CN109673118A - A kind of damping - Google Patents
A kind of damping Download PDFInfo
- Publication number
- CN109673118A CN109673118A CN201811645020.9A CN201811645020A CN109673118A CN 109673118 A CN109673118 A CN 109673118A CN 201811645020 A CN201811645020 A CN 201811645020A CN 109673118 A CN109673118 A CN 109673118A
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- China
- Prior art keywords
- component
- connecting portion
- damping
- interconnecting piece
- line
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
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- 238000013016 damping Methods 0.000 title claims abstract description 35
- 238000004891 communication Methods 0.000 claims abstract description 27
- 238000000034 method Methods 0.000 abstract description 4
- 238000004519 manufacturing process Methods 0.000 abstract description 2
- 230000008569 process Effects 0.000 abstract description 2
- 238000010586 diagram Methods 0.000 description 7
- 238000005516 engineering process Methods 0.000 description 5
- 238000001228 spectrum Methods 0.000 description 5
- 230000005540 biological transmission Effects 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 230000007246 mechanism Effects 0.000 description 3
- 239000003381 stabilizer Substances 0.000 description 2
- 238000011161 development Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 238000002955 isolation Methods 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 229920006395 saturated elastomer Polymers 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
Classifications
-
- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
- H05K5/00—Casings, cabinets or drawers for electric apparatus
- H05K5/02—Details
- H05K5/0204—Mounting supporting structures on the outside of casings
Landscapes
- Engineering & Computer Science (AREA)
- Microelectronics & Electronic Packaging (AREA)
- Vibration Prevention Devices (AREA)
Abstract
A kind of damping, including the first component, second component and interconnecting piece, it is characterized by: the first component with communication terminal for being fixedly connected, the second component with extraneous aircraft or satellite for being fixedly connected, the interconnecting piece extends between the first component and second component, and interconnecting piece reciprocation extension back and forth between the first component and second component.The damping, not only structure it is simple, it is easy to process and production, and damping performance and elasticity it is all preferable, stable structure is hardly damaged, the environment suitable for spatial complex.
Description
Technical field
The present invention relates to a kind of satellite communication communication terminals, more particularly to a kind of damping of communication terminal.
Background technique
It is realized currently, air communications mainly passes through microwave satellite.When being communicated by the Microwave Radio, due to nothing
Line electric frequency is the basis that space system is able to run well, and is the channel of information transmission, in order to prevent inter-satellite electromagnetic interference,
Need to keep the certain intervals of communication frequency to carry out frequency isolation, therefore the utilization of radio-frequency spectrum will be extremely restricted.
Existing aviation interconnection technique is generally divided into three categories, is the up-link based on the telecomm base station of land respectively
Technology (Air To Ground, ATG), stationary orbit (GEO) satellite, low orbit (LEO) constellation.
ATG is a kind of land-air communication system, it is using mature land mobile technology, such as 3G, 4G technology,
But since it is radio communication, however it remains the problem that frequency spectrum is saturated and bandwidth is limited.
GEO satellite is currently the mainstream that satellite is applied in aviation field.According to frequency spectrum be broadly divided into SBB, Ku (including
2Ku and KuHTS), three kinds of Ka etc..But since it is radio communication, the audio range frequency used is limited, and communication bandwidth can not
Meet mass data demand for interconnection.
LEO low orbit constellation, since rail position is rare, recent years is a dark horse, and becomes the new force of satellite internet.
Compared to GEO, low-orbit satellite rail position is within 1500 kilometers, track of ten thousand kilometers compared to GE03.6, and antenna complex degree is low, logical
Letter delay is small, whole volume is big.Since it is radio communication, the still frequency spectrum that low orbit constellation primarily solves is limited and band
The limited problem of width.
Aeronautical communications network technology in the prior art, all has the problem of frequency spectrum, Bandwidth-Constrained, can not accomplish big data
The transmission of high-speed also cannot achieve the real-time Transmission and monitoring of aircraft data itself.
Therefore, laser communication technology communicates in satellite over the ground and to the field of aircraft communication, has greatly development empty
Between.This requires on satellite or aircraft, communication terminal structure is installed, regardless of be satellite or aircraft, all in
In the state of complicated space environment and long-term motion, so, it is particularly important for the shock-damping structure of communication terminal, such as Fig. 1
It is shown, for the common fixed connection structure of communication terminal 10, the structure generally include to be fixed under communication terminal in the prior art
The stabilizer blade 20 of side, the stabilizer blade are herringbone structure, and upper end and communication terminal 10 are fixed, lower end be separately in crotch shape and satellite or
Person's aircraft is fixedly connected, but such structure, and damping effect and effect are all not very good, to be improved.
Summary of the invention
That technical problem to be solved by the invention is to provide a kind of structures is simple, at low cost, and good damping effect subtracts
Shake mechanism.
