CN105576461B - A kind of aircraft electricity consumption air separation - Google Patents
A kind of aircraft electricity consumption air separation Download PDFInfo
- Publication number
- CN105576461B CN105576461B CN201610077472.6A CN201610077472A CN105576461B CN 105576461 B CN105576461 B CN 105576461B CN 201610077472 A CN201610077472 A CN 201610077472A CN 105576461 B CN105576461 B CN 105576461B
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- CN
- China
- Prior art keywords
- plane
- aircraft
- electrical outlets
- electric connector
- plug base
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Classifications
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- 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
- H01R13/00—Details of coupling devices of the kinds covered by groups H01R12/70 or H01R24/00 - H01R33/00
- H01R13/46—Bases; Cases
-
- 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
- H01R13/633—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 disengagement only
Landscapes
- Details Of Connecting Devices For Male And Female Coupling (AREA)
- Connector Housings Or Holding Contact Members (AREA)
Abstract
The invention belongs to aeronautical and space technology research field, more particularly to a kind of aircraft electricity consumption air separation, including Plug base, electric connector, electrical outlets, wherein Plug base is fixed on vehicle launch frame or launching tube；Electrical outlets are fixed on board the aircraft；Electric connector is placed in Plug base, and is inserted in electrical outlets；Electric connector is installed inclined-plane and inserted by Plug base inclined-plane in electrical outlets.Separate mode of the present invention is novel, protects the structure of aircraft and separator itself, and carry-on device part does not interfere with aeroperformance, and structure is friendly.
Description
Technical field
The invention belongs to aeronautical and space technology research field, more particularly to a kind of aircraft electricity consumption air separation.
Background technology
, it is necessary to carry out information exchange with ground launch control device during the vehicle launchs such as guided missile, rocket and unmanned plane,
Therefore there is a set of electrical separation device between aircraft and launch control unit, to realize information exchange and electrical separation work(
Can, complete emission control task.
Existing electrical separation mode mainly have it is following two, as depicted in figs. 1 and 2：(1) parallel longitudinal separate mode, i.e.,
Socket 2 is parallel with the course of aircraft 1 with the detaching direction of plug 3, and plug is fixed on emitter 4；(2) oblique cutting separation side
Formula, the course of socket 2 and the detaching direction and aircraft 1 of plug 3 is angled, and plug is fixed on emitter 4.(1)
During using parallel longitudinal separate mode, electrical separation device space-consuming is big, when using launching tube launch craft, separates past
Toward can be only positioned at aircraft afterbody, the parts-layout of aircraft component is limited.(2) space used in oblique cutting separate mode is small, but
During launch craft, its navigation is inconsistent with socket plug direction, and socket and plug cored wire can be to aircraft and transmitting when separating
Device causes certain damage, simultaneously because seating depression can have an impact in aircraft to flight vehicle aerodynamic performance.
The content of the invention
In view of it is above-mentioned the problems of in the prior art, the present invention provides a kind of vehicle launch and filled with electrical separation
Put, solve the problems such as existing electrical separation device volume is big, is difficult to install, causes aircraft compared with macrolesion, realize guided missile, fire
The aircraft such as arrow and unmanned plane transmitting when with ground installation electrical separation.
The concrete technical scheme of the present invention is as follows：
A kind of aircraft electricity consumption air separation, including Plug base, electric connector, electrical outlets, wherein Plug base
It is fixed on vehicle launch frame or launching tube；Electrical outlets are fixed on board the aircraft；Electric connector is placed in Plug base, and
Insert in electrical outlets；Electric connector is installed inclined-plane and inserted by Plug base inclined-plane in electrical outlets.
On the basis of above-mentioned technical proposal, it can also increase following technical characteristic：
1) during vehicle launch, the parallel sliding motion between electric connector and Plug base is converted into electric connector with inserting
Vertical movement between head pedestal, realizes being smoothly detached for electric connector and electrical outlets.
2) electric connector is " work " shaped plug, and comprising plate and lock pin, plate, which is provided with, coordinates plane with coordinating inclined-plane,
Wherein lock pin totally 20.Further, Plug base includes the groove of " work " font, and provided with cooperation plane with coordinating inclined-plane.
3) Plug base bottom is cambered surface, and top is plane；Cambered surface is engaged with body face or aircraft face.
Beneficial effects of the present invention are：
Separate mode of the present invention is novel, protects the structure of aircraft and separator itself, and carry-on device
Part does not interfere with aeroperformance, and structure is friendly.
Brief description of the drawings
The present invention is described in detail with instantiation below in conjunction with the accompanying drawings.
Fig. 1 shows existing parallel longitudinal separate mode schematic diagram.
Fig. 2 shows existing oblique cutting separate mode schematic diagram.
