CN115750663A - Vibration isolation device of control moment gyro and control moment gyro - Google Patents
Vibration isolation device of control moment gyro and control moment gyro Download PDFInfo
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- CN115750663A CN115750663A CN202211328855.8A CN202211328855A CN115750663A CN 115750663 A CN115750663 A CN 115750663A CN 202211328855 A CN202211328855 A CN 202211328855A CN 115750663 A CN115750663 A CN 115750663A
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Abstract
The invention relates to a vibration isolation device of a control moment gyroscope and the control moment gyroscope, wherein the vibration isolation device of the control moment gyroscope comprises two groups of same vibration isolation components, each vibration isolation component comprises a top plate, a bottom plate and a vibration isolator, and two vibration isolators are arranged between the bottom plate and the top plate; two sets of vibration isolation subassemblies are arranged side by side at intervals, the isolator on the vibration isolation subassembly inclines and draws close each other towards another vibration isolation subassembly respectively, and the center pin of four isolators of two sets of vibration isolation subassemblies is located four edges of same rectangular pyramid respectively. According to the vibration isolation device, the two vibration isolation assemblies are arranged, and the vibration isolators on the two vibration isolation assemblies are arranged into the pyramid-like shape, so that the stress of the four vibration isolators is uniformly balanced, the influence of the micro-vibration of the control moment gyroscope on a load (such as a space camera) can be reduced, the vibration environment in the transmitting stage can be inhibited, and in addition, the vibration isolation device is simple in design, convenient to install, stable in structure and suitable for batch application.
Description
Technical Field
The invention relates to the technical field of micro-vibration isolation, in particular to a vibration isolation device of a control moment gyro and the control moment gyro.
Background
Control Moment gyros (CMGs for short) are a class of important attitude Control execution mechanisms of a spacecraft, and provide acting Moment for space attitude adjustment of the spacecraft by using a momentum compensation principle. However, in the working process, the static and dynamic unbalance characteristics of the high-speed rotor of the actuating mechanism, the design defects of the bearing and other factors become the main source of micro-vibration on the spacecraft, and the high-precision and high-stability development requirements of the spacecraft are greatly restricted.
To date, there has been a lot of research on micro-vibration isolation devices at home and abroad. Typical viscous fluid damping vibration isolators include U.S. harb space telescopes, stewart-configuration platform vibration isolators, and knuckle-arm-beam-configuration vibration isolators, proposed by d.kamesh, india, among others. The existing micro-vibration isolation device generally has the defects of complex configuration, low reliability and stability, limited high-frequency vibration isolation effect and the like, thereby restricting the use of the micro-vibration isolation device.
Disclosure of Invention
In order to solve one or more of the above technical problems, the present invention provides a vibration isolation device for a control moment gyro and a control moment gyro.
The technical scheme for solving the technical problems is as follows: a vibration isolation device for a control moment gyroscope comprises two groups of identical vibration isolation assemblies, wherein each vibration isolation assembly comprises a top plate, a bottom plate and a vibration isolator; two groups of vibration isolation assemblies are arranged side by side at intervals, the vibration isolators on the vibration isolation assemblies respectively incline towards the other vibration isolation assembly and are close to each other, and the central shafts of the four vibration isolators of the two groups of vibration isolation assemblies are respectively positioned on the four edges of the same rectangular pyramid.
The beneficial effects of the invention are: according to the vibration isolation device, the two vibration isolation assemblies are arranged, and the vibration isolators on the two vibration isolation assemblies are arranged into the pyramid-like shape, so that the stress of the four vibration isolators is uniformly balanced, the influence of the micro-vibration of the control moment gyroscope on a load (such as a space camera) can be reduced, the vibration environment in the transmitting stage can be inhibited, and in addition, the vibration isolation device is simple in design, convenient to install, stable in structure and suitable for batch application.
On the basis of the technical scheme, the invention can be further improved as follows.
Further, the vibration isolator comprises an upper base, a lower base and a metal spring, wherein two ends of the metal spring are respectively and fixedly connected with the upper base and the lower base; the upper base is fixed on the top plate, and the lower base is fixed on the bottom plate.
