Integrated vibration isolation and damping support and mounting structure for satellite momentum wheels

Abstract

The application provides a vibration isolation and buffering integrated support and mounting structure for a satellite momentum wheel, comprising a mounting platform, a vibration isolation assembly and a mounting support, one end of the vibration isolation assembly being connected to the mounting platform, the other end of the vibration isolation assembly being connected to the mounting support; the vibration isolation assembly comprises two pairs of orthogonal elastic sheets installed along the axial direction of the vibration isolation assembly, and any pair of elastic sheets is filled with damping energy dissipation material. The application further comprises a momentum wheel and a satellite structure plate, the mounting platform being fastened to the momentum wheel, and the mounting support being fastened to the satellite structure plate. When the vibration isolation assembly is subjected to a transverse force in the bending direction of the elastic sheets, the vibration isolation assembly is prone to transverse displacement, the transverse linear stiffness of the vibration isolation assembly in two orthogonal directions is similar and far less than the axial linear stiffness, when the vibration isolation assembly is subjected to transverse vibration, the corresponding elastic sheets drive the damping energy dissipation material to produce shear deformation, thereby greatly consuming vibration energy, which helps to reduce the amplitude of the momentum wheel and ensure that the momentum wheel safely passes through the launch section.

Description

Technical Field

[0001] This invention relates to the field of vibration isolation technology for satellite momentum wheels, specifically to an integrated support and mounting structure for vibration isolation and buffering of satellite momentum wheels. Background Technology

[0002] Momentum wheels, as crucial rotating components in satellites and other spacecraft for positioning, energy storage, and control, generate broadband micro-excitations during on-orbit operation due to their structural characteristics. This induces micro-vibrations on the satellite platform, severely impacting the pointing accuracy and stability of sensitive onboard payloads and reducing the resolution of ultra-high-precision instruments. Therefore, researching micro-vibration suppression technologies for momentum wheels is particularly important for the development of high-resolution satellites in my country.

[0003] Currently, the main approach to addressing this issue is to install a support with passive vibration isolation between the momentum wheel and the satellite to suppress vibration. However, in practice, to obtain a wider isolation frequency band while ensuring the momentum wheel can safely pass through the vibration environment of the launch section, it is usually necessary to add an unlocking mechanism to the vibration isolation support. This results in additional mass and resource consumption, and also reduces system reliability.

[0004] A Chinese patent application with publication number CN207374708U discloses a momentum wheel bracket that avoids the influence of micro-vibration resonance. The bracket includes a top structural wall, a left structural wall, a right structural wall, a middle structural wall, a front outer structural wall, a mounting structural wall, a rear outer structural wall, an ear mounting plate, a momentum wheel bracket mounting hole, and a momentum wheel mounting hole, which are used for mounting the momentum wheel actuator of a spacecraft.

[0005] The support in the aforementioned prior art only relies on increasing the natural frequency to avoid coupling with the momentum wheel interference, and does not have on-orbit vibration isolation function. Furthermore, it provides rigid support for the momentum wheel in the launch section and cannot provide a buffer function.

[0006] Existing Chinese patent application document CN114060466B discloses a lightweight vibration-isolated metal composite flywheel bracket, its preparation method, and its application, belonging to the field of metal material structure design and processing technology. This metal composite flywheel bracket includes a lightweight and high-damping magnesium alloy base plate, a titanium alloy lattice sandwich flywheel mounting surface with vibration-damping function, and a high-rigidity titanium alloy support beam. The lightweight vibration-isolated metal composite flywheel bracket is prepared by combining metal block processing and metal 3D printing.

[0007] The existing support technology described above has a high first-order frequency and a narrow vibration isolation bandwidth, making it unsuitable for isolating low-frequency disturbances. Currently, there is an urgent need for a method that can meet the vibration isolation requirements caused by the momentum wheel in orbit, ensuring the momentum wheel safely passes through the vibration environment of the launch section. Summary of the Invention

[0008] To address the shortcomings of existing technologies, the purpose of this invention is to provide an integrated support and mounting structure for vibration isolation and buffering of satellite momentum wheels.

[0009] According to the present invention, an integrated support for vibration isolation and buffering of a satellite momentum wheel includes a mounting platform, a vibration isolation component, and a mounting bracket. One end of the vibration isolation component is connected to the mounting platform, and the other end of the vibration isolation component is connected to the mounting bracket. The vibration isolation component includes two pairs of orthogonal elastic sheets mounted along the axial direction of the vibration isolation component, and damping energy dissipation material is filled between each pair of elastic sheets.

