CN208523098U - Vibration damping cabinet - Google Patents
Vibration damping cabinet Download PDFInfo
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- CN208523098U CN208523098U CN201820406602.0U CN201820406602U CN208523098U CN 208523098 U CN208523098 U CN 208523098U CN 201820406602 U CN201820406602 U CN 201820406602U CN 208523098 U CN208523098 U CN 208523098U
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Abstract
Present disclose provides a kind of vibration damping cabinet, the vibration damping cabinet includes equipment enclosure component；Top damping assembly is connected with equipment enclosure component top structure；Bottom damping assembly is connected with equipment enclosure component bottom structure；Rod assembly is connected with top damping assembly top structure；Head track component, connecting rod component and aircraft top rail；And ground rail assembly, connect bottom damping assembly and aircraft seat track.The vibration damping cabinet of the disclosure solves the problems, such as that the equipment effectiveness in vibration suppression installed on the existing higher device cabinet of civilian airplane in transportation category is poor, low efficiency, and structure is simple, installation and removal are flexible, easy to use.
Description
Technical field
The disclosure belongs to airborne equipment antivibration area, and in particular to a kind of vibration damping cabinet.
Background technique
The various kinds of equipment cabinet installed and used in civilian transport class Special Aircraft main cabin, to adapt to strength of aircraft, vibration, punching
It the mechanical environment conditions such as hits and needs to add vibration absorber, and to 9g inertial load coefficient requirements before meeting simultaneously.
The equipment cabinets and cabinet vibration damping installed and used in civilian transport class Special Aircraft main cabin common in the art
There are four types of schemes:
The first scheme, electronic equipment are fixed in equipment enclosure by pallet, and equipment enclosure passes through bottom damping assembly
It is fixed on airframe structure；Second scheme, electronic equipment are fixed in equipment enclosure by pallet and vibration absorber, equipment machine
Cabinet and airframe structure are connected；The third scheme, electronic equipment are fixed in equipment enclosure by pallet, and equipment enclosure is directly fixed
On airframe structure.
These three schemes all there is a problem of respective:
The first scheme since vibration damping cabinet is only equipped with vibration absorber in cabinet bottom and fuselage link position, and only by
Damper and aircraft tie point ensure cabinet intensity, to guarantee that cabinet is by stress after inertial load and deformation in flight course
In civil aviaton's prescribed limit, which is highly restricted, and vibration damping scheme may be only available for height
Lower (total height be not more than 0.8 meter), the equipment enclosure of lighter in weight (total weight is not more than double centner), when cabinet is higher,
When heavier-weight, vibration absorber is more difficult to be met before seaworthiness to 9g inertial load coefficient requirements.
The second scheme vibration damping cabinet is connected by cabinet bottom and aircraft, and intensity is higher；Have between equipment and cabinet
Vibration absorber so that the cabinet can load capacity increase, height increase, although solve height it is higher (total height be greater than 0.8
Rice), the equipment enclosure of heavier-weight (total weight is greater than 100 kilograms) meet asking to 9g inertial load coefficient requirements before seaworthiness
Topic, but vibration damping scheme needs to provide vibration absorber for every equipment, increases the usage quantity of vibration absorber, occupies and set
Effect height space is had, the service efficiency of the carrier aircraft confined space is reduced.
The third scheme vibration damping cabinet passes through to be connected between cabinet bottom and aircraft, is connected between equipment and cabinet, intensity
It is higher, greatly improve cabinet can load capacity although solving height higher (total height be greater than 0.8 meter), the equipment of heavier-weight
Cabinet (total weight be greater than double centner) meets before seaworthiness the problem of to 9g inertial load coefficient requirements, but eliminates vibration damping dress
It sets, dress can not be fitted to vibration and the more sensitive electronic equipment of impulse ratio.
4th kind of planning device cabinet assembly is connected by side damping assembly and bottom damping assembly and switching support component
It connects, switching support component and airframe structure are connected.
The first scheme since vibration damping cabinet is only equipped with vibration absorber in cabinet bottom and fuselage link position, and only by
Damper and aircraft tie point ensure cabinet intensity, to guarantee that cabinet is by stress after inertial load and deformation in flight course
In civil aviaton's prescribed limit, which is highly restricted, and vibration damping scheme may be only available for height
Lower (total height be not more than 0.8 meter), the equipment enclosure of lighter in weight (total weight is not more than double centner), when cabinet is higher,
When heavier-weight, vibration absorber is more difficult to be met before seaworthiness to 9g inertial load coefficient requirements.
