CN204004165U - A kind of for suppressing the astrovehicle non-linear vibration damping device of micro-vibration in-orbit - Google Patents
A kind of for suppressing the astrovehicle non-linear vibration damping device of micro-vibration in-orbit Download PDFInfo
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- CN204004165U CN204004165U CN201420010150.6U CN201420010150U CN204004165U CN 204004165 U CN204004165 U CN 204004165U CN 201420010150 U CN201420010150 U CN 201420010150U CN 204004165 U CN204004165 U CN 204004165U
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- permanent magnet
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- vibration
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Abstract
The utility model discloses a kind ofly for suppressing the astrovehicle non-linear vibration damping device of micro-vibration in-orbit, comprise cavity, spring, annular permanent magnet, damping and permanent magnet; The inwall of described annular permanent magnet and cavity is fixed together, and described spring one end is connected with the top of cavity, and the other end is connected with permanent magnet through the inner circle of annular permanent magnet; Described damping one end is connected with the top of cavity, and the other end is connected with permanent magnet through the inner circle of annular permanent magnet.The distinctive structural design of the utility model, be arranged on the position high to vibration damping requirement, astrovehicle inside, make it be suitable for carrying out vibration suppression to working in the structure of microgravity environment, therefore for working in the structural vibration in astrovehicle in space environment, suppress to have good result.This apparatus structure is simple, easily manufactured, cost is low.
Description
Technical field
The utility model relates to mechanical vibration damping field, particularly a kind of for suppressing the astrovehicle non-linear vibration damping device of micro-vibration in-orbit.
Background technique
Growing along with space technology, the vibration suppression problem under the microgravity environment of astrovehicle also becomes more and more outstanding in-orbit, has had a strong impact on the reliability and stability of the precision type instrument such as space camera precision, even causes serious disaster accident.Astrovehicle is at the residing special microgravity working environment of the outer space, more complicated under its operating mode force of gravity environment, and spacecraft structure is flexible greatly in-orbit, damping is little and wideband, natural frequency can not change easily, very responsive to electromagnetic interference, therefore for the key structure vibration suppression of astrovehicle in-orbit, be, insoluble problem.Existing four kinds of microgravity vibration isolation systems are used to space science experiment in the world at present, are respectively suspension instantaneous acceleration suppressors (STABLE); Experiment cabinet active vibration isolation system (ARIS); Microgravity vibrating isolation system (MIM); The integrated microgravity vibrating isolation system of glove box (g-LIMIT).But these microgravity vibration isolation systems also exist and can only realize and suppressing for low frequency or dither, be difficult to realize wideband vibration suppression, the problem such as self reliability is not enough, and vibration isolation quality is larger.For experiment cabinet active vibration isolation system, because astrovehicle flexibility is increasing in-orbit, mode is intensive, and ACTIVE CONTROL cannot adapt to close frequency and reliability control system is low etc. that reason cannot be applied.
Model utility content
The utility model proposes a kind ofly for suppressing the astrovehicle non-linear vibration damping device of micro-vibration in-orbit, object is to solve the inner key structure vibration suppression of the astrovehicle problem under microgravity environment.This device can be arranged on astrovehicle inside, and quality is little, and this becomes the natural frequency of structure in astrovehicle hardly, to electronic component in astrovehicle, without electromagnetic effect, can realize the non-linear vibration damping device of wideband vibration suppression.
The technological scheme that the utility model technical solution problem adopts is:
For suppressing an astrovehicle non-linear vibration damping device for micro-vibration in-orbit, comprise cavity, spring, annular permanent magnet, damping and permanent magnet; The inwall of described annular permanent magnet and cavity is fixed together, and described spring one end is connected with the top of cavity, and the other end is connected with permanent magnet through the inner circle of annular permanent magnet; Described damping one end is connected with the top of cavity, and the other end is connected with permanent magnet through the inner circle of annular permanent magnet.
Further, described cavity is cylinder-shaped thin wall cavity, one end sealing, an end opening.
Further, described spring is strong nonlinearity spiral spring, and elastic force becomes the spring of strong nonlinearity relation with kinematic parameter.
