CN117212375A - Vibration isolator suitable for satellite momentum wheel vibration isolation support - Google Patents
Vibration isolator suitable for satellite momentum wheel vibration isolation support Download PDFInfo
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- CN117212375A CN117212375A CN202311051034.9A CN202311051034A CN117212375A CN 117212375 A CN117212375 A CN 117212375A CN 202311051034 A CN202311051034 A CN 202311051034A CN 117212375 A CN117212375 A CN 117212375A
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- 238000002955 isolation Methods 0.000 title claims abstract description 36
- 238000013016 damping Methods 0.000 claims abstract description 37
- 239000000463 material Substances 0.000 claims abstract description 21
- 230000021715 photosynthesis, light harvesting Effects 0.000 claims abstract description 8
- 238000005452 bending Methods 0.000 claims description 11
- 238000005265 energy consumption Methods 0.000 claims description 8
- 230000006835 compression Effects 0.000 claims 3
- 238000007906 compression Methods 0.000 claims 3
- 230000007704 transition Effects 0.000 claims 1
- 238000013461 design Methods 0.000 abstract description 3
- 238000012545 processing Methods 0.000 abstract description 3
- 238000000034 method Methods 0.000 description 3
- 230000003287 optical effect Effects 0.000 description 3
- 238000007789 sealing Methods 0.000 description 3
- 230000001629 suppression Effects 0.000 description 3
- 229920005549 butyl rubber Polymers 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 229910052751 metal Inorganic materials 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical group [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 1
- 229910000639 Spring steel Inorganic materials 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 229920001971 elastomer Polymers 0.000 description 1
- 230000005284 excitation Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 230000035945 sensitivity Effects 0.000 description 1
- 238000010008 shearing Methods 0.000 description 1
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
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Abstract
The application provides an isolator suitable for a satellite momentum wheel vibration isolation bracket, which comprises a first retaining block (2 a), a connecting block (3) and a second retaining block (2 b) which are distributed in sequence; the device also comprises two symmetrically arranged first elastic components (1 a) connected between the first holding block (2 a) and the connecting block (3), and two symmetrically arranged second elastic components (1 b) connected between the connecting block (3) and the second holding block (2 b); damping energy dissipation materials (5) are respectively arranged between the first elastic components (1 a) which are symmetrically arranged and between the second elastic components (1 b) which are symmetrically arranged. The application has lower transverse rigidity, higher axial rigidity and large damping characteristic, and can effectively meet the vibration isolation requirement of the momentum wheel by reasonably arranging the device between the bracket and the momentum wheel; the application has the advantages of simple and compact structure, convenient processing and assembly, high design freedom, stable and reliable performance, light weight, low cost and the like.
Description
Technical Field
The application relates to the technical field of satellite momentum wheel vibration isolation, in particular to a vibration isolator suitable for a satellite momentum wheel vibration isolation bracket. In particular to a large-damping vibration isolator which is suitable for a satellite momentum wheel vibration isolation bracket.
Background
With the continuous progress of remote sensing satellite technology, high-resolution satellites carrying various advanced optical loads become the current trend of earth observation satellites. Since such loads generally have extremely high sensitivity and performance is susceptible to small disturbances, satellite in-orbit micro-vibrations become a big factor limiting their resolution and stability of observation.
The momentum wheel is used as a typical micro-vibration source of a spacecraft such as a satellite, and when in-orbit operation, the momentum wheel can output broadband micro-excitation to the outside due to the characteristics of the structure of the momentum wheel, so that the micro-vibration is induced to the satellite platform, and the micro-vibration is transferred to sensitive optical load through the structure, so that the response of an optical load system is caused. Therefore, research on the micro-vibration suppression technology aiming at the momentum wheel is particularly important to the development of high-resolution satellites in China.
At present, the aim of vibration suppression is mainly achieved by installing a bracket with a passive vibration isolation function between the momentum wheel and the star, and the vibration isolation function is achieved by a plurality of vibration isolators connected in parallel between the momentum wheel and the bracket.