The second scheme vibration damping cabinet is connected by cabinet bottom and aircraft, and intensity is higher；Have between equipment and cabinet
Vibration absorber so that the cabinet can load capacity increase, height increase, although solve height it is higher (total height be greater than 0.8
Rice), the equipment enclosure of heavier-weight (total weight is greater than 100 kilograms) meet asking to 9g inertial load coefficient requirements before seaworthiness
Topic, but vibration damping scheme needs to provide vibration absorber for every equipment, increases the usage quantity of vibration absorber, occupies and set
Effect height space is had, the service efficiency of the carrier aircraft confined space is reduced.
The third scheme vibration damping cabinet passes through to be connected between cabinet bottom and aircraft, is connected between equipment and cabinet, intensity
It is higher, greatly improve cabinet can load capacity although solving height higher (total height be greater than 0.8 meter), the equipment of heavier-weight
Cabinet (total weight be greater than double centner) meets before seaworthiness the problem of to 9g inertial load coefficient requirements, but eliminates vibration damping dress
It sets, dress can not be fitted to vibration and the more sensitive electronic equipment of impulse ratio.
4th kind of scheme side of cabinet and cabinet bottom are respectively equipped with vibration absorber, and switching support component subtracts side
Vibration component, bottom damping assembly and airframe structure connect, and have reached preferable effectiveness in vibration suppression；But the program occupy compared with
Large space, and when equipment enclosure height is greater than 1.3 meters, total weight is greater than 150 kilograms, the more difficult satisfaction of program structural strength is suitable
To 9g inertial load coefficient requirements before boat.
Utility model content
(1) technical problems to be solved
Present disclose provides a kind of vibration damping cabinets, at least partly to solve technical problem set forth above.
(2) technical solution
Present disclose provides a kind of vibration damping cabinets, comprising: equipment enclosure；Top damping assembly, the top with equipment enclosure
Structure is connected；Bottom damping assembly is connected with the bottom structure of equipment enclosure；Rod assembly, the top with top damping assembly
Structure is connected；Head track component, connecting rod component and aircraft top rail；And ground rail assembly, connection bottom damping assembly and
Aircraft seat track.
In some embodiments of the present disclosure, equipment enclosure includes several equipment cabinets, and equipment cabinets use guide rail knot
Structure installation, and be connected by front panel and equipment enclosure, without vibration reducing measure between equipment cabinets and equipment enclosure.
In some embodiments of the present disclosure, top damping assembly includes 2,3 or 4 dampers, and damper is parallel to machine
Cabinet side is arranged successively.
In some embodiments of the present disclosure, bottom damping assembly includes 4,6 or 8 dampers, and damper is at cabinet bottom
Portion uniformly arranges on each side.
In some embodiments of the present disclosure, damper is wire rope damper.
In some embodiments of the present disclosure, top damping assembly further includes upper and lower structural slab, is located at damper two
Side, structural slab are stainless steel, No. 20 steel or sheet metal component.
In some embodiments of the present disclosure, rod assembly includes: pull rod, and there are mounting hole, front end mounting hole in both ends
It is connect by fastening stud with enclosure top connecting plate；Locking plate is connect by fastening stud with back end of tie rod mounting hole；With
And locking level, lock the position of pull rod and locking plate.
In some embodiments of the present disclosure, head track component includes exchanging structure, and exchanging structure passes through sliding block and fastener
It is connected with aircraft top rail, is connected by screw and rod assembly.
In some embodiments of the present disclosure, ground rail assembly is the bedframe being welded by 6063 quarter bends, bottom
It is fixedly connected by anchor nut, scotch with aircraft seat track, top is fixedly connected by screw with damper.
In some embodiments of the present disclosure, height >=1.3 meter of equipment enclosure, total weight >=150 kilogram.