Further, the position of described annular permanent magnet in cavity is the mid point of spring length under static balancing state.
Further, the magnetic pole of described annular permanent magnet is located thereon lower two end faces, and upper-end surface is the S utmost point, and lower end surface is the N utmost point.
Further, described permanent magnet is cylindrical, and its radius is less than the internal diameter of cavity, can in cavity, move up and down.
Further, the magnetic pole of described permanent magnet is located thereon lower two end faces, and upper-end surface is the N utmost point, and lower end surface is the S utmost point.
Compared with prior art, the utlity model has following substantive distinguishing features and advantage:
The distinctive structural design of the utility model, be arranged on the position high to vibration damping requirement, astrovehicle inside, make it be suitable for carrying out vibration suppression to working in the structure of microgravity environment, therefore for working in the structural vibration in astrovehicle in space environment, suppress to have good result.Whole device quality is less, changes hardly the natural frequency of astrovehicle inner structure.Spring in this device is strong nonlinearity spring, therefore can realize wideband vibration suppression.Cavity in this device adopts the material of electromagnetic shielding to make, therefore to electronic component in astrovehicle without electromagnetic interference.This apparatus structure is simple, easily manufactured, cost is low.
Accompanying drawing explanation
Fig. 1 is the structural representation of the utility model device.
Embodiment
Below in conjunction with accompanying drawing, specific embodiment of the utility model is described further.
As shown in Figure 1, a kind of for suppressing the astrovehicle non-linear vibration damping device of micro-vibration in-orbit, comprise cavity 1, spring 2, annular permanent magnet 3, damping 4 and permanent magnet 5; Described annular permanent magnet 3 is fixed together with the inwall of cavity 1, and described spring 2 one end are connected with the top of cavity 1, and the other end is connected with permanent magnet 5 through the inner circle of annular permanent magnet 3; Described damping 4 one end are connected with the top of cavity 1, and the other end is connected with permanent magnet 5 through the inner circle of annular permanent magnet 3.
Described cavity 1 is cylinder-shaped thin wall cavity, one end sealing, an end opening.Described spring 2 is strong nonlinearity spiral spring, and spring rate value is given by simulation analysis or experimental result by the concrete structure that suppresses as required vibration.The position of described annular permanent magnet 3 in cavity 1 is the mid point of spring 2 length under static balancing state.The magnetic pole of described annular permanent magnet 3 is located thereon lower two end faces, and upper-end surface is the S utmost point, and lower end surface is the N utmost point.The concrete structure that the damping value of described damping 4 suppresses vibration is as required given by simulation analysis or experimental result.Described permanent magnet 5 is cylindrical, and its radius is less than the internal diameter of cavity 1, can in cavity 1, move up and down.The magnetic pole of described permanent magnet 5 is located thereon lower two end faces, and upper-end surface is the N utmost point, and lower end surface is the S utmost point.
Working principle of the present utility model is: cavity 1 is fixed in astrovehicle, and when vibration occurs astrovehicle inner structure, cavity 1 vibrates together with annular permanent magnet 3 generals thereupon.Because annular permanent magnet 3 lower end surfaces are the N utmost point, permanent magnet 5 upper-end surfaces are the N utmost point, therefore the magnetic force between annular permanent magnet 3 and permanent magnet 5 is repulsive force, under magnetic force, permanent magnet 5 will be done the forced vibration of vertical direction with respect to cavity 1, the Kind of Nonlinear Dynamical System consisting of the damping 4 that is connected with cavity 1 and permanent magnet 5 and spring 2 completes the vibration suppression under wide band.
Claims (7)
1. for suppressing an astrovehicle non-linear vibration damping device for micro-vibration in-orbit, it is characterized in that, comprise cavity (1), spring (2), annular permanent magnet (3), damping (4) and permanent magnet (5); Described annular permanent magnet (3) is fixed together with the inwall of cavity (1), and described spring (2) one end is connected with the top of cavity (1), and the other end is connected with permanent magnet (5) through the inner circle of annular permanent magnet (3); Described damping (4) one end is connected with the top of cavity (1), and the other end is connected with permanent magnet (5) through the inner circle of annular permanent magnet (3).
