CN110002012A - A kind of synchronization docking facilities between aircraft bay section - Google Patents
A kind of synchronization docking facilities between aircraft bay section Download PDFInfo
- Publication number
- CN110002012A CN110002012A CN201910360027.4A CN201910360027A CN110002012A CN 110002012 A CN110002012 A CN 110002012A CN 201910360027 A CN201910360027 A CN 201910360027A CN 110002012 A CN110002012 A CN 110002012A
- Authority
- CN
- China
- Prior art keywords
- cabin
- docking
- circuit board
- printed circuit
- synchronized
- 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.)
- Granted
Links
- 238000003032 molecular docking Methods 0.000 title claims abstract description 73
- 230000001360 synchronised effect Effects 0.000 claims abstract description 65
- 238000003466 welding Methods 0.000 claims abstract description 13
- 230000013011 mating Effects 0.000 claims description 7
- 239000000463 material Substances 0.000 claims description 6
- 238000000034 method Methods 0.000 abstract description 7
- 230000000694 effects Effects 0.000 abstract description 4
- 230000002411 adverse Effects 0.000 abstract description 3
- 108010066057 cabin-1 Proteins 0.000 description 8
- 230000005611 electricity Effects 0.000 description 3
- 238000005452 bending Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000007639 printing Methods 0.000 description 2
- 239000007787 solid Substances 0.000 description 2
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000004519 grease Substances 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 229920001296 polysiloxane Polymers 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
- 239000000741 silica gel Substances 0.000 description 1
- 229910002027 silica gel Inorganic materials 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
- B64G1/646—Docking or rendezvous systems
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01R—ELECTRICALLY-CONDUCTIVE CONNECTIONS; STRUCTURAL ASSOCIATIONS OF A PLURALITY OF MUTUALLY-INSULATED ELECTRICAL CONNECTING ELEMENTS; COUPLING DEVICES; CURRENT COLLECTORS
- H01R12/00—Structural associations of a plurality of mutually-insulated electrical connecting elements, specially adapted for printed circuits, e.g. printed circuit boards [PCB], flat or ribbon cables, or like generally planar structures, e.g. terminal strips, terminal blocks; Coupling devices specially adapted for printed circuits, flat or ribbon cables, or like generally planar structures; Terminals specially adapted for contact with, or insertion into, printed circuits, flat or ribbon cables, or like generally planar structures
- H01R12/70—Coupling devices
- H01R12/71—Coupling devices for rigid printing circuits or like structures
- H01R12/712—Coupling devices for rigid printing circuits or like structures co-operating with the surface of the printed circuit or with a coupling device exclusively provided on the surface of the printed circuit
- H01R12/716—Coupling device provided on the PCB
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01R—ELECTRICALLY-CONDUCTIVE CONNECTIONS; STRUCTURAL ASSOCIATIONS OF A PLURALITY OF MUTUALLY-INSULATED ELECTRICAL CONNECTING ELEMENTS; COUPLING DEVICES; CURRENT COLLECTORS
- H01R13/00—Details of coupling devices of the kinds covered by groups H01R12/70 or H01R24/00 - H01R33/00
- H01R13/62—Means for facilitating engagement or disengagement of coupling parts or for holding them in engagement
- H01R13/629—Additional means for facilitating engagement or disengagement of coupling parts, e.g. aligning or guiding means, levers, gas pressure electrical locking indicators, manufacturing tolerances
- H01R13/631—Additional means for facilitating engagement or disengagement of coupling parts, e.g. aligning or guiding means, levers, gas pressure electrical locking indicators, manufacturing tolerances for engagement only
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01R—ELECTRICALLY-CONDUCTIVE CONNECTIONS; STRUCTURAL ASSOCIATIONS OF A PLURALITY OF MUTUALLY-INSULATED ELECTRICAL CONNECTING ELEMENTS; COUPLING DEVICES; CURRENT COLLECTORS
- H01R24/00—Two-part coupling devices, or either of their cooperating parts, characterised by their overall structure
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01R—ELECTRICALLY-CONDUCTIVE CONNECTIONS; STRUCTURAL ASSOCIATIONS OF A PLURALITY OF MUTUALLY-INSULATED ELECTRICAL CONNECTING ELEMENTS; COUPLING DEVICES; CURRENT COLLECTORS
- H01R2201/00—Connectors or connections adapted for particular applications
- H01R2201/26—Connectors or connections adapted for particular applications for vehicles
Landscapes
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Combinations Of Printed Boards (AREA)
Abstract
The present invention provides the synchronization docking facilities between a kind of aircraft bay section, including the first transfer panel, the second transfer panel, the first printed circuit board and the second printed circuit board；First transfer panel is along the first cabin that the cross section of the first cabin of docking to be synchronized is fixed at docking to be synchronized, second transfer panel is along the second cabin that the cross section of the second cabin of docking to be synchronized is fixed at docking to be synchronized, the first printed circuit board is fixed on first transfer panel, the second printed circuit board is fixed on second transfer panel, welding equipment has electric connector, the first printed circuit board and the second printed circuit board to be connected to by electric connector and is arranged on first printed circuit board and the second printed circuit board；Structure is simple, at low cost, simplifies assembling process and docking operation between aircraft bay section, and electrical connection is facilitated to operate, and avoids generating adverse effect to the reliability of aircraft electrical system, is particularly suitable for the synchronous docking of small aircraft cabin.
