A spacecraft bracket and a spacecraft based on a lightweight vibration reduction and isolation lattice structure

Abstract

The present invention provides a spacecraft support and a spacecraft based on a lightweight vibration reduction and isolation lattice structure, and relates to the field of aerospace technology. The spacecraft support is formed by a plurality of spatially periodically arranged cell structures, and the outline of the cell structure forms a rhombus dodecahedron; the rhombus dodecahedron includes eight first vertices, two second vertices and four third vertices, wherein the first vertex is formed by the intersection of three obtuse angles of rhombuses; the second vertex and the third vertex are both formed by the intersection of four acute angles of rhombuses, and the two second vertices are opposite; the cell structure includes eight first straight rods, eight second straight rods, eight first vibrators, four third vibrators and sixteen springs, each first vibrator is located at a corresponding first vertex, and each third vibrator is located at a corresponding third vertex; one end of each first straight rod intersects with the body center of the rhombus dodecahedron, and the other end is connected to the corresponding first vibrator. The spacecraft support has a good vibration reduction and isolation effect on the basis of lightweight.

Description

Technical Field

[0001] The present invention relates to the field of aerospace technology, and in particular to a spacecraft bracket and a spacecraft based on a lightweight vibration reduction and isolation lattice structure. Background Art

[0002] Various precision instruments and equipment on aerospace vehicles are very sensitive to vibrations, and even slight vibrations may affect their performance and accuracy. For example, in the installation structures of optical instruments and communication equipment on satellites, vibrations can cause image blur and distortion, seriously affecting the safety of aerospace vehicles.

[0003] In the related art, the brackets used to support precision instruments in aerospace vehicles have certain limitations in terms of vibration reduction and isolation. Moreover, they are all assembled together with multiple parts, with complex structures and large mass, which makes it difficult to meet the aerospace vehicle's requirements for high-performance vibration reduction and isolation and lightweight. Summary of the invention

[0004] The purpose of the present invention is to provide a spacecraft bracket and a spacecraft based on a lightweight vibration reduction and isolation lattice structure, so as to solve the technical problem that the existing brackets are difficult to simultaneously meet the requirements of aerospace vehicles for high-performance vibration reduction and isolation and lightweight.

[0005] In order to achieve the above object, the present invention provides the following technical solutions:

[0006] In a first aspect, the present invention provides a spacecraft bracket based on a lightweight vibration reduction and isolation lattice structure, wherein the spacecraft bracket is formed by a plurality of spatially periodically arranged cell structures, and the outline of the cell structure forms a rhombic dodecahedron;

[0007] The rhombic dodecahedron includes eight first vertices, two second vertices and four third vertices, wherein the first vertices are formed by the intersection of three obtuse angles of rhombuses; the second vertices and the third vertices are both formed by the intersection of four acute angles of rhombuses, and two of the second vertices are opposite;

[0008] The cell structure includes eight first straight rods, eight second straight rods, eight first vibrators, four third vibrators and sixteen springs, each of the first vibrators is located at a corresponding first vertex, and each of the third vibrators is located at a corresponding third vertex;

[0009] One end of each of the first straight rods intersects with the body center of the rhombic dodecahedron, and the other end is connected to the corresponding first oscillator;

[0010] One end of each of the second straight rods intersects at the second vertex, and the other end is connected to the corresponding first vibrator and located at the edge of the rhombic dodecahedron; the two ends of each of the springs are respectively connected to the third vibrator and the corresponding first vibrator, and are located at the remaining edges of the rhombic dodecahedron.

[0011] According to at least one embodiment of the present invention, the cell structure further includes eight third straight rods, one end of each of the third straight rods is connected to the corresponding first oscillator, and the other end extends in a direction away from the body center of the rhombic dodecahedron;

[0012] Each of the third straight rods is coaxial with the first straight rod connected to the same first vibrator.

[0013] According to at least one embodiment of the present invention, the spring is one of a single helical spring and a double helical spring.

[0014] According to at least one embodiment of the present invention, the cross-section of the spring has a shape selected from the group consisting of a rectangle, a circle, an ellipse, a ring or a triangle.

[0015] According to at least one embodiment of the present invention, the cross-sections of the first straight rod, the second straight rod, and the third straight rod may be in the shape of a rectangle, a circle, an ellipse, a ring, or a triangle.

[0016] According to at least one embodiment of the present invention, the shape of the first vibrator includes one of a sphere and an ellipsoid; and / or,

[0017] The shape of the third vibrator includes one of a spherical shape and an ellipsoidal shape.

