CN203516585U - Large-area compound damping vibration attenuation structure applicable to spacecraft - Google Patents
Large-area compound damping vibration attenuation structure applicable to spacecraft Download PDFInfo
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- CN203516585U CN203516585U CN201320554340.XU CN201320554340U CN203516585U CN 203516585 U CN203516585 U CN 203516585U CN 201320554340 U CN201320554340 U CN 201320554340U CN 203516585 U CN203516585 U CN 203516585U
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Abstract
Provided is a large-area compound damping vibration attenuation structure applicable to a spacecraft. The large-area compound damping vibration attenuation structure applicable to the spacecraft comprises a mounting plate, a constraint plate, a damping layer, conductive adhesives, bolts, nuts and a mounting flange for a device with vibration to be attenuated, wherein the damping layer is clamped between the mounting plate and the constraint plate, the damping layer, the mounting plate and the constraint plate are bonded to form an integral structure, a plurality of adhesive filling through holes and a plurality of countersinks are punched in the integral structure, the adhesive filling through holes are filled with the conductive adhesives, and the bolts penetrate through the countersinks, and are used in cooperation with the nuts so that the mounting flange for the device with vibration to be attenuated and the mounting plate can be fixed together. According to the large-area compound damping vibration attenuation structure applicable to the spacecraft, the damping effect of the whole large-area compound damping vibration attenuation structure is remarkably improved, the vibration response peak of a spacecraft large-area sheet structure within a resonance frequency range can be reduced by about 60%, and then the vibration environment of a stand-alone device mounted on the sheet structure is effectively improved.
Description
Technical field
The utility model relates to a kind of large size compostie damp vibration damping structure that is applicable to spacecraft, belongs to spacecraft structural vibration reduction technical field.
Background technique
In the main structure design of spacecraft, conventionally comprise large-area thin plate structure, and instrument and equipment is arranged on thin-slab structure, and aircraft is in transmitting powered phase and autonomous flight process, all bear the dynamics environment load of Various Complex, aerodynamic noise, engine ignition and shutdown etc. that the thrust that mainly comprises motor causes when pulsing, transonic speed flying, above-mentioned reason has caused the comparatively harsh vibration environment of instrument and equipment.In order to improve the vibration environment of product facility, traditional design mainly comprises by ABAP Adapter to be carried out integral vibration damping or stand-alone device is carried out to the basic modes such as local vibration damping rocket useful load.Wherein, integral vibration damping design is mainly that the adapter structure of the aircraft such as satellite is taked to damping vibration attenuation measure, has the problems such as size is large, complex process, and is not suitable for the situation of docking without ABAP Adapter between aircraft and vehicle; And local vibration damping to stand-alone device mounting dampers exists equally because mounting dampers affects Product Precision and product heat dissipation problem.
Model utility content
Technology of the present utility model is dealt with problems and is: overcome the deficiencies in the prior art, solve the integral vibration damping problem of spacecraft large-area thin plate structure, and the equipotential requirement based on spacecraft, design the equipotential structural type of composite damping board, solved the installation precision problem due to the sensitive equipment that uses damping material to cause simultaneously.
Technical solution of the present utility model is:
A large size compostie damp vibration damping structure that is applicable to spacecraft, is characterized in that comprising: mounting plate, restraining plate, damping layer, conducting resinl, bolt, nut, treat dampening apparatus mounting flange;
Damping layer is clipped between mounting plate and restraining plate and damping layer and mounting plate and the bonding as a whole structure of restraining plate, in this overall structure, be equipped with a plurality of encapsulating through holes and counterbore, filled conductive glue in described encapsulating through hole, bolt, through described counterbore, matches with nut and will treat that dampening apparatus mounting flange and mounting plate are fixed together.
Described damping layer adopts viscoelastic material.Described viscoelastic material is ZN-1 butyl rubber.
The utility model beneficial effect is compared with prior art:
(1) the utility model structure has significantly increased the damping effect of total, make the vibrating response peak value of spacecraft large-area thin plate structure in resonant frequency range reduce by 60% left and right, and then effectively improved the vibration environment that is installed on the stand-alone device on thin-slab structure.
(2) the utility model structural design the equipotential structural type of composite damping board, overcome and because nonmetallic material are non-conductive, caused spacecraft structure may have the problem of isolated conductor, countersunk head by composite damping board mounting hole designs simultaneously, has guaranteed that sensitive equipment is in the structural installation precision of composite damping board.
Accompanying drawing explanation
Fig. 1 is the utility model structural representation.
Embodiment
The utility model is for the vibration damping requirement of spacecraft large-area thin plate structure, composite damping board vibration damping structure has been proposed, broken through traditional vibration damping mode, effectively reduced the vibratory response of aircraft key structure, for aircraft environment, improved and proposed brand-new mentality of designing; Meanwhile, the equipotential requirement based on spacecraft, the utility model innovative design the equipotential structural type of compostie damp layer, and solved the installation precision problem of sensitive equipment at compostie damp layer.
For reducing the vibrating response peak value of the large-area thin plate structure in spacecraft, general design idea of the present utility model is on thin-slab structure, to paste damp film and restraining plate, constraint due to restraining plate, while making structural vibration, damping layer bears larger shear deformation and a part of tension and compression deformation, thereby under synthetic alternating stress effect, the destruction of the molecular chain by visco-elastic damping material long-chain molecule and loss vibrational energy, and then effectively reduce thin-slab structure vibratory response.The method reliability is high, strong robustness; In the situation that there is no rigidity and the quality of remarkable change system, effectively reduce the amplitude of vibratory response resonance peak.