Description
Technical field
The present invention relates to aircraft overall assembling technical field, synchronizing to tipping between specially a kind of aircraft bay section
It sets.
Background technique
With being constantly progressive for system integration technology, aircraft function even more complex, performance is constantly promoted, and volume is more next
It is smaller.Multifunction integrated design, modularization and Miniaturization Design technology have become the mainstay thinking of contemporary aircraft.With
The diminution of structure size and the raising of integrated level, docking space is constantly compressed between aircraft bay section, assembly method between bay section
Urgently improve.
Generally, it is electrically docked first between two bay section of aircraft in assembly, electric interconnection will be used between two bay sections
Electric connector plug together locking, and superfluous cable carried out sufficiently fixed；Then mechanical splice is carried out, the machinery of two bay sections is connect
Mouth is matched, and is attached fastening to the two with threaded fastener.The narrow office of bulk for small aircraft
Promote, this mode seriously limits electrical connection operation, and subdivision cable is compressed in cabin, and bending state is indefinite, sometimes also
It can be interfered with below deck equipment, adverse effect can be generated to the reliability of aircraft electrical system.
Summary of the invention
Aiming at the problems existing in the prior art, the present invention provides the synchronization docking facilities between a kind of aircraft bay section, knot
Structure is simple, at low cost, and electrical connection is facilitated to operate, and avoids generating adverse effect to the reliability of aircraft electrical system.
The present invention is to be achieved through the following technical solutions:
A kind of synchronization docking facilities between aircraft bay section, including the first transfer panel, the second transfer panel, the first printed circuit
Plate and the second printed circuit board；
First transfer panel is fixed at docking to be synchronized along the cross section of the first cabin of docking to be synchronized
In first cabin, the second transfer panel is fixed at the second of docking to be synchronized along the cross section of the second cabin of docking to be synchronized
In cabin, it is fixed with the first printed circuit board on the first transfer panel, is fixed with the second printed circuit board on the second transfer panel, first
Welding equipment has electric connector on printed circuit board and the second printed circuit board, and the first printed circuit board and the second printed circuit board pass through
Electric connector connection setting.
Preferably, welding equipment is positioned on first printed circuit board has socket, positions welding equipment on the second printed circuit board
There is plug, socket and plug plugs together matching setting.
Further, the front of socket is provided with several jacks, and the front of plug is provided with several contact pins set gradually, inserts
The contact pin of head and the jack of socket correspond mating.
Preferably, circumferential by the first sunk screw between first transfer panel and the first cabin to be synchronized docked
Positioning assembly, the second transfer panel pass through the circumferentially positioned assembly of the second sunk screw with the second cabin to be synchronized docked.
Preferably, first printed circuit board is assemblied on the first transfer panel by the first positioning finger setting, and first
Printed circuit board is fixed on the first transfer panel by the first screw, and the second printed circuit board passes through the second positioning finger setting assembly
On the second transfer panel, the second printed circuit board is fixed on the second transfer panel by the second screw.
Preferably, the second cabin axial direction grafting of the first cabin of the docking to be synchronized and docking to be synchronized is arranged.
Further, the shape of the second cabin of the docking to be synchronized be multi-diameter shaft, the first cabin of docking to be synchronized with
The multi-diameter shaft clearance fit of second cabin of docking to be synchronized.
Further, the first cabin of the docking to be synchronized is circumferentially fixed by guide pin with the second cabin to be synchronized docked
First cabin of position, docking to be synchronized is fixedly installed by bolt with the second cabin to be synchronized docked.
Preferably, the first cabin of the docking to be synchronized is coated with the mating surface of the second cabin to be synchronized docked and leads
Hot material.
