CN117208232A - Vibration isolation and buffer integrated support and mounting structure for satellite momentum wheel - Google Patents
Vibration isolation and buffer integrated support and mounting structure for satellite momentum wheel Download PDFInfo
- Publication number
- CN117208232A CN117208232A CN202311036068.0A CN202311036068A CN117208232A CN 117208232 A CN117208232 A CN 117208232A CN 202311036068 A CN202311036068 A CN 202311036068A CN 117208232 A CN117208232 A CN 117208232A
- Authority
- CN
- China
- Prior art keywords
- vibration isolation
- momentum wheel
- mounting
- isolation assembly
- platform
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000002955 isolation Methods 0.000 title claims abstract description 97
- 239000000872 buffer Substances 0.000 title claims abstract description 41
- 238000013016 damping Methods 0.000 claims abstract description 29
- 239000000463 material Substances 0.000 claims abstract description 12
- 230000021715 photosynthesis, light harvesting Effects 0.000 claims abstract description 7
- 230000003139 buffering effect Effects 0.000 claims description 26
- 238000006073 displacement reaction Methods 0.000 abstract description 5
- 238000005452 bending Methods 0.000 abstract description 3
- 238000005265 energy consumption Methods 0.000 abstract description 2
- 238000010008 shearing Methods 0.000 abstract description 2
- 238000009434 installation Methods 0.000 description 14
- 230000004044 response Effects 0.000 description 4
- 230000000712 assembly Effects 0.000 description 3
- 238000000429 assembly Methods 0.000 description 3
- 230000002238 attenuated effect Effects 0.000 description 3
- 239000007853 buffer solution Substances 0.000 description 3
- 238000013461 design Methods 0.000 description 3
- 230000005284 excitation Effects 0.000 description 3
- 239000002905 metal composite material Substances 0.000 description 3
- 229910001069 Ti alloy Inorganic materials 0.000 description 2
- 239000000654 additive Substances 0.000 description 2
- 230000000996 additive effect Effects 0.000 description 2
- 229920005549 butyl rubber Polymers 0.000 description 2
- 230000008878 coupling Effects 0.000 description 2
- 238000010168 coupling process Methods 0.000 description 2
- 238000005859 coupling reaction Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000003754 machining Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 230000007246 mechanism Effects 0.000 description 2
- 229910052751 metal Inorganic materials 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012545 processing Methods 0.000 description 2
- 230000001629 suppression Effects 0.000 description 2
- 238000010146 3D printing Methods 0.000 description 1
- 229910000861 Mg alloy Inorganic materials 0.000 description 1
- 230000001133 acceleration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 238000004146 energy storage Methods 0.000 description 1
- 230000005764 inhibitory process Effects 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 229920002379 silicone rubber Polymers 0.000 description 1
- 239000004945 silicone rubber Substances 0.000 description 1
- 238000013519 translation Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
- F16F15/02—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems
- F16F15/04—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using elastic means
- F16F15/08—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using elastic means with rubber springs ; with springs made of rubber and metal
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
- B64G1/28—Guiding or controlling apparatus, e.g. for attitude control using inertia or gyro effect
- B64G1/285—Guiding or controlling apparatus, e.g. for attitude control using inertia or gyro effect using momentum wheels
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Aviation & Aerospace Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Physics & Mathematics (AREA)
- Acoustics & Sound (AREA)
- Mechanical Engineering (AREA)
- Radar, Positioning & Navigation (AREA)
- Vibration Prevention Devices (AREA)
Abstract
The application provides a vibration isolation and buffer integrated bracket and a mounting structure for a satellite momentum wheel, wherein the vibration isolation and buffer integrated bracket comprises a mounting platform, a vibration isolation assembly and a mounting bracket, one end of the vibration isolation assembly is connected with the mounting platform, and the other end of the vibration isolation assembly is connected with the mounting bracket; the vibration isolation assembly comprises two orthogonal pairs of elastic sheets which are axially arranged along the vibration isolation assembly, and damping energy dissipation materials are filled between any pair of elastic sheets. The device also comprises a momentum wheel and a satellite structure plate, wherein the mounting platform is fixedly connected with the momentum wheel, and the mounting bracket is fixedly connected with the satellite structure plate. When the vibration isolation assembly is subjected to transverse force in the bending direction of the elastic sheet, transverse displacement is easy to generate, the transverse linear rigidity of the vibration isolation assembly in two orthogonal directions is close to and far smaller than the axial linear rigidity, and when the vibration isolation assembly transversely vibrates, the elastic sheet in the corresponding direction can drive damping energy consumption materials to generate shearing deformation, so that vibration energy is greatly consumed, the amplitude of the momentum wheel is reduced, and the momentum wheel is ensured to safely pass through the transmitting section.