Further, the top plate and the bottom plate are both horizontally arranged, the upper end of the upper base is a horizontal plane fixedly connected with the top plate, and the lower end of the upper base is an upper inclined plane fixedly connected with the upper end of the metal spring; the lower end of the lower base is a horizontal plane fixedly connected with the bottom plate, and the upper end of the lower base is a lower inclined plane fixedly connected with the lower end of the metal spring.
The beneficial effect of adopting the further scheme is that: the upper base and the lower base are matched, and the inclined planes are arranged on the upper base and the lower base respectively, so that the inclination angle and the inclination direction of the metal spring can be adjusted conveniently.
Further, the upper inclined plane and the lower inclined plane are arranged in parallel.
Furthermore, the metal spring comprises a spring sleeve, a plurality of rows of arc-shaped notches which are arranged in parallel to the axial direction of the spring sleeve are formed in the side wall of the spring sleeve, and two adjacent rows of arc-shaped notches are arranged in a crossed and staggered manner; damping glue is poured into the arc-shaped notch.
The beneficial effect of adopting the further scheme is that: the damping glue can increase damping and play a role in damping vibration of the emission active section and the in-orbit operation section.
Further, the arc incision is rectangular shape structure and follows spring sleeve's circumference extends, the notched both ends of arc are equipped with the circular port respectively, the diameter of circular port is greater than the notched width of arc.
Further, the metal spring is connected with the upper base through threads or integrally, and the metal spring is connected with the lower base through threads or integrally.
Further, a vibration isolator is installed between one end of the bottom plate and one end of the top plate, and a vibration isolator is installed between the other end of the bottom plate and the other end of the top plate.
The beneficial effect of adopting the further scheme is that: the vibration isolation supporting effect between the top plate and the bottom plate is better.
Further, the both ends of roof face towards respectively and extend with one side and form first connection otic placode, the both ends of bottom plate face respectively and extend with one side and form second connection otic placode, the both ends of isolator respectively with the first connection otic placode and the second connection otic placode fixed connection that correspond.
The beneficial effect of adopting the further scheme is that: the stable installation of the vibration isolator is convenient, and the stress condition of the whole vibration isolation device can be adjusted conveniently.
A control moment gyro comprises the vibration isolation devices and a control moment gyro body, wherein the control moment gyro body is respectively installed on top plates of two vibration isolation assemblies, and the center of gravity of the control moment gyro body is located on the central shaft of a rectangular pyramid.
The invention has the beneficial effects that: according to the control moment gyro disclosed by the invention, the control moment gyro body is arranged on the vibration isolation device, so that the vibration attenuation effect on the control moment gyro can be realized in the rocket launching stage, and the isolation effect on the micro vibration of the control moment gyro is also realized in the satellite in-orbit stage, so that the in-orbit imaging or other tasks of loads such as a space camera and the like are not influenced.
Drawings
FIG. 1 is a front view of the vibration isolation assembly of the present invention;
FIG. 2 is a schematic bottom view of the vibration isolation assembly of the present invention;
FIG. 3 is a schematic perspective view of the vibration isolation device of the present invention;
FIG. 4 is a schematic perspective view of a control moment gyroscope according to the present invention;
FIG. 5 is a schematic view of the vibration isolation apparatus of the present invention;
FIG. 6 is a schematic structural view of the vibration isolator of the present invention;
fig. 7 is a schematic perspective view of the metal spring of the present invention.
In the drawings, the components represented by the respective reference numerals are listed below:
1. a vibration isolation assembly; 11. a top plate; 12. a base plate; 13. a vibration isolator; 131. an upper base; 132. a lower base; 133. a metal spring; 134. an arc-shaped notch; 135. a circular hole; 136. damping glue; 14. a first connecting lug plate; 15. a second connecting lug plate; 16. a connection bump; 2. and the moment control gyro body.
Detailed Description
The principles and features of this invention are described below in conjunction with the following drawings, which are set forth by way of illustration only and are not intended to limit the scope of the invention.
