CN211202723U - Damping vibration attenuation structure for space satellite-borne instrument - Google Patents
Damping vibration attenuation structure for space satellite-borne instrument Download PDFInfo
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- CN211202723U CN211202723U CN201921931191.8U CN201921931191U CN211202723U CN 211202723 U CN211202723 U CN 211202723U CN 201921931191 U CN201921931191 U CN 201921931191U CN 211202723 U CN211202723 U CN 211202723U
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Abstract
The patent discloses a damping vibration attenuation structure for space satellite-borne instrument. The damping vibration attenuation structure comprises a supporting cylinder main body, a damping assembly and a vibration attenuation assembly. The supporting cylinder main body is independent of the damped component and is fixed with other supports in the satellite-borne instrument. The damping component is fixed on the supporting cylinder main body, and the damped component is positioned between the damping components. The threads on the tail of the metal damper effect axial adjustment so that the end of the metal damper contacts the damped component. The number of damping components is 3 ~ 6 of circumference equipartition, arranges two sets ofly from top to bottom. The advantage of this patent lies in: on the premise of not changing the stress of a key structure under normal working conditions, the vibration amplitude limiting protection effect is achieved on the cantilever, and materials used for the structure are light, free of air release and free of pollution to space loads.
Description
Technical Field
The patent relates to a damping vibration attenuation design for a space satellite-borne instrument. In particular to a principle, a structural form and a material, which are mainly applied to space satellite-borne instruments. By adopting the auxiliary supporting means, the vibration amplitude limiting protection effect is achieved on the cantilever of some precise components on the premise of not changing the stress of the key structure of the normal working condition. Meanwhile, the structure of the auxiliary device and the selection of the damping material both consider the characteristics of light weight and no air release, the pollution of the high-temperature high-vacuum air release of the common damping material to the space load is avoided, and the precise component assembly can be helped to pass the space environment examination.
Background
The space satellite-borne instrument is designed with light weight and high specific rigidity of the pursuit structure. The most severe of the mechanical resistance conditions is the vibration during firing. If the margin in the design is too high, the economic rationality is greatly reduced. Therefore, weak links which can pass vibration examination but have high precision requirements can be added with auxiliary support and improved design.
The cantilever structure in the satellite-borne instrument can generate larger amplitude under the vibration condition, and the auxiliary supporting means is adopted, so that the limit is arranged in the direction (non-axial direction) with larger amplitude of oscillation of the cantilever structure, and the constraint is not carried out in the axial direction. The vibration amplitude limiting protection effect on the cantilever can be realized on the premise of not changing the normal stress.
Meanwhile, the structure of the auxiliary device and the selection of the damping material both consider the characteristics of light weight and no air release, the pollution of the high-temperature high-vacuum air release of the common damping material to the space load is avoided, and the precise component assembly can be helped to pass the space environment examination.
Disclosure of Invention
In order to solve the problems in the prior art, the patent provides a damping vibration attenuation design for a space satellite-borne instrument.
The technical scheme adopted by the patent for solving the technical problem is as follows:
A damping vibration attenuation structure used on a space satellite-borne instrument comprises a supporting cylinder body 1 and a damping component 2; the supporting cylinder main body 1 is independent of the vibration-damped component and is fixed with other supports in the satellite-borne instrument, the damping component 2 is fixed on the supporting cylinder main body 1, and the vibration-damped component 3 is positioned between the damping components 2; the thread at the tail part of the metal damper 2-1 realizes axial adjustment, so that the end part of the metal damper 2-1 is contacted with the vibration damping component 3; two sets of damping components 2 distributed up and down are circumferentially and uniformly distributed on the supporting cylinder main body 1, and each set is 3-6 in number.
The damping assembly 2 is formed by assembling a metal damper 2-1 with a threaded tail part and a damping connecting sheet 2-2 through screws 2-3, the metal damper 2-1 is connected in a screw hole of the damping connecting sheet 2-2 through the thread of the tail part, the damping connecting sheet 2-2 is connected on the supporting cylinder main body 1 through the screws 2-3, and the tail part is adjusted to ensure effective contact with the vibration-damped assembly 3.
The supporting cylinder main body 1 is provided with a metal damper 2-1 mounting hole on the cylinder wall, and the aperture is larger than the diameter of the metal damper 2-1; the support cylinder main body 1 is made of carbon fiber composite materials, magnesium alloys or aluminum alloy materials.
The damper 2-1 is made of stainless steel wires and is in a shape of a net cylinder or a cuboid.