Description
Technical Field
The application relates to the technical field of vibration isolation of satellite momentum wheels, in particular to a vibration isolation and buffer integrated bracket for a satellite momentum wheel and an installation structure.
Background
The momentum wheel is used as a rotating component with important functions of positioning, energy storage, control and the like of spacecrafts such as satellites, and the like, and can output broadband tiny excitation to the outside due to the characteristics of the structure of the momentum wheel when in-orbit operation, so that the satellite platform is induced to generate tiny vibration, the pointing precision and stability of sensitive loads on the satellites are seriously affected, and the resolution ratio of an ultra-high precision instrument is reduced. 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.
Aiming at the problem, 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. However, in order to obtain a wider vibration isolation frequency band in engineering and simultaneously ensure that the momentum wheel can safely pass through the vibration environment of the transmitting section, an unlocking mechanism is generally required to be added to the vibration isolation bracket, so that additional quality and resource consumption can be brought, and meanwhile, the reliability of the system can be reduced.
The prior Chinese patent application document with the publication number of CN207374708U discloses a momentum wheel bracket for avoiding the influence of micro-vibration resonance, which comprises 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, a lug mounting plate, a momentum wheel bracket mounting hole and a momentum wheel mounting hole, and is used for mounting a momentum wheel executing mechanism of a spacecraft.
The support in the prior art only depends on improving the natural frequency to avoid coupling with the momentum wheel interference, does not have an on-orbit vibration isolation function, provides a rigid support for the momentum wheel in the transmitting section, and cannot provide a buffering function.
The present publication number is CN114060466B, which discloses a light vibration isolation metal composite flywheel bracket and a preparation method and application thereof, and belongs to the technical field of metal material structural design and processing. The metal composite flywheel bracket comprises a magnesium alloy bottom plate with light weight and high damping performance, a titanium alloy lattice sandwich flywheel mounting surface with a vibration buffering function, and a titanium alloy supporting beam with high rigidity; the lightweight vibration isolation metal composite flywheel bracket is prepared by a method combining metal block processing and metal 3D printing.
The bracket in the prior art has high first-order frequency and narrow vibration isolation frequency band, and cannot be suitable for isolating low-frequency disturbance. At present, an on-orbit vibration isolation requirement caused by a momentum wheel is needed to be met, and the momentum wheel is ensured to safely pass through a vibration environment of a transmitting section.
Disclosure of Invention
Aiming at the defects in the prior art, the application aims to provide a vibration isolation and buffering integrated bracket and a mounting structure for a satellite momentum wheel.
The application provides a vibration isolation and buffering integrated support for a satellite momentum wheel, which comprises a mounting platform, a vibration isolation assembly and a mounting support, wherein one end of the vibration isolation assembly is connected with the mounting platform, and the other end of the vibration isolation assembly is connected with the mounting support; the vibration isolation assembly comprises two orthogonal pairs of elastic thin sheets which are axially arranged along the vibration isolation assembly, and damping energy dissipation materials are filled between any pair of elastic thin sheets.
Preferably, the vibration isolation assembly further comprises two connecting blocks and a retaining block, and the two connecting blocks are respectively arranged at two sides of the retaining block along the axial direction of the vibration isolation assembly; one pair of the elastic sheets connects one connecting block and the holding block, and the other pair of the elastic sheets connects the other connecting block and the holding block.
