A universal vibration reduction device for satellite platform and its design method

Abstract

The present invention discloses a universal vibration reduction device for a satellite platform, wherein an upper connecting ring is connected to a satellite body, a lower connecting ring is connected to a carrier adapter, and a metal rubber unit is installed between the upper and lower connecting rings; in the metal rubber unit, a support seat includes a shaft and a support platform, a metal rubber mesh block is sleeved on the outside of the shaft and separated by the support platform; an outer cover is arranged on the outside of the metal rubber mesh block, and the lower end of the outer cover is fixedly connected to the lower connecting ring. The present invention discloses a design method for a vibration reduction device, wherein a finite element model is constructed based on the preliminarily determined bearing area of ​​a single metal rubber unit, the number of metal rubber units, and the elastic modulus of the metal rubber mesh block, and the optimal design value is obtained by simulation verification. The present invention realizes effective vibration isolation and buffering, and can meet the satellite's requirements for stability and reliability without affecting the satellite configuration layout and the assembly process, and can adapt to the special environmental requirements of aerospace applications.

Description

Technical Field

[0001] The invention belongs to the field of satellite launch technology dynamic environment suppression, and in particular relates to a universal vibration reduction device for a satellite platform and a design method thereof. Background Art

[0002] The vibration and impact problems during satellite launch have always been one of the focuses of the aerospace engineering community in various countries. At present, a series of research and engineering applications have been carried out in China for the vibration reduction and isolation technology of the whole satellite. Some vibration isolation devices have been used in the improvement of satellite rocket adapters, and have achieved good application results. However, for some small satellites, especially 500kg-1500kg satellites, rigid docking rings are still used to connect the satellite and the adapter. With the development of my country's aerospace industry and the increase in the number of small satellite launches, the research and development of vibration reduction devices for small satellite platforms is imperative.

[0003] Implementing vibration reduction on satellites can significantly reduce the damage that satellites may suffer during the launch process. It can also provide a good mechanical environment for equipment on satellites and improve the protection capabilities of precision instruments. It is of great significance to enhancing my country's satellite capabilities.

[0004] At present, the satellite docking ring is connected to the carrier through a rigid strap. As we all know, when launching a satellite, it is necessary to eliminate most of the vibration and impact of key equipment, so as to improve the stability and reliability of the satellite during launch, so that its comprehensive capabilities can meet the requirements of various environments. In the existing technology, the docking ring of small satellites in the actual launch process is a rigid connection, with high rigidity, weak damping, and poor vibration isolation and vibration reduction efficiency, which affects the life of key equipment in the satellite body.

[0005] During the launch process of the satellite, the mechanical environment is relatively harsh. In order to reduce the impact of the mechanical environment, it is necessary to improve and optimize the vibration reduction capability of the entire satellite. Summary of the invention

[0006] The purpose of the present invention is to overcome the above-mentioned defects and provide a universal vibration reduction device for a satellite platform, comprising an upper connecting ring, a lower connecting ring and a plurality of metal rubber units;

[0007] The upper connecting ring is fixedly connected to the satellite body, the lower connecting ring is rigidly connected to the carrier adapter, and the metal rubber unit is installed between the upper connecting ring and the lower connecting ring and the number of the metal rubber units is greater than 1;

[0008] The metal rubber unit comprises an outer cover, a support seat and two metal rubber mesh blocks, which are respectively recorded as a first metal rubber mesh block and a second metal rubber mesh block; the metal rubber mesh block is a mesh structure formed by spiral metal wires; the support seat comprises a shaft and a support platform, the upper end of the shaft is fixedly connected to an upper connecting ring, the support platform is connected to the shaft and is perpendicular to the axial direction of the shaft, the first metal rubber mesh block and the second metal rubber mesh block are sleeved on the outside of the shaft, and the first metal rubber mesh block and the second metal rubber mesh block are separated by the support platform; the outer cover is arranged on the outside of the metal rubber mesh block, and the lower end of the outer cover is fixedly connected to the lower connecting ring.

