CN1663884A - Vibration reduction restriction damping layer of spacecraft - Google Patents
Vibration reduction restriction damping layer of spacecraft Download PDFInfo
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- CN1663884A CN1663884A CN 200510009838 CN200510009838A CN1663884A CN 1663884 A CN1663884 A CN 1663884A CN 200510009838 CN200510009838 CN 200510009838 CN 200510009838 A CN200510009838 A CN 200510009838A CN 1663884 A CN1663884 A CN 1663884A
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Abstract
The invention is the spacecraft damping restraining layer, and relates to a damping structure. The invention comprises the restraining layer (1) and the damp layer (2), the damp layer is adhered on the inner and outer faces (3) of the connecting piece, the restraining layer (1) is adhered on the upper surface of the damp layer (2). The additive restraining damp layer of the invention does not change the present interfaces, not damage the original structure and not lower the bearing rigidity. The invention has apparent damping effect. The computer emulation shows that the twinkle acceleration response of binding surfaces falls about 70%, the biggest relative acceleration falls from 3.6g to 1g; the twinkle displacement of binding surfaces falls about 55% and the biggest relative displacement falls from 0.35mm to 0.15mm.
Description
Technical field:
The present invention relates to a kind of vibration-proof structure, be specifically related to a kind of vibration reduction restriction damping layer that is mainly used in spacecraft.
Background technology:
In whole work life, spacecraft residing dynamics environment in emission process is the most abominable.With compare in the rail state of flight, spacecraft residing mechanical environment in the rocket launching process is more abominable.Therefore, guarantee that it is the main effort that current spacecraft structural strength designing institute carries out that spacecraft can survive in the mechanical environment of emission process.The cost that improves spacecraft structural strength is the quality that increases spacecraft, thereby launching costs is increased, and the quality that increases spacecraft rail normal in service be invalid load.
Summary of the invention:
The purpose of this invention is to provide a kind of vibration reduction restriction damping layer of spacecraft, this restriction damping layer is attached to the surface of spacecraft and carrier rocket link, can economical, reliably and effectively improve the dynamics environment in the spacecraft emission process, extension as enhancement of environment, spacecraft structure and instruments design can reduce intensity index thus, thereby implementation structure weight reduces.Vibration reduction restriction damping layer of spacecraft of the present invention comprises restraint layer 1 and damping layer 2 compositions, and damping layer 2 is bonded on the attaching parts inner and outer surface layers 3 by lining cement, and restraint layer 1 is bonded on the upper surface of damping layer 2 by lining cement.
Vibrational load mainly comes from the fricative aerodynamic loading of Launch Vehicle Engine vibration, fairing of launch vehicle and atmosphere, and is passed to spacecraft by attaching parts.Satellite and the rocket attaching parts is a flexible structure, produces vibration, generating period elastic deformation under the effect of vibrational load.Combine firm damping layer 2 with attaching parts uppermost layer 3 and follow the 3 generating period distortion of attaching parts uppermost layer simultaneously, force the strand in damping layer 2 materials to produce relative displacement, by intermolecular internal friction, change a part of mechanical energy into heat energy and dissipate, thereby play damping energy-absorbing, damping of vibrations; Restraint layer 1 is arranged on the damping layer 2, bending vibrattion is subjected to the obstruction from restraint layer 1 when making damping layer 2 elongations, when damping layer 2 pressurizeds, restraint layer 1 hinders it again and produces compressive deformation, after damping layer 2 suffers restraints, produce shear strain and shearing stress, thereby improved the dissipation of vibrational energy.
Additional constraint damping layer of the present invention does not change existing interface, does not damage original structure, does not reduce support stiffness yet, has obtained tangible effectiveness in vibration suppression with less quality cost, therefore, is " useful and harmless " to carrier rocket one Space Vehicle System.Because it has high reliability and safety, make it in the very high space flight and aviation industry of safety and reliability requirement, can be widely used.Damping technology based on restriction damping layer, the restriction damping layer structure can be carried out prefabricated according to the form of structure, thereby it has multiple application form and application fields, not only can be applied to the spacecraft vibration damping, also applicable to the vibration damping demand of some other system, for example: place with similar slab construction, beam column structure, conical shell formula structure.The present invention's additional constraint damping layer structure on space booster attaching parts original structure basis has tangible effectiveness in vibration suppression (Fig. 5～6) to spacecraft.Computer Simulation shows, it is about 70% that the response of interface instantaneous acceleration can reduce, and maximum relative acceleration is reduced to 1g by 3.6g; It is about 55% that interface transient Displacements response reduces, and maximum relative displacement drops to 0.15mm by 0.35mm.