Compared with prior art, the invention has the following beneficial technical effects:
Synchronization docking facilities of the invention pass through the first transfer panel and the second transfer panel for the first printed circuit board and second
Printed circuit board is fixed in the first cabin of docking to be synchronized and the second cabin of docking to be synchronized, the first printed circuit
Welding equipment has electric connector on plate and the second printed circuit board, then by the first printed circuit board and the second printed circuit board to be electrically connected
The mode for connecing device connection setting simplifies assembling process and docking operation between aircraft bay section, is particularly suitable for small aircraft
The synchronous docking of cabin.
Further, the first cabin of docking to be synchronized is coated with thermally conductive with the mating surface of the second cabin to be synchronized docked
Material is conducive to fill fit clearance, reduces thermal contact resistance, can promote the efficiency of heat transfer between bay section；This be mainly based upon as
Lower to consider the problems of: heat transfer docking is usually ignored between two bay sections, as the electronic equipment carried on aircraft is more and more,
Power density is increasing, carries out heat transfer by adjacent bay section, expands and utilize the thermal capacitance of adjacent bay section, so that entire flight
Device uniform heat distribution is very necessary；Finally realize two bay section room machines, electrical docking synchronous with heat transfer.
Detailed description of the invention
Fig. 1 is a top view of the synchronous docking facilities of the present invention.
Fig. 2 is the A-A cross-sectional view of Fig. 1.
Fig. 3 is another top view of the synchronous docking facilities of the present invention.
Fig. 4 is the B-B cross-sectional view of Fig. 3.
In figure: the first cabin 1 of docking to be synchronized, the first transfer panel 2, the first printed circuit board 3, socket 4, the first positioning
Pin 51, the second positioning pin 52, the second cabin 6 of docking to be synchronized, the second transfer panel 7, the second printed circuit board 8, plug 9 are led
To pin 10, bolt 11, the first sunk screw 12, the second sunk screw 13, guide groove 14, the first screw 15, the second screw 16.
Specific embodiment
Below with reference to specific embodiment, the present invention is described in further detail, it is described be explanation of the invention and
It is not to limit.
The main object of the present invention is the problems applied on small aircraft for docking mode between existing bay section
A kind of synchronous docking design device is provided, the device is based on the electric connector for having the function of that guiding plugs together and positions welding equipment function
Carry out, using a series of positioning and guide frame, realizes electric connector, printed circuit board, transfer panel and aircraft cabin
Mutual positioning assembly realizes the guiding assembly between two bay sections, and smears Heat Conduction Material in two bay section mating surfaces, realizes
Two bay section room machines, electrical docking synchronous with heat transfer；This mode simplifies the assembling process between aircraft bay section, improves
Docking operation technique improves heat conduction efficiency between bay section, is particularly suitable for the Interface design of small aircraft.
Synchronization docking facilities between a kind of aircraft bay section of the present invention, as shown in Figure 1, Figure 2, Figure 3 and Figure 4, including first
Transfer panel 2, the second transfer panel 7, the first printed circuit board 3 and the second printed circuit board 8；First transfer panel 2 is matched by cylindrical surface
It closes, along the first cabin 1 that the cross section of the first cabin 1 of docking to be synchronized is fixed at docking to be synchronized, the second switching
Disk 7 is cooperated by cylindrical surface, and the second cabin of docking to be synchronized is fixed at along the cross section of the second cabin 6 of docking to be synchronized
In body 6, it is fixed with the first printed circuit board 3 on the first transfer panel 2, the second printed circuit board 8 is fixed on the second transfer panel 7,
Welding equipment has electric connector, the first printed circuit board 3 and the second printing electricity on first printed circuit board 3 and the second printed circuit board 8
Road plate 8 is connected to by electric connector to be arranged, it is ensured that electrical connection is smooth.
In this example, as shown in Figure 2 and Figure 4, positioning assembly and welding equipment have socket 4, the second print on the first printed circuit board 3
Positioning assembly and welding equipment have plug 9 on circuit board 8 processed, and socket 4 and plug 9 all have guiding and plug together function and positioning welding equipment function
Can, the back side of socket 4 is provided with positioning pin, and socket 4 is set by the positioning pin at its back side with the positioning assembly of the first printed circuit board 3
It sets, the back side of plug 9 is also equipped with positioning pin, and plug 9 is assembled by the positioning pin at its back side and the positioning of the second printed circuit board 8
Setting, the front of socket 4 are provided with several jacks, and the front of plug 9 is provided with several contact pins set gradually, and plug 9 is inserted
The jack of needle and socket 4 corresponds mating；By each between first transfer panel 2 and the first cabin 1 to be synchronized docked
The circumferentially positioned assembly of the first sunk screw 12 on the outside of cabin, the second transfer panel 7 pass through each with the second cabin 6 to be synchronized docked
The circumferentially positioned assembly of the second sunk screw 13 on the outside of cabin；It is fixed that first printed circuit board 3 and the design of the second printed circuit board 8 have
Position pin hole is equipped with the first positioning pin 51 and the second positioning pin 52, the first printing electricity on the first transfer panel 2 and the second transfer panel 7
Road plate 3 is assemblied on the first transfer panel 2 by the positioning of the first positioning pin 51, and the first printed circuit board 3 is solid by the first screw 15
It being scheduled on the first transfer panel 2, the second printed circuit board 8 is assemblied on the second transfer panel 7 by the positioning of the second positioning pin 52, and second
Printed circuit board 8 is fixed on the second transfer panel 7 by the second screw 16.