Fig. 3 shows the exploded perspective view of an instantiation of electrical separation device of the present invention.
Fig. 4 shows electric connector structural representation.
Fig. 5 shows Plug base structural representation.
Fig. 6 shows electric connector and Plug base assembling schematic diagram.
Mark is as follows shown in figure：1 aircraft；2 electrical outlets；3 electric connectors；4 Plug bases；5 electric connectors are matched somebody with somebody
Close plane；The cooperation inclined-plane of 6 electric connectors；7 plates；8 lock pins；The top planes of 9 Plug bases；10 " work " font grooves；11 insert
The cooperation plane of head pedestal；The cooperation inclined-plane of 12 Plug bases；The bottom cambered surface of 13 Plug bases.
Embodiment
Present invention improves over existing aircraft electrical appliance separate mode, i.e., by parallel cunning when being separated between electrical separation device
Dynamic to move the separate mode for being converted to vertical movement, embodiment is as follows：
As shown in figure 3, electrical separation device includes electrical outlets 2, electric connector 3, Plug base 4.Electrical outlets 2 are fixed
On aircraft 1, Plug base 4 is arranged on vehicle launch frame or launching tube, and electric connector 3 can insert Plug base 4 simultaneously
Insert in electrical outlets 2.Wherein, electrical outlets 2 include 20 jacks.
As shown in figure 4, electric connector 3 is " work " shaped plug, comprising plate 7 and lock pin 8, plate 7 is provided with to coordinate and put down
Face 5 is with coordinating inclined-plane 6, wherein lock pin 8 totally 20.Plug base 5 includes the groove of " work " font, and provided with cooperation plane 11 with matching somebody with somebody
Close inclined-plane 12.Wherein cambered surface 13 is engaged with body face or aircraft face, and plane 9 is exposed on the outside of launching tube or launcher.
As shown in figure 5, when it is implemented, Plug base 4 is arranged on vehicle launch frame or launching tube, " work " font is electric
Gas plug 3 is placed in the Plug base 4 with " work " font groove, the cooperation plane 5 and cooperation inclined-plane 6 of electric connector 3 respectively with
The cooperation plane 11 and cooperation inclined-plane 12 of Plug base 4 are in contact so that electric connector 3 and the physical engagement of Plug base 4.Electrically
In electrical outlets 2 of 20 lock pins insertion comprising 20 jacks of plug 3.Whole electrical separation device realizes information exchange and electricity
Gas separation function.
For the present invention in use, after electric connector 3 and the physical engagement of electrical outlets 2, its lock pin 8 inserts electrical outlets 2
In jack, the information exchange between aircraft and ground launch control device is helped through.During vehicle launch, electric connector 3
Relative slide is occurred by its respective inclined-plane with Plug base 4 so that relative between aircraft and launching tube or launcher
The vertical movement being converted between electric connector 3 and electrical outlets 2 is slided, so as to which electric connector 3 be separated with electrical outlets 2,
Realize that aircraft separates with launching tube or launcher.
Claims (5)
- A kind of 1. aircraft electricity consumption air separation, it is characterised in that：Including Plug base, electric connector, electrical outlets, wherein Plug base is fixed on vehicle launch frame or launching tube；Electrical outlets are fixed on board the aircraft；Electric connector is placed in plug In pedestal, and insert in electrical outlets；Electric connector is " work " shaped plug, and comprising plate and lock pin, plate, which is provided with, to be coordinated Plane with coordinating inclined-plane, install inclined-plane and inserted by Plug base inclined-plane in electrical outlets by electric connector.
- 2. aircraft electricity consumption air separation according to claim 1, it is characterised in that：, will be electric during vehicle launch Parallel sliding motion between plug and Plug base is converted to the vertical movement between electric connector and electrical outlets, realizes and electrically inserts Head is smoothly detached with electrical outlets.
- 3. aircraft electricity consumption air separation according to claim 1, it is characterised in that：Lock pin totally 20.
- 4. aircraft electricity consumption air separation according to claim 3, it is characterised in that：Plug base includes " work " font Groove, and provided with coordinate plane with coordinate inclined-plane.