Description of drawings:
Fig. 1 is a vibration reduction restriction damping layer of spacecraft structural representation of the present invention, Fig. 2 is a conical shell formula space booster link additional constraint damping structure scheme drawing, Fig. 3 is a beam column formula space booster link additional constraint damping structure scheme drawing, Fig. 4 is the birds-eye view of Fig. 3, Fig. 5 suppresses design sketch for additional constraint damping structure space booster interface transient state response, and Fig. 6 suppresses design sketch for additional constraint damping structure space booster interface steady state response.
The specific embodiment:
The specific embodiment one: the vibration reduction restriction damping layer of spacecraft of present embodiment is made up of restraint layer 1 and damping layer 2, uses lining cement that prefabricated visco-elastic damping material 2 is bonded on the attaching parts inner and outer surface layers 3, makes bonding firm through pressure treatment; After treating that lining cement solidifies, prefabricated restraint layer 1 is bonded on damping layer 2 upper surfaces, the process pressure treatment makes bonding firm, and the key of pasting restraint layer 1 is to make any position adhesion of its end edge and attaching parts uppermost layer 3.If certain part adhesion of the edge of restraint layer 1 and attaching parts uppermost layer 3 then can some vibration directly reach restraint layer 1 by the adhesion position, and then weaken its effect of contraction to damping layer 2, can not make effectiveness in vibration suppression reach best.As shown in Figure 1, constrained damping structure is for being clipped in visco-elastic damping material the structure of forming between the structure (inside face or outside face) that needs control and the restraint layer, and the structure that wherein is capped is a basic unit.
Restraint layer adopts the higher sheet material of rigidity to carry out prefabricated according to the outer profile size of structure usually.Constrained layer material can use multiple high rigidity prefabricated, as using carbon fiber board, aluminium alloy plate, glass woven fabric etc., also can change the thickness of restraint layer, uses thicker restraint layer can obtain better effectiveness in vibration suppression.The selection of thickness can reference configuration allows the maximum weightening finish; The used visco-elastic material of damping layer is wanted reference material subsidiary damping characteristic curve or chart, select the bigger visco-elastic material of each frequency range loss factor value can obtain the better damping effect, damping layer must have certain volume as the power consumption material, but the thickening damping layer might not improve effectiveness in vibration suppression.Lining cement will be selected with reference to its service instructions, select damping layer, restraint layer, base adhesive lining cement satisfactory for result.
Lining cement described in the present embodiment is J47D foamed glue, J47C pad pasting or J133 is gluing connects; The material of damping layer 2 is the ZN-1 visco-elastic material, and thickness is 1～2mm; The material of restraint layer 1 is C/E composite material T300/AG80, carbon fiber board, aluminium alloy plate or glass woven fabric, and thickness is 1.2mm.
The specific embodiment two: present embodiment is that conical shell formula structure is an example with the spacecraft link, as shown in Figure 2, vibration reduction restriction damping layer of spacecraft is made up of restraint layer 1 and damping layer 2, damping layer 2 is bonded on attaching parts (as positions such as driving engine coverings on Payload Attach Fitting, spacecraft conic adapter, the star) uppermost layer 3 between spacecraft and the carrier rocket, and restraint layer 1 is bonded on the surface of damping layer 2.It is the visco-elastic material of ZN-1 that additional damping layer 2 can adopt the trade mark, and thickness is 1mm, and damping layer 2 is made as multi-disc in advance according to the outside face size of conical shell structure; Restraint layer 1 adopts C/E composite material T300/AG80, and thickness is 1.2mm; Use J47D foamed glue, J47C pad pasting between each layer or J133 is gluing connects.
The specific embodiment three: it is example that present embodiment has the beam column structure with the spacecraft link, shown in Fig. 3 and 4, the vibration reduction restriction damping layer of spacecraft structure is identical with the specific embodiment one, it is the visco-elastic material of ZN-1 that additional damping layer 2 can adopt the trade mark, thickness is 1mm, and damping layer 2 is prefabricated according to the beam size; Restraint layer 1 adopts double glass cloth (thickness in monolayer 0.2mm) to be wrapped in the outside face of damping layer 2, and adds glue and soak into and drive bubble and make it sclerosis, and constituting with glue is the composite material of body.