The technical scheme of the invention to solve the technical problem is: a kind of damping, including the first component,
Two components and interconnecting piece, it is characterised in that: for being fixedly connected with communication terminal, the second component is used for the first component
It is fixedly connected with extraneous aircraft or satellite, the interconnecting piece extends between the first component and second component, and described
Interconnecting piece reciprocation extension back and forth between the first component and second component.
Preferably, line two sides of the interconnecting piece between the first component and second component in the two are back and forth prolonged back and forth
It stretches.
Preferably, the interconnecting piece is in " S " type reciprocation extension back and forth between the first component and second component.
Preferably, the interconnecting piece includes first connecting portion and second connecting portion, and the first connecting portion is in the first component
Interval is extended at least one between second component, and the second connecting portion has at least two, and the second connecting portion is by institute
The first component, first connecting portion and second component is stated to be sequentially connected.
Preferably, the second connecting portion successively joins end to end the first component, first connecting portion and second component.
Preferably, when the first connecting portion has at least two, at least two first connecting portion is parallel to each other interval,
The second connecting portion is parallel to each other interval.
Preferably, the first connecting portion is vertical with the line between the first component and second component, second connection
Line between portion and the first component and second component is parallel.
Preferably, the lateral dimension of the interconnecting piece is consistent between the first component and the second component；Described first
The lateral dimension of the interconnecting piece is gradually increased between component and second component；Or between the first component and second component
The lateral dimension of the interconnecting piece is gradually increased after being gradually reduced.
Preferably, the first connecting portion and second connecting portion are integrally formed.
Preferably, the first component, second component and interconnecting piece are integrally formed.
Compared with the prior art, the advantages of the present invention are as follows the dampings, and not only structure is simple, easy to process and raw
It produces, and damping performance and elasticity are all preferable, stable structure is hardly damaged, the environment suitable for spatial complex.
Detailed description of the invention
Fig. 1 is the schematic diagram of the fixed mechanism of communication terminal in the prior art.
Fig. 2 is the schematic diagram of the damping of first embodiment of the invention.
Fig. 3 is the stereoscopic schematic diagram of the damping of first embodiment of the invention.
Fig. 4 is the schematic diagram of the damping of second embodiment of the invention.
Fig. 5 is the stereoscopic schematic diagram of the damping of second embodiment of the invention.
Fig. 6 is the schematic diagram of the damping of third embodiment of the invention.
Fig. 7 is the stereoscopic schematic diagram of the damping of third embodiment of the invention.
Specific embodiment
The embodiment of the present invention is described below in detail, examples of the embodiments are shown in the accompanying drawings, wherein from beginning to end
Same or similar label indicates same or similar element or element with the same or similar functions.Below with reference to attached
The embodiment that Fig. 1-7 is described is exemplary, it is intended to is used to explain the present invention, and is not considered as limiting the invention.
Term " first ", " second " be used for descriptive purposes only and cannot be understood as indicating or suggesting relative importance or
Implicitly indicate the quantity of indicated technical characteristic." first " is defined as a result, the feature of " second " can be expressed or imply
Ground includes one or more of the features.In the description of the present invention, the meaning of " plurality " is two or more, unless
Separately there is clearly specific restriction.
In the present invention unless specifically defined or limited otherwise, term " installation ", " connected ", " connection ", " fixation " etc.
Term shall be understood in a broad sense, for example, it may be being fixedly connected, may be a detachable connection, or integral；It can be mechanical connect
It connects, is also possible to be electrically connected；It can be directly connected, can also can be in two elements indirectly connected through an intermediary
The interaction relationship of the connection in portion or two elements.It for the ordinary skill in the art, can be according to specific feelings
Condition understands the concrete meaning of above-mentioned term in the present invention.
As shown in Figure 2,3, the damping of the first embodiment of the present invention, including be fixedly connected with communication terminal 10
One component 1, with the spaced second component 2 of the first component 1, the first component 1 is fixedly connected on 10 bottom of communication terminal,
Second component 2 is used to be fixedly connected with extraneous satellite or aircraft.