[0009] The present invention also provides a design method for a universal vibration reduction device for a satellite platform. First, the bearing area of ​​a single metal rubber unit and the number of metal rubber units are preliminarily determined according to the overall parameters of the satellite; then, the elastic modulus of the metal rubber mesh block in the metal rubber unit is preliminarily determined according to the bearing area of ​​the single metal rubber unit and the number of metal rubber units; finally, a finite element model of the vibration reduction device and the entire satellite is constructed according to the preliminarily determined bearing area of ​​the single metal rubber unit, the number of metal rubber units and the elastic modulus of the metal rubber mesh block in the metal rubber unit, the vibration reduction efficiency of the vibration reduction device is simulated and verified, and the optimal values ​​of the bearing area of ​​the metal rubber unit, the number of metal rubber units and the elastic modulus of the metal rubber mesh block in the metal rubber unit are obtained.

[0010] The present invention realizes effective vibration isolation and buffering, can meet the satellite's requirements for stability and reliability without affecting the satellite configuration layout and assembly process, and can adapt to the special environmental requirements of aerospace applications.

[0011] In order to achieve the above-mentioned object of the invention, the present invention provides the following technical solutions:

[0012] A universal vibration reduction device for a satellite platform, characterized in that it comprises an upper connecting ring, a lower connecting ring and a metal rubber unit;

[0013] The upper connecting ring is fixedly connected to the satellite body, the lower connecting ring is rigidly connected to the carrier adapter, and the metal rubber unit is installed between the upper connecting ring and the lower connecting ring and the number of the metal rubber units is greater than 1;

[0014] The metal rubber unit comprises an outer cover, a support seat and two metal rubber mesh blocks, which are respectively recorded as a first metal rubber mesh block and a second metal rubber mesh block; the metal rubber mesh block is a mesh structure formed by spiral metal wires; the support seat comprises a shaft and a support platform, the upper end of the shaft is fixedly connected to an upper connecting ring, the support platform is connected to the shaft and is perpendicular to the axial direction of the shaft, the first metal rubber mesh block and the second metal rubber mesh block are sleeved on the outside of the shaft, and the first metal rubber mesh block and the second metal rubber mesh block are separated by the support platform; the outer cover is arranged on the outside of the metal rubber mesh block, and the lower end of the outer cover is fixedly connected to the lower connecting ring.

[0015] Further, the upper end surface of the first metal rubber mesh block contacts the inner wall of the top of the outer cover, the lower end surface of the first metal rubber mesh block contacts the upper surface of the support platform, the upper end surface of the second metal rubber mesh block contacts the lower surface of the support platform, and the lower end surface of the second metal rubber mesh block contacts the upper surface of the lower connecting ring;

[0016] The inner surfaces of the first metal rubber mesh block and the second metal rubber mesh block are in contact with the outer surface of the shaft, and the outer surfaces of the first metal rubber mesh block and the second metal rubber mesh block are in contact with the inner wall of the side surface of the outer cover.

[0017] Furthermore, the support platform in the support seat is a circular structure; the first metal rubber mesh block and the second metal rubber mesh block are coaxial.

[0018] Furthermore, the above-mentioned universal vibration reduction device for a satellite platform further includes a bolt, a fixing screw and a fixing nut;

[0019] The upper connecting ring is provided with a first connecting hole, the shaft of the supporting seat is provided with a second connecting hole along the axial direction, the second connecting hole is a threaded hole, and the bolt cooperates with the first connecting hole and the second connecting hole to realize the fixed connection between the upper end of the shaft and the upper connecting ring;

[0020] The lower end of the outer cover is fixedly connected to the lower connecting ring through a fixing screw and a fixing nut.

