A three-dimensional impact isolation device suitable for microsatellites

Abstract

This utility model relates to the field of vibration isolation technology for satellite optical systems, and discloses a three-dimensional impact isolation device suitable for microsatellites. The device includes an installation structure comprising a fixed base plate and a connecting plate; and a vibration isolation structure, which has multiple sets and includes a lower fixed plate, an upper fixed plate, and vibration isolation layers. This utility model achieves three-dimensional vibration isolation for the supporting structure through multiple sets of vibration isolation layers. When the supporting structure experiences vertical vibration, the elasticity of the multiple sets of vibration isolation layers isolates and buffers the vibration. When the supporting structure experiences horizontal vibration, it can drive the multiple sets of frame layers and vibration isolation layers to translate, thus isolating and buffering the horizontal vibration received by the supporting structure. Furthermore, the material properties of the multiple sets of frame layers and the elasticity of the damping sleeve effectively suppress the swaying of the multiple sets of vibration isolation layers, enabling them to quickly return to their original position.

Description

Technical Field

[0001] This utility model relates to the field of vibration isolation technology for satellite optical systems, and more specifically, to a three-dimensional impact isolation device suitable for microsatellites. Background Technology

[0002] With the rapid development of low-cost aerospace technology, the application of microsatellites (mass ≤500kg, especially CubeSat standard) has surged in remote sensing, communication and scientific research. During the launch phase, microsatellites must withstand the three-dimensional transient impact generated by the pyrotechnic separation device (such as explosive bolts) of the launch vehicle, and their high-frequency characteristics can easily induce resonance in onboard equipment.

[0003] Traditional unidirectional vibration isolators cannot suppress multi-directional coupled vibrations (especially lateral resonance), which will increase the damage rate of precision loads to a certain extent. Therefore, it is extremely important and urgent to design a three-dimensional shock isolation device suitable for microsatellites to effectively absorb or improve the shock environment and ensure the safety and reliability of sensitive components on the satellite. Utility Model Content

[0004] In order to overcome the shortcomings of the existing technology, this utility model provides a three-dimensional impact isolation device suitable for microsatellites, which has the advantage of isolating three-dimensional impacts.

[0005] To achieve the above objectives, this utility model provides the following technical solution: a three-dimensional impact isolation device suitable for microsatellites, comprising: an installation structure, wherein the installation structure includes a fixed base plate and a connecting plate;

[0006] The vibration isolation structure is provided in multiple sets, and the vibration isolation structure includes a lower fixed plate, an upper fixed plate and a vibration isolation layer, wherein the multiple sets of lower fixed plates are all fixedly connected to the upper surface of the connecting plate;

[0007] The supporting structure includes a supporting base plate and an anti-vibration mesh, wherein the upper surface of the supporting base plate is fixedly connected to the upper surface of multiple sets of upper fixing plates.

[0008] As a preferred technical solution of this utility model, mounting plates are welded to the outer surfaces of both ends of the fixed base plate, and mounting holes are opened inside the two sets of mounting plates. The connecting plate is fixedly connected to the upper surface of the fixed base plate.

[0009] As a preferred embodiment of this utility model, a damping sleeve is fixedly connected to the upper surface of the lower fixing plate, and the lower surface of the upper fixing plate is fixedly connected to the upper surface of the damping sleeve. The damping sleeve is made of high-damping nitrile rubber.

[0010] As a preferred technical solution of this utility model, the upper fixing plate is provided with a skeleton layer and a vibration isolation layer inside, and multiple sets of both the skeleton layer and the vibration isolation layer are provided, and the multiple sets of skeleton layers and vibration isolation layers are stacked alternately.

[0011] As a preferred embodiment of this invention, the skeleton layer is made of nickel-titanium shape memory alloy, and the vibration isolation layer is made of high-damping nitrile rubber.

[0012] As a preferred technical solution of this utility model, a connecting seat is fixedly connected to the upper surface of the supporting base plate, and an upper cover plate is fixedly connected to the upper surface of the connecting seat. The upper surface of the upper cover plate is provided with threaded connection holes, and multiple sets of threaded connection holes are provided.

[0013] As a preferred technical solution of this utility model, the vibration-damping mesh is fixedly connected to the inside of the connecting seat, the upper surface of the vibration-damping mesh is attached to the lower surface of the upper cover plate, the vibration-damping mesh is made of titanium alloy, and multiple sets of honeycomb holes are opened inside the vibration-damping mesh.