Preferably, a joint is arranged on one side of any connecting block facing away from the retaining block.
Preferably, the mounting platform is provided with a platform connection groove, the mounting bracket is provided with a bracket connection groove, a connector on one connecting block of the vibration isolation assembly is fixedly connected with the platform connection groove, and a connector on the other connecting block of the vibration isolation assembly is fixedly connected with the bracket connection groove.
Preferably, the platform connecting grooves are uniformly distributed on the mounting platform along the circumferential direction of the mounting platform, the support connecting grooves are uniformly distributed on the mounting support along the circumferential direction of the mounting support, the array axes of the platform connecting grooves and the array axes of the support connecting grooves are collinear, the number of the platform connecting grooves is equal to the number of the support connecting grooves, and the distance between the center of each platform connecting groove and the array axis is the same as the distance between the center of each support connecting groove and the array axis.
Preferably, the central axis of the vibration isolation assembly is parallel or collinear with the array axis of the platform attachment recess.
Preferably, any one of the elastic sheets is arc-shaped, and the arc-shaped middle part of any one of the elastic sheets is concave towards the direction close to the central shaft of the vibration isolation assembly.
Preferably, a buffer system is arranged between the mounting platform and the mounting bracket, the buffer system comprises a buffer sleeve arranged on the mounting platform and a buffer shaft arranged on the mounting bracket, and the buffer shaft and the buffer sleeve are coaxially nested and mounted.
Preferably, the buffer shaft is sleeved with a buffer washer, the buffer washer is in contact with 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 buffer shaft is in clearance fit with the bottom of the impact exchange sleeve.
According to the installation structure for the satellite momentum wheel, provided by the application, the installation structure further comprises the momentum wheel and a satellite structure plate, the installation platform is fixedly connected with the momentum wheel, and the installation support is fixedly connected with the satellite structure plate.
Compared with the prior art, the application has the following beneficial effects:
1. according to the application, when the vibration isolation assembly is subjected to transverse force in the bending direction of the elastic sheet, transverse displacement is easy to generate, so that the transverse linear rigidity of the vibration isolation assembly in two orthogonal directions is close to and far smaller than the axial linear rigidity, and when the vibration isolation assembly transversely vibrates, the elastic sheet in the corresponding direction can drive the damping energy dissipation material to generate shearing deformation, so that vibration energy is greatly consumed, the vibration amplitude effect is reduced, and the momentum wheel is ensured to safely pass through the transmitting section.
2. According to the application, by starting from the micro-excitation characteristic generated by the momentum wheel, the device has high-efficiency inhibition capability on the radial disturbance force related to the rotation frequency generated by the momentum wheel during the operation, so that the response of the disturbance force of the momentum wheel is amplified by no more than twice during the rotation speed increasing process, and the vibration in the operation rotation speed interval (1000 rpm-5000 rpm) can be effectively attenuated.
3. The buffering system is simple in structure and high in bearing capacity, and can effectively buffer radial large-magnitude vibration suffered by the momentum wheel in the transmitting section, so that the response of the directional vibration is amplified by not more than 2 times; meanwhile, the bearing capacity is kept large enough in the axial direction, so that a traditional unlocking device is replaced, the momentum wheel is protected to safely pass through the transmitting section, and the micro-vibration isolation performance of the momentum wheel by the on-orbit section is not influenced.
4. The vibration isolation assembly adopted by the application has lower radial rigidity and higher axial-radial rigidity ratio, can well adapt to the vibration isolation requirement of the momentum wheel, and can improve the energy dissipation efficiency of the damping energy consumption material; the vibration isolation assembly adopts the elastic thin plate as the elastic element, has simple structure, is easy to assemble, and is convenient for miniaturization and light weight.
5. The vibration isolation assembly layout adopted by the application can fully utilize the rigidity characteristic of the vibration isolation assembly, stagger the natural frequency of radial translation and the natural frequencies of other 4 degrees of freedom, and ensure that the coupling vibration does not occur in the working frequency conversion interval of the momentum wheel.
