CN108652286A - A kind of space station scientific experimentation cabinet skin assemblies and preparation method - Google Patents
A kind of space station scientific experimentation cabinet skin assemblies and preparation method Download PDFInfo
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- CN108652286A CN108652286A CN201810373811.4A CN201810373811A CN108652286A CN 108652286 A CN108652286 A CN 108652286A CN 201810373811 A CN201810373811 A CN 201810373811A CN 108652286 A CN108652286 A CN 108652286A
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- Prior art keywords
- space station
- scientific experimentation
- skin assemblies
- damping
- cabinet skin
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Classifications
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- A—HUMAN NECESSITIES
- A47—FURNITURE; DOMESTIC ARTICLES OR APPLIANCES; COFFEE MILLS; SPICE MILLS; SUCTION CLEANERS IN GENERAL
- A47B—TABLES; DESKS; OFFICE FURNITURE; CABINETS; DRAWERS; GENERAL DETAILS OF FURNITURE
- A47B96/00—Details of cabinets, racks or shelf units not covered by a single one of groups A47B43/00 - A47B95/00; General details of furniture
- A47B96/20—Furniture panels or like furniture elements
- A47B96/205—Composite panels, comprising several elements joined together
- A47B96/206—Composite panels, comprising several elements joined together with laminates comprising planar, continuous or separate layers
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/40—Shaping or impregnating by compression not applied
- B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Composite Materials (AREA)
- Mechanical Engineering (AREA)
- Vibration Prevention Devices (AREA)
Abstract
The invention discloses a kind of space station scientific experimentation cabinet skin assemblies and preparation method.Wherein, which includes first part, second part and Part III；Wherein, first part and second part integrally connected, second part and Part III integrally connected.The present invention has construction weight is not generated and increases, do not change structure original configuration, not changing structural modal, the rigidity of structure/intensity is not generated significantly affect under the premise of, improve structure structure d amping coefficient, reduce vibratory response advantage.
Description
Technical field
The invention belongs to vibration control field more particularly to a kind of space station scientific experimentation cabinet skin assemblies and preparation sides
Method.
Background technology
Vibration has its advantageous one side, and various vibrating machines can be made using vibration principle, improve work efficiency.Vibration also has
Its harmful one side, such as vibration can influence the function of precision instrument and equipment, reduce machining accuracy, aggravate the fatigue and mill of component
Damage shortens the service life of machine and structure, and adverse condition etc..
Usually said vibration control actually refers to vibration suppression, that is, by vibration source, pipeline and system sheet
Body structure takes certain measure, and hazard of vibration is restricted to minimum limit or is reduced to degree of admission.
Vibration suppression can be divided into passive type with it is active.The former belongs to the vibration suppression disposably designed in advance；Afterwards
Person utilizes feedback control, automatically carries out vibration suppression.
Passive type vibration control technology：It is optimized by the dynamic mechanics parameter to system structure, makes to be transmitted to
The vibrational energy of Sensitive Apparatus is isolated, converts or shifts, to reduce the vibratory response on Sensitive Apparatus.Passive type shakes
Dynamic control technology includes structure design, vibration isolation, damping vibration attenuation and dynamic absorber technology etc..
Structure-design technique：In structured design phase, using finite element simulation technology, by being carried out to system-wide mode
Analysis, the system-wide frequency distribution of rational allocation make the local mode of Sensitive Apparatus be released with total system mode and excitation and couple.
In addition, smaller due to being strained under high frequency, reinforced often through to sensitive equipment, i.e. the method for rigidifying reach reduce stress and
Strain improves the mechanical environment of sensing device or component.This method advantage is that this method designs the early period for structure, therefore
Once structure frequency allotment is reasonable, the vibration control for greatly simplifying the later stage is worked.Large scale structure is since complicated, mode is non-
Often intensive, this method haves the shortcomings that big to structural modification, Modes Decoupling is difficult, and in the early period of structure design, to structure mould
State and exiting form are unable to get an accurate numerical value, therefore easy to produce some omissions.