[0010] Preferably, the vibration isolation assembly further includes two connecting blocks and a retaining block, with the two connecting blocks respectively disposed on both sides of the retaining block along the axial direction of the vibration isolation assembly; a pair of elastic sheets connects one connecting block and the retaining block, and another pair of elastic sheets connects the other connecting block and the retaining block.

[0011] Preferably, each of the connecting blocks has a connector on the side opposite to the retaining block.

[0012] Preferably, the mounting platform is provided with a platform connection groove, the mounting bracket is provided with a bracket connection groove, the connector on one connecting block of the vibration isolation component is fastened to the platform connection groove, and the connector on the other connecting block of the vibration isolation component is fastened to the bracket connection groove.

[0013] Preferably, the platform connecting grooves are evenly distributed in multiples along the circumference of the mounting platform, and the bracket connecting grooves are evenly distributed in multiples along the circumference of the mounting bracket. The array axis of the platform connecting grooves and the array axis of the bracket connecting grooves are collinear. The number of platform connecting grooves and the number of bracket connecting grooves are equal, and the distance between the center of any platform connecting groove and the array axis is the same as the distance between the center of any bracket connecting groove and the array axis.

[0014] Preferably, the central axis of the vibration isolation component is parallel or collinear with the array axis of the platform connecting groove.

[0015] Preferably, each of the elastic sheets is arc-shaped, and the middle part of the arc of each elastic sheet is concave towards the central axis of the vibration isolation component.

[0016] Preferably, a buffer system is provided between the mounting platform and the mounting bracket. The buffer system includes a buffer sleeve disposed on the mounting platform and a buffer shaft disposed on the mounting bracket. The buffer shaft and the buffer sleeve are coaxially nested together.

[0017] Preferably, a buffer washer is fitted on the buffer shaft, the buffer washer contacts the inner wall of the buffer sleeve, and a radial buffer space is formed between the buffer shaft and the inner wall of the buffer sleeve; the bottom of the buffer shaft and the flushing sleeve are clearance fitted.

[0018] According to the present invention, a mounting structure for a satellite momentum wheel further includes a momentum wheel and a satellite structure plate, wherein the mounting platform is fastened to the momentum wheel and the mounting bracket is fastened to the satellite structure plate.

[0019] Compared with the prior art, the present invention has the following beneficial effects:

[0020] 1. The present invention utilizes the vibration isolation component to generate lateral displacement when subjected to lateral force in the bending direction of the elastic sheet. As a result, the lateral linear stiffness of the vibration isolation component in the two orthogonal directions is similar and much smaller than the axial linear stiffness. When the vibration isolation component vibrates laterally, the elastic sheet in the corresponding direction will drive the damping energy dissipation material to undergo shear deformation, thereby greatly consuming vibration energy, which helps to reduce the amplitude effect and ensure that the momentum wheel safely passes through the launch section.

[0021] 2. This invention, starting from the micro-excitation characteristics generated by the momentum wheel, has a high efficiency in suppressing the radial disturbance force related to the rotational frequency generated when the momentum wheel is working, so that the amplification of the disturbance force response of the momentum wheel does not exceed two times as the rotational speed increases, and the vibration in the working speed range (1000rpm~5000rpm) can be effectively attenuated.

[0022] 3. The buffer system of the present invention has a simple structure and a large load-bearing capacity. It can effectively buffer the large-scale radial vibrations suffered by the momentum wheel in the launch section, so that the vibration response in this direction is amplified by no more than 2 times. At the same time, it maintains a sufficiently large load-bearing capacity in the axial direction, thereby replacing the traditional unlocking device, protecting the momentum wheel to pass safely through the launch section, and not affecting the micro-vibration isolation performance of the momentum wheel in the track section.

[0023] 4. The vibration isolation component used in this invention has low radial stiffness and a high ratio of axial to radial stiffness, which can not only well meet the vibration isolation requirements of the momentum wheel, but also improve the energy dissipation efficiency of the damping energy dissipation material. The vibration isolation component uses an elastic thin plate as an elastic element, which has a simple structure, is easy to assemble, and is easy to miniaturize and lighten.

[0024] 5. The vibration isolation component layout adopted in this invention can make full use of the stiffness characteristics of the vibration isolation component, and stagger the radial translational natural frequency and the natural frequencies of the other four degrees of freedom, so that the coupled vibration does not occur in the working frequency range of the momentum wheel.