(3) beneficial effect
It can be seen from the above technical proposal that disclosure vibration damping cabinet at least has the advantages that one of them:
(1) it is connected due to program bottom, top with aircraft, takes full advantage of aircraft altitude to space, to is suitable for
Higher equipment enclosure；
(2) due to the program by bottom damping assembly, rail assembly be connected with aircraft track, pass through top vibration damping group
Part, rod assembly are connected with aircraft head track, and upper and lower connection structure and vibration-proof structure have ensured cabinet intensity and shock resistance, vibration
Between balance, solve the problems, such as that electronic apparatus vibration requirement is contradicted with before seaworthiness to 9g inertial load coefficient requirements；
(3) since the program uses modularized design, top, bottom are respectively adopted array damper assembly and cabinet, fly
Machine structure is connected, and has the advantages that good damping result, structure are simple, installs or dismantle flexible, easy to use.
Detailed description of the invention
Fig. 1 is vibration damping cabinet schematic diagram described in the utility model embodiment.
Fig. 2 is the fixed form schematic diagram of electronic equipment chassis in vibration damping cabinet shown in Fig. 1.
Fig. 3 is rod assembly schematic diagram in vibration damping cabinet shown in Fig. 1.
[embodiment of the present disclosure main element symbol description in attached drawing]
10- equipment enclosure；
11- electronic equipment chassis；12- guide rail；
Damping assembly at the top of 20-；
The bottom 30- damping assembly；
40- rod assembly；
50- head track component；
The ground 60- rail assembly；
41- pull rod；42- fastening stud；
43- locking level；44- locking plate.
Specific embodiment
Present disclose provides a kind of vibration damping cabinet, the vibration damping cabinet includes equipment enclosure component；Top damping assembly, with
Equipment enclosure component top structure is connected；Bottom damping assembly is connected with equipment enclosure component bottom structure；Rod assembly, with
Top damping assembly top structure is connected；Head track component, connecting rod component and aircraft top rail；And ground rail assembly, even
Connect bottom damping assembly and aircraft seat track.The vibration damping cabinet of the disclosure solves the existing higher device of civilian airplane in transportation category
The problem of equipment effectiveness in vibration suppression installed on cabinet is poor, low efficiency, structure is simple, installation and removal are flexible, easy to use.
For the purposes, technical schemes and advantages of the disclosure are more clearly understood, below in conjunction with specific embodiment, and reference
The disclosure is further described in attached drawing.
Disclosure some embodiments will be done referring to appended attached drawing in rear and more comprehensively describe to property, some of but not complete
The embodiment in portion will be shown.In fact, the various embodiments of the disclosure can be realized in many different forms, and should not be construed
To be limited to this several illustrated embodiment；Relatively, these embodiments are provided so that the disclosure meets applicable legal requirement.
In an exemplary embodiment of the disclosure, a kind of vibration damping cabinet is provided.Fig. 1 is in one embodiment of the disclosure
Vibration damping cabinet schematic diagram.As shown in Figure 1, disclosure vibration damping cabinet includes: equipment enclosure component 10；Top damping assembly 20, with
10 top structure of equipment enclosure component is connected；Bottom damping assembly 30 is connected with 10 bottom structure of equipment enclosure component；Pull rod group
Part 40 is connected with 20 top structure of top damping assembly；Head track component 50, connecting rod component 40 and aircraft top rail；With
And ground rail assembly 60, connect bottom damping assembly 30 and aircraft seat track.
Each component part of the present embodiment vibration damping cabinet is described in detail individually below.
In the present embodiment, top damping assembly 20 is made of 2,3 or 4 dampers and upper and lower structural slab, and damper is steel
Cord damper, arrangement mode are to be arranged successively, and structural slab is stainless steel or No. 20 steel, sheet metal component.
In the present embodiment, bottom damping assembly is made of 4,6 or 8 dampers, and damper is wire rope damper, arrangement
Mode is that each side in cabinet bottom is uniformly arranged.
As shown in Figure 1, the cabinet of equipment enclosure component installs equipment cabinets using guide rail structure pattern, and pass through equipment machine
Case front panel and cabinet are connected, without vibration reducing measure between equipment cabinets and cabinet.
Head track component is made of 2 sets of exchanging structures, sliding block and fastener, and exchanging structure is by sliding block and fastener and flies
Machine top rail is connected, and is connected by screw and rod assembly.