Claims (7)
1, vibration reduction restriction damping layer of spacecraft is characterized in that it comprises restraint layer (1) and damping layer (2), and damping layer (2) is bonded on the attaching parts inner and outer surface layers (3) by lining cement, and restraint layer (1) is bonded on the upper surface of damping layer (2) by lining cement.
2, vibration reduction restriction damping layer of spacecraft according to claim 1 is characterized in that described lining cement is J47D foamed glue, J47C pad pasting or J133 is gluing connects.
3, vibration reduction restriction damping layer of spacecraft according to claim 1, the material that it is characterized in that described damping layer (2) is the ZN-1 visco-elastic material.
4, vibration reduction restriction damping layer of spacecraft according to claim 1, the thickness that it is characterized in that described damping layer (2) is 1～2mm.
5, vibration reduction restriction damping layer of spacecraft according to claim 1, the material that it is characterized in that described restraint layer (1) are C/E composite material T300/AG80, carbon fiber board, aluminium alloy plate or glass woven fabric.
6, vibration reduction restriction damping layer of spacecraft according to claim 1, the thickness that it is characterized in that described restraint layer (1) is 1.2mm.
7, vibration reduction restriction damping layer of spacecraft according to claim 1, it is characterized in that restraint layer (1) end edge can not with any position adhesion of attaching parts uppermost layer (3).
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| CN 200510009838 CN1663884A (en) | 2005-03-22 | 2005-03-22 | Vibration reduction restriction damping layer of spacecraft |
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| CN 200510009838 CN1663884A (en) | 2005-03-22 | 2005-03-22 | Vibration reduction restriction damping layer of spacecraft |
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Cited By (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN100436261C (en) * | 2006-08-25 | 2008-11-26 | 郑钢铁 | Integrated shock absorbing vibrating isolation device for stellite |
| CN102407628A (en) * | 2011-09-13 | 2012-04-11 | 江苏东旭科技有限公司 | Viscoelastic composite damping vibration attenuation rubber plate of ship deck |
| CN104139873A (en) * | 2014-08-06 | 2014-11-12 | 上海新跃仪表厂 | Passive damping device for solar panel |
| CN104565189A (en) * | 2014-12-19 | 2015-04-29 | 中国航空工业集团公司沈阳发动机设计研究所 | Multilayer constraining and damping implementation method for vibration damping of case of aeroengine |
| CN105269882A (en) * | 2014-07-22 | 2016-01-27 | 中国科学院声学研究所 | Light-weight constraint damping plate and manufacture method thereof |
| CN106096142A (en) * | 2016-06-14 | 2016-11-09 | 华北水利水电大学 | Hydraulic steel radial gate restriction damping layer Vibration Absorption Designing method |
| CN106763468A (en) * | 2016-11-22 | 2017-05-31 | 中国科学院沈阳自动化研究所 | A kind of space truss and space flight load structure for space operation |
| CN106882399A (en) * | 2015-12-16 | 2017-06-23 | 北京空间技术研制试验中心 | Spacecraft equipment surge guard device |
| CN108488532A (en) * | 2018-06-22 | 2018-09-04 | 中国船舶科学研究中心（中国船舶重工集团公司第七0二研究所） | Pipeline damping-constraining vibration-proof structure and its laying method |
| CN108801581A (en) * | 2018-09-04 | 2018-11-13 | 中国空气动力研究与发展中心高速空气动力研究所 | Wind tunnel force measurement model vibration damping strut based on constrained damping structure |
| CN109305344A (en) * | 2018-10-09 | 2019-02-05 | 东北大学 | Has the unmanned plane rotor arm configuration of segmentation restriction damping layer in a kind of outer surface |
| CN109801776A (en) * | 2019-04-04 | 2019-05-24 | 青岛云路先进材料技术股份有限公司 | Stereo amorphous alloy wound iron core and its single frame |