For the above problems, the following is searched:
patent document CN108443382a discloses an active-passive composite vibration isolator adopting electromagnetic negative rigidity and a control method, and the vibration isolator comprises a shell, a dowel bar, a cross beam spring piece, an annular rotor, a permanent magnet, a stator, a fixed iron core, a working air gap, a coil framework and an excitation coil. However, the application adopts the form of active electromagnetic negative rigidity, and can effectively reduce vibration isolation frequency bands although the negative rigidity is adjustable, control equipment and power supply resources are required to be attached, and meanwhile, the on-track reliability is not as good as that of the passive vibration isolation form adopted by the application.
Patent document CN109099107a discloses an eddy current vibration isolator for spacecraft micro-vibration suppression, comprising: the damping structure comprises a rigidity structure and an internal damping structure, wherein the lower side and the internal of the rigidity structure are provided with magnetic sealing structures for sealing the damping structure. However, the application requires additional permanent magnets and sealing structures due to eddy current damping, so that the application occupies a large volume and has a large overall weight.
Disclosure of Invention
Aiming at the defects in the prior art, the application aims to provide the vibration isolator suitable for the satellite momentum wheel vibration isolation bracket.
The application provides an isolator suitable for a satellite momentum wheel vibration isolation bracket, which comprises a first retaining block 2a, a connecting block 3 and a second retaining block 2b which are distributed in sequence;
further comprising two symmetrically arranged first elastic members 1a connected between the first holding block 2a and the connection block 3, and two symmetrically arranged second elastic members 1b connected between the connection block 3 and the second holding block 2b;
damping and energy-consuming materials 5 are respectively arranged between the first elastic components 1a and the second elastic components 1b which are symmetrically arranged.
Preferably, the first elastic member 1a and the second elastic member 1b are disposed upside down and orthogonal in cross section in the axial direction, and are intermediate-transited by the connection block 3.
Preferably, the first elastic member 1a and the second elastic member 1b are both elastic sheets 101;
the elastic sheet 101 has a C-shaped structure formed by elastically bending a flat plate;
one end of the elastic sheet 101 is embedded into the limit grooves 201 of the first holding block 2a and the second holding block 2b of the holding blocks 2, the elastic sheet 101 is fixed on the holding block inclined surface 202 of the limit groove 201 by using the screw and the pressing gasket 4, the other end of the elastic sheet 101 is embedded into the limit groove 301 of the connecting block 3, and the elastic sheet 101 is fixed on the connecting block inclined surface 302 by using the screw and the pressing gasket 4; when the two elastic sheets 101 are in place, only bending deformation can be generated to the central surface.
Preferably, the elastic members 1a and 1b are displaced laterally when receiving a lateral force in the bending direction of the elastic sheet 101.
Preferably, the elastic member 1 has a hyperbolic shape in lateral cross section; in the hyperbolic plane, the transverse stiffness of the elastic component 1 is far smaller than the stiffness in the other two translational directions.
Preferably, when the transverse vibration occurs, the elastic component 1 in the corresponding direction drives the damping energy dissipation material 5 to generate shear deformation, so as to dissipate vibration energy.
Preferably, the connecting block 3 has four limit grooves 301 which are orthogonally distributed; each limit groove 301 is connected with one elastic sheet 101; the lateral cross sections of the two symmetrically arranged elastic components 1 are mutually orthogonal after the elastic components are installed in place.
Preferably, the end face of the pressing pad 4 has rounded corners, allowing the elastic sheet 101 to be bent and deformed.
Preferably, the first holding block 2a is connected to the momentum wheel mounting platform 7 and the second holding block 2b is connected to the bracket 8.
Preferably, damping energy dissipation materials 5 are filled between the two symmetrically arranged first elastic parts 1a, and are encapsulated by a baffle 6; damping energy dissipation materials 5 are filled between the two symmetrically arranged second elastic parts 1b, and are encapsulated by a baffle 6.