Ground rail assembly forms frame structure by thin-walled square tube interconnection, and bottom passes through anchor nut, scotch and aircraft
Track is fixedly connected, and top is fixedly connected by screw with damper.
Fig. 2 is the fixed form schematic diagram of electronic equipment in vibration damping cabinet shown in Fig. 1.As shown in Fig. 2, electronic equipment chassis
11 are fixed on equipment enclosure component 10 by guide rail 12, (equipment cabinets of corresponding size can be installed according to specifically used demand,
Cabinet, to being sequentially placed, is fixed on cabinet in height by two sides guide rail and front panel mounting hole.Equipment enclosure component 10
It is directly anchored on airframe structure.Equipment enclosure component total height is >=1.3 meters, total weight >=150 kilogram.
Fig. 3 is rod assembly schematic diagram in vibration damping cabinet shown in Fig. 1.As shown in figure 3, rod assembly 40 is by 4 sets of pull rods
41,8 sets of 42,2 sets of fastening stud, 43,2 sets of locking level locking plate 44 compositions, pull rod is elongate rod-like structures, both ends mounting hole
It is interconnected by fastening stud and locking plate, enclosure top connecting plate, locking level is used to lock the position of pull rod and locking plate, makes him
Do not relatively rotate or move, the installation site of rod assembly is adjustable.
The installation of vibration damping cabinet, dismantlement scheme are as follows in the present embodiment: head track component being installed to aircraft head rail first
It is upper, rail assembly be installed in aircraft seat track, then bottom damping assembly is fixed on ground rail assembly, by equipment enclosure
It is fixed in enclosure top and head track component fixed on the damping assembly of bottom, then by top damping assembly, finally sets electronics
It is standby to be respectively installed in equipment enclosure；Dismantlement scheme is carried out according to the backward of mount scheme；If head track component is hidden in aircraft
The inside of top trim panel can increase next installation speed then without disassembly.
In conclusion the vibration damping cabinet includes equipment enclosure component present disclose provides a kind of vibration damping cabinet；Top subtracts
Shake component, is connected with equipment enclosure component top structure；Bottom damping assembly is connected with equipment enclosure component bottom structure；It draws
Bar assembly is connected with top damping assembly top structure；Head track component, connecting rod component and aircraft top rail；And ground
Rail assembly connects bottom damping assembly and aircraft seat track.It is existing that the vibration damping cabinet of the disclosure solves civilian airplane in transportation category
There is the problem of poor equipment effectiveness in vibration suppression installed on higher device cabinet, low efficiency, structure is simple, installation and removal are flexible, makes
With conveniently.
It should also be noted that, the direction term mentioned in embodiment, for example, "upper", "lower", "front", "rear", " left side ",
" right side " etc. is only the direction with reference to attached drawing, not is used to limit the protection scope of the disclosure.Through attached drawing, identical element by
Same or similar appended drawing reference indicates.When may cause understanding of this disclosure and cause to obscure, conventional structure will be omitted
Or construction.
And the shape and size of each component do not reflect actual size and ratio in figure, and only illustrate the embodiment of the present disclosure
Content.In addition, in the claims, any reference symbol between parentheses should not be configured to the limit to claim
System.
Furthermore word "comprising" does not exclude the presence of element or step not listed in the claims.It is located in front of the element
Word "a" or "an" does not exclude the presence of multiple such elements.
The word of ordinal number such as " first ", " second ", " third " etc. used in specification and claim, with modification
Corresponding element, itself is not meant to that the element has any ordinal number, does not also represent the suitable of a certain element and another element
Sequence in sequence or manufacturing method, the use of those ordinal numbers are only used to enable an element and another tool with certain name
Clear differentiation can be made by having the element of identical name.
Similarly, it should be understood that in order to simplify the disclosure and help to understand one or more of each open aspect,
Above in the description of the exemplary embodiment of the disclosure, each feature of the disclosure is grouped together into single implementation sometimes
In example, figure or descriptions thereof.However, the disclosed method should not be interpreted as reflecting the following intention: i.e. required to protect
The disclosure of shield requires features more more than feature expressly recited in each claim.More precisely, as following
Claims reflect as, open aspect is all features less than single embodiment disclosed above.Therefore,
Thus the claims for following specific embodiment are expressly incorporated in the specific embodiment, wherein each claim itself
All as the separate embodiments of the disclosure.