6. The mounting bracket and the mounting platform are processed by adopting an advanced additive manufacturing technology, so that the mounting bracket and the mounting platform have high design freedom and good mechanical performance, and cost is saved compared with a traditional machining mode.
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 diagram of the overall structure of an integrated vibration isolation and buffer bracket embodying the present application;
fig. 2 is a schematic view of the overall structure of a vibration isolation assembly embodying the present application;
FIG. 3 is a schematic view of the structure of the mounting surface of the mounting platform and mounting bracket of the present application;
fig. 4 is a schematic diagram of a semi-sectional structure of a bracket mainly embodying vibration isolation and buffering of the present application;
FIG. 5 is a schematic view of the overall structure of a mounting bracket embodying the present application;
fig. 6 is a schematic view of a mounting structure for a momentum wheel of a satellite according to the present application.
The figure shows:
mounting platform 1 damping energy dissipation material 204
Platform connection groove 101 mounting bracket 3
Buffer sleeve 102 bracket connection groove 301
Vibration isolation assembly 2 buffer shaft 302
Elastic sheet 201 cushioning system 4
Buffer gasket 5 of holding block 203
Joint 202a momentum wheel 6
Connecting block 202 satellite structural plate 7
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.
As shown in fig. 1 and 2, the vibration isolation and buffering integrated support and the installation structure for the satellite momentum wheel provided by the application comprise an installation platform 1, a vibration isolation assembly 2 and an installation support 3, wherein one end of the vibration isolation assembly 2 is connected with the installation platform 1, and the other end of the vibration isolation assembly 2 is connected with the installation support 3. A buffer system 4 is also arranged between the mounting platform 1 and the mounting bracket 3. The vibration isolation assembly 2 comprises two orthogonal pairs of elastic sheets 201 which are axially arranged along the vibration isolation assembly 2, and damping energy dissipation materials 204 are filled between any pair of elastic sheets 201.
Specifically, the vibration isolation assembly 2 further includes two connection blocks 202 and one holding block 203, and the two connection blocks 202 are disposed on both sides of the holding block 203 in the axial direction of the vibration isolation assembly 2, respectively. One pair of elastic sheets 201 connects one connection block 202 and holding block 203, and the other pair of elastic sheets 201 connects the other connection block 202 and holding block 203. One possible implementation is: the elastic sheet 201 is processed by 65Mn, has the thickness of 0.2mm and the chord length after being installed in place is 30mm. Further, any one of the elastic sheets 201 is arc-shaped, and the arc-shaped middle part of any one of the elastic sheets 201 is concave towards the direction close to the central axis of the vibration isolation assembly 2.
The vibration isolation assembly 2 is subject to lateral displacement when subjected to a lateral force in the bending direction of the elastic lamina 201, and thus the lateral linear stiffness of the vibration isolation assembly 2 in two orthogonal directions is close and much smaller than the axial linear stiffness. The damping and energy-dissipating materials 204 are filled between the elastic sheets 201, and when the vibration isolation assembly 2 vibrates transversely, the elastic sheets 201 in the corresponding directions drive the damping and energy-dissipating materials 204 to generate shear deformation, so that vibration energy is greatly dissipated. In one possible embodiment: butyl rubber is selected as the damping and energy dissipating material 204.
As shown in fig. 3, 4 and 5, more specifically, the mounting platform 1 is provided with a platform connection groove 101, the mounting bracket 3 is provided with a bracket connection groove 301, both the platform connection groove 101 and the bracket connection groove 301 may be rectangular grooves, and two ends of the vibration isolation assembly 2 are respectively fastened and connected with the mounting platform 1 and the mounting bracket 3. Further, the two connection blocks 202 in the vibration isolation assembly 2 are each provided with a joint 202a on a side facing away from the holding block 203, and the joint 202a on one connection block 202 of the vibration isolation assembly 2 is fixedly connected with the platform connection groove 101, and the joint 202a on the other connection block 202 of the vibration isolation assembly 2 is fixedly connected with the bracket connection groove 301.