The beneficial effect of this patent is: the damping shock absorber is in contact with the damped component and is not connected with the damped component, the shock absorber only plays a role in one-way limiting of the damped component during vibration, and the vibration amplitude limiting protection effect on the cantilever can be achieved on the premise that normal stress is not changed.
The device is suitable for the cantilever in the vibration-damping component, and the part connected with the cantilever has a weak link.
Drawings
FIG. 1 is a schematic diagram of the structural principles and parameters;
FIG. 2 is a view of structural components;
In the figure: 1 is a supporting cylinder main body, 2 is a damping component, 2-1 is a metal damper at the tail part of a thread, 2-2 is a damping connecting sheet, 2-3 is a screw, and 3 is a component to be damped; d1 is the inner diameter of the supporting cylinder body, D2 is the diameter of the metal damper, D3 is the diameter of the damped component, h1 is the depth of the supporting cylinder body, h 2 is the distance in the height direction of the damper, h3 is the height of the damped component, and D1 is the thickness of the supporting cylinder.
Detailed Description
According to the method, the specific structure is designed as follows: the main body of the supporting cylinder is fixed on a bracket through 4M 6 screws, and is fixed on a bottom plate and a head cantilever by a damping component 3. The two groups of damping assemblies are 8 in total and distributed on two layers, and each layer is uniformly distributed with 4.
Wherein
D1＝120mm； D2＝12mm； D3＝88mm；
h1＝85mm； h2＝88mm； h3＝148mm； d1＝3mm。
And (3) test results: after damping, the head response of the damped piece 3 is reduced by 30%.
Claims (4)
1. The utility model provides a damping vibration attenuation structure for on space satellite-borne instrument, includes a support section of thick bamboo main part (1), damping subassembly (2), its characterized in that:
The supporting cylinder main body (1) is independent of the damped component and is fixed with other supports in the satellite-borne instrument, the damping component (2) is fixed on the supporting cylinder main body (1), and the damped component (3) is positioned between the damping components (2); the thread at the tail part of the metal damper (2-1) realizes axial adjustment, so that the end part of the metal damper (2-1) is contacted with the vibration damping component (3); the damping assemblies (2) which are arranged up and down are circumferentially and uniformly distributed on the supporting cylinder main body (1), and each group is 3-6 in number.
2. The damping structure for the space satellite borne instrument according to claim 1, is characterized in that: the damping assembly (2) is formed by assembling a metal damper (2-1) with a threaded tail part and a damping connecting piece (2-2) through screws (2-3), the metal damper (2-1) is connected in a screw hole of the damping connecting piece (2-2) through the thread of the tail part, the damping connecting piece (2-2) is connected to the supporting cylinder main body (1) through the screws (2-3), and the tail part is adjusted to ensure effective contact with the damped assembly (3).
3. The damping structure for the space satellite borne instrument according to claim 1, is characterized in that: the supporting cylinder main body (1) is provided with a metal damper (2-1) mounting hole on the cylinder wall, and the aperture is larger than the diameter of the metal damper (2-1); the support cylinder main body (1) is made of carbon fiber composite materials, magnesium alloys or aluminum alloy materials.
4. The damping structure for the space satellite borne instrument according to claim 1, is characterized in that: the damper (2-1) is made of stainless steel wires and is in a shape of a net cylinder or a cuboid.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921931191.8U CN211202723U (en) | 2019-11-11 | 2019-11-11 | Damping vibration attenuation structure for space satellite-borne instrument |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921931191.8U CN211202723U (en) | 2019-11-11 | 2019-11-11 | Damping vibration attenuation structure for space satellite-borne instrument |
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| Publication Number | Publication Date |
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| CN211202723U true CN211202723U (en) | 2020-08-07 |
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| CN201921931191.8U Active CN211202723U (en) | 2019-11-11 | 2019-11-11 | Damping vibration attenuation structure for space satellite-borne instrument |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110778642A (en) * | 2019-11-11 | 2020-02-11 | 中国科学院上海技术物理研究所 | Damping vibration attenuation structure for space satellite-borne instrument |
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2019
- 2019-11-11 CN CN201921931191.8U patent/CN211202723U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110778642A (en) * | 2019-11-11 | 2020-02-11 | 中国科学院上海技术物理研究所 | Damping vibration attenuation structure for space satellite-borne instrument |
| WO2021093549A1 (en) * | 2019-11-11 | 2021-05-20 | 中国科学院上海技术物理研究所 | Damping vibration attenuation structure for space satellite-borne instrument |
| CN110778642B (en) * | 2019-11-11 | 2024-03-19 | 中国科学院上海技术物理研究所 | Damping vibration attenuation structure for space satellite-borne instrument |
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