As shown in fig. 1 to 7, the vibration isolation device for a control moment gyro of the present embodiment includes two identical vibration isolation assemblies 1, where each vibration isolation assembly 1 includes a top plate 11, a bottom plate 12 and two vibration isolators 13, and two vibration isolators 13 are installed between the bottom plate 12 and the top plate 11; the two groups of vibration isolation assemblies 1 are arranged side by side at intervals, the vibration isolators 13 on the vibration isolation assemblies 1 respectively incline towards the other vibration isolation assembly 1 and are close to each other, and the central shafts of the four vibration isolators 13 of the two groups of vibration isolation assemblies 1 are respectively positioned on the four edges of the same rectangular pyramid.
As shown in fig. 1 to 7, the vibration isolator 13 of the present embodiment includes an upper base 131, a lower base 132 and a metal spring 133, wherein two ends of the metal spring 133 are respectively fixedly connected to the upper base 131 and the lower base 132; the upper base 131 is fixed to the top plate 11, and the lower base 132 is fixed to the bottom plate 12.
As shown in fig. 1 and 3, the top plate 11 and the bottom plate 12 of the present embodiment are both horizontally arranged, the upper end of the upper base 131 is a horizontal plane fixedly connected with the top plate 11, and the lower end of the upper base 131 is an upper inclined plane fixedly connected with the upper end of the metal spring 133; the lower end of the lower base 132 is a horizontal plane fixedly connected to the bottom plate 12, and the upper end of the lower base 132 is a lower inclined plane fixedly connected to the lower end of the metal spring 133. The upper base and the lower base are matched, and the inclined planes are arranged on the upper base and the lower base respectively, so that the inclination angle and the inclination direction of the metal spring can be adjusted conveniently.
As shown in fig. 6, the upper slope and the lower slope of the present embodiment are arranged in parallel.
As shown in fig. 6 and 7, the metal spring 133 of the present embodiment includes a spring sleeve, a plurality of rows of arc-shaped notches 134 are formed on a side wall of the spring sleeve and arranged along an axial direction parallel to the spring sleeve, and two adjacent rows of arc-shaped notches 134 are arranged in a staggered manner; the arc-shaped notch 134 is filled with damping glue 136. The damping glue is injected into the arc-shaped notch of the metal spring in a pouring mode. The damping rubber material can be selected from polyurethane rubber, silicon rubber and the like, and the important requirements are good adhesion, large damping and small rigidity. The damping glue has the main function of increasing damping and plays a role in damping vibration of the emission active section and the on-rail running section. The rigidity of the system can be adjusted by adjusting the parameters of the metal spring, and the damping of the system can be adjusted by adjusting the material proportion of the damping glue.
As shown in fig. 6 and 7, the arc-shaped notch 134 of the present embodiment is in a long strip-shaped structure and extends along the circumferential direction of the spring sleeve, circular holes 135 are respectively disposed at two ends of the arc-shaped notch 134, and the diameter of the circular hole 135 is greater than the width of the arc-shaped notch 134.
Two adjacent arc-shaped incisions 134 that are staggered with each other are a group, and two groups of arc-shaped incisions are generally preferred, and one group, three groups or multiple groups of arc-shaped incisions can also be adopted. The material of the metal spring 133 is preferably an aluminum alloy in consideration of the properties such as the weight of the emission and the rigidity, and may be a titanium alloy or other metals. The rigidity of the metal spring can be adjusted by changing the outer diameter and the inner diameter of the metal spring, the thickness of the arc-shaped notch, the diameters of round holes at two ends of the arc-shaped notch, the width of the residual material after the arc-shaped notch is formed and the like.
As shown in fig. 1 to 6, the metal spring 133 of the present embodiment is connected to the upper base 131 by a screw or integrally, and the metal spring 133 is connected to the lower base 132 by a screw or integrally.
As shown in fig. 1 to 5, a vibration isolator 13 is installed between one end of the bottom plate 12 and one end of the top plate 11, and a vibration isolator 13 is installed between the other end of the bottom plate 12 and the other end of the top plate 11. The vibration isolation supporting effect between the top plate and the bottom plate is better.
