Vibration isolators suitable for satellite momentum wheel vibration isolation brackets

Abstract

This invention provides a vibration isolator suitable for a satellite momentum wheel vibration isolation support, comprising a first retaining block (2a), a connecting block (3), and a second retaining block (2b) arranged sequentially; it also includes two symmetrically arranged first elastic components (1a) connected between the first retaining block (2a) and the connecting block (3), and two symmetrically arranged second elastic components (1b) connected between the connecting block (3) and the second retaining block (2b); damping energy dissipation materials (5) are respectively provided between the symmetrically arranged first elastic components (1a) and between the symmetrically arranged second elastic components (1b). This invention has low lateral stiffness, high axial stiffness, and large damping characteristics. By reasonably arranging and installing it between the support and the momentum wheel, it can effectively meet the vibration isolation requirements of the momentum wheel; this invention has advantages such as simple and compact structure, convenient processing and assembly, high design freedom, stable and reliable performance, light weight, and low cost.

Description

Technical Field

[0001] This invention relates to the field of vibration isolation technology for satellite momentum wheels, specifically, to vibration isolators suitable for satellite momentum wheel vibration isolation supports. In particular, it relates to high-damping vibration isolators suitable for satellite momentum wheel vibration isolation supports. Background Technology

[0002] With the continuous advancement of remote sensing satellite technology, high-resolution satellites carrying various advanced optical payloads have become the current trend in the development of Earth observation satellites. Because these payloads typically possess extremely high sensitivity, their performance is easily affected by minute disturbances. Therefore, on-orbit micro-vibrations have become a major factor limiting their observation resolution and stability.

[0003] Momentum wheels, as typical sources of micro-vibration in satellites and other spacecraft, generate broadband micro-excitations during on-orbit operation due to their structural characteristics. This induces micro-vibrations on the satellite platform, which are then transmitted through the structure to sensitive optical payloads, causing responses in the optical payload system. Therefore, research on micro-vibration suppression techniques targeting momentum wheels is particularly important for the development of high-resolution satellites in my country.

[0004] Currently, the main approach to addressing this issue is to install a support with passive vibration isolation function between the momentum wheel and the celestial body to achieve vibration suppression. The vibration isolation function is achieved by several vibration isolators connected in parallel between the momentum wheel and the support.

[0005] In response to the above issues, the following search was conducted:

[0006] Patent document CN108443382A discloses a combined active and passive vibration isolator and its control method using electromagnetic negative stiffness. The isolator includes a housing, a force transmission rod, a crossbeam spring sheet, a ring mover, a permanent magnet, a stator, a fixed iron core, a working air gap, a coil frame, and an excitation coil. However, this invention uses active electromagnetic negative stiffness, which, while achieving adjustable negative stiffness and effectively reducing the vibration isolation frequency band, requires additional control equipment and power supply resources. Furthermore, its on-orbit reliability is not as good as the passive vibration isolation method used in this invention.

[0007] Patent document CN109099107A discloses an eddy current vibration isolator for suppressing micro-vibrations in spacecraft, comprising: a stiffening structure and an internal damping structure, wherein the lower side and the interior of the stiffening structure have a magnetic sealing structure for sealing the damping structure. However, this invention requires additional permanent magnets and sealing structures for eddy current damping, resulting in a large volume and overall weight. Summary of the Invention

[0008] To address the shortcomings of existing technologies, the purpose of this invention is to provide a vibration isolator suitable for satellite momentum wheel vibration isolation supports.

[0009] According to the present invention, a vibration isolator suitable for a satellite momentum wheel vibration isolation bracket includes a first retaining block 2a, a connecting block 3, and a second retaining block 2b arranged in sequence.

[0010] It also includes two symmetrically arranged first elastic components 1a connected between the first retaining block 2a and the connecting block 3, and two symmetrically arranged second elastic components 1b connected between the connecting block 3 and the second retaining block 2b;

[0011] Damping energy-dissipating materials 5 are respectively provided between the symmetrically arranged first elastic components 1a and between the symmetrically arranged second elastic components 1b.

[0012] Preferably, the first elastic component 1a and the second elastic component 1b are arranged inverted relative to each other along the axial direction and have orthogonal cross sections, and are connected in the middle by the connecting block 3.