[0021] Furthermore, the upper connecting ring, the lower connecting ring and the outer cover are made of aluminum alloy material, and the supporting seat is made of steel material;

[0022] The upper connecting ring and the lower connecting ring have the same size, and the metal rubber units are evenly distributed along the circumference of the upper connecting ring and the lower connecting ring.

[0023] Furthermore, the lower end of the shaft in the support seat does not contact the lower connecting ring, the upper end of the shaft passes through the top of the outer cover, and the upper end of the shaft does not contact the top of the outer cover.

[0024] The above-mentioned design method of a universal vibration reduction device for a satellite platform comprises the following steps:

[0025] S1 preliminarily determines the bearing area A of a single metal rubber unit and the number N of metal rubber units based on the overall parameters of the satellite;

[0026] S2 Preliminarily determine the elastic modulus of the metal rubber mesh block in the metal rubber unit based on the bearing area A of a single metal rubber unit and the number of metal rubber units N.

[0027] S3 is based on the preliminarily determined bearing area A of a single metal rubber unit, the number of metal rubber units N, and the elastic modulus of the metal rubber mesh block. Finite element models of the vibration reduction device and the entire satellite are constructed, and the vibration reduction efficiency of the vibration reduction device is simulated and verified to obtain the optimal values ​​of the bearing area of ​​the metal rubber unit, the number of metal rubber units, and the elastic modulus of the metal rubber mesh block.

[0028] Furthermore, in step S1 of the design method of a universal vibration reduction device for a satellite platform, the satellite overall parameters include the interface size constraint D when the satellite is connected to the vibration reduction device. max , satellite mass m, and satellite moment of inertia I;

[0029] The calculation formulas for the initial value A of the bearing area of ​​a single metal rubber unit and the initial value N of the number of metal rubber units are as follows:

[0030]

[0031] Where D and d are the outer diameter and inner diameter of the metal rubber mesh block in the metal rubber unit, g is the gravitational acceleration, and F is a is the load-bearing capacity per unit area of ​​the metal rubber unit determined empirically. The midpoint of the line connecting the center of the upper connecting ring and the center of the lower connecting ring is defined as the overall center O of the connecting ring. R is the distance between the metal rubber unit and the overall center O of the connecting ring. Any metal rubber unit among the N metal rubber units is defined as the first metal rubber unit. The connection direction between the first metal rubber unit and the overall center O of the connecting ring is defined as the transverse symmetry axis. θ i is the angle between the line connecting the i-th metal rubber unit and the center O of the connecting ring and the transverse symmetry axis.

[0032] Furthermore, in step S2 of the above-mentioned method for designing a universal vibration reduction device for a satellite platform, the elastic modulus of the metal rubber mesh block in the metal rubber unit is The calculation formula is as follows:

[0033]

[0034] Where ΔF represents the pressure variation of a single metal rubber unit, k min represents the stiffness condition required by the overall design of the satellite, Δh represents the deformation of the metal rubber block after being subjected to ΔF, h represents the original height of the metal rubber block, dε represents the change of the compressive strain within Δh, dσ represents the change of the compressive stress within Δh, F represents the pressure on a single metal rubber unit obtained according to the number of metal rubber units N, represents the elastic modulus, ε represents the compressive strain parameter, a and b are empirical coefficients obtained by fitting the test data, and D l The diameter of the spiral coil of the spiral wire in the metal rubber mesh block, d s represents the wire diameter, ρ MR Indicates the relative density of the metal rubber unit.

[0035] Furthermore, in step S3 of the above-mentioned method for designing a universal vibration reduction device for a satellite platform, the vibration reduction efficiency η of the vibration reduction device is simulated and verified using the following formula:

[0036]

[0037] Among them, ω o and ω e They are the target frequency and simulation calculation frequency of the satellite respectively;

[0038] A o is the peak value of the dynamic response when the upper connecting ring is rigidly connected to the lower connecting ring, A e It is the peak value of dynamic response of the vibration reduction device.