As shown in fig. 1 and fig. 3, in this embodiment, two ends of the top plate 11 respectively extend towards the same side to form a first connecting ear plate 14, two ends of the bottom plate 12 respectively extend towards the same side to form a second connecting ear plate 15, and two ends of the vibration isolator 13 are respectively fixedly connected with the corresponding first connecting ear plate 14 and the second connecting ear plate 15. The stable installation of the vibration isolator is convenient, and the stress condition of the whole vibration isolation device can be adjusted conveniently.
In the vibration isolation device of the embodiment, for the purpose of uniform and balanced stress of the four vibration isolators, the four vibration isolators of the vibration isolation device are arranged in a pyramid configuration, and the four vibration isolators are symmetrically arranged relative to the X plane and the Y plane. In addition, the Z axis coincides with the central axis AB of the pyramid, and the central point O of the control moment gyro coincides with the central axis of the pyramid. The vibration absorber with the pyramid structure is adopted for layout, the gravity center of the moment gyro is controlled to be on the gravity center shaft of the pyramid, the stress is uniform, and no additional moment exists. The metal spring and the damping glue are used together, the metal spring provides rigidity required by vibration attenuation, and the damping glue plays a role in damping vibration attenuation. The whole vibration damper is simple in structure, good in reliability and stability and convenient to design, process and replace.
The vibration isolation device of the embodiment has the advantages that the two vibration isolation assemblies are arranged, the vibration isolators on the two vibration isolation assemblies are arranged into the pyramid-shaped shapes similar to a pyramid, so that the stress of the four vibration isolators is uniform and balanced, the influence of the micro-vibration of the control moment gyroscope on a load (such as a space camera) can be reduced, and the vibration environment in the transmitting stage can be inhibited.
As shown in fig. 4, the control moment gyro of the present embodiment includes the vibration isolation device, and further includes a control moment gyro body 2, the control moment gyro body 2 is respectively mounted on the top plates 11 of the two vibration isolation assemblies 1, and the center of gravity of the control moment gyro body 2 is located on the central axis of the rectangular pyramid. The edge of the top plate 11 is provided with a connecting bump 16, and the control moment gyroscope body 2 is fixed on the connecting bump 16.
The control moment gyro of this embodiment through installing control moment gyro body on the vibration isolation device, can play the damping effect to control moment gyro in rocket launch stage, and the satellite still plays the isolation effect to control moment gyro micro-vibration in the stage of the orbit to avoid influencing load such as space camera in the formation of image or other tasks executions in the orbit.
In the description of the present invention, it is to be understood that the terms "central," "longitudinal," "transverse," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," "circumferential," and the like are used in the orientations and positional relationships indicated in the drawings for convenience in describing the invention and to simplify the description, but are not intended to indicate or imply that the device or element so referred to must have a particular orientation, be constructed and operated in a particular orientation, and are not to be construed as limiting the invention.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or to implicitly indicate the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present invention, "a plurality" means at least two, e.g., two, three, etc., unless explicitly specified otherwise.
In the present invention, unless otherwise explicitly stated or limited, the terms "mounted," "connected," "fixed," and the like are to be construed broadly, e.g., as being permanently connected, detachably connected, or integral; can be mechanically or electrically connected; they may be directly connected or indirectly connected through intervening media, or they may be connected internally or in any other suitable relationship, unless expressly stated otherwise. The specific meanings of the above terms in the present invention can be understood according to specific situations by those of ordinary skill in the art.
In the present invention, unless expressly stated or limited otherwise, the first feature "on" or "under" the second feature may be directly contacting the second feature or the first and second features may be indirectly contacting each other through intervening media. Also, a first feature "on," "above," and "over" a second feature may be directly on or obliquely above the second feature, or simply mean that the first feature is at a higher level than the second feature. A first feature "under," "beneath," and "under" a second feature may be directly under or obliquely under the second feature, or may simply mean that the first feature is at a lesser elevation than the second feature.
In the description of the specification, reference to the description of "one embodiment," "some embodiments," "an example," "a specific example," or "some examples" or the like means that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, the schematic representations of the terms used above are not necessarily intended to refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, various embodiments or examples and features of different embodiments or examples described in this specification can be combined and combined by one skilled in the art without contradiction.
Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made to the above embodiments by those of ordinary skill in the art within the scope of the present invention.
Claims (10)
1. The vibration isolation device for the control moment gyroscope is characterized by comprising two groups of identical vibration isolation assemblies, wherein each vibration isolation assembly comprises a top plate, a bottom plate and a vibration isolator; two groups of vibration isolation assemblies are arranged side by side at intervals, the vibration isolators on the vibration isolation assemblies respectively incline towards the other vibration isolation assembly and are close to each other, and the central shafts of the four vibration isolators of the two groups of vibration isolation assemblies are respectively positioned on the four edges of the same rectangular pyramid.
2. The vibration isolation device of a control moment gyro according to claim 1, wherein the vibration isolator comprises an upper base, a lower base and a metal spring, and two ends of the metal spring are fixedly connected with the upper base and the lower base respectively; the upper base is fixed on the top plate, and the lower base is fixed on the bottom plate.
3. The vibration isolation device of a control moment gyro according to claim 2, wherein the top plate and the bottom plate are both horizontally arranged, the upper end of the upper base is a horizontal plane fixedly connected with the top plate, and the lower end of the upper base is an upper inclined plane fixedly connected with the upper end of the metal spring; the lower end of the lower base is a horizontal plane fixedly connected with the bottom plate, and the upper end of the lower base is a lower inclined plane fixedly connected with the lower end of the metal spring.
4. A vibration damping arrangement for a control moment gyro according to claim 3, characterized in that the upper and lower inclined surfaces are arranged in parallel.
5. The vibration isolation device for the control moment gyro according to claim 2, wherein the metal spring comprises a spring sleeve, a plurality of rows of arc-shaped notches are formed in the side wall of the spring sleeve and are arranged in parallel with the axial direction of the spring sleeve, and two adjacent rows of arc-shaped notches are arranged in a staggered manner; damping glue is poured into the arc-shaped notch.
6. The vibration isolation device of a control moment gyro according to claim 5, wherein the arc-shaped notch is of a long strip structure and extends along the circumferential direction of the spring sleeve, circular holes are respectively formed at two ends of the arc-shaped notch, and the diameter of each circular hole is larger than the width of the arc-shaped notch.
7. The vibration isolation apparatus for a control moment gyro according to claim 2, wherein the metal spring is connected with the upper base by a screw or integrally, and the metal spring is connected with the lower base by a screw or integrally.
8. The vibration isolation apparatus of a control moment gyro according to claim 1, wherein a vibration isolator is installed between one end of said bottom plate and one end of said top plate, and a vibration isolator is installed between the other end of said bottom plate and the other end of said top plate.
9. The vibration isolation apparatus for a control moment gyro according to claim 1, wherein both ends of the top plate extend toward the same side to form a first connecting ear plate, both ends of the bottom plate extend toward the same side to form a second connecting ear plate, and both ends of the vibration isolator are fixedly connected to the corresponding first connecting ear plate and the corresponding second connecting ear plate.
10. A control moment gyro, comprising the vibration isolation devices according to any one of claims 1 to 9, and further comprising a control moment gyro body mounted on top plates of the two vibration isolation assemblies, respectively, wherein the center of gravity of the control moment gyro body is located on the central axis of the rectangular pyramid.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202211328855.8A CN115750663A (en) | 2022-10-27 | 2022-10-27 | Vibration isolation device of control moment gyro and control moment gyro |
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| CN202211328855.8A CN115750663A (en) | 2022-10-27 | 2022-10-27 | Vibration isolation device of control moment gyro and control moment gyro |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN118008996A (en) * | 2023-12-28 | 2024-05-10 | 东莞理工学院 | Variable damping variable stiffness and broadband parallel vibration isolation system for spacecraft control moment gyro |
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- 2022-10-27 CN CN202211328855.8A patent/CN115750663A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN118008996A (en) * | 2023-12-28 | 2024-05-10 | 东莞理工学院 | Variable damping variable stiffness and broadband parallel vibration isolation system for spacecraft control moment gyro |
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