[0025] 6. The mounting bracket and mounting platform of the present invention are processed using advanced additive manufacturing technology, which allows for high design freedom, good mechanical properties, and cost savings compared to traditional machining methods. Attached Figure Description

[0026] 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:

[0027] Figure 1 This is a schematic diagram illustrating the overall structure of the integrated vibration isolation and buffer support of the present invention.

[0028] Figure 2 This is a schematic diagram illustrating the overall structure of the vibration isolation component, which is the main feature of this invention.

[0029] Figure 3 This is a structural diagram illustrating the assembly surface of the mounting platform and the mounting bracket, which are the main components of this invention.

[0030] Figure 4 This is a half-sectional structural diagram of the integrated vibration isolation and buffer support of the present invention.

[0031] Figure 5 This is a schematic diagram illustrating the overall structure of the mounting bracket, which is the main feature of this invention.

[0032] Figure 6 This is a schematic diagram illustrating the installation structure of the momentum wheel for satellites, which is the main feature of this invention.

[0033] As shown in the figure:

[0034] Installation platform 1, damping energy dissipation material 204

[0035] Platform connection groove 101 Mounting bracket 3

[0036] Buffer sleeve 102, bracket connecting groove 301

[0037] Vibration isolation component 2, buffer shaft 302

[0038] Elastic sheet 201 buffer system 4

[0039] 203 retaining block and 5 buffer washers

[0040] Connector 202a Momentum wheel 6

[0041] Connecting block 202 Satellite structural plate 7 Detailed Implementation

[0042] 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.

[0043] like Figure 1 and Figure 2 As shown, an integrated support and mounting structure for vibration isolation and buffering of a satellite momentum wheel, according to the present invention, includes a mounting platform 1, a vibration isolation component 2, and a mounting bracket 3. One end of the vibration isolation component 2 is connected to the mounting platform 1, and the other end of the vibration isolation component 2 is connected to the mounting bracket 3. A buffer system 4 is also provided between the mounting platform 1 and the mounting bracket 3. The vibration isolation component 2 includes two pairs of orthogonal elastic sheets 201 mounted along the axial direction of the vibration isolation component 2, and damping energy dissipation material 204 is filled between each pair of elastic sheets 201.

[0044] Specifically, the vibration isolation component 2 further includes two connecting blocks 202 and a retaining block 203. The two connecting blocks 202 are respectively disposed on both sides of the retaining block 203 along the axial direction of the vibration isolation component 2. A pair of elastic sheets 201 connect one connecting block 202 and the retaining block 203, and another pair of elastic sheets 201 connect the other connecting block 202 and the retaining block 203. One feasible implementation is as follows: the elastic sheets 201 are made of 65Mn, with a thickness of 0.2mm, and a chord length of 30mm after installation. Further, each elastic sheet 201 is arc-shaped, and the middle part of the arc of each elastic sheet 201 is recessed towards the central axis of the vibration isolation component 2.

[0045] When the vibration isolation component 2 is subjected to a lateral force in the bending direction of the elastic sheet 201, it is prone to lateral displacement. Therefore, the lateral linear stiffness of the vibration isolation component 2 in the two orthogonal directions is similar and much smaller than its axial linear stiffness. Damping energy-dissipating material 204 is filled between the elastic sheets 201. When the vibration isolation component 2 undergoes lateral vibration, the elastic sheets 201 in the corresponding direction will cause the damping energy-dissipating material 204 to undergo shear deformation, thereby significantly dissipating vibration energy. In a feasible embodiment, the damping energy-dissipating material 204 is selected as butyl rubber.

[0046] like Figure 3 , Figure 4 as well as Figure 5 As shown, more specifically, the mounting platform 1 is provided with a platform connecting groove 101, and the mounting bracket 3 is provided with a bracket connecting groove 301. Both the platform connecting groove 101 and the bracket connecting groove 301 can be rectangular grooves. The two ends of the vibration isolation component 2 are respectively fastened to the mounting platform 1 and the mounting bracket 3. Further, each of the two connecting blocks 202 in the vibration isolation component 2 has a connector 202a on the side opposite to the retaining block 203. The connector 202a on one connecting block 202 of the vibration isolation component 2 is fastened to the platform connecting groove 101, and the connector 202a on the other connecting block 202 of the vibration isolation component 2 is fastened to the bracket connecting groove 301.