[0039] Compared with the prior art, the present invention has at least one of the following beneficial effects:

[0040] (1) When the lower end surface of the lower connecting ring of the satellite vibration reduction device of the present invention receives vibration impact energy, the energy can be squeezed through the outer cover and the support seat to squeeze the metal rubber mesh block, and the large damping property of the metal rubber mesh block and the dry friction damping generated by the elastic deformation of the metal wire and the slip between the wires under the action of the excitation load are utilized to absorb and dissipate a large amount of system energy, thereby achieving effective vibration isolation and buffering;

[0041] (2) The vibration reduction device of the present invention has a simple structure, is easy to install, has good impact resistance, is resistant to space radiation, is resistant to aging, and is resistant to high and low temperatures. It can effectively suppress the dynamic environment during satellite launch, and does not affect the satellite configuration layout and assembly process while also meeting the satellite's requirements for stability and reliability, and can also meet the carrier interface requirements;

[0042] (3) The present invention provides a complete set of simulation analysis and verification test processes for the design optimization of the metal rubber unit, which improves the flexibility of the vibration reduction device and its versatility, and can adapt to the special environmental requirements of aerospace applications. BRIEF DESCRIPTION OF THE DRAWINGS

[0043] Figure 1 It is a schematic diagram of the plane structure of the vibration reduction device of the present invention;

[0044] Figure 2 It is a schematic diagram of the internal structure of the vibration reduction device of the present invention;

[0045] Figure 3 It is a schematic diagram of the structure of the upper connecting ring of the present invention;

[0046] Figure 4 It is a schematic diagram of the structure of the lower connecting ring of the present invention;

[0047] Figure 5This is an overall schematic diagram of the vibration reduction device according to Example 1 of the present invention.

[0048] In the figure: 1-upper connecting ring, 2-outer cover, 3-fixing nut, 4-lower connecting ring, 5-first mesh block (first metal rubber mesh block), 6-second mesh block (second metal rubber mesh block), 7-bolt, 8-axis, 9 fixing screw. DETAILED DESCRIPTION

[0049] The following detailed description of the present invention will make the features and advantages of the present invention more clear and explicit.

[0050] The word "exemplary" is used exclusively herein to mean "serving as an example, embodiment, or illustration." Any embodiment described herein as "exemplary" is not necessarily to be construed as preferred or advantageous over other embodiments. Although various aspects of the embodiments are shown in the drawings, the drawings are not necessarily drawn to scale unless otherwise noted.

[0051] like Figure 1 The present invention discloses a universal vibration reduction device for a satellite platform, comprising an upper connecting ring 1, a lower connecting ring 4 and a metal rubber unit, wherein the metal rubber unit comprises an outer cover 2, a supporting seat and a metal rubber mesh block, the supporting seat comprises a shaft 8 and a supporting platform, and the number of the metal rubber units is preferably selected according to the required bearing capacity of the satellite.

[0052] like Figure 2 As shown, the two metal rubber mesh blocks are respectively recorded as the first mesh block 5 and the second mesh block 6; the upper connecting ring 1 is provided with a first connecting hole, the number of the first connecting holes is equal to the number of the bolts 7, the shaft 8 is provided with a second connecting hole along the axial direction, the second connecting hole is a threaded hole, the bolt 7 is threadedly connected to the shaft 8, the first mesh block 5 and the second mesh block 6 are respectively installed on the periphery of the shaft 8 from top to bottom, the first mesh block 5 and the second mesh block 6 are respectively provided with an outer cover 2 on the periphery, the lower end surface of the outer cover 2 is connected to the upper end surface of the lower connecting ring 4, four third connecting holes are opened at the bottom of the outer cover 2, and the lower connecting ring 4 is opened with a fourth connecting hole, and the fixing screw 9 passes through the third connecting hole and the fourth connecting hole and cooperates with the fixing nut 3 to realize the fixed connection between the outer cover 2 and the lower connecting ring 4.