Vibration isolation technique：Vibration isolator is substantially a kind of mechanical low-pass filter, is installed between equipment and basis, to high frequency
Buffer action is played in vibration, and vibrational energy is isolated in transmission path.It is relatively simple that vibration isolator is suitable for stress transfer channel
Structural system is highly suitable for later stage repairing when single machine frequency is coupled with system frequency generation, generally has very high vibration damping
Efficiency.There is also following disadvantages for this method：It is larger to structural modal change, and vibration isolator is larger to the interface change of structure, it is right
For approved product, mode will produce large effect with structure interface change；Vibration isolation technique would generally make structure mould
State declines, rigidity reduces, displacement increases in vibration processes, for some single machines (such as optical device) relatively high to required precision
For can not use.
Damping vibration attenuation technology：Visco-elastic damping material is added in structure by certain mode, increases the mode of structure
Damping ratio effectively inhibits the dynamic response near resonance region, significantly improves the dynamic for being installed on the precision instrument in structure
Mechanical environment.From the point of view of energy, damping material passes through the interior friction of material by following basal body structure to generate strain together
Effect converts the vibrational energy of structure to thermal energy.There are mainly two types of damping vibration attenuation forms at present：Free damping technology and constraint
Damping.Free damping technology pastes one layer of visco-elastic damping material in the substrate surface for needing vibration damping, due to damping layer thickness
It is smaller, density is relatively low, to structure increase weight it is smaller but smaller to structural damping increase, do not use generally.Damping-constraining technology is waiting for
The substrate surface of vibration damping pastes one layer of visco-elastic damping material and the preferable restraint layer of a stiffness layer (generally metal or multiple material),
Structural damping can be increased to 10%~20% by this technology, but restraining plate is heavier, be increased weight to structure larger, therefore be not suitable for
To the more sensitive equipment of weight.
Dynamic absorber technology：Using antiresonance principle, by installing an additional quality-spring system on basal body structure
System (tuning dynamic vibration absorber) or quality-spring-glue pot system (tuning dynamic damper), by the vibrational energy in main structure
It is transferred on dynamic vibration absorber.Dynamic absorber technology is suitable for the large scale structure that first three technology can not be applicable in, such as building, bridge
Deng.This method has a disadvantage that：Acting frequency region is relatively narrow, is only used for exciting force and structure frequency and relatively stablizes and be narrowband
In the case of；Additional mass is generally no less than the 5% of equipment to be damped, and weightening is more.
Invention content
Present invention solves the technical problem that being：A kind of space station scientific experimentation is overcome the deficiencies of the prior art and provide
Cabinet skin assemblies and preparation method have and do not increase construction weight generation, do not change structure original configuration, not changing structure mould
State under the premise of not generating and significantly affecting to the rigidity of structure/intensity, improves structure structure d amping coefficient, reduces vibratory response advantage.
The object of the invention is achieved by the following technical programs：According to an aspect of the invention, there is provided a kind of sky
Between station use scientific experimentation cabinet skin assemblies, including：First part, second part and Part III；Wherein, first part and second
Part integrally connected, second part and Part III integrally connected.
With in scientific experimentation cabinet skin assemblies, first part and Part III include the first composite material for above-mentioned space station
Laying, damping glued membrane and the second composite plys；Wherein, first composite plys are layed in the damping glued membrane
Upper surface；Second composite plys are layed in the lower surface of the damping glued membrane.
With in scientific experimentation cabinet skin assemblies, the second part is made of composite plys for above-mentioned space station.
With in scientific experimentation cabinet skin assemblies, the thickness of the composite plys is 1.5-2mm for above-mentioned space station.
With in scientific experimentation cabinet skin assemblies, the thickness of first composite plys is 0.3- for above-mentioned space station
0.6m。
With in scientific experimentation cabinet skin assemblies, the thickness of the damping glued membrane is 0.1-0.2mm for above-mentioned space station.
With in scientific experimentation cabinet skin assemblies, the thickness of second composite plys is 0.9-1mm for above-mentioned space station.
According to another aspect of the present invention, a kind of preparation side of space station scientific experimentation cabinet skin assemblies is additionally provided
Method, described method includes following steps：Make the outer former to match with the shape of space station scientific experimentation cabinet skin assemblies；
The surface coating release agent of external former, and externally former is preheated；In the corresponding outer former of first part and Part III
Outer surface be laid with the first composite plys, damping glued membrane and the second composite plys successively, it is corresponding in second part
Outer former outer surface be laid with composite plys；The outer former laid is subjected to molded curing；Heating, intermediate temperature setting one
It fixes time；It is cooling after the completion of solidification, demoulding, removing surface.
In preparation method of the above-mentioned space station with scientific experimentation cabinet skin assemblies, intermediate temperature setting 8-10 hours.
In preparation method of the above-mentioned space station with scientific experimentation cabinet skin assemblies, by the outer former laid in autoclave
Cured.
The present invention has the advantages that compared with prior art：
(1) present invention compared to other vibration damping schemes need to change structure size or interface or weight and to having been formed knot
Structure produces bigger effect, and the skin assemblies of this structure type have no need to change the size and interface of original structure, therefore for
Product through sizing is very convenient processing method；
(2) (structure-reinforced, damping-constraining moves the case where present invention need to increase construction weight compared to other vibration damping schemes
Power absorbing is both needed to increase larger quality, and vibration isolation technique weightening is smaller), this structure type does not generate structure weightening, therefore some are right
The component of weight sensitive uses this structure type；
(3) present invention need to change mode of oscillation (vibration isolation technique, the dynamic absorber meeting pole of structure compared to other vibration damping schemes
Big change structural modal, structure-reinforced, damping-constraining can lesser degree of change structural modals), this structure type will not change
The mode for becoming original structure, will not change the mode vectors correlation of system, and the vibration test done to structure has inheritance (can edge
With the vibration test result of original structure).
(4) present invention need to change rigidity/intensity of structure (in vibration isolation technique, dynamic absorber compared to other vibration damping schemes
The intensity of rubber needs emphasis to consider, damping-constraining need to consider the adhesion strength of restraint layer, structure-reinforced rigidity/intensity to structure
Influence uncertain), this structure type is very small to rigidity/intensity effect of structure, and the strength test done to original structure has
Inheritance.
Description of the drawings
By reading the detailed description of hereafter preferred embodiment, various other advantages and benefit are common for this field
Technical staff will become clear.Attached drawing only for the purpose of illustrating preferred embodiments, and is not considered as to the present invention
Limitation.And throughout the drawings, the same reference numbers will be used to refer to the same parts.In the accompanying drawings：
Fig. 1 is the structural schematic diagram of scientific experimentation cabinet skin assemblies in space station provided in an embodiment of the present invention；
Fig. 1-1 is the separation schematic diagram of scientific experimentation cabinet skin assemblies in space station provided in an embodiment of the present invention；
Fig. 2 is the composition schematic diagram of first part provided in an embodiment of the present invention and Part III；
Fig. 3 is the flow chart of the preparation method of scientific experimentation cabinet skin assemblies in space station provided in an embodiment of the present invention.
Specific implementation mode
The exemplary embodiment of the disclosure is more fully described below with reference to accompanying drawings.Although showing the disclosure in attached drawing
Exemplary embodiment, it being understood, however, that may be realized in various forms the disclosure without should be by embodiments set forth here
It is limited.On the contrary, these embodiments are provided to facilitate a more thoroughly understanding of the present invention, and can be by the scope of the present disclosure
Completely it is communicated to those skilled in the art.It should be noted that in the absence of conflict, embodiment in the present invention and
Feature in embodiment can be combined with each other.The present invention will be described in detail below with reference to the accompanying drawings and embodiments.
Fig. 1 is the structural schematic diagram of scientific experimentation cabinet skin assemblies in space station provided in an embodiment of the present invention.Fig. 1-1 is
The separation schematic diagram of space station provided in an embodiment of the present invention scientific experimentation cabinet skin assemblies.It, should as shown in Fig. 1 and Fig. 1-1
Scientific experimentation cabinet skin assemblies in space station include：First part 100, second part 200 and Part III 300；Wherein, first
200 integrally connected of part 100 and second part, 300 integrally connected of second part 200 and Part III.
Fig. 2 is the composition schematic diagram of first part provided in an embodiment of the present invention and Part III.As shown in Fig. 2, first
Part 100 and Part III 300 include the first composite plys 1, damping glued membrane 2 and the second composite plys 3；Its
In, the first composite plys 1 are layed in the upper surface of damping glued membrane 2；Second composite plys 3 are layed in damping glued membrane 2
Lower surface.Second part 200 is made of composite plys, and the thickness of composite plys is 1.5-2mm.First composite wood
Expect that the thickness of laying 1 is 0.3-0.6m.The thickness for damping glued membrane 2 is 0.1-0.2mm.The thickness of second composite plys 3 is
0.9-1mm.Damping glued membrane 2 is that Damping material layer is bonded as one with glued membrane, due to the cohesive force of damping material and composite material
It is small, using adding one layer between damping material and composite plys preferable bonding is all had with damping material and composite material
The special glued membrane of power is ensured with improving the cohesive force of damping material and composite material between damping material and composite plys
Interlaminar shear strength meet the requirements.
Fig. 3 is the flow chart of the preparation method of scientific experimentation cabinet skin assemblies in space station provided in an embodiment of the present invention.
The present embodiment additionally provides a kind of preparation method of space station scientific experimentation cabinet skin assemblies, as shown in figure 3, this method includes
Following steps：
Make the outer former to match with the shape of space station scientific experimentation cabinet skin assemblies；
The surface coating release agent of external former, and externally former is preheated；
It is compound that it is laid with first successively in the outer surface of first part (100) and the corresponding outer former of Part III (300)
Material laying (1), damping glued membrane (2) and the second composite plys (3), in the corresponding outer former of second part (200)
Outer surface is laid with composite plys；
The outer former laid is subjected to molded curing；
Heating, intermediate temperature setting 8-10 hours；
It is cooling after the completion of solidification, demoulding, removing surface.
Skin assemblies are the coverings of scientific experimentation cabinet, and scientific experimentation cabinet is in space station for installing scientific experimentation instrument
Cabinet.Covering is 5 face closures, 1 face opening, and covering is composite material integrated molding.
The present embodiment is hindered in the specific region (first part and Part III) of covering with the high damping visco-elastic of 0.15mm
After the completion of damping material replaces one layer of composite plys therein, multiple material to be laid with, damping material is consolidated together with composite material
Change, make inside damping material embedded composite material laying, realizes and increase do not generated to construction weight, do not change the original structure of structure
Type under the premise of not changing structural modal, not generating and significantly affect to the rigidity of structure/intensity, improves the structural damping system of component
Number, reduces the purpose of the vibratory response of structure.
Structural damping integration stressed-skin construction main body is carbon fiber/epoxy resin based composites in the present embodiment, wherein
Compound one layer of visco-elastic damping material.
Structural damping integral structure and former stressed-skin construction performance comparison in the present embodiment.
1 primary antenna supporting structure of table and the comparison of inventive antenna supporting structure mechanical property
The present embodiment compared to other vibration damping schemes need to change structure size or interface or weight and to having been formed knot
Structure produces bigger effect, and the skin assemblies of this structure type have no need to change the size and interface of original structure, therefore for
Product through sizing is very convenient processing method.The present embodiment need to increase the feelings of construction weight compared to other vibration damping schemes
Condition (structure-reinforced, damping-constraining, dynamic absorber are both needed to increase larger quality, and vibration isolation technique weightening is smaller), this structure type is not
Structure weightening is generated, therefore some use this structure type to the component of weight sensitive.The present embodiment is compared to other vibration damping sides
Case need to change the mode of oscillation of structure, and (vibration isolation technique, dynamic absorber can greatly change structural modal, structure-reinforced, constraint resistance
Buddhist nun can lesser degree of change structural modal), this structure type will not change the mode of original structure, will not change the mode of system
Matching, the vibration test done to structure have inheritance (the vibration test result that can continue to use original structure).The present embodiment
Need to changing rigidity/intensity of structure compared to other vibration damping schemes, (intensity of rubber needs emphasis to examine in vibration isolation technique, dynamic absorber
Consider, damping-constraining need to consider that the adhesion strength of restraint layer, structure-reinforced rigidity/intensity effect to structure are uncertain), this structure
Form is very small to rigidity/intensity effect of structure, and the strength test done to original structure has inheritance.The present embodiment designs
Structural damping integration skin assemblies using structure and damping layer fusion integrated molding process program.Covering is spread by 10 layers
Layer is laid with.In the region for needing to be laid with damping layer, laying includes 9 layers of composite plys and one layer of damping layer；It is being not required to
It is laid with the region of damping layer, laying includes 10 layers of composite plys.It is compound being laid with where being routed to damping layer when layer
It is laid with for the mode of butted layup between material laying and the region of damping layer.After the completion of all layings are laid with, using hot pressing
Tank shaping process, by covering one-pass molding.One-pass molding can ensure the cohesive force between damping layer and composite plys,
Ensure the mechanical property of composite plys.
Embodiment described above is the present invention more preferably specific implementation mode, and those skilled in the art is in this hair
The usual variations and alternatives carried out in bright technical proposal scope should be all included within the scope of the present invention.
Claims (10)
1. a kind of space station scientific experimentation cabinet skin assemblies, it is characterised in that including：First part (100), second part
(200) and Part III (300)；Wherein, first part (100) and second part (200) integrally connected, second part (200)
With Part III (300) integrally connected.
2. space station according to claim 1 scientific experimentation cabinet skin assemblies, it is characterised in that：First part (100)
Include the first composite plys (1), damping glued membrane (2) and the second composite plys (3) with Part III (300)；Its
In,
First composite plys (1) are layed in the upper surface of the damping glued membrane (2)；
Second composite plys (3) are layed in the lower surface of the damping glued membrane (2).
3. space station according to claim 1 scientific experimentation cabinet skin assemblies, it is characterised in that：The second part
(200) it is made of composite plys.
4. space station according to claim 3 scientific experimentation cabinet skin assemblies, it is characterised in that：The composite material paving
The thickness of layer is 1.5-2mm.
5. space station according to claim 2 scientific experimentation cabinet skin assemblies, it is characterised in that：First composite wood
Expect that the thickness of laying (1) is 0.3-0.6m.
6. space station according to claim 2 scientific experimentation cabinet skin assemblies, it is characterised in that：The damping glued membrane
(2) thickness is 0.1-0.2mm.
7. space station according to claim 2 scientific experimentation cabinet skin assemblies, it is characterised in that：Second composite wood
Expect that the thickness of laying (3) is 0.9-1mm.
8. a kind of space station preparation method of scientific experimentation cabinet skin assemblies, which is characterized in that the method includes walking as follows
Suddenly：
Make the outer former to match with the shape of space station scientific experimentation cabinet skin assemblies；
The surface coating release agent of external former, and externally former is preheated；
It is laid with the first composite material successively in the outer surface of first part (100) and the corresponding outer former of Part III (300)
Laying (1), damping glued membrane (2) and the second composite plys (3), in the appearance of the corresponding outer former of second part (200)
Face is laid with composite plys；
The outer former laid is molded or is cured；
Heating, intermediate temperature setting certain time；
It is cooling after the completion of solidification, demoulding, removing surface.
9. the space station according to claim 8 preparation method of scientific experimentation cabinet skin assemblies, it is characterised in that：Medium temperature
Solidification 8-10 hours.
10. the space station according to claim 8 preparation method of scientific experimentation cabinet skin assemblies, it is characterised in that：It will
The outer former laid is cured in autoclave.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810373811.4A CN108652286B (en) | 2018-04-24 | 2018-04-24 | Scientific test cabinet skin assembly for space station and preparation method |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810373811.4A CN108652286B (en) | 2018-04-24 | 2018-04-24 | Scientific test cabinet skin assembly for space station and preparation method |
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| Publication Number | Publication Date |
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| CN108652286A true CN108652286A (en) | 2018-10-16 |
| CN108652286B CN108652286B (en) | 2021-07-09 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109446702A (en) * | 2018-11-09 | 2019-03-08 | 中国科学院沈阳自动化研究所 | A kind of passive type oscillation damping method of space science experiment cabinet |
Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH11177252A (en) * | 1997-12-05 | 1999-07-02 | Nippon Columbia Co Ltd | Cabinet |
| JP2008034477A (en) * | 2006-07-26 | 2008-02-14 | Swcc Showa Device Technology Co Ltd | Soundproofing system for electric apparatus |
| CN201489824U (en) * | 2009-09-04 | 2010-05-26 | 深圳市证通数码科技有限公司 | Shock-absorbing device of computer hard disk |
| CN102009509A (en) * | 2010-05-10 | 2011-04-13 | 梁森 | Manufacturing technology of embedded co-curing high-damping composite and laminate material structure |
| CN203111318U (en) * | 2013-01-17 | 2013-08-07 | 上海萃智科技发展有限公司 | Passenger car skin structure |
| KR20140038250A (en) * | 2012-09-20 | 2014-03-28 | 엘지전자 주식회사 | Washing machine |
| CN204253703U (en) * | 2011-04-11 | 2015-04-08 | 湾流航空航天公司 | For reducing system and the aircraft of the noise in aircraft cabin |
| CN104507294A (en) * | 2014-12-18 | 2015-04-08 | 中航光电科技股份有限公司 | Aeronautic electric equipment cabinet |
| CN204264408U (en) * | 2014-10-17 | 2015-04-15 | 江苏宏强船舶重工有限公司 | A kind of floating base plate for cabin noise reduction |
| CN206657969U (en) * | 2017-03-31 | 2017-11-21 | 广州电力机车有限公司 | A kind of low-floor tramcar energy storage device |
| CN206914317U (en) * | 2017-07-19 | 2018-01-23 | 徐州徐工矿山机械有限公司 | Quarry tipper accumulator cabinet |
| CN107831801A (en) * | 2017-12-08 | 2018-03-23 | 北京海月星科技有限公司 | A kind of vibration absorber |
| CN207149605U (en) * | 2017-09-15 | 2018-03-27 | 绵阳鹏志远科技有限公司 | Carry the battery rack of cooling function |
-
2018
- 2018-04-24 CN CN201810373811.4A patent/CN108652286B/en active Active
Patent Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH11177252A (en) * | 1997-12-05 | 1999-07-02 | Nippon Columbia Co Ltd | Cabinet |
| JP2008034477A (en) * | 2006-07-26 | 2008-02-14 | Swcc Showa Device Technology Co Ltd | Soundproofing system for electric apparatus |
| CN201489824U (en) * | 2009-09-04 | 2010-05-26 | 深圳市证通数码科技有限公司 | Shock-absorbing device of computer hard disk |
| CN102009509A (en) * | 2010-05-10 | 2011-04-13 | 梁森 | Manufacturing technology of embedded co-curing high-damping composite and laminate material structure |
| CN204253703U (en) * | 2011-04-11 | 2015-04-08 | 湾流航空航天公司 | For reducing system and the aircraft of the noise in aircraft cabin |
| KR20140038250A (en) * | 2012-09-20 | 2014-03-28 | 엘지전자 주식회사 | Washing machine |
| CN203111318U (en) * | 2013-01-17 | 2013-08-07 | 上海萃智科技发展有限公司 | Passenger car skin structure |
| CN204264408U (en) * | 2014-10-17 | 2015-04-15 | 江苏宏强船舶重工有限公司 | A kind of floating base plate for cabin noise reduction |
| CN104507294A (en) * | 2014-12-18 | 2015-04-08 | 中航光电科技股份有限公司 | Aeronautic electric equipment cabinet |
| CN206657969U (en) * | 2017-03-31 | 2017-11-21 | 广州电力机车有限公司 | A kind of low-floor tramcar energy storage device |
| CN206914317U (en) * | 2017-07-19 | 2018-01-23 | 徐州徐工矿山机械有限公司 | Quarry tipper accumulator cabinet |
| CN207149605U (en) * | 2017-09-15 | 2018-03-27 | 绵阳鹏志远科技有限公司 | Carry the battery rack of cooling function |
| CN107831801A (en) * | 2017-12-08 | 2018-03-23 | 北京海月星科技有限公司 | A kind of vibration absorber |
Non-Patent Citations (1)
| Title |
|---|
| 杨云昭等: "民用飞机机身蒙皮阻尼减振降噪效果分析", 《装备制造技术》 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109446702A (en) * | 2018-11-09 | 2019-03-08 | 中国科学院沈阳自动化研究所 | A kind of passive type oscillation damping method of space science experiment cabinet |
| CN109446702B (en) * | 2018-11-09 | 2022-10-14 | 中国科学院沈阳自动化研究所 | Passive vibration reduction method of space science experiment cabinet |
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| Publication number | Publication date |
|---|---|
| CN108652286B (en) | 2021-07-09 |
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