[0018] According to at least one embodiment of the present invention, when the cross-sections of the first straight rod, the second straight rod, and the third straight rod are circular, the shapes of the first vibrator and the third vibrator are spherical, the first straight rod, the second straight rod, and the third straight rod have the same first diameter r, and the first vibrator and the third vibrator have the same second diameter R;

[0019] Among them, R≥2r.

[0020] According to at least one embodiment of the present invention, the spacecraft bracket is an integrally formed part; and / or,

[0021] The material of the one-piece molded part includes one or two of 1Cr18Ni9 stainless steel, AlSi10Mg aluminum alloy, and 2B50 aluminum alloy.

[0022] According to at least one embodiment of the present invention, the band gap of the forbidden band of the cell structure ranges from 2700 Hz to 3500 Hz.

[0023] In a second aspect, the present invention further provides a spacecraft, comprising the spacecraft bracket described in the first aspect.

[0024] Among the one or more technical solutions provided in the exemplary embodiments of the present invention, at least one of the following beneficial effects can be achieved.

[0025] The spacecraft bracket based on the lightweight vibration reduction and isolation lattice structure of the exemplary embodiment of the present invention is formed by a plurality of cell structures arranged periodically in space. The main contour of the cell structure forms a frame of a rhombic dodecahedron, wherein eight first straight bars and eight second straight bars constitute the mechanical bearing part of the cell structure; eight first vibrators, four third vibrators and sixteen springs constitute the vibration reduction and isolation part of the cell structure; further, eight first vibrators, four third vibrators, sixteen springs and eight second straight bars constitute a structurally stable rhombic dodecahedron frame structure, which is highly symmetrical and stable, and has good bearing performance and stability.

[0026] When the frame structure of the rhombus dodecahedron is subjected to external pressure, since the four edges of the rhombus are of equal length, the angular relationship between adjacent rhombus faces enables the force to be effectively dispersed in the structure, so that each rod (the first straight rod, the second straight rod) interacts with each other and jointly bears the external force, thereby enhancing the overall bearing capacity.

[0027] When the frame structure is subjected to external vibration, the vibration reduction and isolation part of the cell structure will reduce the amplitude of the vibration, the spring consumes part of the vibration energy during the deformation process, and the first vibrator and the third vibrator swing when subjected to the combined force, further consuming part of the vibration energy. Based on this, the cell structure of the exemplary embodiment of the present invention has the effect of vibration isolation in three directions of space, and has the advantages of light weight and the ability to design a dot matrix arrangement according to the shape. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] The accompanying drawings illustrate exemplary embodiments of the present invention and together with the description serve to explain the principles of the present invention, and these drawings are included to provide a further understanding of the present invention and are incorporated in and constitute a part of this specification;

[0029] Figure 1 is an axonometric structural schematic diagram of a cell structure according to an embodiment of the present invention;

[0030] Figure 2 is a schematic diagram of the axonometric structure of the load-bearing part of the cell structure according to an embodiment of the present invention;

[0031] Figure 3 is a schematic diagram of the axonometric structure of a vibration reduction and isolation part in a cell structure according to an embodiment of the present invention;

[0032] Figure 4 is an axonometric structural diagram of a superstructure according to an embodiment of the present invention;

[0033] Figure 5 is a first-order vibration mode diagram of a cell structure according to an embodiment of the present invention;

[0034] Figure 6 is an energy band diagram of a cell structure according to an embodiment of the present invention;

[0035] Figure 7 is a stress cloud diagram of a cell structure according to an embodiment of the present invention.

[0036] Figure numerals: 10, first straight rod; 20, second straight rod; 30, third straight rod; 41, first vibrator; 43, third vibrator; 50, spring. DETAILED DESCRIPTION

[0037] In order to make the technical problems, technical solutions and beneficial effects to be solved by the present invention more clearly understood, the present invention is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not used to limit the present invention.

[0038] During the flight, the spacecraft will be subjected to various dynamic loads, such as engine vibration, aerodynamic impact, etc. The brackets of various precision instruments in the spacecraft require high-performance vibration reduction and isolation to ensure their accuracy. In addition, the spacecraft also has very strict requirements on weight. While meeting the requirements of structural strength and stiffness, reducing the weight of the structure as much as possible can improve the carrying capacity of the spacecraft and reduce the launch cost.