[0013] Preferably, both the first elastic component 1a and the second elastic component 1b are elastic sheets 101;

[0014] The elastic sheet 101 is a C-shaped structure formed by elastically bending a flat plate;

[0015] One end of the elastic sheet 101 is embedded in the limiting groove 201 of the first retaining block 2a and the second retaining block 2b, and the elastic sheet 101 is fixed on the retaining block inclined surface 202 of the limiting groove 201 with screws and clamping washers 4. The other end is embedded in the limiting groove 301 of the connecting block 3, and the elastic sheet 101 is fixed on the connecting block inclined surface 302 with screws and clamping washers 4. When the two elastic sheets 101 are installed in place, they can only bend and deform towards the center surface.

[0016] Preferably, the first elastic component 1a and the second elastic component 1b, when subjected to a lateral force in the bending direction of the elastic sheet 101, generate lateral displacement.

[0017] Preferably, the lateral cross-section of the elastic component 1 is hyperbolic; in the hyperbolic plane, the lateral stiffness of the elastic component 1 is much smaller than the stiffness in the other two translational directions.

[0018] Preferably, when lateral vibration occurs, the elastic component 1 in the corresponding direction drives the damping energy-dissipating material 5 to undergo shear deformation, thereby consuming vibration energy.

[0019] Preferably, the connecting block 3 has four orthogonally distributed limiting grooves 301; each limiting groove 301 is connected to one of the elastic sheets 101; after the two symmetrically arranged elastic components 1 are installed in place, their lateral cross sections are orthogonal to each other.

[0020] Preferably, the end face of the compression pad 4 has rounded corners, allowing the elastic sheet 101 to bend and deform.

[0021] Preferably, the first retaining block 2a is connected to the momentum wheel mounting platform 7, and the second retaining block 2b is connected to the bracket 8.

[0022] Preferably, the space between the two symmetrically arranged first elastic components 1a is filled with damping energy dissipation material 5 and encapsulated with baffle 6; the space between the two symmetrically arranged second elastic components 1b is filled with damping energy dissipation material 5 and encapsulated with baffle 6.

[0023] The present invention also provides a satellite momentum wheel vibration isolation bracket, including the vibration isolator suitable for the satellite momentum wheel vibration isolation bracket, wherein one or more parallel vibration isolators suitable for the satellite momentum wheel vibration isolation bracket are connected between the momentum wheel mounting platform 7 and the bracket 8.

[0024] Compared with the prior art, the present invention has the following beneficial effects:

[0025] 1. Based on the micro-excitation characteristics generated by the momentum wheel, this invention, with its small lateral stiffness and large axial stiffness, can effectively isolate the radial disturbance force related to the rotational frequency generated during the operation of the momentum wheel by reasonably arranging and installing it between the bracket and the momentum wheel. By configuring reasonable structural parameters, the vibration of the momentum wheel in the operating speed range can be effectively suppressed.

[0026] 2. This invention utilizes a bent elastic thin plate as an elastic component, resulting in a simple and compact structure that is easy to process and assemble. The interface design with the support and momentum wheel is convenient, and it has significant advantages in weight and cost compared to traditional slotted metal springs.

[0027] 3. This invention utilizes the deformation characteristics of elastic components to improve the energy dissipation efficiency of damping materials, exhibiting high damping characteristics. During the operation of the momentum wheel, the amplification of the disturbance force response can be controlled to less than 2 times. Attached Figure Description

[0028] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0029] Figure 1 This is a schematic diagram of the overall appearance of the present invention.

[0030] Figure 2 This is an exploded view of the entire invention.

[0031] Figure 3 This is a schematic diagram comparing the cross-sectional structures of the present invention from multiple angles.

[0032] Figure 4 This is a schematic diagram illustrating the implementation status of the present invention.

[0033] As shown in the figure:

[0034] Detailed Implementation

[0035] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0036] The purpose of this invention is to provide a high-damping vibration isolator suitable for satellite momentum wheel vibration isolation supports, which can connect the satellite momentum wheel to the support, effectively suppress the micro-interference force of the momentum wheel, and ensure the normal on-orbit operation of high-precision, high-resolution sensitive loads.

[0037] like Figure 1 , Figure 2 , Figure 3 , Figure 4 As shown, according to the present invention, a large-damping vibration isolator suitable for satellite momentum wheel vibration isolation support is provided. The two orthogonal lateral stiffnesses of the large-damping vibration isolator are close and much smaller than the axial stiffness. It includes: an elastic component 1, a retaining block 2, a connecting block 3, a clamping pad 4, a damping energy dissipation material 5, and a baffle 6.

[0038] The elastic component 1 includes two symmetrically arranged elastic sheets 101; one end of the elastic sheet 101 is embedded in the limiting groove 201 of the retaining block 2, and the elastic sheet 101 is fixed on the inclined surface 202 with screws and clamping washers 4, and the other end is embedded in the limiting groove 301 of the connecting block 3, and the elastic sheet 101 is also fixed on the inclined surface 302 with screws and clamping washers 4.

[0039] The elastic sheet 101 is a C-shaped structure formed by elastic bending of a flat plate. In its free state, it is a flat plate with a bending curvature of 0. When the two elastic sheets 101 are installed in place, they can only bend towards the center plane. The lateral cross section of the elastic component 1 is hyperbolic.

[0040] The parameters of the elastic sheet 101 include its width, thickness, mounting chord length, and chord height. The mounting chord length and chord height of the elastic sheet 101 can be determined by the mounting length and the inclined surfaces 202 and 203 of the retaining block. Damping energy-dissipating material 5 is filled between the two elastic sheets 101 of the elastic component and encapsulated with a baffle 6 to reduce the impact of the space radiation environment on the damping energy-dissipating material 5. In a preferred embodiment, the elastic sheet 101 is made of spring steel, the damping energy-dissipating material 5 is made of butyl rubber, and the remaining key components are all made of aluminum alloy.

[0041] The connecting block 3 has four orthogonally distributed limiting grooves 301; each limiting groove 301 is connected to one of the elastic sheets 101; such as Figure 3 As shown, the lateral cross-sections of the two elastic components 1 are orthogonal to each other after they are installed in place.

[0042] The structural parameters of the large-damping vibration isolator include the width, thickness, mounting chord length, and chord height of the elastic sheet 101. The mounting chord length and chord height of the elastic sheet 101 can be determined by the mounting length and the inclined surface 202 of the retaining block 2 and the inclined surface 302 of the connecting block 3. In a preferred embodiment, the elastic sheet 101 has a width of 10mm, a thickness of 0.2mm, a mounting chord length of 30mm, and a chord height of 4mm, and is machined from 65Mn steel.

[0043] The end face of the clamping pad 4 has rounded corners, which allows the elastic sheet 101 to bend. Therefore, when the elastic component 1 is subjected to a lateral force in the bending direction of the elastic sheet 101, it is easy to generate lateral displacement, that is, the lateral stiffness of the elastic component (1) (in the hyperbolic plane) is much smaller than the stiffness in the other two translational directions.

[0044] The space between the two elastic sheets 101 of the elastic component 1 is filled with damping energy-dissipating material 5 and encapsulated with a baffle 6, thereby reducing the impact of the space irradiation environment on the damping energy-dissipating material 5. When the present invention experiences lateral vibration in a certain direction, the elastic component 1 in the corresponding direction will cause the damping energy-dissipating material 5 to undergo shear deformation, thereby significantly dissipating vibration energy. In a preferred embodiment, the damping energy-dissipating material 5 is butyl rubber.

[0045] like Figure 4One application of the present invention is given, comprising six high-damping vibration isolators provided by the present invention for satellite momentum wheel vibration isolation brackets. These are evenly distributed circumferentially between the bracket 8 and the momentum wheel mounting platform 7. They can be connected to the momentum wheel mounting platform 7 through the threaded hole of the upper end connector 203a of the first retaining block 2a, and connected to the bracket 8 through the threaded hole of the lower end connector 203b of the second retaining block 2b. This achieves a low radial translational stiffness and a high axial translational stiffness for the overall vibration isolation bracket, ensuring that the radial disturbance force is effectively controlled when the momentum wheel is started up in the track section.