The application also provides a satellite momentum wheel vibration isolation support, which comprises the vibration isolator suitable for the satellite momentum wheel vibration isolation support, wherein one or more vibration isolators which are connected in parallel and are suitable for the satellite momentum wheel vibration isolation support are connected between the momentum wheel mounting platform 7 and the support 8.
Compared with the prior art, the application has the following beneficial effects:
1. the application starts from the micro-excitation characteristic generated by the momentum wheel, and by virtue of smaller transverse rigidity and larger axial rigidity, the radial disturbance force related to rotation frequency generated when the momentum wheel works can be effectively isolated by reasonably arranging the momentum wheel between the bracket and the momentum wheel, and the vibration of the momentum wheel in the working rotation speed interval can be effectively inhibited by configuring reasonable structural parameters.
2. The application uses the bent elastic sheet as the elastic component, has simple and compact structure, is convenient to process and assemble, has convenient interface design with the bracket and the momentum wheel, and has obvious weight and cost advantages compared with the traditional grooving metal spring.
3. The application improves the energy consumption efficiency of the damping material by utilizing the deformation characteristic of the elastic component, has large damping characteristic, and can amplify and control the response of the disturbance force to be less than 2 times in the running process of the momentum wheel.
Drawings
Other features, objects and advantages of the present application will become more apparent upon reading of the detailed description of non-limiting embodiments, given with reference to the accompanying drawings in which:
FIG. 1 is a schematic view of the whole appearance of the present application.
Fig. 2 is an overall exploded view of the present application.
FIG. 3 is a schematic diagram showing a comparison of cross-sectional structures between angles according to the present application.
Fig. 4 is a schematic diagram of an embodiment of the present application.
The figure shows:
Detailed Description
The present application will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the present application, but are not intended to limit the application in any way. It should be noted that variations and modifications could be made by those skilled in the art without departing from the inventive concept. These are all within the scope of the present application.
The application aims to provide a large-damping vibration isolator suitable for a satellite momentum wheel vibration isolation support, which can connect a satellite momentum wheel with the support, effectively inhibit micro-interference force of the momentum wheel and ensure on-orbit normal operation of high-precision and high-resolution sensitive loads.
As shown in fig. 1, 2, 3 and 4, the present application provides a large damping vibration isolator suitable for a satellite momentum wheel vibration isolation support, wherein two orthogonal transverse rigidities of the large damping vibration isolator are close and far smaller than an axial rigidity, and the large damping vibration isolator comprises: elastic component 1, holding piece 2, connecting block 3, compress tightly gasket 4, damping power consumption material 5 and baffle 6.
The elastic member 1 comprises two symmetrically arranged elastic sheets 101; one end of the elastic sheet 101 is embedded in the limit groove 201 of the holding block 2, the elastic sheet 101 is fixed on the inclined plane 202 by using the screw and the pressing gasket 4, and the other end is embedded in the limit groove 301 of the connecting block 3, and the elastic sheet 101 is fixed on the inclined plane 302 by using the screw and the pressing gasket 4.
The elastic sheet 101 has a C-shaped structure formed by elastically bending a flat plate, and is flat in a free state, and the bending curvature is 0; when the two elastic sheets 101 are in place, bending deformation can only be generated to the central surface, and the lateral cross section of the elastic part 1 is hyperbolic.
Parameters of the elastic sheet 101 include width, thickness, mounting chord length, and chord height of the elastic sheet; wherein the installation chord length and chord height of the elastic sheet 101 can be determined by the installation length and the holding block inclined surface 202 and the connecting block inclined surface 203. Damping energy consumption materials 5 are filled between two elastic sheets 101 of the elastic component, and are packaged by a baffle 6, so that the influence of space irradiation environment on the damping energy consumption materials 5 is reduced. In a preferred embodiment, the elastic sheet 101 is made of spring steel, the damping energy dissipation material 5 is made of butyl rubber, and the rest key parts are made of aluminum alloy materials.