Particular embodiments described above has carried out further in detail the purpose of the disclosure, technical scheme and beneficial effects
Describe in detail it is bright, it is all it should be understood that be not limited to the disclosure the foregoing is merely the specific embodiment of the disclosure
Within the spirit and principle of the disclosure, any modification, equivalent substitution, improvement and etc. done should be included in the guarantor of the disclosure
Within the scope of shield.
Claims (10)
1. a kind of vibration damping cabinet is applied on aircraft characterized by comprising
Equipment enclosure (10)；
Top damping assembly (20) is connected with the top structure of the equipment enclosure (10)；
Bottom damping assembly (30) is connected with the bottom structure of the equipment enclosure (10)；
Rod assembly (40) is connected with the top structure of the top damping assembly (20)；
Head track component (50) connects the rod assembly (40) and aircraft top rail；And
Ground rail assembly (60) connects the bottom damping assembly (30) and aircraft seat track.
2. vibration damping cabinet according to claim 1, which is characterized in that
The equipment enclosure (10) includes several equipment cabinets, and the equipment cabinets are installed using guide rail structure, and before passing through
Panel and the equipment enclosure (10) are connected, without vibration reducing measure between the equipment cabinets and the equipment enclosure (10).
3. vibration damping cabinet according to claim 1, which is characterized in that
The top damping assembly (20) includes 2,3 or 4 dampers, and the damper is parallel to side of cabinet and is arranged successively.
4. vibration damping cabinet according to claim 1, which is characterized in that
The bottom damping assembly (30) includes 4,6 or 8 dampers, and the damper is uniformly arranged on each side in cabinet bottom.
5. vibration damping cabinet according to claim 3 or 4, which is characterized in that
The damper is wire rope damper.
6. vibration damping cabinet according to claim 3, which is characterized in that
The top damping assembly (20) further includes upper and lower structural slab, is located at the damper two sides, and the structural slab is not
Become rusty steel, No. 20 steel or sheet metal component.
7. vibration damping cabinet according to claim 1, which is characterized in that
The rod assembly (40) includes:
There is mounting hole at pull rod (41), both ends, and front end mounting hole is connect by fastening stud (42) with enclosure top connecting plate；
Locking plate (44) is connect by fastening stud (42) with the pull rod (41) rear end mounting hole；And
Locking level (43) locks the position of the pull rod (41) and the locking plate (44).
8. vibration damping cabinet according to claim 1, which is characterized in that
The head track component (50) includes exchanging structure, and the exchanging structure is solid by sliding block and fastener and aircraft top rail
Even, it is connected by screw and the rod assembly (40).
9. vibration damping cabinet according to claim 4, which is characterized in that
Described ground rail assembly (60) is the bedframe being welded by 6063 quarter bends, and bottom passes through anchor nut, scotch
It is fixedly connected with aircraft seat track, top is fixedly connected by screw with the damper.
10. vibration damping cabinet described in any one of according to claim 1~4 or 6~9, which is characterized in that equipment enclosure (10)
Highly >=1.3 meter, total weight >=150 kilogram.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820406602.0U CN208523098U (en) | 2018-03-23 | 2018-03-23 | Vibration damping cabinet |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820406602.0U CN208523098U (en) | 2018-03-23 | 2018-03-23 | Vibration damping cabinet |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208523098U true CN208523098U (en) | 2019-02-19 |
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ID=65341134
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201820406602.0U Active CN208523098U (en) | 2018-03-23 | 2018-03-23 | Vibration damping cabinet |
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| Country | Link |
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| CN (1) | CN208523098U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113573511A (en) * | 2020-12-22 | 2021-10-29 | 北京航天控制仪器研究所 | Vibration reduction cabinet for unmanned ship and vibration reduction method thereof |
-
2018
- 2018-03-23 CN CN201820406602.0U patent/CN208523098U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113573511A (en) * | 2020-12-22 | 2021-10-29 | 北京航天控制仪器研究所 | Vibration reduction cabinet for unmanned ship and vibration reduction method thereof |
| CN113573511B (en) * | 2020-12-22 | 2023-06-06 | 航天时代(青岛)海洋装备科技发展有限公司 | Vibration reduction cabinet for unmanned ship and vibration reduction method thereof |
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