[0014] Compared with the prior art, the beneficial effects of this utility model are as follows:

[0015] 1. This utility model can provide three-dimensional vibration isolation for the supporting structure through multiple sets of vibration isolation layers. When the supporting structure experiences vertical vibration, the vibration can be isolated and buffered by the elasticity of the multiple sets of vibration isolation layers. When the supporting structure experiences horizontal vibration, it can drive the multiple sets of frame layers and vibration isolation layers to translate. At this time, the horizontal vibration received by the supporting structure can be isolated and buffered. Furthermore, the material properties of the multiple sets of frame layers and the elasticity of the damping sleeve can effectively suppress the swaying of the multiple sets of vibration isolation layers and enable them to quickly return to their original position.

[0016] 2. This utility model uses the honeycomb core inside the vibration-damping mesh to cause microscopic bending deformation when the mesh vibrates. Combined with the internal air viscous friction, mechanical energy can be converted into heat energy, thereby significantly reducing the overall resonance amplitude of the supporting structure. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of the structure of this utility model;

[0018] Figure 2 This is a partial schematic diagram of the structure of this utility model;

[0019] Figure 3 This is an exploded view of the vibration isolation structure of this utility model;

[0020] Figure 4 This is a partial explosion diagram of the vibration isolation structure of this utility model;

[0021] Figure 5This is a cross-sectional schematic diagram of the support structure of this utility model.

[0022] In the diagram: 1. Installation structure; 11. Fixed base plate; 12. Mounting plate; 13. Connecting plate; 2. Vibration isolation structure; 21. Lower fixed plate; 22. Damping sleeve; 23. Upper fixed plate; 24. Frame layer; 25. Vibration isolation layer; 3. Support structure; 31. Support base plate; 32. Connecting seat; 33. Upper cover plate; 34. Threaded connection hole; 35. Vibration-resistant mesh. Detailed Implementation

[0023] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0024] like Figures 1 to 5 As shown, this utility model provides a three-dimensional impact isolation device suitable for microsatellites, including an installation structure 1, which includes a fixed base plate 11 and a connecting plate 13.

[0025] Vibration isolation structure 2, which is provided in multiple sets, includes a lower fixing plate 21, an upper fixing plate 23 and a vibration isolation layer 25. The multiple sets of lower fixing plates 21 are all fixedly connected to the upper surface of the connecting plate 13.

[0026] The support structure 3 includes a support base plate 31 and an anti-vibration net 35. The upper surface of the support base plate 31 is fixedly connected to the upper surface of multiple sets of upper fixing plates 23.

[0027] Mounting plates 12 are welded to the outer surfaces of both ends of the fixed base plate 11, and mounting holes are opened inside the two sets of mounting plates 12. The connecting plate 13 is fixedly connected to the upper surface of the fixed base plate 11.

[0028] By setting up two sets of mounting plates 12, the base plate 11 can be fixed in a suitable installation position using bolts and other tools, and the size of the base plate 11 can be adjusted according to changes in satellite weight and size.

[0029] The upper surface of the lower fixing plate 21 is fixedly connected to the damping sleeve 22, and the lower surface of the upper fixing plate 23 is fixedly connected to the upper surface of the damping sleeve 22. The upper fixing plate 23 is made of high-damping nitrile rubber.

[0030] The vibration isolation structure 2 can be installed between the mounting structure 1 and the support structure 3 by means of bolts or other tools through the lower fixing plate 21 and the upper fixing plate 23. The vibration isolation structure 2 can buffer the support structure 3, thereby effectively reducing the impact of vibration on the support structure 3.

[0031] The upper fixed plate 23 has a frame layer 24 and a vibration isolation layer 25 inside, and there are multiple sets of frame layer 24 and vibration isolation layer 25, and the multiple sets of frame layer 24 and vibration isolation layer 25 are stacked alternately.

[0032] Vibration energy can be absorbed through the viscoelastic deformation of the molecular chains inside the multiple sets of vibration isolation layers 25, which can effectively suppress the micro-vibration interference of precision instruments inside the satellite. The multiple sets of skeleton layers 24 can support the multiple sets of vibration isolation layers 25.

[0033] The skeleton layer 24 is made of nickel-titanium shape memory alloy, and the vibration isolation layer 25 is made of high-damping nitrile rubber.

[0034] Multiple sets of vibration isolation layers 25 can provide elastic deformation capability. When vertical vibration occurs, the support structure 3 can isolate and buffer the vibration through the elasticity of the multiple sets of vibration isolation layers 25. Moreover, its material can meet the high and low temperature cycles that the satellite experiences in space. The setting of multiple sets of skeleton layers 24 can constrain the lateral expansion of the multiple sets of vibration isolation layers 25, enhance the vertical bearing capacity, and ensure the overall stability of the support. In addition, it maintains low stiffness in the horizontal direction to allow deformation.

[0035] The upper surface of the support base plate 31 is fixedly connected to the connecting seat 32, the upper surface of the connecting seat 32 is fixedly connected to the upper cover plate 33, and the upper surface of the upper cover plate 33 is provided with threaded connection holes 34, and multiple sets of threaded connection holes 34 are provided.