More specifically, the platform connecting grooves 101 are uniformly distributed on the mounting platform 1 along the circumferential direction of the mounting platform 1, the support connecting grooves 301 are uniformly distributed on the mounting support 3 along the circumferential direction of the mounting support 3, the array axes of the platform connecting grooves 101 and the array axes of the support connecting grooves 301 are collinear, the number of the platform connecting grooves 101 and the number of the support connecting grooves 301 are equal, and the distance between the center of any platform connecting groove 101 and the array axis and the distance between the center of any support connecting groove 301 and the array axis are the same.
One possible implementation is: six uniformly distributed platform connecting grooves 101 are formed in the mounting platform 1 along the circumferential direction, and six uniformly distributed bracket connecting grooves 301 are formed in the mounting bracket 3 along the circumferential direction. The center of the platform connection groove 101 and the bracket connection groove 301 are located at the same circumference diameter. In a preferred embodiment, the distribution diameter is 240mm.
The number of the vibration isolation assemblies 2 is six, and the joints 202a of the vibration isolation assemblies 2 are matched with the platform connecting grooves 101 and the bracket connecting grooves 301. The upper end of the vibration isolation assembly 2 is fixedly connected with the mounting platform 1 through a joint 202a, and the lower end of the vibration isolation assembly 2 is fixedly connected with the mounting bracket 3 through the joint 202 a. After the vibration isolation assembly 2 is connected with the mounting platform 1 and the mounting bracket 3, the axis of the vibration isolation assembly 2 is parallel or collinear with the array axes of the rectangular grooves of the platform and the rectangular grooves of the bracket, and the cross section of the vibration isolation assembly 2 is perpendicular to the symmetry plane of the mounting bracket 3.
The damping system 4 comprises a damping sleeve 102 arranged on the mounting platform 1 and a damping shaft 302 arranged on the mounting bracket 3, wherein the damping shaft 302 and the damping sleeve 102 are coaxially nested. The central axis of the buffer sleeve 102 coincides with the array axis of the stage connecting grooves 101, and the central axis of the buffer shaft 302 coincides with the array axis of the holder connecting grooves 301. After the vibration isolation assembly 2 is connected with the mounting platform 1 and the mounting bracket 3, the buffer sleeve 102 and the buffer shaft 302 form nested matching. The buffer shaft 302 is sleeved with a buffer washer 5, the buffer washer 5 is in contact with the inner wall of the buffer sleeve 102, a radial buffer space is formed between the buffer shaft 302 and the inner wall of the buffer sleeve 102, and the buffer shaft 302 is in clearance fit with the bottom of the buffer sleeve. In a preferred embodiment: the material of the cushion ring 5 is silicone rubber.
The application provides a connection mode of a buffer gasket 5 and a buffer shaft 302, which comprises the following steps: the buffer shaft 302 is provided with an annular groove, and the buffer washer 5 is embedded in the annular groove.
According to the installation structure for the satellite momentum wheel, as shown in fig. 6, the installation structure further comprises a momentum wheel 6 and a satellite structure plate 7, the installation platform 1 is fixedly connected with the momentum wheel 6, and the installation support 3 is fixedly connected with the satellite structure plate 7.
Specifically, during satellite assembly, the momentum wheel 6 is arranged in the center of the upper surface of the mounting platform 1 through a screw, and the vibration isolation and buffering integrated bracket is integrally connected with the satellite structural plate 7 through a light hole in the bottom surface of the mounting bracket 3 in a threaded manner. When the satellite is in the launching section, the vibration isolation and buffering integrated bracket has smaller linear rigidity along the radial direction of the mounting platform 1 and has larger linear rigidity along the axial direction, so that the momentum wheel 6 almost has no relative displacement in the axial direction and only can vibrate along with the mounting platform 1 in the radial direction, and when the radial vibration displacement exceeds a buffering clearance value in the buffering system 4, the buffering sleeve 102 contacts with the buffering gasket 5, the effect of reducing the amplitude is achieved, and the momentum wheel 6 is ensured to safely pass through the launching section.