[0039] In response to the above problems, the spacecraft bracket provided by the exemplary embodiment of the present invention adopts a cellular structure based on a rhombic dodecahedron frame. Through the rods of the mechanical bearing part, the springs and vibrators of the vibration reduction and isolation part, and the overall highly symmetrical and stable frame structure, the vibration reduction and isolation performance is enhanced while the load-bearing capacity is ensured to remain unchanged, and the structure weight is light.

[0040] Figure 1 is an axonometric structural schematic diagram of a cell structure according to an embodiment of the present invention; Figure 2 is a schematic diagram of the axonometric structure of the load-bearing part of the cell structure according to an embodiment of the present invention; Figure 3 Schematic diagram of the isometric structure of the vibration reduction and isolation part of the cell structure according to the embodiment of the present invention. Figure 1-Figure 3As shown, an exemplary embodiment of the present invention provides a spacecraft bracket based on a lightweight vibration isolation lattice structure, wherein the spacecraft bracket is formed by a plurality of spatially periodically arranged cellular structures, and the outline of the cellular structure forms a rhombic dodecahedron; the rhombic dodecahedron includes eight first vertices G1, two second vertices G2 and four third vertices G3, wherein the first vertex G1 is formed by the intersection of three obtuse angles of rhombuses; the second vertex G2 and the third vertex G3 are both formed by the intersection of four acute angles of rhombuses, and the two second vertices G2 are opposite.

[0041] Specifically, the cell structure includes eight first straight rods 10, eight second straight rods 20, eight first vibrators 41, four third vibrators 43 and sixteen springs 50, each first vibrator 41 is located at the corresponding first vertex G1, and each third vibrator 43 is located at the corresponding third vertex G3; one end of each first straight rod 10 intersects with the body center G0 of the rhombic dodecahedron, and the other end is connected to the corresponding first vibrator 41; one end of each second straight rod 20 intersects with the second vertex G2, and the other end is connected to the corresponding first vibrator 41 and is located at the edge of the rhombic dodecahedron; the two ends of each spring 50 are respectively connected to the third vibrator 43 and the corresponding first vibrator 41, and are located at the remaining edges of the rhombic dodecahedron.

[0042] The cell structure is a framework of a rhombic dodecahedron as a whole, having two opposite second vertices G2, eight first vertices G1 and four third vertices G3 located in the middle, wherein the eight first vertices G1 are respectively formed by the intersection of the obtuse angles of three adjacent rhombuses, the second vertices G2 and the third vertices G3 are respectively formed by the intersection of the acute angles of four adjacent rhombuses, and the body center G0 is the center point of the rhombic dodecahedron.

[0043] The in-plane portion of the rhombic dodecahedron is formed by eight first straight rods 10 , and the eight first straight rods 10 extend radially from the body center G0 to the positions of the corresponding first vertices G1 .

[0044] The positions of the edges of the rhombic dodecahedron are respectively occupied by eight second straight rods 20 connected between the second vertex G2 and the first vertex G1 and sixteen springs 50 connected between the first vertex G1 and the third vertex G3, forming the overall framework of the rhombic dodecahedron.

[0045] From another perspective, the first vibrator 41 corresponds to the first vertex G1 one by one, and the first vibrator 41 occupies the position of the first vertex G1; the third vibrator 43 corresponds to the third vertex G3 one by one, and the third vibrator 43 occupies the position of the third vertex G3. The first vibrator 41 is respectively connected to a second straight rod 20 and two springs 50; the third vibrator 43 is respectively connected to three springs 50.

[0046] It can be seen from the above that the distance from the body center G0 to the first vertex G1, the distance from the first vertex G1 to the third vertex G3 connected thereto through the spring 50, and the distance from the first vertex G1 to the second vertex G2 connected thereto through the second straight rod 20 are all the same.

[0047] It is understandable that in the cell structure of the spacecraft support provided by the exemplary embodiment of the present invention, the rhombic dodecahedron geometric structure is a polyhedron surrounded by twelve identical rhombuses. The connection between the faces of this geometric structure forms a highly symmetrical and stable spatial structure, so the whole has good bearing performance and stability. When the geometric structure is subjected to external pressure, the force will be transmitted to multiple adjacent faces along the edges of the rhombus and the connecting edges of the adjacent faces, rather than being concentrated on a certain point or a certain face. In other words, this geometric structure is a three-dimensional mesh structure, each face supports each other with the adjacent faces, and its essence is a complex truss system, in which each first straight rod 10 and each second straight rod 20 interact with each other and jointly bear the external force, thereby enhancing the overall bearing capacity.