In a preferred approach, when two cabins carry out mechanical splice, the first cabin 1 of docking to be synchronized and docking to be synchronized
Second cabin 6 is arranged by the grafting of cylindrical surface axial direction；Furthermore, the shape of the second cabin 6 of docking to be synchronized is ladder
Axis, the multi-diameter shaft clearance fit of the first cabin 1 of docking to be synchronized and the second cabin 6 to be synchronized docked；Docking to be synchronized
First cabin 1 is circumferentially positioned and solid by the bolt 11 on the outside of guide pin 10 and each cabin with the second cabin 6 to be synchronized docked
Fixed, wherein being provided with guide groove 14 in the second cabin 6 of docking to be synchronized, guide pin 10 is arranged in guide groove 14, bolt 11
It can also be replaced with dormant bolt；Meanwhile the cooperation of the first cabin 1 of docking to be synchronized and the second cabin 6 to be synchronized docked
Face is uniformly coated with Heat Conduction Material, concretely heat conductive silica gel and heat-conducting silicone grease, is conducive to fill fit clearance, reduces contact heat
Resistance improves the heat conduction efficiency between two bay sections.
This method substantially improves the docking operation between two bay sections, has evaded electric connector and has plugged together locking inconvenience, subdivision electricity
The indefinite problem of cable bending state, improves heat conduction efficiency between bay section, between small aircraft bay section modularized design and
Fast insert-pull replacement operation provides possibility.
Claims (9)
1. the synchronization docking facilities between a kind of aircraft bay section, which is characterized in that including the first transfer panel (2), the second transfer panel
(7), the first printed circuit board (3) and the second printed circuit board (8)；
First transfer panel (2) is fixed at docking to be synchronized along the cross section of the first cabin (1) of docking to be synchronized
The first cabin (1) in, the second transfer panel (7) is fixed at along the cross section of the second cabin (6) of docking to be synchronized to same
In the second cabin (6) for walking docking, it is fixed on the first transfer panel (2) the first printed circuit board (3), on the second transfer panel (7)
It being fixed with the second printed circuit board (8), welding equipment has electric connector on the first printed circuit board (3) and the second printed circuit board (8),
First printed circuit board (3) is connected to setting by electric connector with the second printed circuit board (8).
2. the synchronization docking facilities between a kind of aircraft bay section according to claim 1, which is characterized in that described first
Welding equipment is positioned on printed circuit board (3) to be had socket (4), and welding equipment is positioned on the second printed circuit board (8) to be had plug (9), socket (4)
It is plugged together with plug (9) and matches setting.
3. the synchronization docking facilities between a kind of aircraft bay section according to claim 2, which is characterized in that socket (4)
Front is provided with several jacks, and the front of plug (9) is provided with several contact pins set gradually, the contact pin and socket of plug (9)
(4) jack corresponds mating.
4. the synchronization docking facilities between a kind of aircraft bay section according to claim 1, which is characterized in that described first
By the first sunk screw (12) circumferentially positioned assembly between transfer panel (2) and the first cabin (1) to be synchronized docked, second turn
It connects disk (7) and passes through the second sunk screw (13) circumferentially positioned assembly with the second cabin (6) to be synchronized docked.
5. the synchronization docking facilities between a kind of aircraft bay section according to claim 1, which is characterized in that described first
Printed circuit board (3) is assemblied on the first transfer panel (2) by the first positioning pin (51) positioning, and the first printed circuit board (3) is logical
It crosses the first screw (15) to be fixed on the first transfer panel (2), the second printed circuit board (8) passes through the second positioning pin (52) positioning dress
It fits on the second transfer panel (7), the second printed circuit board (8) is fixed on the second transfer panel (7) by the second screw (16).
6. the synchronization docking facilities between a kind of aircraft bay section according to claim 1, which is characterized in that described to same
The axial grafting setting of the second cabin (6) of the first cabin (1) and docking to be synchronized that walk docking.