After the satellite enters orbit, the momentum wheel 6 starts up to work, excitation generated at the moment is mainly radial micro-interference force related to rotation frequency of the momentum wheel 6, radial amplitude of the mounting platform 1 is smaller than a buffer gap, six vibration isolation assemblies 2 follow-up to generate radial deformation, and butyl rubber in the interior dissipates vibration energy. During acceleration of the momentum wheel 6 from 0rpm, the disturbance force response is amplified by no more than twice, and the excitation in the working speed interval (1000 rpm-5000 rpm) can be effectively attenuated, and the disturbance force response transmitted from the mounting surface to the mounting interface of the bracket and the structural plate can be attenuated by more than 95% in the high frequency band.
For the large-damping vibration isolation and buffering integrated support for the satellite momentum wheel 6, the mounting platform 1 and the mounting support 3 are preferably manufactured by additive manufacturing, and the angle between the upper plane of the mounting support 3 and the mounting surface of the satellite structural plate 7 can be changed according to the whole satellite layout requirement, so that the mounting direction of the momentum wheel 6 in a star body is changed, the design freedom degree is high, the mechanical performance is good, and the cost is saved compared with the traditional machining mode.
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 isolation and buffering integrated support for the satellite momentum wheel is characterized by comprising a mounting platform (1), a vibration isolation assembly (2) and a mounting support (3), wherein one end of the vibration isolation assembly (2) is connected with the mounting platform (1), and the other end of the vibration isolation assembly (2) is connected with the mounting support (3);
the vibration isolation assembly (2) comprises two orthogonal pairs of elastic sheets (201) which are axially arranged along the vibration isolation assembly (2), and damping energy dissipation materials (204) are filled between any pair of elastic sheets (201).
2. The integrated vibration isolation and damping support for a satellite momentum wheel according to claim 1, wherein the vibration isolation assembly (2) further comprises two connection blocks (202) and one holding block (203), the two connection blocks (202) being arranged on both sides of the holding block (203) along the axial direction of the vibration isolation assembly (2), respectively;
one pair of the elastic sheets (201) connects one connection block (202) and the holding block (203), and the other pair of the elastic sheets (201) connects the other connection block (202) and the holding block (203).
3. The integrated vibration isolation and damping mount for a satellite momentum wheel according to claim 2, wherein a joint (202 a) is provided on either side of the connection block (202) facing away from the retaining block (203).
4. A vibration isolation and buffering integrated support for a satellite momentum wheel according to claim 3, characterized in that a platform connection groove (101) is arranged on the mounting platform (1), a support connection groove (301) is arranged on the mounting support (3), a joint (202 a) on one connecting block (202) of the vibration isolation assembly (2) is tightly connected with the platform connection groove (101), and a joint (202 a) on the other connecting block (202) of the vibration isolation assembly (2) is tightly connected with the support connection groove (301).
5. The vibration isolation and buffering integrated bracket for the satellite momentum wheel according to claim 4, wherein a plurality of platform connecting grooves (101) are uniformly distributed on the mounting platform (1) along the circumferential direction of the mounting platform (1), a plurality of bracket connecting grooves (301) are uniformly distributed on the mounting bracket (3) along the circumferential direction of the mounting bracket (3), the array axes of the platform connecting grooves (101) and the array axes of the bracket connecting grooves (301) are collinear, the number of the platform connecting grooves (101) and the number of the bracket connecting grooves (301) are equal, and the distance between the center of any one of the platform connecting grooves (101) and the array axis and the distance between the center of any one of the bracket connecting grooves (301) and the array axis are the same.
6. The integrated vibration isolation and damping mount for a satellite momentum wheel according to claim 5, wherein the central axis of the vibration isolation assembly (2) is parallel or collinear with the array axis of platform attachment grooves (101).
7. The integrated vibration isolation and damping support for a satellite momentum wheel according to claim 1, wherein any one of the elastic sheets (201) is arc-shaped, and the arc-shaped middle part of any one of the elastic sheets (201) is concave in a direction approaching to the central axis of the vibration isolation assembly (2).