[0047] More specifically, multiple platform connecting grooves 101 are evenly distributed along the circumference of the mounting platform 1, and multiple bracket connecting grooves 301 are evenly distributed along the circumference of the mounting bracket 3. The array axis of the platform connecting grooves 101 and the array axis of the bracket connecting grooves 301 are collinear. The number of platform connecting grooves 101 and the number of bracket connecting grooves 301 are equal, and the distance between the center of any platform connecting groove 101 and the array axis is the same as the distance between the center of any bracket connecting groove 301 and the array axis.

[0048] One feasible implementation is as follows: the mounting platform 1 has six evenly distributed platform connecting grooves 101 along the circumference, and the mounting bracket 3 has six evenly distributed bracket connecting grooves 301 along the circumference. The circumferential diameter of the center of the platform connecting grooves 101 and the bracket connecting grooves 301 is the same. In a preferred embodiment, the distribution diameter is 240 mm.

[0049] There are six vibration isolation components 2. The connectors 202a of the vibration isolation components 2 are matched with the platform connecting groove 101 and the bracket connecting groove 301. The upper end of the vibration isolation component 2 is fixed to the mounting platform 1 through the connectors 202a, and the lower end of the vibration isolation component 2 is fixed to the mounting bracket 3 through the connectors 202a. After the vibration isolation components 2 are connected to the mounting platform 1 and the mounting bracket 3, the axis of the vibration isolation components 2 is parallel to or collinear with the array axis of the rectangular grooves of the platform and the rectangular grooves of the bracket, and the cross-section of the vibration isolation components 2 is perpendicular to the symmetry plane of the mounting bracket 3.

[0050] The buffer system 4 includes a buffer sleeve 102 mounted on the mounting platform 1 and a buffer shaft 302 mounted on the mounting bracket 3. The buffer shaft 302 and the buffer sleeve 102 are coaxially nested together. The central axis of the buffer sleeve 102 coincides with the array axis of the platform connecting groove 101, and the central axis of the buffer shaft 302 coincides with the array axis of the bracket connecting groove 301. After the vibration isolation assembly 2 connects the mounting platform 1 and the mounting bracket 3, the buffer sleeve 102 and the buffer shaft 302 form a nested fit. A buffer washer 5 is fitted on the buffer shaft 302, and the buffer washer 5 contacts the inner wall of the buffer sleeve 102. A radial buffer space is formed between the inner wall of the buffer shaft 302 and the buffer sleeve 102, and the bottom of the buffer shaft 302 and the replacement sleeve have a clearance fit. In a preferred embodiment, the material of the buffer washer 5 is silicone rubber.

[0051] This application provides a connection method between a buffer washer 5 and a buffer shaft 302: the buffer shaft 302 is provided with an annular groove, and the buffer washer 5 is embedded in the annular groove.

[0052] According to the present invention, a mounting structure for a satellite momentum wheel is provided, such as... Figure 6As shown, it also includes a momentum wheel 6 and a satellite structure plate 7. The mounting platform 1 is fastened to the momentum wheel 6, and the mounting bracket 3 is fastened to the satellite structure plate 7.

[0053] Specifically, during satellite assembly, the momentum wheel 6 is mounted on the center of the upper surface of the mounting platform 1 using screws. The vibration isolation and buffer integrated bracket is threaded to the satellite structure plate 7 through the light hole on the bottom surface of the mounting bracket 3. When the satellite is in the launch phase, because the vibration isolation and buffer integrated bracket has low linear stiffness in the radial direction and high linear stiffness in the axial direction of the mounting platform 1, the momentum wheel 6 has almost no relative displacement in the axial direction and will only vibrate radially with the mounting platform 1. When the radial vibration displacement exceeds the buffer gap value in the buffer system 4, the buffer sleeve 102 contacts the buffer washer 5 to reduce the amplitude and ensure that the momentum wheel 6 safely passes through the launch phase.

[0054] After the satellite enters orbit, momentum wheel 6 is activated. The excitation generated at this time is mainly radial micro-disturbance force related to the rotational frequency of momentum wheel 6. The radial amplitude of the mounting platform 1 is less than the buffer gap, and the six vibration isolation components 2 undergo radial deformation accordingly. The internal butyl rubber dissipates the vibration energy. During the acceleration of momentum wheel 6 from 0 rpm, the disturbance force response is amplified by no more than two times, and the excitation within the operating speed range (1000 rpm to 5000 rpm) can be effectively attenuated. The disturbance force response transmitted from the mounting surface to the mounting interface between the bracket and the structural plate can be attenuated by more than 95% in the high-frequency band.

