modulus of the material, I is the moment of inertia of a single layer of the plate section, m is the mass borne by each vibration damping structure, n is the number of layers, and L is the length of the plate along the direction from the second region to the first region.

2. The vibration reduction structure for avionics equipment according to claim 1, characterized in that, The distance from the bottom surface of the bottom mounting plate to the top surface of the top mounting plate is 15-20mm, and the thickness of the bottom mounting plate, the shelf, and the top mounting plate ranges from 2-4mm.

3. The vibration reduction structure for avionics equipment according to claim 1, characterized in that, The side lengths of the shelf and the top mounting plate are 30-40 mm.

4. The vibration reduction structure for avionics equipment according to claim 1, characterized in that, The top mounting plate is provided with mounting holes for connecting equipment, or; The top is integrated into the device.

5. The vibration reduction structure for avionics equipment according to claim 1, characterized in that, The second area is connected to the external body by screws or rivets.

6. The vibration reduction structure for avionics equipment according to claim 1, characterized in that, The spacing of the gaps is greater than the maximum amplitude of the device divided by the number of gaps.

7. The vibration reduction structure for avionics equipment according to claim 1, characterized in that, The gap is filled with damping material, and the damping coefficient of the damping material is greater than 0.

1.

8. The vibration reduction structure for avionics equipment according to claim 1, characterized in that, The top mounting plate, several layers of plates, and the bottom mounting plate are formed by bending the sheet material into one piece multiple times.

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