Under space plasma environment, spacecraft structure should be taked equipotential design.The utility model is between mounting plate and restraining plate, to take to seal the mode of conducting resinl, makes restraining plate and mounting plate and whole Flight Vehicle Structure meet equipotential requirement.In addition, this method designs simultaneously processes larger-diameter through hole on restraining plate and damp film, and fastening piece countersunk head is installed, and is directly pressed on mounting plate, has guaranteed the installation precision of sensitive equipment at composite damping board.
As shown in Figure 1, the utility model provides a kind of large size compostie damp vibration damping structure that is applicable to spacecraft, comprising: mounting plate 1, restraining plate 2, damping layer 3, conducting resinl 4, bolt 5, nut 6, treat dampening apparatus mounting flange 7; Mounting plate 1, restraining plate 2 and damping layer 3 are thin-slab structure.
Take certain type spacecraft is example, has verified the effectiveness in vibration suppression of this kind of method by ground experiment.Test result shows, is not taking under the condition of the utility model structure, and on mounting plate, the power spectral density maximum value of crucial measuring point in the frequency range of 150Hz-300Hz is 1.3g
2/ Hz; After taking compostie damp oscillation damping method, the power spectral density of mounting plate measuring point is also reduced to 0.4g
2/ Hz.As can be seen here, the utility model structure has significantly been improved the vibratory response of spacecraft key position in low-frequency range, for Flight Vehicle Structure and product facility provide good Environmental Conditions.
Claims (4)
1. a large size compostie damp vibration damping structure that is applicable to spacecraft, is characterized in that comprising:
Mounting plate (1), restraining plate (2), damping layer (3), conducting resinl (4), bolt (5), nut (6), treat dampening apparatus mounting flange (7);
Damping layer (3) is clipped between mounting plate (1) and restraining plate (2) and damping layer (3) and mounting plate (1) and the bonding as a whole structure of restraining plate (2), in this overall structure, be equipped with a plurality of encapsulating through holes (8) and counterbore (9), the interior filled conductive glue of described encapsulating through hole (8) (4), bolt (5), through described counterbore (9), matches with nut (6) and will treat that dampening apparatus mounting flange (7) and mounting plate (1) are fixed together.
2. a kind of large size compostie damp vibration damping structure that is applicable to spacecraft according to claim 1, is characterized in that: described damping layer (3) adopts viscoelastic material.
3. a kind of large size compostie damp vibration damping structure that is applicable to spacecraft according to claim 1 and 2, is characterized in that: described mounting plate (1), restraining plate (2) and damping layer (3) are thin-slab structure.
4. a kind of large size compostie damp vibration damping structure that is applicable to spacecraft according to claim 2, is characterized in that: described viscoelastic material is ZN-1 butyl rubber.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320554340.XU CN203516585U (en) | 2013-09-06 | 2013-09-06 | Large-area compound damping vibration attenuation structure applicable to spacecraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320554340.XU CN203516585U (en) | 2013-09-06 | 2013-09-06 | Large-area compound damping vibration attenuation structure applicable to spacecraft |
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| CN203516585U true CN203516585U (en) | 2014-04-02 |
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| CN201320554340.XU Expired - Lifetime CN203516585U (en) | 2013-09-06 | 2013-09-06 | Large-area compound damping vibration attenuation structure applicable to spacecraft |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104455196A (en) * | 2014-09-30 | 2015-03-25 | 西安空间无线电技术研究所 | Rigidity-adjustable device with characteristics of heat conduction, electric conduction and high damping |
| CN104565716A (en) * | 2014-12-25 | 2015-04-29 | 贵州黔程天力智能科技有限公司 | Receiver vibration attenuation supporting seat |
| CN104595636A (en) * | 2014-12-25 | 2015-05-06 | 贵州黔程天力智能科技有限公司 | Receiver damping supporting base |
| CN105864341A (en) * | 2016-05-23 | 2016-08-17 | 航天材料及工艺研究所 | High-reliability combined type shock absorber |
| CN108626290A (en) * | 2018-05-04 | 2018-10-09 | 南京大学 | A kind of enhancing damping-constraining device |
-
2013
- 2013-09-06 CN CN201320554340.XU patent/CN203516585U/en not_active Expired - Lifetime
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104455196A (en) * | 2014-09-30 | 2015-03-25 | 西安空间无线电技术研究所 | Rigidity-adjustable device with characteristics of heat conduction, electric conduction and high damping |
| CN104455196B (en) * | 2014-09-30 | 2016-06-01 | 西安空间无线电技术研究所 | A kind of rigidity tunable arrangement with heat conduction, conduction, high damping characteristic |
| CN104565716A (en) * | 2014-12-25 | 2015-04-29 | 贵州黔程天力智能科技有限公司 | Receiver vibration attenuation supporting seat |
| CN104595636A (en) * | 2014-12-25 | 2015-05-06 | 贵州黔程天力智能科技有限公司 | Receiver damping supporting base |
| CN105864341A (en) * | 2016-05-23 | 2016-08-17 | 航天材料及工艺研究所 | High-reliability combined type shock absorber |
| CN108626290A (en) * | 2018-05-04 | 2018-10-09 | 南京大学 | A kind of enhancing damping-constraining device |
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Legal Events
| Date | Code | Title | Description |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term |
Granted publication date: 20140402 |
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| CX01 | Expiry of patent term |