- 5. the aircraft electricity consumption air separation according to claim 1 or 4, it is characterised in that：Plug base bottom is arc Face, top are plane；Cambered surface is engaged with aircraft face.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610077472.6A CN105576461B (en) | 2016-01-28 | 2016-01-28 | A kind of aircraft electricity consumption air separation |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610077472.6A CN105576461B (en) | 2016-01-28 | 2016-01-28 | A kind of aircraft electricity consumption air separation |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105576461A CN105576461A (en) | 2016-05-11 |
| CN105576461B true CN105576461B (en) | 2018-03-16 |
Family
ID=55886316
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610077472.6A Active CN105576461B (en) | 2016-01-28 | 2016-01-28 | A kind of aircraft electricity consumption air separation |
Country Status (1)
| Country | Link |
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| CN (1) | CN105576461B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107492753A (en) * | 2017-07-19 | 2017-12-19 | 贵州航天风华精密设备有限公司 | A kind of safe escape mechanism for guided missile electrical fitting |
| CN110414018B (en) * | 2018-04-27 | 2023-06-16 | 中国航天科工飞航技术研究院（中国航天海鹰机电技术研究院） | Virtual reality simulation method and system for interstage separation of aircraft |
| CN113745906B (en) * | 2021-08-24 | 2023-11-17 | 上海机电工程研究所 | Axial falling-off separating structure of box spring electric connector |
Citations (10)
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|---|---|---|---|---|
| CN1127944A (en) * | 1994-10-12 | 1996-07-31 | 惠特克公司 | Housing assembly and electrical device using same |
| CN1838488A (en) * | 2006-04-28 | 2006-09-27 | 杭州航天电子技术有限公司 | Electric connector guide rail separation method and apparatus |
| CN201623321U (en) * | 2010-03-01 | 2010-11-03 | 深圳市洲明科技股份有限公司 | Electric plug device |
| CN102124608A (en) * | 2006-03-13 | 2011-07-13 | 伊利诺斯工具制品有限公司 | Aircraft power connector with differential engagement and operational retention forces |
| EP2469663A1 (en) * | 2010-12-24 | 2012-06-27 | Nigel Greig | Magnetic connector apparatus |
| EP2607662A2 (en) * | 2011-12-22 | 2013-06-26 | Rolls-Royce plc | Electrical Connectors |
| CN103328331A (en) * | 2011-01-12 | 2013-09-25 | 空中客车营运有限公司 | Overhead panel for an aircraft cockpit and aircraft including such a panel |
| CN203617536U (en) * | 2013-10-30 | 2014-05-28 | 北京航天长征飞行器研究所 | Mechanical separation mechanism used for concurrent electric connector |
| CN203774600U (en) * | 2013-10-16 | 2014-08-13 | 北京特种机械研究所 | Unmanned plane plug automatic-separating mechanism |
| CN105228902A (en) * | 2012-12-21 | 2016-01-06 | 欧洲航空防务与空间公司Eads法国 | For fuel resupply device in-flight and the aircraft being equipped with this device of electric memory system |
-
2016
- 2016-01-28 CN CN201610077472.6A patent/CN105576461B/en active Active
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1127944A (en) * | 1994-10-12 | 1996-07-31 | 惠特克公司 | Housing assembly and electrical device using same |
| CN102124608A (en) * | 2006-03-13 | 2011-07-13 | 伊利诺斯工具制品有限公司 | Aircraft power connector with differential engagement and operational retention forces |
| CN1838488A (en) * | 2006-04-28 | 2006-09-27 | 杭州航天电子技术有限公司 | Electric connector guide rail separation method and apparatus |
| CN201623321U (en) * | 2010-03-01 | 2010-11-03 | 深圳市洲明科技股份有限公司 | Electric plug device |
| EP2469663A1 (en) * | 2010-12-24 | 2012-06-27 | Nigel Greig | Magnetic connector apparatus |
| CN103328331A (en) * | 2011-01-12 | 2013-09-25 | 空中客车营运有限公司 | Overhead panel for an aircraft cockpit and aircraft including such a panel |
| EP2607662A2 (en) * | 2011-12-22 | 2013-06-26 | Rolls-Royce plc | Electrical Connectors |
| CN105228902A (en) * | 2012-12-21 | 2016-01-06 | 欧洲航空防务与空间公司Eads法国 | For fuel resupply device in-flight and the aircraft being equipped with this device of electric memory system |
| CN203774600U (en) * | 2013-10-16 | 2014-08-13 | 北京特种机械研究所 | Unmanned plane plug automatic-separating mechanism |
| CN203617536U (en) * | 2013-10-30 | 2014-05-28 | 北京航天长征飞行器研究所 | Mechanical separation mechanism used for concurrent electric connector |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105576461A (en) | 2016-05-11 |
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Effective date of registration: 20190624 Address after: 010010 No. 65 Xinhua East Street, New District, Hohhot City, Inner Mongolia Autonomous Region Co-patentee after: The No.41 Research Institute of the Sixth Academy of China Aerospace Science & Industry Corp. Patentee after: China Academy of Aerospace Science, Engineering and Power Technology Address before: 010010 Sixth Space Academy 41, No. 65 Xinhua East Street, Hohhot City, Inner Mongolia Autonomous Region Patentee before: The No.41 Research Institute of the Sixth Academy of China Aerospace Science & Industry Corp. |
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