Extend between the first component 1 and second component 2 and be equipped with interconnecting piece 3, the interconnecting piece 3 connects the first component 1 and the
Two components 2.The interconnecting piece 3 includes first connecting portion 31 and second connecting portion 32, and the first connecting portion 31 is in the first component 1
Between second component 2, be arranged at intervals at least one with the first component 1 and second component 2, the second connecting portion 32 have to
It is two few.Preferably, the first connecting portion 31 and the line direction of the first component 1 and second component 2 extend vertically.Such as Fig. 2,3
It is shown, it is also possible to first connecting portion 31 and the line direction of the first component 1 and second component 2 is obliquely installed, multiple first connects
Socket part 31 can be parallel to each other, and can also be not parallel to each other, for example, the line between the first component and second component 2, such as Fig. 3
Shown line A-A, first connecting portion 31 includes spaced multiple, and multiple first connecting portions 31 and the line A-A are to two
Direction is arranged at an angle, such as a first connecting portion 31 and line A-A are arranged in angle a, another adjacent first connection
Portion and line A-A are arranged in angle-a, and latter one first connecting portion 31 and line A-A are in angle a setting, subsequent first connecting portion again
31 are arranged with line A-A in angle-a, i.e., successively deviate in identical angle to both direction with line A-A and be arranged.The second connecting portion
32 are sequentially connected end to end the first component 1, first connecting portion 31 and second component 2.Preferably, the second connecting portion 32 and A-A
Line is parallel, or is arranged at an angle.The second connecting portion 32 should be divided into the first component 1 and second component 2 to be multiple
Line line A-A two sides, multiple second connecting portions 32 can be parallel to each other, can also be not parallel to each other.
As shown in Figure 2,3, which is separately connected two adjacent first connecting portions 31, and the second connection
Portion 32 is staggered successively set on the two sides of first connecting portion 31.For example, as shown in Figure 2,3, which has 3, the
One second connecting portion 32 connects the first end and the first component 1 of first first connecting portion 31, second second connecting portion 32
The second end of first connecting portion 31 and the second end of second second connecting portion 32 are connected, third second connecting portion 32 connects the
The first end of two second connecting portions 32 and the first end of third second connecting portion 32, the 4th connection of second connecting portion 32 the
The second end and second component 2 of three second connecting portions 32.
Those skilled in the art can also understand that, and be also possible to the first connecting portion 31 with 3, first second connects
Socket part 32 connects the first end and the first component 1 of first first connecting portion 31, and second second connecting portion 32 connects first
The second end of the second end of first connecting portion 31 and second first connecting portion, the connection of third second connecting portion 32 second the
The first end of one interconnecting piece 31 and the second end of third first connecting portion, the 4th second connecting portion 32 connect third first
The first end and second component 2 of interconnecting piece.Those skilled in the art can also be arranged according to above-mentioned principle first connecting portion and
Second connecting portion, as long as the entirety that the first connecting portion 31 and second connecting portion 32 are formed, in the first component 1 and second component 2
Between in " S " type reciprocation extension back and forth, further, between the first component 1 and second component 2, in the two line A-A
The two sides of line reciprocation extension back and forth.
Such setting so that interconnecting piece 3 extends between the first component 1 and second component 2, and has certain elasticity
And shock-absorbing function.Moreover, the first component 1, second component 2 and interconnecting piece 3 can be integrally formed, it is subsequently processed into as shown in the figure
Shape, or connection molding after processing respectively.The first component 1 with communication terminal for the ease of connecting, it can be provided with
The structure that communication terminal securely connects, second component 2 with extraneous aircraft or satellite for the ease of connecting, it can be provided just
In the structure being connected and fixed with aircraft or satellite.First, second component can be with damping performance either damping machine
Structure itself can not also have shock-absorbing function, by the elastic shock attenuation of interconnecting piece.
As shown in Figure 2,3, above-mentioned first connecting portion 31 is parallel to each other, and is correspondingly arranged up and down, i.e., entire interconnecting piece from
On down size be unanimously arranged.And the first component 1 is a plates, is fixedly connected on the side of communication terminal 10, second
Component 2 is also a plates, and is laterally arranged, and the size of horizontal direction is all larger than interconnecting piece, be easy to structure stabilization and
Convenient for being installed with extraneous aircraft or satellite.
It as shown in Figure 4,5, is the second embodiment of the present invention, other in the embodiment and the structure phase in first embodiment
Together, unlike, length gradually increases multiple first connecting portions 31 from top to bottom, and therefore, entire interconnecting piece is past from the first component
Its transverse width of second component gradually increases, in this way, making interconnecting piece not only has elasticity and damping performance, structure is also more steady
Gu.
It as shown in Figure 6,7, is the third embodiment of the present invention, other structures are implemented with first, second in the embodiment
Example is identical, unlike, length is gradually reduced and gradually increases multiple first connecting portions 31 from top to bottom, the cross of entire interconnecting piece
It is gradually increased again to tapering width, not only increases elasticity and damping performance, and make entire mechanism more firm.
Those skilled in the art can on the basis of above-mentioned principle designed, designed interconnecting piece structure, as long as the interconnecting piece
The reciprocation extension back and forth between the first component 1 and second component 2.Such damping, not only structure is simple, is easy to add
Work and production, and damping performance and elasticity are all preferable, and stable structure is hardly damaged, the environment suitable for spatial complex.