According to shown in claim 1 for suppressing the astrovehicle non-linear vibration damping device of micro-vibration in-orbit, it is characterized in that, described cavity (1) is cylinder-shaped thin wall cavity, one end sealing, an end opening.
According to shown in claim 1 for suppressing the astrovehicle non-linear vibration damping device of micro-vibration in-orbit, it is characterized in that, described spring (2) is strong nonlinearity spiral spring, elastic force becomes the spring of strong nonlinearity relation with kinematic parameter.
According to shown in claim 1 for suppressing the astrovehicle non-linear vibration damping device of micro-vibration in-orbit, it is characterized in that, the position of described annular permanent magnet (3) in cavity (1) is the mid point of spring (2) length under static balancing state.
According to shown in claim 1 for suppressing the astrovehicle non-linear vibration damping device of micro-vibration in-orbit, it is characterized in that, the magnetic pole of described annular permanent magnet (3) is located thereon lower two end faces, upper-end surface is the S utmost point, lower end surface is the N utmost point.
According to shown in claim 1 for suppressing the astrovehicle non-linear vibration damping device of micro-vibration in-orbit, it is characterized in that, described permanent magnet (5) is cylindrical, its radius is less than the internal diameter of cavity (1), can in cavity (1), move up and down.
According to shown in claim 1 for suppressing the astrovehicle non-linear vibration damping device of micro-vibration in-orbit, it is characterized in that, the magnetic pole of described permanent magnet (5) is located thereon lower two end faces, upper-end surface is the N utmost point, lower end surface is the S utmost point.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420010150.6U CN204004165U (en) | 2014-01-08 | 2014-01-08 | A kind of for suppressing the astrovehicle non-linear vibration damping device of micro-vibration in-orbit |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420010150.6U CN204004165U (en) | 2014-01-08 | 2014-01-08 | A kind of for suppressing the astrovehicle non-linear vibration damping device of micro-vibration in-orbit |
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| Publication Number | Publication Date |
|---|---|
| CN204004165U true CN204004165U (en) | 2014-12-10 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420010150.6U Withdrawn - After Issue CN204004165U (en) | 2014-01-08 | 2014-01-08 | A kind of for suppressing the astrovehicle non-linear vibration damping device of micro-vibration in-orbit |
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| CN (1) | CN204004165U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103758921A (en) * | 2014-01-08 | 2014-04-30 | 上海大学 | Nonlinear vibration damping device for suppressing in-orbit micro-vibration of spacecraft |
| CN106742091A (en) * | 2016-12-27 | 2017-05-31 | 哈尔滨工业大学 | One class has the zero of zero-frequency vibration isolation feature（It is micro-）Levitation method and device |
| CN106956785A (en) * | 2015-07-15 | 2017-07-18 | 北京卫星环境工程研究所 | The in-orbit micro-vibration low frequency vibration isolation device of spacecraft |
-
2014
- 2014-01-08 CN CN201420010150.6U patent/CN204004165U/en not_active Withdrawn - After Issue
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103758921A (en) * | 2014-01-08 | 2014-04-30 | 上海大学 | Nonlinear vibration damping device for suppressing in-orbit micro-vibration of spacecraft |
| CN103758921B (en) * | 2014-01-08 | 2016-02-17 | 上海大学 | A kind of for suppressing the non-linear vibration damping device of astrovehicle micro-vibration in-orbit |
| CN106956785A (en) * | 2015-07-15 | 2017-07-18 | 北京卫星环境工程研究所 | The in-orbit micro-vibration low frequency vibration isolation device of spacecraft |
| CN106742091A (en) * | 2016-12-27 | 2017-05-31 | 哈尔滨工业大学 | One class has the zero of zero-frequency vibration isolation feature（It is micro-）Levitation method and device |
| CN106742091B (en) * | 2016-12-27 | 2018-07-06 | 哈尔滨工业大学 | A kind of zero-g or microgravity suspension process and device with zero-frequency vibration isolation feature |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20141210 Effective date of abandoning: 20160217 |
|
| C25 | Abandonment of patent right or utility model to avoid double patenting |