[0053] The first mesh block 5 and the second mesh block 6 are metal rubber mesh blocks selected to meet the requirements of satellite dynamic environment, and are formed by warp knitting, winding and pressing of metal wires, preferably stainless corrosion-resistant steel wires, and the metal wires in the mesh blocks are spiral.

[0054] like Figure 3 and Figure 4The upper connecting ring 1 and the lower connecting ring 2 are structural schematic diagrams respectively. The upper connecting ring 1 is rigidly connected to the satellite body and adapted to the satellite installation interface. The lower connecting ring 4 is rigidly connected to the carrier adapter and adapted to the adapter installation interface. When the universal vibration reduction device for satellite platform of the present invention is installed on the satellite and works normally, it can improve the dynamic environment of the satellite launch stage.

[0055] The upper connecting ring 1, the lower connecting ring 4 and the outer cover 2 are respectively an aluminum alloy component; the bolt 7 and the supporting seat in the metal rubber unit are a steel component.

[0056] The upper connecting ring 1 is in full contact with the bolt 7 and the shaft 8 , and the upper end of the shaft 8 is in contact with the lower surface of the upper connecting ring 1 .

[0057] The first net block 5 and the second net block 6 are in full contact with the shaft 8 on the inner side and in full contact with the outer cover 2 on the outer side, thereby forming radial constraints to achieve vibration reduction and buffering of lateral vibration or impact of the satellite.

[0058] The upper and lower annular surfaces of the first mesh block 5 are in contact with the inner top surface of the outer cover 2 and the upper end surface of the "cross" structure support platform respectively, and the upper and lower annular surfaces of the second mesh block 6 are in contact with the lower end surface of the support platform and the upper surface of the lower connecting ring 4 respectively.

[0059] A design method for a universal vibration reduction device for a satellite platform, which enables a metal rubber unit to meet the satellite dynamic environment requirements, comprises the following steps:

[0060] 1) Calculate the initial value A of the bearing area of ​​a single metal rubber unit and the initial value N of the number of metal rubber units. The calculation formula is as follows:

[0061]

[0062] Among them, D max is the interface size constraint when the satellite is connected to the vibration reduction device, m is the satellite mass, I is the satellite moment of inertia; D and d are the outer diameter and inner diameter of the metal rubber mesh block in the metal rubber unit, g is the gravitational acceleration, and F a The load capacity per unit area of ​​the metal rubber unit determined by experience is defined. The midpoint of the line connecting the center of the upper connecting ring 1 and the center of the lower connecting ring 4 is defined as the overall center O of the connecting ring. R is the distance between the metal rubber unit and the overall center O of the connecting ring. Any metal rubber unit among the N metal rubber units is defined as the first metal rubber unit. The connection direction between the first metal rubber unit and the overall center O of the connecting ring is defined as the transverse symmetry axis. θ i is the angle between the line connecting the center O of the ith metal rubber unit and the connecting ring and the transverse symmetry axis. 2) According to the bearing area A of a single metal rubber unit and the number of metal rubber units N, the elastic modulus of the metal rubber mesh block in the metal rubber unit is preliminarily determined. Elastic modulus of metal rubber mesh in metal rubber unit The calculation formula is as follows:

[0063]

[0064] Where ΔF represents the pressure variable of a single metal rubber unit, which is measured by the sensor in simulation or experiment, k min represents the stiffness condition required by the overall design of the satellite, Δh represents the deformation of the metal rubber block after being subjected to the ΔF pressure variable, which is measured by the sensor in the simulation or test, h represents the original height of the metal rubber block, dε represents the change (differential) of the compressive strain within Δh, dσ represents the change (differential) of the compressive stress within Δh, F represents the pressure on a single metal rubber unit obtained according to the number of metal rubber units N, represents the elastic modulus, ε represents the compressive strain parameter, a and b are empirical coefficients obtained by fitting the test data, and D l The diameter of the spiral coil of the spiral wire in the metal rubber mesh block, d s represents the wire diameter, ρ MR Indicates the relative density of metal rubber.

[0065] 3) A vibration reduction device model was established in the finite element simulation software. Combined with the satellite overall model, the vibration reduction efficiency η of the vibration reduction device was simulated and verified using the following formula:

[0066]

[0067] Among them, ω o and ω e They are the target frequency and simulation calculation frequency of the satellite respectively;

[0068] A o is the peak value of the dynamic response when the upper connecting ring is rigidly connected to the lower connecting ring, A e It is the peak value of dynamic response of the vibration reduction device.

[0069] (4) According to the vibration reduction efficiency calculated in step 3, if the vibration reduction requirements cannot be met, reselect the number of metal rubber units N, the bearing area A of a single metal rubber unit, and the elastic modulus of the metal rubber mesh block. (For example, by changing the spiral winding diameter D of the spiral wire of the metal rubber mesh block l , wire diameter d s 、Relative density of metal rubber ρ MR The elastic modulus of the metal rubber mesh is changed by the following parameters ) until the vibration reduction requirements are met.

[0070] The vibration reduction device provided by the present invention has a simple structure, is easy to install, has good impact resistance, is resistant to space radiation, is resistant to aging, and is resistant to high and low temperatures. It can effectively suppress the dynamic environment during satellite launch, and does not affect the satellite configuration layout and the general assembly process while also meeting the satellite's requirements for stability and reliability. At the same time, the present invention has formulated a set of systematic and complete simulation analysis and verification test processes for the optimization of the appropriate stiffness and damping of its metal rubber mesh block to adapt to the special environmental requirements of aerospace applications. When installing the present invention, the metal rubber mesh block is sleeved on the shaft, and the metal rubber mesh block is fixed to the inner cavity of the metal rubber unit by bolts, outer covers, fixing nuts, and fixing screws. It is simple and convenient, and the installation is stable; when disassembling, only the fixing nuts need to be removed, which is very convenient, and does not affect the satellite configuration layout and the general assembly process, and can also meet the carrier interface. That is, without changing the type of the satellite-rocket adapter, the structure is simple, easy to install and disassemble, and conducive to repair and maintenance, which is very convenient.

[0071] Embodiment 1:

[0072] like Figure 5 The universal vibration reduction device for satellite platform in this embodiment includes an upper connecting ring 1, a lower connecting ring 4 and 31 metal rubber units, wherein the metal rubber unit includes an outer cover 2, a support seat and a metal rubber mesh block, and the support seat includes a shaft 8 and a support platform. The upper connecting ring 1 is connected to the satellite body by bolts, the lower connecting ring 4 is connected to the carrier adapter by a rigid wrapping belt, and the metal rubber unit is placed between the upper connecting ring 1 and the lower connecting ring 4 and is fixedly connected to the upper connecting ring 1 and the lower connecting ring 4.

[0073] The upper connecting ring 1 is provided with 31 first connecting holes, and the upper connecting ring 1 is fixedly connected to 31 metal rubber units by 31 bolts 7. The lower connecting ring 4 is provided with 124 fourth connecting holes, and the fixed connection between the outer cover 2 and the lower connecting ring 4 is achieved by a combination of 124 fixing screws 9 and fixing nuts 3.

[0074] The metal rubber unit is provided with rigidity and damping by two metal rubber mesh blocks connected in series up and down, which plays the role of vibration reduction and isolation. The first mesh block 5 and the second mesh block 6 are respectively installed above and below the periphery of the shaft 8, and the periphery of the metal rubber unit-the first mesh block 5, the first mesh block 5 and the second mesh block 6 is provided with an outer cover 2, and the lower end surface of the outer cover 2 is connected to the upper end surface of the lower connecting ring 4.

[0075] The upper connecting ring 1, the lower connecting ring 4 and the outer cover 2 are respectively an aluminum alloy component, which is light in weight and has strong compatibility. The bolt 7 and the support seat in the metal rubber unit are a steel component, which has high strength.

[0076] The first mesh block 5 and the second mesh block 6 are made of stainless corrosion-resistant steel wire warp knitted mesh, which are wound and pressed into shape, and are tightly connected, so as to have a good buffering effect.

[0077] The present invention has been described in detail above in conjunction with specific implementations and exemplary examples, but these descriptions cannot be understood as limiting the present invention. Those skilled in the art understand that, without departing from the spirit and scope of the present invention, a variety of equivalent substitutions, modifications or improvements may be made to the technical solution of the present invention and its implementation methods, all of which fall within the scope of the present invention. The scope of protection of the present invention shall be subject to the attached claims.

[0078] The contents not described in detail in the specification of the present invention belong to the common knowledge of those skilled in the art.

Claims

1. A universal vibration reduction device for a satellite platform, characterized in that: It comprises an upper connecting ring (1), a lower connecting ring (4) and a metal rubber unit; The upper connecting ring (1) is fixedly connected to the satellite body, the lower connecting ring (4) is rigidly connected to the carrier adapter, and the metal rubber unit is installed between the upper connecting ring (1) and the lower connecting ring (4) and the number of the metal rubber units is greater than 1; The metal rubber unit comprises an outer cover (2), a support seat and two metal rubber mesh blocks, the two metal rubber mesh blocks are respectively referred to as a first metal rubber mesh block (5) and a second metal rubber mesh block (6); the metal rubber mesh block is a mesh structure formed by spiral metal wires; the support seat comprises a shaft (8) and a support platform, the upper end of the shaft (8) is fixedly connected to an upper connecting ring (1), the support platform is connected to the shaft (8) and is perpendicular to the axial direction of the shaft (8), the first metal rubber mesh block (5) and the second metal rubber mesh block (6) are sleeved on the outside of the shaft (8), and the first metal rubber mesh block (5) and the second metal rubber mesh block (6) are separated by the support platform; the outer cover (2) is arranged on the outside of the metal rubber mesh block, and the lower end of the outer cover (2) is fixedly connected to a lower connecting ring (4).

2. A universal vibration reduction device for a satellite platform according to claim 1, characterized in that: The upper end surface of the first metal rubber mesh block (5) contacts the inner wall of the top of the outer cover (2), the lower end surface of the first metal rubber mesh block (5) contacts the upper surface of the support platform, the upper end surface of the second metal rubber mesh block (6) contacts the lower surface of the support platform, and the lower end surface of the second metal rubber mesh block (6) contacts the upper surface of the lower connecting ring (4); The inner surfaces of the first metal rubber mesh block (5) and the second metal rubber mesh block (6) are in contact with the outer surface of the shaft (8), and the outer surfaces of the first metal rubber mesh block (5) and the second metal rubber mesh block (6) are in contact with the inner wall of the side of the outer cover (2).

3. A universal vibration reduction device for a satellite platform according to claim 1, characterized in that: The support platform in the support seat is a circular structure; the first metal rubber mesh block (5) and the second metal rubber mesh block (6) are coaxial.

4. A universal vibration reduction device for a satellite platform according to claim 1, characterized in that: It also includes a bolt (7), a fixing screw (9) and a fixing nut (3); The upper connecting ring (1) is provided with a first connecting hole, the shaft (8) of the supporting seat is provided with a second connecting hole along the axial direction, the second connecting hole is a threaded hole, and the bolt (7) cooperates with the first connecting hole and the second connecting hole to realize fixed connection between the upper end of the shaft (8) and the upper connecting ring (1); The lower end of the outer cover (2) is fixedly connected to the lower connecting ring (4) via a fixing screw (9) and a fixing nut (3).

