CN105576461A - Electrical separation device for aircraft - Google Patents
Electrical separation device for aircraft Download PDFInfo
- Publication number
- CN105576461A CN105576461A CN201610077472.6A CN201610077472A CN105576461A CN 105576461 A CN105576461 A CN 105576461A CN 201610077472 A CN201610077472 A CN 201610077472A CN 105576461 A CN105576461 A CN 105576461A
- Authority
- CN
- China
- Prior art keywords
- aircraft
- plane
- electric connector
- plug base
- electrical
- 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
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Classifications
-
- 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
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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
- 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
Abstract
The invention belongs to the field of aerospace technology research, in particular relates to an electrical separation device for an aircraft. The electrical separation device comprises a plug base, an electrical plug and an electrical socket, wherein the plug base is fixed on an aircraft launching rack or launching cylinder, the electrical socket is fixed on the aircraft, the electrical plug is arranged in the socket base and inserted into the electrical socket, and an electrical plug installation inclined surface is inserted into the electrical socket by a plug base inclined surface. The electrical separation device is novel in separation mode, the aircraft and the structure of the separation device are protected, the aerodynamic performance cannot be affected by the device part on the aircraft, and the structure is user friendly.
Description
Technical field
The invention belongs to aeronautical and space technology research field, particularly relate to a kind of aircraft electricity consumption air separation.
Background technology
During the vehicle launchs such as guided missile, rocket and unmanned plane, need to carry out information interaction with ground launch control device, therefore between aircraft and launch control unit, there is a set of electrical separation device, to realize information interaction and electrical separation function, complete emission control task.
Existing electrical separation mode mainly contains following two kinds, and as depicted in figs. 1 and 2: (1) parallel longitudinal separate mode, namely 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 separate mode, socket 2 and the detaching direction of plug 3 and the course of aircraft 1 angled, plug is fixed on emitter 4.(1) when using parallel longitudinal separate mode, electrical separation device takes up room greatly, when using launching tube launch craft, being separated and often can only being positioned at aircraft afterbody, limiting the parts-layout of aircraft component.(2) oblique cutting separate mode space used is little, but during launch craft, its navigation is inconsistent with socket plug direction, certain damage can be caused to aircraft and emitter when socket is separated with plug heart yearn, simultaneously because seating depression is in aircraft, can have an impact to flight vehicle aerodynamic performance.
Summary of the invention
In view of problem existing in above-mentioned prior art, the invention provides a kind of vehicle launch electricity consumption air separation, solve existing electrical separation device volume large, be difficult to install, the comparatively problem such as macrolesion caused to aircraft, realize the aircraft such as guided missile, rocket and unmanned plane when launching and ground installation electrical separation.
Concrete technical scheme of the present invention is as follows:
A kind of aircraft electricity consumption air separation, comprise Plug base, electric connector, electrical outlets, wherein Plug base is fixed on vehicle launch frame or launching tube; Electrical outlets is fixing on board the aircraft; Electric connector is placed in Plug base, and inserts in electrical outlets; Electric connector is installed inclined-plane and is inserted in electrical outlets by Plug base inclined-plane.
On the basis of technique scheme, also can increase following technical characteristic:
1), during vehicle launch, the parallel sliding motion between electric connector and Plug base is converted to moving both vertically between electric connector and Plug base, realizes being separated smoothly of electric connector and electrical outlets.
2) electric connector is " work " shaped plug, comprises plate and lock pin, and plate is provided with and coordinates plane and coordinate inclined-plane, wherein lock pin totally 20.Further, the groove of font that Plug base comprises " work ", and be provided with cooperation plane and coordinate inclined-plane.
3) bottom Plug base be cambered surface, top is plane; Cambered surface matches with body face or aircraft face.
Beneficial effect of the present invention is:
Separate mode of the present invention is novel, protect the structure of aircraft and separator self, and carry-on device section can not affect aeroperformance, and structure is friendly.
Accompanying drawing explanation
Below in conjunction with accompanying drawing and instantiation, the present invention is described in detail.
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.
Shown in figure, mark is as follows: 1 aircraft; 2 electrical outlets; 3 electric connectors; 4 Plug bases; The cooperation plane of 5 electric connectors; The cooperation inclined-plane of 6 electric connectors; 7 plates; 8 lock pins; The top planes of 9 Plug bases; 10 " work " font groove; The cooperation plane of 11 Plug bases; 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, by when being separated between electrical separation device parallel sliding motion be converted to move both vertically separate mode, embodiment is as follows:
As shown in Figure 3, electrical separation device comprises electrical outlets 2, electric connector 3, Plug base 4.Electrical outlets 2 is fixed on aircraft 1, and Plug base 4 is arranged on vehicle launch frame or launching tube, and electric connector 3 can be inserted Plug base 4 and be inserted in electrical outlets 2.Wherein, electrical outlets 2 comprises 20 jacks.