The connecting block 3 is provided with 4 limit grooves 301 which are distributed in an orthogonal mode; each limit groove 301 is respectively connected with 1 elastic sheet 101; as shown in fig. 3, the lateral cross sections of 2 of said elastic members 1 are orthogonal to each other after being mounted in place.
The structural parameters of the large damping vibration isolator include the width, thickness, mounting chord length and chord height of the elastic sheet 101; wherein 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 holding block 2 and the inclined surface 302 of the connecting block 3. In a preferred embodiment, the elastic sheet 101 is 10mm wide, 0.2mm thick, 30mm long with a mounting chord, 4mm high with a chord length of 65 Mn.
The end face of the pressing pad 4 has rounded corners, which allow the elastic sheet 101 to bend. Therefore, when the elastic member 1 receives a transverse force in the bending direction of the elastic sheet 101, a transverse displacement is liable to occur, that is, the transverse stiffness (in the hyperbolic plane) of the elastic member (1) is much smaller than the stiffness in the other two translational directions.
Damping energy consumption materials 5 are filled between two elastic sheets 101 of the elastic component 1 and are packaged by a baffle 6, so that the influence of space irradiation environment on the damping energy consumption materials 5 is reduced; when the application generates transverse vibration in a certain direction, the elastic component 1 in the corresponding direction can drive the damping energy dissipation material 5 to generate shearing deformation, thereby greatly dissipating vibration energy. In a preferred embodiment, the damping and energy dissipating material 5 is butyl rubber.
As shown in FIG. 4, a use form of the application is provided, 6 large damping vibration isolators suitable for a satellite momentum wheel vibration isolation support are provided, the large damping vibration isolators are circumferentially and uniformly distributed between the support 8 and the momentum wheel mounting platform 7, the large damping vibration isolators can be connected with the momentum wheel mounting platform 7 through threaded holes of an upper end joint 203a of a first holding block 2a, threaded holes of a lower end joint 203b of a second holding block 2b are connected with the support 8, the overall lower radial translational rigidity and the higher axial translational rigidity of the vibration isolation support are realized, and the radial disturbance force during startup operation of an on-orbit momentum wheel is ensured to be effectively controlled.
For the large damping vibration isolator suitable for the satellite momentum wheel vibration isolation bracket, the materials adopted in processing are mature staring materials, and the reliability is ensured. The structural parameters of the elastic component 1 can be flexibly adjusted according to actual requirements, and the design freedom degree is high. The application has simple and compact structure, is convenient for processing and assembly, and has obvious advantages in weight and economy compared with the traditional metal spring-rubber vibration isolator.
The application also provides a satellite momentum wheel vibration isolation support using the vibration isolator suitable for the satellite momentum wheel vibration isolation support, which comprises one or more large-damping vibration isolators connected in parallel, wherein the large-damping vibration isolators are connected with the satellite momentum wheel and the support, and the number of the parallel vibration isolators can be determined according to actual vibration isolation requirements.
In the description of the present application, it should be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, are merely for convenience in describing the present application and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present application.
The foregoing describes specific embodiments of the present application. It is to be understood that the application is not limited to the particular embodiments described above, and that various changes or modifications may be made by those skilled in the art within the scope of the appended claims without affecting the spirit of the application. The embodiments of the application and the features of the embodiments may be combined with each other arbitrarily without conflict.
Claims (10)
1. The vibration isolator suitable for the satellite momentum wheel vibration isolation support is characterized by comprising a first retaining block (2 a), a connecting block (3) and a second retaining block (2 b) which are distributed in sequence;
the device also comprises two symmetrically arranged first elastic components (1 a) connected between the first holding block (2 a) and the connecting block (3), and two symmetrically arranged second elastic components (1 b) connected between the connecting block (3) and the second holding block (2 b);
damping energy dissipation materials (5) are respectively arranged between the first elastic components (1 a) which are symmetrically arranged and between the second elastic components (1 b) which are symmetrically arranged.