[0048] Furthermore, the structure composed of the first straight rod 10 and the second straight rod 20 can ensure the transmission of force. The spring 50 with the first vibrator 41 and the third vibrator 43 located in the middle part of the rhombic dodecahedron (between the third vertex G3 and the first vertex G1) can first undergo elastic deformation when the external force is transmitted to the vibration reduction part, and then generate an elastic restoring force in the opposite direction of the external force. This process will convert part of the vibration energy into the elastic potential energy of the spring 50, thereby slowing down the movement speed of the third vibrator 43 and reducing the amplitude of vibration; during the elastic deformation process of the spring 50, the internal friction generated inside it will also convert part of the mechanical energy into heat energy, thereby consuming part of the vibration energy.

[0049] Furthermore, the third vibrator 43 has a large mass. Due to its inertia, its vibration speed is lower than the vibration speed of the spring 50. In addition, due to the symmetry of its structural shape, the surrounding springs 50 will provide a restoring force for the third vibrator 43 in the opposite direction of each external force. When subjected to the combined force, the third vibrator 43 will swing within a certain range, thereby consuming part of the vibration energy.

[0050] In some embodiments, Figure 1 and Figure 2 As shown, in the spacecraft bracket provided by the exemplary embodiment of the present invention, the cellular structure also includes eight third straight rods 30, one end of each third straight rod 30 is connected to the corresponding first vibrator 41, and the other end extends in a direction away from the body center G0 of the rhombic dodecahedron; each third straight rod 30 is coaxial with the first straight rod 10 connected to the same first vibrator 41.

[0051] The eight third straight rods 30, the eight first straight rods 10 and the eight second straight rods 20 can form a stable triangular support structure, giving full play to the mechanical bearing function of each cell structure. At the same time, the end of the eight third straight rods 30 away from the body center G0 can be connected with other cell structures of the spacecraft support in a periodic array arrangement in the X, Y and Z directions, thereby forming a super structure.

[0052] It should be noted that the superstructure provided by the exemplary embodiment of the present invention is a local resonance superstructure with vibration isolation characteristics. When the frequency of the elastic wave propagating in the superstructure is close to the resonance frequency of the cell structure, the cell structure will have a strong coupling effect with the elastic wave, so that it cannot continue to propagate forward, thereby resulting in the generation of a bandgap. When the elastic wave propagates in the superstructure, it is prevented from propagating within a certain frequency range (bandgap) by the internal structure of the superstructure, but can propagate losslessly in other frequency ranges (passband).

[0053] The bandgap position of the superstructure is determined by the internal cell structure. In order to achieve the effect of vibration reduction and isolation, the cell structure must be arranged periodically. The cell structure with spatial periodic arrangement will produce local resonance when the elastic wave is transmitted, thereby generating passband and bandgap.

[0054] In some embodiments, the spring 50 is a single helical spring or a double helical spring. Compared with the single helical spring, when each spring 50 is a double helical spring, its stability is higher, the vibration energy that can be consumed is more, and the weight will not increase too much.

[0055] Exemplarily, the cross-sectional shape of the spring 50 includes one of a rectangular, circular, elliptical, annular or triangular shape. The springs 50 with different cross-sectional shapes have different moments of inertia, which may affect the resonance frequency of the cell structure.

[0056] For example, when the cross-sectional shape of the spring 50 is rectangular, the moment of inertia of the cross-sectional shape is the smallest, followed by circular.

[0057] Furthermore, the size of the cross section of the spring 50 can also be adjusted as needed.

[0058] When the cross-sectional shape of the spring 50 is circular, its diameter is r1, and the cross-sectional shapes of the first straight rod 10, the second straight rod 20, and the third straight rod 30 are circular, and they have the same first diameter r. The cross-sectional diameter of the spring 50 should satisfy: r≥4r1, so that the spring 50 and the first vibrator 41 and the third vibrator 43 at its two ends can fully exert the best vibration reduction and isolation effect.

[0059] Exemplarily, the cross-sectional shapes of the first straight rod 10 , the second straight rod 20 , and the third straight rod 30 may also include one of a rectangular shape, an elliptical shape, a circular ring shape, or a triangular shape.

[0060] Exemplarily, the shape of the first vibrator 41 includes a sphere or an ellipsoid; the shape of the third vibrator 43 includes a sphere or an ellipsoid. The following description is made by taking the spherical shapes of the first vibrator 41 and the third vibrator 43 as examples.