[0055] For the satellite momentum wheel 6 large damping vibration isolation and buffer integrated bracket provided by the present invention, the mounting platform 1 and the mounting bracket 3 are preferably manufactured by additive manufacturing. According to the overall satellite layout requirements, the angle between the upper plane of the mounting bracket 3 and the mounting surface of the satellite structure plate 7 can be changed, thereby changing the installation direction of the momentum wheel 6 in the satellite. It has a high degree of design freedom, good mechanical performance, and saves costs compared with traditional machining methods.

[0056] 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.

[0057] 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. An integrated support for vibration isolation and buffering of a satellite momentum wheel, characterized in that, It includes an installation platform (1), a vibration isolation component (2) and an installation bracket (3), one end of the vibration isolation component (2) is connected to the installation platform (1) and the other end of the vibration isolation component (2) is connected to the installation bracket (3); The vibration isolation component (2) includes two pairs of orthogonal elastic sheets (201) installed along the axial direction of the vibration isolation component (2), and each pair of elastic sheets (201) is filled with damping energy dissipation material (204); the transverse linear stiffness of the vibration isolation component in the two orthogonal directions is much smaller than the axial linear stiffness. The vibration isolation assembly (2) further includes two connecting blocks (202) and a retaining block (203), with the two connecting blocks (202) respectively disposed on both sides of the retaining block (203) along the axial direction of the vibration isolation assembly (2); One pair of the elastic sheets (201) connects a connecting block (202) and a retaining block (203), and another pair of the elastic sheets (201) connects another connecting block (202) and a retaining block (203); Each of the elastic sheets (201) is arc-shaped, and the middle part of the arc of each elastic sheet (201) is concave towards the central axis of the vibration isolation component (2).

2. The integrated vibration isolation and buffer bracket for satellite momentum wheels as described in claim 1, characterized in that, Each of the connecting blocks (202) is provided with a connector (202a) on the side opposite to the retaining block (203).

3. The integrated vibration isolation and buffer bracket for satellite momentum wheels as described in claim 2, characterized in that, The installation platform (1) is provided with a platform connection groove (101), the installation bracket (3) is provided with a bracket connection groove (301), the connector (202a) on one connecting block (202) of the vibration isolation component (2) is fastened to the platform connection groove (101), and the connector (202a) on the other connecting block (202) of the vibration isolation component (2) is fastened to the bracket connection groove (301).

4. The integrated vibration isolation and buffer bracket for satellite momentum wheels as described in claim 3, characterized in that, The platform connecting groove (101) is evenly distributed along the circumference of the mounting platform (1), and the bracket connecting groove (301) is evenly distributed along the circumference of the mounting bracket (3). The array axis of the platform connecting groove (101) and the array axis of the bracket connecting groove (301) are collinear. The number of platform connecting grooves (101) and the number of bracket connecting grooves (301) are equal. The distance between the center of any platform connecting groove (101) and the array axis is the same as the distance between the center of any bracket connecting groove (301) and the array axis.

5. The vibration isolation and buffer integrated bracket for satellite momentum wheels as described in claim 4, characterized in that, The central axis of the vibration isolation component (2) is parallel or collinear with the array axis of the platform connecting groove (101).

6. The integrated vibration isolation and buffer bracket for satellite momentum wheels as described in claim 1, characterized in that, A buffer system (4) is provided between the installation platform (1) and the installation bracket (3). The buffer system (4) includes a buffer sleeve (102) provided on the installation platform (1) and a buffer shaft (302) provided on the installation bracket (3). The buffer shaft (302) and the buffer sleeve (102) are coaxially nested together.

7. The integrated vibration isolation and buffer bracket for satellite momentum wheels as described in claim 6, characterized in that, A buffer washer (5) is fitted on the buffer shaft (302), the buffer washer (5) is in contact with the inner wall of the buffer sleeve (102), and a radial buffer space is formed between the inner wall of the buffer shaft (302) and the buffer sleeve (102). The buffer shaft (302) and the bottom of the replacement sleeve are fitted with a clearance.

8. A mounting structure for a satellite momentum wheel, characterized in that, The vibration isolation and buffer integrated bracket for satellite momentum wheel according to any one of claims 1-7 further includes momentum wheel (6) and satellite structure plate (7), the mounting platform (1) is fastened to momentum wheel (6), and the mounting bracket (3) is fastened to satellite structure plate (7).

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