2. Vibration isolator for a satellite momentum wheel vibration isolation mount according to claim 1, characterized in that the first elastic member (1 a) and the second elastic member (1 b) are axially reversed and cross-sectionally orthogonal arranged and intermediate transition through the connection block (3).
3. The vibration isolator for a satellite momentum wheel vibration isolation support according to claim 2, wherein the first elastic member (1 a) and the second elastic member (1 b) are elastic sheets (101);
the elastic sheet (101) is of a C-shaped structure formed by elastically bending a flat plate;
one end of the elastic sheet (101) is embedded into limit grooves (201) of the first holding block (2 a) and the second holding block (2 b) of the holding blocks (2), the elastic sheet (101) is fixed on a holding block inclined plane (202) of the limit groove (201) by using a screw and a compression gasket (4), the other end of the elastic sheet is embedded into a limit groove (301) of the connecting block (3), and the elastic sheet (101) is fixed on a connecting block inclined plane (302) by using the screw and the compression gasket (4); when the two elastic sheets (101) are in place, bending deformation can only be generated to the central surface.
4. A vibration isolator for a satellite momentum wheel vibration isolation mount according to claim 3, wherein the first elastic member (1 a) and the second elastic member (1 b) are arranged such that the elastic members (1) are displaced laterally when receiving a lateral force in the bending direction of the elastic sheet (101).
5. The vibration isolator for a satellite momentum wheel vibration isolation mount according to claim 4, characterized in that the elastic member (1) has a hyperbolic shape in lateral cross-section; in the hyperbolic plane, the transverse rigidity of the elastic part (1) is far smaller than the rigidity of the other two translation directions.
6. The vibration isolator for the satellite momentum wheel vibration isolation support according to claim 1, wherein when transverse vibration occurs, the elastic component (1) in the corresponding direction drives the damping energy dissipation material (5) to generate shear deformation, so as to consume vibration energy.
7. A vibration isolator for a satellite momentum wheel vibration isolation support according to claim 3, characterized in that the connection block (3) has four orthogonally distributed limit grooves (301); each limit groove (301) is respectively connected with one elastic sheet (101); the lateral sections of the two symmetrically arranged elastic components (1) are mutually orthogonal after the elastic components are arranged in place.
8. A vibration isolator for a satellite momentum wheel vibration isolation mount according to claim 3, characterized in that the end surface of the compression washer (4) has rounded corners allowing bending deformation of the elastic sheet (101).
9. The vibration isolator for a satellite momentum wheel vibration isolation mount according to claim 1, wherein the first holding block (2 a) is connected to a momentum wheel mounting platform (7) and the second holding block (2 b) is connected to a mount (8); damping energy consumption materials (5) are filled between the two symmetrically arranged first elastic parts (1 a), and are encapsulated by a baffle plate (6); damping energy consumption materials (5) are filled between the two symmetrically arranged second elastic parts (1 b), and the damping energy consumption materials are packaged by a baffle plate (6).
10. A satellite momentum wheel vibration isolation mount comprising a vibration isolator according to any one of claims 1 to 9 adapted for use in a satellite momentum wheel vibration isolation mount, wherein one or more vibration isolators adapted for use in a satellite momentum wheel vibration isolation mount in parallel are connected between the momentum wheel mounting platform (7) and the mount (8).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311051034.9A CN117212375A (en) | 2023-08-18 | 2023-08-18 | Vibration isolator suitable for satellite momentum wheel vibration isolation support |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311051034.9A CN117212375A (en) | 2023-08-18 | 2023-08-18 | Vibration isolator suitable for satellite momentum wheel vibration isolation support |
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| Publication Number | Publication Date |
|---|---|
| CN117212375A true CN117212375A (en) | 2023-12-12 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311051034.9A Pending CN117212375A (en) | 2023-08-18 | 2023-08-18 | Vibration isolator suitable for satellite momentum wheel vibration isolation support |
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| Country | Link |
|---|---|
| CN (1) | CN117212375A (en) |
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2023
- 2023-08-18 CN CN202311051034.9A patent/CN117212375A/en active Pending
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