[0061] Exemplarily, the first vibrator 41 and the third vibrator 43 have the same second diameter R; the relationship between the second diameter R and the first diameter r should satisfy: R ≥ 2r. When the diameter of the third vibrator 43 satisfies the above relationship, its mass is greater than the mass of the spring 50. Due to the inertia of the vibrator, its vibration speed is less than the vibration speed of the spring 50. In addition, due to the symmetry of its structural shape, the surrounding spring 50 will provide a restoring force for the third vibrator 43 in the opposite direction of each external force. When subjected to the combined force, the third vibrator 43 will swing within a certain range and consume vibration energy.

[0062] In order to achieve the desired vibration reduction and isolation effect of the spacecraft bracket, the corresponding local resonance phenomenon can be generated by arranging the cell structure in a periodic array. There are many ways to arrange the cell structure in a periodic array.

[0063] For example, the cell structure is periodically arranged along a single direction, so that the superstructure for vibration reduction and isolation is in the shape of a beam; the cell structure is periodically arranged along two directions perpendicular to each other at the same time, so that the superstructure for vibration reduction and isolation is in the shape of a plate; the cell structure is periodically arranged along three directions perpendicular to each other at the same time, so that the superstructure for vibration reduction and isolation is in the shape of a body, such as Figure 4 As shown, the cell structure is arranged in a periodic array in three mutually perpendicular directions, X, Y, and Z, presenting a body shape. Figure 4 is a schematic diagram of an axonometric structure of a superstructure according to an embodiment of the present invention.

[0064] It should be noted that the periodic arrangement of the above-mentioned cell structure can be determined according to actual application requirements, and the bandgap range of vibration reduction and isolation of superstructures with different periodic arrangements is also different.

[0065] In some embodiments, the spacecraft bracket is an integrally formed part; the material of the integrally formed part includes one or more of 1Cr18Ni9 stainless steel, AlSi10Mg aluminum alloy, and 2B50 aluminum alloy.

[0066] For example, the superstructure of a spacecraft bracket can be printed in one piece through additive manufacturing, which has the technical advantages of being lightweight, easy to process, and customizable according to the array arrangement of the cell structure. Furthermore, through additive manufacturing, the one-piece molded part does not have the mechanical property differences of conventional rod connections.

[0067] The following article will take AlSi10Mg aluminum alloy as an example to explain the density of this alloy is 2.68g / cm 3 , the elastic modulus is 70GPa and the Poisson's ratio is 0.33.

[0068] The lattice constant of the cell structure is 8 mm, that is, the overall shape of the cell structure is Cube, such as Figure 1 As shown, the distance between the free ends of two adjacent third straight rods 30 is 8 mm.

[0069] The lengths of the first straight rod 10, the second straight rod 20 and the third straight rod 30 are all 3.464 mm, and the distance between the centroids of the first vibrator 41 and the third vibrator 43 connected to the same spring 50 is 3.464 mm; the second diameter R of the spherical first vibrator 41 and the third vibrator 43 is 1 mm; the diameter r of the circular first straight rod 10, the second straight rod 20 and the third straight rod 30 is 0.4 mm; the cross-sectional shape of the double helical spring 50 is circular, and its diameter r1 is 0.1 mm.

[0070] Figure 5 is a first-order vibration mode diagram of the cell structure according to an embodiment of the present invention. Figure 5 As shown, the displacement display diagram when the excitation frequency of the external force is equal to the natural frequency of the cell structure, wherein the position where the third vibrator 43 is located (the third vertex G3) is the point of maximum displacement, that is, at this time, the energy transmitted by the external vibration is regularly swung within a certain range through the spherical third vibrator 43, and the maximum dissipation is obtained, thereby reducing the influence of the external vibration on the entire cell structure.

[0071] Figure 6 is an energy band diagram of a cell structure according to an embodiment of the present invention. Figure 6 As shown, it shows the energy band diagram in the X direction of the irreducible Brillouin zone, indicating that it can produce a band gap (band gap) that prohibits the propagation of waves. Specifically, for the vibration propagation of the entire cell structure in the X direction, the first twelve eigenfrequencies of the structure are calculated, where the band gap is the part marked by gray shadows, and the band gap range is 2714Hz~3402Hz. Within this band gap range, the wave propagation of vibration along the X direction is prohibited, indicating that the cell structure can play a good vibration reduction effect.