[0036] By opening multiple sets of threaded connection holes 34, the components that need vibration isolation can be fixedly connected to the upper surface of the upper cover plate 33, thereby enabling the support structure 3 to support the components that need vibration isolation.

[0037] The vibration-damping mesh 35 is fixedly connected to the inside of the connecting seat 32. The upper surface of the vibration-damping mesh 35 is attached to the lower surface of the upper cover plate 33. The vibration-damping mesh 35 is made of titanium alloy and has multiple sets of honeycomb holes inside.

[0038] The honeycomb core inside the vibration damping mesh 35 causes the mesh to undergo microscopic bending deformation during vibration. Combined with the internal air viscous friction, mechanical energy can be converted into heat energy, thereby significantly reducing the overall resonance amplitude of the support structure 3. Furthermore, the low density of titanium alloy can reduce the overall weight of the device.

[0039] The working principle and usage process of this utility model are as follows: First, the mounting structure 1 is installed in a suitable position using bolts and other tools. Then, the components that need vibration isolation are installed on the upper surface of the cover plate 33 through the threaded connection holes 34 using bolts. When the satellite is subjected to impact and vibrates, the support structure 3 will move vertically or horizontally. When the support structure 3 vibrates vertically, the vibration can be isolated and buffered by the elasticity of the multiple sets of vibration isolation layers 25. When the support structure 3 vibrates horizontally, it can drive the multiple sets of skeleton layers 24 and vibration isolation layers 25 to move horizontally. At this time, the horizontal vibration received by the support structure 3 can be isolated and buffered. Then, the material properties of the multiple sets of skeleton layers 24 and the elasticity of the damping sleeve 22 can effectively suppress the swaying of the multiple sets of vibration isolation layers 25 and make them quickly return to their original position. Furthermore, the vibration-damping net 35 can effectively reduce the overall resonance amplitude of the support structure 3, thereby effectively isolating the components that need vibration isolation.

[0040] It should be noted that, in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such process, method, article, or apparatus.

[0041] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A three-axial shock isolation device suitable for microsatellites, comprising; a mounting structure (1), characterized in that, The mounting structure (1) includes a fixed base plate (11) and a connecting plate (13); Vibration isolation structure (2), the vibration isolation structure (2) is provided in multiple sets, and the vibration isolation structure (2) includes a lower fixing plate (21), an upper fixing plate (23) and a vibration isolation layer (25), and the multiple sets of the lower fixing plates (21) are all fixedly connected to the upper surface of the connecting plate (13); The support structure (3) includes a support base plate (31) and an anti-vibration net (35). The upper surface of the support base plate (31) is fixedly connected to the upper surface of multiple sets of upper fixing plates (23).

2. A three-axis shock isolation device suitable for use with microsatellites according to claim 1, characterized in that: Mounting plates (12) are welded to the outer surfaces of both ends of the fixed base plate (11), and mounting holes are opened inside the two sets of mounting plates (12). The connecting plate (13) is fixedly connected to the upper surface of the fixed base plate (11).

3. The three-axis shock isolation device for small satellites of claim 1, wherein: A damping sleeve (22) is fixedly connected to the upper surface of the lower fixing plate (21), and the lower surface of the upper fixing plate (23) is fixedly connected to the upper surface of the damping sleeve (22). The damping sleeve (22) is made of high-damping nitrile rubber.

4. A three-axis shock isolation device suitable for use with microsatellites according to claim 3, characterized in that: The upper fixing plate (23) is provided with a skeleton layer (24) and a vibration isolation layer (25) inside, and multiple sets of skeleton layers (24) and vibration isolation layers (25) are provided, and multiple sets of skeleton layers (24) and vibration isolation layers (25) are stacked in an alternating manner.

5. A three-axis shock isolation device suitable for use with microsatellites according to claim 4, characterized in that: The skeleton layer (24) is made of nickel-titanium shape memory alloy, and the vibration isolation layer (25) is made of high-damping nitrile rubber.

6. The three-axis shock isolation device for small satellites of claim 1, wherein: The upper surface of the support base plate (31) is fixedly connected to a connecting seat (32), the upper surface of the connecting seat (32) is fixedly connected to an upper cover plate (33), and the upper surface of the upper cover plate (33) is provided with a threaded connection hole (34), and the threaded connection hole (34) is provided in multiple sets.

7. The three-axis shock isolation device for small satellites of claim 1, wherein: The vibration damping mesh (35) is fixedly connected to the inside of the connecting seat (32). The upper surface of the vibration damping mesh (35) is attached to the lower surface of the upper cover plate (33). The vibration damping mesh (35) is made of titanium alloy and has multiple sets of honeycomb holes inside.

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