5. The universal vibration reduction device for a satellite platform according to claim 1, characterized in that: The upper connecting ring (1), the lower connecting ring (4) and the outer cover (2) are made of aluminum alloy material, and the supporting seat is made of steel material; The upper connecting ring (1) and the lower connecting ring (4) have the same size, and the metal rubber units are evenly distributed along the circumference of the upper connecting ring (1) and the lower connecting ring (4).

6. A universal vibration reduction device for a satellite platform according to claim 2, characterized in that: The lower end of the shaft (8) in the support seat does not contact the lower connecting ring (4), the upper end of the shaft (8) passes through the top of the outer cover (2), and the upper end of the shaft (8) does not contact the top of the outer cover (2).

7. A design method for a universal vibration reduction device for a satellite platform according to any one of claims 1 to 6, characterized in that: The steps include: S1 preliminarily determines the bearing area A of a single metal rubber unit and the number N of metal rubber units based on the overall parameters of the satellite; S2 Preliminarily determine the elastic modulus of the metal rubber mesh block in the metal rubber unit based on the bearing area A of a single metal rubber unit and the number of metal rubber units N. S3 is based on the preliminarily determined bearing area A of a single metal rubber unit, the number of metal rubber units N, and the elastic modulus of the metal rubber mesh block. Finite element models of the vibration reduction device and the entire satellite are constructed, and the vibration reduction efficiency of the vibration reduction device is simulated and verified to obtain the optimal values ​​of the bearing area of ​​the metal rubber unit, the number of metal rubber units, and the elastic modulus of the metal rubber mesh block.

8. The design method of a universal vibration reduction device for a satellite platform according to claim 7, characterized in that: In step S1, the satellite overall parameters include the interface size constraint D when the satellite is connected to the vibration reduction device. max , satellite mass m, and satellite moment of inertia I; The calculation formulas for the initial value A of the bearing area of ​​a single metal rubber unit and the initial value N of the number of metal rubber units are as follows: Where D and d are the outer diameter and inner diameter of the metal rubber mesh block in the metal rubber unit, g is the gravitational acceleration, and F is a The load capacity per unit area of ​​the metal rubber unit is determined empirically. The midpoint of the line connecting the center of the upper connecting ring (1) and the center of the lower connecting ring (4) is defined as the overall center O of the connecting ring. R is the distance between the metal rubber unit and the overall center O of the connecting ring. Any metal rubber unit among the N metal rubber units is defined as the first metal rubber unit. The connection direction between the first metal rubber unit and the overall center O of the connecting ring is defined as the transverse symmetry axis. θ i is the angle between the line connecting the i-th metal rubber unit and the center O of the connecting ring and the transverse symmetry axis.

9. The design method of a universal vibration reduction device for a satellite platform according to claim 7, characterized in that: In the step S2, the elastic modulus of the metal rubber mesh block in the metal rubber unit The calculation formula is as follows: Where ΔF represents the pressure variation of a single metal rubber unit, k min represents the stiffness condition required by the overall design of the satellite, Δh represents the deformation of the metal rubber block after being subjected to ΔF, h represents the original height of the metal rubber block, dε represents the change of the compressive strain within Δh, dσ represents the change of the compressive stress within Δh, F represents the pressure on a single metal rubber unit obtained according to the number of metal rubber units N, represents the elastic modulus, ε represents the compressive strain parameter, a and b are empirical coefficients obtained by fitting the test data, and D l The diameter of the spiral coil of the spiral wire in the metal rubber mesh block, d s represents the wire diameter, ρ MR Indicates the relative density of the metal rubber unit.

10. The design method of a universal vibration reduction device for a satellite platform according to claim 7, characterized in that: In step S3, the vibration reduction efficiency η of the vibration reduction device is simulated and verified using the following formula: Among them, ω o and ω e They are the target frequency and simulation calculation frequency of the satellite respectively; A o is the peak value of the dynamic response when the upper connecting ring is rigidly connected to the lower connecting ring, A e It is the peak value of dynamic response of the vibration reduction device.

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