| CN110001170A (en) * | 2019-04-02 | 2019-07-12 | 中国兵器工业第五九研究所 | A kind of flexible foam filled honeycomb damping-constraining sandwich and preparation method thereof |
| CN110043592A (en) * | 2019-03-19 | 2019-07-23 | 上海大学 | A kind of non-linear dashpot using viscoelastic damper |
| CN110562501A (en) * | 2019-09-27 | 2019-12-13 | 中国科学院沈阳自动化研究所 | Space station is with compound damping scientific experiment cabinet that attenuates vibration |
| CN112607057A (en) * | 2020-12-28 | 2021-04-06 | 长光卫星技术有限公司 | High-rigidity high-damping satellite platform structure |
| CN113272098A (en) * | 2019-01-18 | 2021-08-17 | 株式会社牧野铣床制作所 | Feeding device of machine tool |
-
2005
- 2005-03-22 CN CN 200510009838 patent/CN1663884A/en active Pending
Cited By (20)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN100436261C (en) * | 2006-08-25 | 2008-11-26 | 郑钢铁 | Integrated shock absorbing vibrating isolation device for stellite |
| CN102407628A (en) * | 2011-09-13 | 2012-04-11 | 江苏东旭科技有限公司 | Viscoelastic composite damping vibration attenuation rubber plate of ship deck |
| CN105269882A (en) * | 2014-07-22 | 2016-01-27 | 中国科学院声学研究所 | Light-weight constraint damping plate and manufacture method thereof |
| CN104139873A (en) * | 2014-08-06 | 2014-11-12 | 上海新跃仪表厂 | Passive damping device for solar panel |
| CN104565189A (en) * | 2014-12-19 | 2015-04-29 | 中国航空工业集团公司沈阳发动机设计研究所 | Multilayer constraining and damping implementation method for vibration damping of case of aeroengine |
| CN106882399A (en) * | 2015-12-16 | 2017-06-23 | 北京空间技术研制试验中心 | Spacecraft equipment surge guard device |
| CN106882399B (en) * | 2015-12-16 | 2018-12-25 | 北京空间技术研制试验中心 | Spacecraft equipment surge guard device |
| CN106096142A (en) * | 2016-06-14 | 2016-11-09 | 华北水利水电大学 | Hydraulic steel radial gate restriction damping layer Vibration Absorption Designing method |
| CN106096142B (en) * | 2016-06-14 | 2019-03-15 | 华北水利水电大学 | Hydraulic steel radial gate restriction damping layer Vibration Absorption Designing method |
| CN106763468A (en) * | 2016-11-22 | 2017-05-31 | 中国科学院沈阳自动化研究所 | A kind of space truss and space flight load structure for space operation |
| CN106763468B (en) * | 2016-11-22 | 2019-04-09 | 中国科学院沈阳自动化研究所 | A kind of space truss and space flight load structure for space operation |
| CN108488532A (en) * | 2018-06-22 | 2018-09-04 | 中国船舶科学研究中心（中国船舶重工集团公司第七0二研究所） | Pipeline damping-constraining vibration-proof structure and its laying method |
| CN108801581A (en) * | 2018-09-04 | 2018-11-13 | 中国空气动力研究与发展中心高速空气动力研究所 | Wind tunnel force measurement model vibration damping strut based on constrained damping structure |
| CN109305344A (en) * | 2018-10-09 | 2019-02-05 | 东北大学 | Has the unmanned plane rotor arm configuration of segmentation restriction damping layer in a kind of outer surface |
| CN113272098A (en) * | 2019-01-18 | 2021-08-17 | 株式会社牧野铣床制作所 | Feeding device of machine tool |
| CN110043592A (en) * | 2019-03-19 | 2019-07-23 | 上海大学 | A kind of non-linear dashpot using viscoelastic damper |
| CN110001170A (en) * | 2019-04-02 | 2019-07-12 | 中国兵器工业第五九研究所 | A kind of flexible foam filled honeycomb damping-constraining sandwich and preparation method thereof |
| CN109801776A (en) * | 2019-04-04 | 2019-05-24 | 青岛云路先进材料技术股份有限公司 | Stereo amorphous alloy wound iron core and its single frame |
| CN110562501A (en) * | 2019-09-27 | 2019-12-13 | 中国科学院沈阳自动化研究所 | Space station is with compound damping scientific experiment cabinet that attenuates vibration |
| CN112607057A (en) * | 2020-12-28 | 2021-04-06 | 长光卫星技术有限公司 | High-rigidity high-damping satellite platform structure |
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