[0072] Figure 7 is a stress cloud diagram of a cell structure according to an embodiment of the present invention. Figure 7 As shown, a simulated stress cloud diagram is obtained by subjecting the cell structure of an exemplary embodiment of the present invention to a compression test in finite element simulation software. Figure 7The content in the upper left box is the stress values ​​corresponding to different colors. The colors are arranged from bottom to top, and the corresponding stress values ​​are getting larger and larger. Light red is the color with the largest stress value, and light blue is the color with the smallest stress value. The positions marked by the boxes in the downward displacement diagram, the center of mass G0, the second vertex G2, and the contact surface of the free end of the third straight rod 30 are the points with the largest stress. This shows that: during the compression process, the entire cell structure is Figure 2 The supporting structure can effectively disperse and transfer the external force to each rod, so that they can jointly bear the external force and enhance the overall bearing capacity of the structure.

[0073] An exemplary embodiment of the present invention further provides a spacecraft, comprising the spacecraft bracket in the above embodiment.

[0074] The spacecraft bracket may be a bracket inside the spacecraft for supporting or fixing precision instruments, and the precision instruments may be a gyroscope, an optical equipment gimbal, etc.

[0075] The technical advantages of the above-mentioned spacecraft over the prior art are the same as the technical advantages of the spacecraft bracket of the above-mentioned embodiment, which will not be repeated here.

[0076] It should be understood by those skilled in the art that the above embodiments are only for the purpose of clearly illustrating the present invention, and are not intended to limit the scope of the present invention. For those skilled in the art, other changes or modifications may be made based on the above disclosure, and these changes or modifications are still within the scope of the present invention.

Claims

1. A spacecraft bracket based on a lightweight vibration reduction and isolation lattice structure, characterized in that: The spacecraft support is formed by a plurality of spatially periodically arranged cell structures, and the outline of the cell structure forms a rhombic dodecahedron; The rhombic dodecahedron includes eight first vertices, two second vertices and four third vertices, wherein the first vertices are formed by the intersection of three obtuse angles of rhombuses, the second vertices and the third vertices are formed by the intersection of four acute angles of rhombuses, and two of the second vertices are opposite to each other; The cell structure includes eight first straight rods, eight second straight rods, eight first vibrators, four third vibrators and sixteen springs, each of the first vibrators is located at a corresponding first vertex, and each of the third vibrators is located at a corresponding third vertex; One end of each of the first straight rods intersects with the body center of the rhombic dodecahedron, and the other end is connected to the corresponding first oscillator; One end of each of the second straight rods intersects at the second vertex, and the other end is connected to the corresponding first vibrator and located at the edge of the rhombic dodecahedron; two ends of each of the springs are respectively connected to the third vibrator and the corresponding first vibrator and located at the remaining edges of the rhombic dodecahedron; The cross-sections of the first straight rod and the second straight rod are circular, the first straight rod and the second straight rod have the same first diameter r, and the cross-section of the spring is circular with a diameter of r1; wherein r≥4r1.

2. The spacecraft bracket according to claim 1, characterized in that: The cell structure further includes eight third straight rods, one end of each of the third straight rods is connected to the corresponding first oscillator, and the other end of each of the third straight rods extends in a direction away from the body center of the rhombic dodecahedron; Each of the third straight rods is coaxial with the first straight rod connected to the same first vibrator.

3. The spacecraft bracket according to claim 2, characterized in that: The spring is a single helical spring or a double helical spring.

4. The spacecraft bracket according to claim 1, characterized in that: The shape of the first vibrator includes a spherical shape or an ellipsoidal shape; and / or, The shape of the third vibrator includes one of a sphere and an ellipsoid.

5. The spacecraft bracket according to claim 2, characterized in that: The cross section of the third straight rod is circular, the first vibrator and the third vibrator are spherical, the first straight rod, the second straight rod and the third straight rod have the same first diameter r, and the first vibrator and the third vibrator have the same second diameter R; Among them, R≥2r.

6. The spacecraft bracket according to claim 5, characterized in that: The spacecraft bracket is an integrally formed part; and / or, The material of the spacecraft bracket includes one or more of 1Cr18Ni9 stainless steel, AlSi10Mg aluminum alloy, and 2B50 aluminum alloy.

7. The spacecraft bracket according to claim 6, characterized in that: The band gap of the forbidden band of the cell structure ranges from 2700 Hz to 3500 Hz.

8. A spacecraft, characterized in that: A spacecraft bracket comprising any one of claims 1-7.

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