7. the synchronization docking facilities between a kind of aircraft bay section according to claim 6, which is characterized in that described to be synchronized
The shape of the second cabin (6) of docking is multi-diameter shaft, the first cabin (1) of docking to be synchronized and the second cabin to be synchronized docked
(6) multi-diameter shaft clearance fit.
8. the synchronization docking facilities between a kind of aircraft bay section according to claim 7, which is characterized in that described to be synchronized
The first cabin (1) of docking is circumferentially positioned by guide pin (10) with the second cabin (6) to be synchronized docked, docking to be synchronized
First cabin (1) is fixedly installed by bolt (11) with the second cabin (6) to be synchronized docked.
9. the synchronization docking facilities described in any one between a kind of aircraft bay section, feature exist according to claim 1~8
In the first cabin (1) of the docking to be synchronized is coated with heat conduction material with the mating surface of the second cabin (6) to be synchronized docked
Material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910360027.4A CN110002012B (en) | 2019-04-30 | 2019-04-30 | Synchronous butt joint device between aircraft cabin sections |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910360027.4A CN110002012B (en) | 2019-04-30 | 2019-04-30 | Synchronous butt joint device between aircraft cabin sections |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110002012A true CN110002012A (en) | 2019-07-12 |
| CN110002012B CN110002012B (en) | 2022-12-06 |
Family
ID=67175211
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910360027.4A Active CN110002012B (en) | 2019-04-30 | 2019-04-30 | Synchronous butt joint device between aircraft cabin sections |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110002012B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111332492A (en) * | 2020-03-06 | 2020-06-26 | 北京机电工程研究所 | Aircraft cabin section cable-free butt joint device and butt joint method thereof |
| CN113682497A (en) * | 2021-08-25 | 2021-11-23 | 北京微纳星空科技有限公司 | Test method for preventing satellite sailboard from being unfolded mistakenly and power supply circuit |
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| US5537947A (en) * | 1994-10-24 | 1996-07-23 | Sippican, Inc. | Expendable underwater vehicle |
| CN101460028A (en) * | 2007-12-12 | 2009-06-17 | 中国科学院沈阳自动化研究所 | Underwater electronic connection rack |
| CN105357870A (en) * | 2015-11-24 | 2016-02-24 | 上海空间电源研究所 | Printed circuit board based on modular structure and corresponding mother board installation method |
| CN105346703A (en) * | 2015-11-19 | 2016-02-24 | 江西洪都航空工业集团有限责任公司 | Cabin section connecting structure |
| CN106275331A (en) * | 2016-08-29 | 2017-01-04 | 苏州探海海洋科技有限责任公司 | A kind of direct insertion underwater sailing body cabin section connection structure |
| CN107579324A (en) * | 2017-07-27 | 2018-01-12 | 中国船舶重工集团公司第七二四研究所 | A kind of T/R components multichannel water power loads in mixture blindmate structure |
| CN109229432A (en) * | 2018-09-29 | 2019-01-18 | 北京卫星制造厂有限公司 | A kind of multifunctional all interface module |
-
2019
- 2019-04-30 CN CN201910360027.4A patent/CN110002012B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5537947A (en) * | 1994-10-24 | 1996-07-23 | Sippican, Inc. | Expendable underwater vehicle |
| CN101460028A (en) * | 2007-12-12 | 2009-06-17 | 中国科学院沈阳自动化研究所 | Underwater electronic connection rack |
| CN105346703A (en) * | 2015-11-19 | 2016-02-24 | 江西洪都航空工业集团有限责任公司 | Cabin section connecting structure |
| CN105357870A (en) * | 2015-11-24 | 2016-02-24 | 上海空间电源研究所 | Printed circuit board based on modular structure and corresponding mother board installation method |
| CN106275331A (en) * | 2016-08-29 | 2017-01-04 | 苏州探海海洋科技有限责任公司 | A kind of direct insertion underwater sailing body cabin section connection structure |
| CN107579324A (en) * | 2017-07-27 | 2018-01-12 | 中国船舶重工集团公司第七二四研究所 | A kind of T/R components multichannel water power loads in mixture blindmate structure |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111332492A (en) * | 2020-03-06 | 2020-06-26 | 北京机电工程研究所 | Aircraft cabin section cable-free butt joint device and butt joint method thereof |
| CN113682497A (en) * | 2021-08-25 | 2021-11-23 | 北京微纳星空科技有限公司 | Test method for preventing satellite sailboard from being unfolded mistakenly and power supply circuit |
Also Published As
| Publication number | Publication date |
|---|---|
| CN110002012B (en) | 2022-12-06 |
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