Although the preferred embodiment of the present invention has been described in detail above, it is to be clearly understood that for this field
Technical staff for, the invention may be variously modified and varied.Done within the spirit and principles of the present invention
What modification, equivalent replacement, improvement etc., should all be included in the protection scope of the present invention.
Claims (10)
1. a kind of damping, including the first component (1), second component (2) and interconnecting piece (3), it is characterised in that: described first
Component (1) with communication terminal (10) for being fixedly connected, and the second component (2) with extraneous aircraft or satellite for fixing
Connection, the interconnecting piece (3) extends between the first component (1) and second component (2), and the interconnecting piece (3) is first
Reciprocation extension back and forth between component (1) and second component (2).
2. damping as described in claim 1, it is characterised in that: the interconnecting piece (3) is in the first component (1) and second
In the line two sides of the two reciprocation extension back and forth between part (2).
3. damping as claimed in claim 2, it is characterised in that: the interconnecting piece (3) is in the first component (1) and second
It is in " S " type reciprocation extension back and forth between part (2).
4. damping as claimed in any one of claims 1-3, it is characterised in that: the interconnecting piece (3) includes the first company
Socket part (31) and second connecting portion (32), the first connecting portion (31) are spaced between the first component (1) and second component (2)
Be extended at least one, the second connecting portion has at least two, the second connecting portion (32) by the first component (1),
First connecting portion (31) and second component (2) are sequentially connected.
5. damping as claimed in claim 4, it is characterised in that: the second connecting portion (32) is by the first component
(1), first connecting portion (31) and second component (2) successively join end to end.
6. damping as claimed in claim 4, it is characterised in that: when the first connecting portion (31) has at least two, institute
It states at least two first connecting portions (31) to be parallel to each other interval, the second connecting portion (32) is parallel to each other interval.
7. damping as claimed in claim 6, it is characterised in that: the first connecting portion (31) and the first component (1) and
Line between second component (2) is vertical, between the second connecting portion (32) and the first component (1) and second component (2)
Line is parallel.
8. damping as claimed in any one of claims 1-3, it is characterised in that: in the first component (1) and second
The lateral dimension of the interconnecting piece (3) is consistent between component (2)；The company between the first component (1) and second component (2)
The lateral dimension of socket part (3) is gradually increased；Or the interconnecting piece (3) between the first component (1) and second component (2)
Lateral dimension is gradually increased after being gradually reduced.
9. damping as claimed in claim 4, it is characterised in that: the first connecting portion (1) and second connecting portion (32)
It is integrally formed.
10. damping as described in claim 1, it is characterised in that: the first component (1), second component (2) and connection
Portion (3) is integrally formed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811645020.9A CN109673118A (en) | 2018-12-29 | 2018-12-29 | A kind of damping |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811645020.9A CN109673118A (en) | 2018-12-29 | 2018-12-29 | A kind of damping |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109673118A true CN109673118A (en) | 2019-04-23 |
Family
ID=66146663
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811645020.9A Pending CN109673118A (en) | 2018-12-29 | 2018-12-29 | A kind of damping |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109673118A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20040051321A1 (en) * | 2002-09-17 | 2004-03-18 | Isao Hanai | Shock-absorbing bumper device |
| CN206409571U (en) * | 2016-12-23 | 2017-08-15 | 昊翔电能运动科技(昆山)有限公司 | Speed regulator vibration damping sheet and unmanned plane |
| CN107370323A (en) * | 2017-04-14 | 2017-11-21 | 瑞声科技(新加坡)有限公司 | Resonator device and electronic equipment |
| CN207819918U (en) * | 2018-02-01 | 2018-09-04 | 南京荧火泰讯信息科技有限公司 | A kind of satellite communication terminal with shock-absorbing function |
| CN208165250U (en) * | 2018-09-12 | 2018-11-30 | 王珈懿 | It is a kind of be easily installed disassembly damping device aircraft |
-
2018
- 2018-12-29 CN CN201811645020.9A patent/CN109673118A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20040051321A1 (en) * | 2002-09-17 | 2004-03-18 | Isao Hanai | Shock-absorbing bumper device |
| CN206409571U (en) * | 2016-12-23 | 2017-08-15 | 昊翔电能运动科技(昆山)有限公司 | Speed regulator vibration damping sheet and unmanned plane |
| CN107370323A (en) * | 2017-04-14 | 2017-11-21 | 瑞声科技(新加坡)有限公司 | Resonator device and electronic equipment |
| CN207819918U (en) * | 2018-02-01 | 2018-09-04 | 南京荧火泰讯信息科技有限公司 | A kind of satellite communication terminal with shock-absorbing function |
| CN208165250U (en) * | 2018-09-12 | 2018-11-30 | 王珈懿 | It is a kind of be easily installed disassembly damping device aircraft |
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| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20190423 |
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