[0046] The high-damping vibration isolator for satellite momentum wheel vibration isolation supports provided by this invention uses mature materials suitable for satellite applications, ensuring reliability. The structural parameters of the elastic component 1 can be flexibly adjusted according to actual needs, offering high design freedom. This invention features a simple and compact structure, facilitating processing and assembly, and offers significant advantages in weight and economy compared to traditional metal spring-rubber vibration isolators.

[0047] According to the present invention, a satellite momentum wheel vibration isolation bracket utilizing the aforementioned vibration isolator suitable for satellite momentum wheel vibration isolation bracket is also provided, comprising one or more parallel high-damping vibration isolators connected to the satellite momentum wheel and the bracket, the number of which can be determined according to actual vibration isolation requirements.

[0048] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0049] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A vibration isolator suitable for a satellite momentum wheel vibration isolation bracket, characterized in that, It includes a first holding block (2a), a connecting block (3), and a second holding block (2b) distributed sequentially. It also includes two symmetrically arranged first elastic components (1a) connected between the first retaining block (2a) and the connecting block (3), and two symmetrically arranged second elastic components (1b) connected between the connecting block (3) and the second retaining block (2b). Damping energy-dissipating materials (5) are respectively provided between the symmetrically arranged first elastic components (1a) and between the symmetrically arranged second elastic components (1b). The first elastic component (1a) and the second elastic component (1b) are arranged in opposite directions along the axial direction and with orthogonal cross sections, and are connected in the middle by the connecting block (3); Both the first elastic component (1a) and the second elastic component (1b) are elastic sheets (101). The elastic sheet (101) is a C-shaped structure formed by elastically bending a flat plate; One end of the elastic sheet (101) is embedded in the limiting groove (201) of the first retaining block (2a) and the second retaining block (2b), and the elastic sheet (101) is fixed on the retaining block inclined surface (202) of the limiting groove (201) with screws and clamping washers (4). The other end is embedded in the limiting groove (301) of the connecting block (3), and the elastic sheet (101) is fixed on the connecting block inclined surface (302) with screws and clamping washers (4). When the two elastic sheets (101) are installed in place, they can only bend and deform towards the center surface.

2. The vibration isolator for a satellite momentum wheel vibration isolation bracket according to claim 1, characterized in that, The first elastic component (1a) and the second elastic component (1b) generate lateral displacement when subjected to a lateral force in the bending direction of the elastic sheet (101).

3. The vibration isolator for a satellite momentum wheel vibration isolation bracket according to claim 2, characterized in that, The elastic component (1) has a hyperbolic cross-section in the lateral direction; in the hyperbolic plane, the lateral stiffness of the elastic component (1) is much smaller than the stiffness in the other two translational directions.

4. The vibration isolator for a satellite momentum wheel vibration isolation bracket according to claim 1, characterized in that, When lateral vibration occurs, the elastic component (1) in the corresponding direction drives the damping energy-dissipating material (5) to undergo shear deformation, thereby consuming vibration energy.

5. The vibration isolator for a satellite momentum wheel vibration isolation bracket according to claim 1, characterized in that, The connecting block (3) has four orthogonally distributed limiting grooves (301); each limiting groove (301) is connected to one of the elastic sheets (101); the two symmetrically arranged elastic components (1) are installed in place and their lateral sections are orthogonal to each other.

6. The vibration isolator for a satellite momentum wheel vibration isolation bracket according to claim 1, characterized in that, The end face of the compression pad (4) has rounded corners, allowing the elastic sheet (101) to bend and deform.

7. The vibration isolator for a satellite momentum wheel vibration isolation bracket according to claim 1, characterized in that, The first retaining block (2a) is connected to the momentum wheel mounting platform (7), and the second retaining block (2b) is connected to the bracket (8); the space between the two symmetrically arranged first elastic components (1a) is filled with damping energy dissipation material (5) and encapsulated with baffle (6); the space between the two symmetrically arranged second elastic components (1b) is filled with damping energy dissipation material (5) and encapsulated with baffle (6).

8. A satellite momentum wheel vibration isolation bracket, characterized in that, The vibration isolator for the satellite momentum wheel vibration isolation bracket according to any one of claims 1 to 7, wherein one or more parallel vibration isolators for the satellite momentum wheel vibration isolation bracket are connected between the momentum wheel mounting platform (7) and the bracket (8).

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