As shown in Figure 4, electric connector 3 is " work " shaped plug, comprises plate 7 and lock pin 8, and plate 7 is provided with and coordinates plane 5 and coordinate inclined-plane 6, wherein lock pin 8 totally 20.Plug base 5 comprises the groove of " work " font, and is provided with cooperation plane 11 and coordinates inclined-plane 12.Wherein cambered surface 13 matches with body face or aircraft face, and plane 9 is exposed at outside launching tube or launcher.
As shown in Figure 5, during concrete enforcement, Plug base 4 is arranged on vehicle launch frame or launching tube, " work " font electric connector 3 is placed in the Plug base 4 with " work " font groove, the cooperation plane 5 of electric connector 3 and coordinate inclined-plane 6 respectively with the cooperation plane 11 of Plug base 4 with coordinate inclined-plane 12 to contact, makes electric connector 3 and Plug base 4 physical engagement.20 lock pins of electric connector 3 insert and comprise in the electrical outlets 2 of 20 jacks.Whole electrical separation device realizes information interaction and electrical separation function.
When the present invention uses, after electric connector 3 and electrical outlets 2 physical engagement, its lock pin 8 inserts in the jack of electrical outlets 2, helps through the information interaction between aircraft and ground launch control device.During vehicle launch, electric connector 3 and Plug base 4 are by its respective inclined-plane generation relative sliding, the relative sliding between aircraft and launching tube or launcher is made to be converted into moving both vertically between electric connector 3 and electrical outlets 2, thus electric connector 3 is separated with electrical outlets 2, realize aircraft and be separated with launching tube or launcher.
Claims (5)
1. an aircraft electricity consumption air separation, is characterized in that: comprise Plug base, electric connector, electrical outlets, and wherein Plug base is fixed on vehicle launch frame or launching tube; Electrical outlets is fixing on board the aircraft; Electric connector is placed in Plug base, and inserts in electrical outlets; Electric connector is installed inclined-plane and is inserted in electrical outlets by Plug base inclined-plane.
2. aircraft electricity consumption air separation according to claim 1, it is characterized in that: during vehicle launch, parallel sliding motion between electric connector and Plug base is converted to moving both vertically between electric connector and Plug base, realizes being separated smoothly of electric connector and electrical outlets.
3. aircraft electricity consumption air separation according to claim 1, is characterized in that: electric connector is " work " shaped plug, comprises plate and lock pin, and plate is provided with and coordinates plane and coordinate inclined-plane, wherein lock pin totally 20.
4. aircraft electricity consumption air separation according to claim 3, is characterized in that: the groove of font that Plug base comprises " work ", and is provided with cooperation plane and coordinates inclined-plane.
5. the aircraft electricity consumption air separation according to claim 1 or 4, is characterized in that: be cambered surface bottom Plug base, top is plane; Cambered surface matches with body face or 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 true CN105576461A (en) | 2016-05-11 |
| CN105576461B 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 |
|---|---|
| CN (1) | CN105576461B (en) |
Cited By (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 |
| CN110414018A (en) * | 2018-04-27 | 2019-11-05 | 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） | A kind of virtual reality simulation method and system of Flight Vehicle Stage Separation |
| CN113745906A (en) * | 2021-08-24 | 2021-12-03 | 上海机电工程研究所 | Box elastic electric connector axial falling and separating structure |
Family Cites Families (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH08125352A (en) * | 1994-10-12 | 1996-05-17 | Whitaker Corp:The | Housing assembly and electric apparatus using it |
| US7871282B2 (en) * | 2006-03-13 | 2011-01-18 | Illinois Tool Works Inc. | Aircraft power connector with differential engagement and operational retention forces |
| CN100405671C (en) * | 2006-04-28 | 2008-07-23 | 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 |
| EP2469663B1 (en) * | 2010-12-24 | 2020-06-17 | Phitek Systems Limited | Magnetic connector apparatus |
| FR2970237B1 (en) * | 2011-01-12 | 2013-02-08 | Airbus Operations Sas | UPPER PANEL FOR AIRCRAFT COCKPIT AND AIRCRAFT COMPRISING SUCH A PANEL |
| GB2498006B (en) * | 2011-12-22 | 2014-07-09 | Rolls Royce Plc | Gas turbine engine systems |
| FR3000029B1 (en) * | 2012-12-21 | 2015-03-06 | Eads Europ Aeronautic Defence | INFLATABLE REFUELING DEVICES FOR AN ELECTRONIC STORAGE SYSTEM AND AIRCRAFT EQUIPPED WITH SUCH A DEVICE |
| 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 |
-
2016
- 2016-01-28 CN CN201610077472.6A patent/CN105576461B/en active Active
Cited By (4)
| 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 |
| CN110414018A (en) * | 2018-04-27 | 2019-11-05 | 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） | A kind of virtual reality simulation method and system of Flight Vehicle Stage Separation |
| CN113745906A (en) * | 2021-08-24 | 2021-12-03 | 上海机电工程研究所 | Box elastic electric connector axial falling and separating structure |
| 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105576461B (en) | 2018-03-16 |
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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. |