8. The integrated vibration isolation and damping support for a satellite momentum wheel according to claim 1, wherein a damping system (4) is arranged between the mounting platform (1) and the mounting support (3), the damping system (4) comprises a damping sleeve (102) arranged on the mounting platform (1) and a damping shaft (302) arranged on the mounting support (3), and the damping shaft (302) and the damping sleeve (102) are coaxially nested and mounted.
9. The vibration isolation and buffering integrated support for the satellite momentum wheel according to claim 8, wherein a buffering washer (5) is sleeved on the buffering shaft (302), the buffering washer (5) is in contact with the inner wall of the buffering sleeve (102), and a radial buffering space is formed between the buffering shaft (302) and the inner wall of the buffering sleeve (102);
the buffer shaft (302) is in clearance fit with the bottom of the exchange sleeve.
10. A mounting structure for a satellite momentum wheel, characterized in that a vibration isolation and buffering integrated bracket for a satellite momentum wheel according to any one of claims 1-9 is adopted, and the mounting structure further comprises a momentum wheel (6) and a satellite structural plate (7), wherein the mounting platform (1) is fixedly connected with the momentum wheel (6), and the mounting bracket (3) is fixedly connected with the satellite structural plate (7).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311036068.0A CN117208232A (en) | 2023-08-16 | 2023-08-16 | Vibration isolation and buffer integrated support and mounting structure for satellite momentum wheel |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311036068.0A CN117208232A (en) | 2023-08-16 | 2023-08-16 | Vibration isolation and buffer integrated support and mounting structure for satellite momentum wheel |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117208232A true CN117208232A (en) | 2023-12-12 |
Family
ID=89043310
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311036068.0A Pending CN117208232A (en) | 2023-08-16 | 2023-08-16 | Vibration isolation and buffer integrated support and mounting structure for satellite momentum wheel |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117208232A (en) |
-
2023
- 2023-08-16 CN CN202311036068.0A patent/CN117208232A/en active Pending
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP2180203B1 (en) | Vibration isolators | |
| US7997157B2 (en) | Control moment gyroscope | |
| EP0069787A1 (en) | A cushioned mounting device | |
| CN105134874B (en) | Satellite flywheel vibration isolation and surge combination formula support | |
| CN103486176A (en) | Micro-vibration integrated dynamic vibration absorber for satellite flywheel | |
| US8876091B2 (en) | Insulating coating with mass amplification | |
| JP5680206B2 (en) | Antenna device | |
| CN117208232A (en) | Vibration isolation and buffer integrated support and mounting structure for satellite momentum wheel | |
| JP2015102244A (en) | Isolators having nested flexure devices and methods for production thereof | |
| Yuan et al. | Microvibration isolation in sensitive payloads: methodology and design | |
| JP5680207B2 (en) | Antenna device | |
| CN114590421B (en) | Multi-friction contact surface nonlinear vibration absorption-energy consumption device for momentum wheel | |
| EP3315419B1 (en) | Mass efficient reaction wheel assembly systems including multi-faceted bracket structures | |
| CN114877012B (en) | Self-balancing active and passive vibration damper | |
| JP2000145889A (en) | Fastening structure of on-board mounted apparatus | |
| CN104879414A (en) | Viscoelastic damping truss vibration isolator | |
| JP4236752B2 (en) | Support mount | |
| CN110486405B (en) | Vibration isolation system with annular metal rubber vibration isolator | |
| CN112829967B (en) | Vibration isolation device suitable for satellite control moment gyroscope | |
| CN117212375A (en) | Vibration isolator suitable for satellite momentum wheel vibration isolation support | |
| KR102638917B1 (en) | Control moment gyro | |
| CN117602114A (en) | Positioning device suitable for on-orbit installation and anti-drifting of space electronic equipment | |
| CN217682989U (en) | Low-amplification rubber shock absorber | |
| CN217805340U (en) | Satellite reaction flywheel module and spacecraft attitude control actuating mechanism | |
| CN114300824A (en) | Large phased array antenna unfolding posture adjusting mechanism suitable for high-orbit environment |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |