CN114336144B - Aeroengine ignition cable interface structure - Google Patents
Aeroengine ignition cable interface structure Download PDFInfo
- Publication number
- CN114336144B CN114336144B CN202111522843.4A CN202111522843A CN114336144B CN 114336144 B CN114336144 B CN 114336144B CN 202111522843 A CN202111522843 A CN 202111522843A CN 114336144 B CN114336144 B CN 114336144B
- Authority
- CN
- China
- Prior art keywords
- bush
- plug bush
- interface structure
- cable interface
- ignition cable
- 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.)
- Active
Links
- 238000002788 crimping Methods 0.000 claims abstract description 6
- 238000007789 sealing Methods 0.000 claims description 17
- -1 polytetrafluoroethylene Polymers 0.000 claims description 4
- 229920001343 polytetrafluoroethylene Polymers 0.000 claims description 4
- 239000004810 polytetrafluoroethylene Substances 0.000 claims description 4
- 230000006978 adaptation Effects 0.000 claims 1
- 238000003825 pressing Methods 0.000 abstract description 4
- 238000009434 installation Methods 0.000 description 6
- 230000006835 compression Effects 0.000 description 5
- 238000007906 compression Methods 0.000 description 5
- 238000000034 method Methods 0.000 description 3
- 238000001125 extrusion Methods 0.000 description 2
- 235000014676 Phragmites communis Nutrition 0.000 description 1
- 230000002411 adverse Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Landscapes
- Spark Plugs (AREA)
- Ignition Installations For Internal Combustion Engines (AREA)
Abstract
The application belongs to the field of engine ignition cable design, and particularly relates to an aircraft engine ignition cable interface structure. The structure comprises a plug sleeve (4), a mandrel (3) integrated with a wire in a crimping way is arranged in the plug sleeve (4), the ratio of the length of the plug sleeve (4) to the inner diameter is between 5 and 6, a first annular cavity (41) and a second annular cavity (42) are arranged on the outer ring of the plug sleeve (4), a lining (7) is directly sleeved outside the plug sleeve (4), a first annular bulge (71) arranged in the first annular cavity (41) is arranged on the inner wall of the lining (7), a nut (5) is arranged outside the lining (7), and the nut (5) can be installed on an ignition device in an adapting way. According to the application, the plug bush is connected with the bushing in a snap-in manner, so that a spring pressing part is omitted, and the matching length size is shortened.
Description
Technical Field
The application belongs to the field of engine ignition cable design, and particularly relates to an aircraft engine ignition cable interface structure.
Background
The existing ignition cable interface structure of a certain aeroengine is of a spring compression type contact pin structure, the outermost layer of the interface is provided with a bushing and a special nut, the bushing and the special nut are connected with an ignition device through threads, the middle layer is insulated by a polytetrafluoroethylene plug bush, the middle layer is compressed through the spring structure during connection, the inner layer is formed by integrating a mandrel and a wire in a compression mode, and the inner layer is clamped and fixed through a retainer ring, as shown in fig. 2.
At present, along with the improvement of the technical state of the engine, the installation position of the ignition cable is changed, the interference problem of the tail of the existing interface of the ignition cable and other equipment is found during assembly, the interference distance is 6.5mm, and the installation requirement cannot be met.
Disclosure of Invention
In order to solve the technical problems, the application provides an aeroengine ignition cable interface structure, wherein the size of a bushing and a special nut are shortened on the outermost layer, a spring compression structure is canceled on the middle layer, the size of a plug sleeve is shortened, the connection mode of the plug sleeve and the bushing is redesigned, the matching size with an ignition device is unchanged, and the like, so that the purpose of reducing the length of the interface structure is achieved.
The application provides an aeroengine ignition cable interface structure, which comprises a plug bush, wherein a mandrel which is integrally connected with a lead in a crimping way is arranged in the plug bush, the ratio of the length of the plug bush to the inner diameter is 5-6, a first annular cavity and a second annular cavity are arranged on the outer ring of the plug bush, a bushing is directly sleeved outside the plug bush, a first annular bulge arranged in the first annular cavity is arranged on the inner wall of the bushing, a second annular bulge arranged at the end part of the bushing is arranged on the outer wall of the bushing, a nut is arranged outside the bushing, the bottom end of the nut is provided with a bottom edge which is clamped with the second annular bulge, the nut can be arranged on an ignition device in an adapting way, and the part of the ignition device positioned in the nut can extrude a sealing ring positioned in the second annular cavity.
Preferably, the plug bush is made of polytetrafluoroethylene.
Preferably, the core rod is clamped and fixed inside the plug sleeve through a retainer ring.
Preferably, the sealing ring is adaptively sleeved in the second annular cavity of the plug bush, and the outer diameter of the sealing ring is larger than the inner diameter of the bushing.
Preferably, an end of the sealing ring facing the ignition device is provided as a conical surface.
Preferably, the outer wall of the plug bush is provided with a plurality of first annular cavities, and the inner wall of the bushing is provided with a plurality of first annular protrusions corresponding to the first annular cavities.
Preferably, the length of the bushing is substantially equivalent to the size of its largest inner diameter.
Preferably, the length of the nut is less than its maximum inner diameter.
According to the application, the plug bush is connected with the bushing in a snap-in manner, so that a spring pressing part is omitted, and the matching length size is shortened. During assembly, the plug bush is embedded into the bushing by extrusion, so that the plug bush is simple and firm in structure and convenient to operate. Meanwhile, 3 parts are reduced, and the production and the processing are easy.
Drawings
Fig. 1 is a schematic structural view of a preferred embodiment of the aircraft engine ignition cable interface structure of the present application.
Fig. 2 is a schematic diagram of a conventional interface structure.
Fig. 3 is a schematic view of the plug housing according to the embodiment of fig. 1.
Fig. 4 is a schematic view of the bushing structure of the embodiment of fig. 1 according to the present application.
The device comprises a 1-retainer ring, a 2-reed, a 3-mandrel, a 4-plug sleeve, a 41-first annular cavity, a 42-second annular cavity, a 5-nut, a 6-wire, a 7-bushing, a 71-first annular bulge, a 72-second annular bulge, an 8-sealing ring, a 9-sealing ring, a 10-spring sleeve and an 11-spring.
Detailed Description
In order to make the objects, technical solutions and advantages of the present application become more apparent, the technical solutions in the embodiments of the present application will be described in more detail with reference to the accompanying drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the application. The embodiments described below by referring to the drawings are exemplary and intended to illustrate the present application and should not be construed as limiting the application. All other embodiments, based on the embodiments of the application, which are apparent to those of ordinary skill in the art without inventive faculty, are intended to be within the scope of the application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
The application provides an aeroengine ignition cable interface structure, which mainly comprises a plug bush 4, wherein a mandrel 3 which is integrated with a lead in a crimping way is arranged in the plug bush 4, the ratio of the length of the plug bush 4 to the inner diameter is 5-6, a first annular cavity 41 and a second annular cavity 42 are arranged on the outer ring of the plug bush 4, a bushing 7 is directly sleeved outside the plug bush 4, a first annular bulge 71 arranged in the first annular cavity 41 is arranged on the inner wall of the bushing 7, a second annular bulge 72 arranged at the end part of the bushing is arranged on the outer wall of the bushing 7, a nut 5 is arranged outside the bushing 7, the bottom end of the nut 5 is provided with a bottom edge which is clamped with the second annular bulge 72, the nut 5 can be arranged on an ignition device in a matching way, and the part of the ignition device positioned in the nut 5 can squeeze a sealing ring 8 positioned in the second annular cavity 42.
The existing ignition cable interface structure adopts a spring compression type contact pin structure, which can meet the performance requirement, but has the defect of larger length, as shown in fig. 2. When the engine is installed in a new state, the problem of interference between the tail attachment of the ignition cable interface and other equipment exists, and the installation requirement cannot be met. In order to reduce the length of the interface and ensure the normal installation and use of the ignition cable, the invention of the aeroengine ignition cable interface structure is researched, and in order to achieve the aim of the invention, the analysis is started from three layers of the interface structure, and the sizes of a bushing and a special nut are shortened at the outermost layer; the middle layer cancels the spring compression structure, shortens the size of the plug sleeve, and redesigns the connection mode of the plug sleeve and the bushing; the inner layer is designed or technically renovated along the aspects of the existing core rod and wire crimping and insulating treatment structure, ensuring the same size as the ignition device, and the like, thereby achieving the purpose of reducing the length of the interface structure.
The improved interface structure redesigns three parts of the bushing, the special nut and the plug bush, wherein in the prior art, the length of the bushing is 27.5mm, the bushing is shortened, so that the length of the bushing 7 is basically equivalent to the dimension of the maximum inner diameter thereof, and in a specific embodiment, as shown in fig. 4, the inner diameter of the bushing is 12mm, and the length is 11.5mm; on the other hand, the special nut of the application shortens the depth of the thread, the total length of the prior art is 20mm, the length of the nut 5 designed by the application is smaller than the maximum inner diameter thereof, for example, the length is shortened to 17mm, and the maximum inner diameter thereof is about 20 mm; third, the present application improves the sleeve length by reducing the sleeve length to 44.5mm in the prior art, such that the ratio of the length of sleeve 4 to the inner diameter is between 5 and 6, for example, in one embodiment, the sleeve length is reduced to 34.5mm and the inner diameter is 6mm, as shown in fig. 3. Compared with the existing interface structure, the length of the interface can be reduced by 20.5mm after improvement.
The application improves the connection mode of the plug bush and the bushing, and in the improved interface, the plug bush and the bushing are connected in a snap-in mode, so that a spring pressing part is omitted, and the matching length dimension is shortened. During assembly, the plug bush is embedded into the bushing by extrusion, so that the plug bush is simple and firm in structure and convenient to operate. Meanwhile, 3 parts are reduced, and the sealing ring 9, the spring sleeve 10 and the spring 11 are reduced by combining fig. 1 and 2, so that the whole structure is easy to produce and process.
In order to verify that the ignition cable interface provided by the patent is reasonable and effective in structure, 1 ignition cable test piece is processed according to the method, the performance parameters of the ignition cable before and after the improvement of the detection interface are shown in table 1.
Table 1 comparison of performance before and after improvement
By comparison, the performance of the ignition cable is not adversely affected after the interface is changed, and the performance meets the requirements. The test piece, the ignition electric nozzle and the ignition device are matched to form an ignition system, a vibration environment test is carried out, the test result is qualified, and the requirement of the engine installation in a new state can be met.
In some alternative embodiments, the plug wrap 4 is made of polytetrafluoroethylene.
In some alternative embodiments, the core rod 3 is clamped inside the plug sleeve 4 through the retainer ring 1, and in this embodiment, the retainer ring 1 is further crimped in the plug sleeve through the crimping reed 2 to crimp the core rod 3 and the wire 6.
In some alternative embodiments, the sealing ring 8 is adapted to be sleeved in the second annular cavity of the plug bush 4, and the outer diameter of the sealing ring 8 is larger than the inner diameter of the bushing 7. Referring to fig. 1, the thickness of the seal ring 8 is set so as to be capable of simultaneously pressing at least the ends of the plug bush 4 and the bush 7.
In some alternative embodiments, the end of the sealing ring 8 facing the ignition device is provided as a conical surface. In this embodiment, the ignition device continuously presses the sealing ring 8 through the conical surface in the process of tightening the nut 5, so that the sealing performance of the structure is improved.
In some alternative embodiments, the outer wall of the plug bush 4 is provided with a plurality of first annular cavities, and the inner wall of the bushing 7 is provided with a plurality of first annular protrusions corresponding to each of the first annular cavities 41. In this embodiment, through the cooperation of a plurality of first ring chambeies and first annular protruding, realize the sealed cooperation of bush and plug cover, improve sealed effect.
The ignition cable interface structure is successfully installed on a new-state engine, and the gap between the ignition cable interface structure and other equipment after installation can reach 14mm, so that the use requirement can be met.
The foregoing is merely illustrative of the present application, and the present application is not limited thereto, and any changes or substitutions easily contemplated by those skilled in the art within the scope of the present application should be included in the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (7)
1. The utility model provides an aeroengine ignition cable interface structure, includes plug bush (4), install in plug bush (4) with wire crimping integrated core rod (3), its characterized in that, the length of plug bush (4) is between 5 ~ 6 with the ratio of internal diameter, plug bush (4) outer loop is provided with first ring chamber (41) and second ring chamber (42), plug bush (4) are outer direct the cover and are equipped with bush (7), and bush (7) inner wall has and arranges in first ring chamber (41) first annular bulge (71), and bush (7) outer wall has and sets up in the second annular bulge (72) of bush tip, installs nut (5) outside bush (7), the bottom of nut (5) has the block the base of second annular bulge (72), and nut (5) can the adaptation install on ignition, the ignition is located the part of nut (5) can extrude and be located sealing washer (8) in second ring chamber (42);
The core rod (3) is clamped and fixed inside the plug bush (4) through the check ring (1), and a boss matched with an inner hole of the plug bush (4) is arranged on the outer side of the core rod (3).
2. An aircraft engine ignition cable interface structure as claimed in claim 1, characterized in that the plug bush (4) is made of polytetrafluoroethylene.
3. An aircraft engine ignition cable interface structure according to claim 1, wherein the sealing ring (8) is adapted to be fitted in the second annular cavity of the plug bush (4), and the outer diameter of the sealing ring (8) is larger than the inner diameter of the bushing (7).
4. An aircraft engine ignition cable interface structure as claimed in claim 1, characterized in that the end of the sealing ring (8) facing the ignition device is provided as a conical surface.
5. The aircraft engine ignition cable interface structure according to claim 1, wherein the plug bush (4) outer wall is provided with a plurality of first annular cavities, and the bushing (7) inner wall is provided with a plurality of first annular projections corresponding to each of the first annular cavities (41).
6. An aircraft engine ignition cable interface structure as claimed in claim 1, characterized in that the length of the bushing (7) is substantially comparable to the size of its largest inner diameter.
7. An aircraft engine ignition cable interface structure as claimed in claim 1, characterized in that the length of the nut (5) is smaller than its maximum internal diameter.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111522843.4A CN114336144B (en) | 2021-12-13 | 2021-12-13 | Aeroengine ignition cable interface structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111522843.4A CN114336144B (en) | 2021-12-13 | 2021-12-13 | Aeroengine ignition cable interface structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114336144A CN114336144A (en) | 2022-04-12 |
| CN114336144B true CN114336144B (en) | 2024-05-03 |
Family
ID=81051537
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111522843.4A Active CN114336144B (en) | 2021-12-13 | 2021-12-13 | Aeroengine ignition cable interface structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114336144B (en) |
Citations (26)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3803593A1 (en) * | 1988-02-06 | 1989-08-17 | Bosch Gmbh Robert | Plug connector on a screened low-voltage cable |
| CN2055892U (en) * | 1989-08-29 | 1990-04-11 | 欧敬亭 | Ring-shaped tooth clamp sleeve connector |
| DE9210735U1 (en) * | 1992-08-11 | 1993-12-16 | Grote & Hartmann | Ignition device plug contact |
| JPH0749076A (en) * | 1993-08-05 | 1995-02-21 | Sumitomo Wiring Syst Ltd | Joint structure in ignition device |
| DE19623399A1 (en) * | 1996-06-12 | 1998-01-02 | Bremicker Auto Elektrik | Ignition coil for internal combustion (IC) engine |
| JP2000110698A (en) * | 1998-10-05 | 2000-04-18 | Sumitomo Wiring Syst Ltd | Ignition cable connection device |
| US6296497B1 (en) * | 1997-08-28 | 2001-10-02 | Xiaoying Xu | Three-phase electrical cable plug-type connector |
| US7189114B1 (en) * | 2006-06-29 | 2007-03-13 | Corning Gilbert Inc. | Compression connector |
| CN102468641A (en) * | 2010-11-18 | 2012-05-23 | 郝丁霞 | Waterproof anti-explosion cable connector |
| JP2013191335A (en) * | 2012-03-13 | 2013-09-26 | Sanpa Kogyo Kk | Method and device for checking core wire connection of multi-core cable |
| CN204004963U (en) * | 2014-08-13 | 2014-12-10 | 林仁国 | A kind of rapid pipe joint of corrugated pipe for gas of improvement |
| CN204254078U (en) * | 2014-11-24 | 2015-04-08 | 宁波恒元精工管阀科技有限公司 | Gas kitchen pipe joint |
| CN204358294U (en) * | 2014-12-29 | 2015-05-27 | 亿达日平机床有限公司 | Cutting ferrule rear end is with cutting edge sleeve and front end has the Bite type fittings of double blade |
| CN204905546U (en) * | 2015-08-12 | 2015-12-23 | 南京南瑞集团公司 | High pressure resistant quick cable butt joint |
| KR20160068450A (en) * | 2014-12-05 | 2016-06-15 | 삼화기전 주식회사 | Cable gland used in flameproof electric wire piping |
| CN105715443A (en) * | 2016-03-31 | 2016-06-29 | 安徽华菱汽车有限公司 | Engine ignition system mounting device and engine with device |
| DE202017006808U1 (en) * | 2017-04-25 | 2018-06-19 | Lisa Dräxlmaier GmbH | Aggregate connection for a vehicle |
| CN207559269U (en) * | 2017-11-30 | 2018-06-29 | 四川泛华航空仪表电器有限公司 | A kind of face contacts conveying type firing cable interface limiting device |
| CN110492297A (en) * | 2019-08-22 | 2019-11-22 | 沈阳兴华航空电器有限责任公司 | A kind of end connecting of rigid cable |
| CN209762481U (en) * | 2019-04-12 | 2019-12-10 | 郑州三金石油设备制造有限公司 | Universal pipeline cutting sleeve type joint assembly |
| CN210743654U (en) * | 2019-11-28 | 2020-06-12 | 沈阳兴华航空电器有限责任公司 | Aerospace engine is with high temperature resistant cable |
| CN211088559U (en) * | 2019-11-15 | 2020-07-24 | 陕西航空电气有限责任公司 | Aviation ignition cable high reliability shell fragment jack structure |
| CN112377309A (en) * | 2020-11-13 | 2021-02-19 | 四川泛华航空仪表电器有限公司 | Repairable aeroengine ignition electric nozzle device |
| CN112636068A (en) * | 2020-12-18 | 2021-04-09 | 陕西航空电气有限责任公司 | Ignition cable contact pin type connecting structure |
| CN112993881A (en) * | 2021-03-16 | 2021-06-18 | 国家电网有限公司 | Wire joint insulation processing device |
| CN213661178U (en) * | 2020-09-07 | 2021-07-09 | 江苏泰普特电气仪表有限公司 | Armored double-seal explosion-proof cable stuffing box |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE202012009001U1 (en) * | 2012-09-19 | 2014-01-15 | Bümach Engineering International B.V. | working cylinder |
| AU2015252103B2 (en) * | 2014-11-17 | 2017-05-25 | Thomas & Betts International, Llc | Grounding link for electrical connector mechanism |
| US9559480B2 (en) * | 2015-01-29 | 2017-01-31 | The Phoenix Company Of Chicago, Inc. | Method and apparatus for making an interconnection between power and signal cables |
-
2021
- 2021-12-13 CN CN202111522843.4A patent/CN114336144B/en active Active
Patent Citations (26)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3803593A1 (en) * | 1988-02-06 | 1989-08-17 | Bosch Gmbh Robert | Plug connector on a screened low-voltage cable |
| CN2055892U (en) * | 1989-08-29 | 1990-04-11 | 欧敬亭 | Ring-shaped tooth clamp sleeve connector |
| DE9210735U1 (en) * | 1992-08-11 | 1993-12-16 | Grote & Hartmann | Ignition device plug contact |
| JPH0749076A (en) * | 1993-08-05 | 1995-02-21 | Sumitomo Wiring Syst Ltd | Joint structure in ignition device |
| DE19623399A1 (en) * | 1996-06-12 | 1998-01-02 | Bremicker Auto Elektrik | Ignition coil for internal combustion (IC) engine |
| US6296497B1 (en) * | 1997-08-28 | 2001-10-02 | Xiaoying Xu | Three-phase electrical cable plug-type connector |
| JP2000110698A (en) * | 1998-10-05 | 2000-04-18 | Sumitomo Wiring Syst Ltd | Ignition cable connection device |
| US7189114B1 (en) * | 2006-06-29 | 2007-03-13 | Corning Gilbert Inc. | Compression connector |
| CN102468641A (en) * | 2010-11-18 | 2012-05-23 | 郝丁霞 | Waterproof anti-explosion cable connector |
| JP2013191335A (en) * | 2012-03-13 | 2013-09-26 | Sanpa Kogyo Kk | Method and device for checking core wire connection of multi-core cable |
| CN204004963U (en) * | 2014-08-13 | 2014-12-10 | 林仁国 | A kind of rapid pipe joint of corrugated pipe for gas of improvement |
| CN204254078U (en) * | 2014-11-24 | 2015-04-08 | 宁波恒元精工管阀科技有限公司 | Gas kitchen pipe joint |
| KR20160068450A (en) * | 2014-12-05 | 2016-06-15 | 삼화기전 주식회사 | Cable gland used in flameproof electric wire piping |
| CN204358294U (en) * | 2014-12-29 | 2015-05-27 | 亿达日平机床有限公司 | Cutting ferrule rear end is with cutting edge sleeve and front end has the Bite type fittings of double blade |
| CN204905546U (en) * | 2015-08-12 | 2015-12-23 | 南京南瑞集团公司 | High pressure resistant quick cable butt joint |
| CN105715443A (en) * | 2016-03-31 | 2016-06-29 | 安徽华菱汽车有限公司 | Engine ignition system mounting device and engine with device |
| DE202017006808U1 (en) * | 2017-04-25 | 2018-06-19 | Lisa Dräxlmaier GmbH | Aggregate connection for a vehicle |
| CN207559269U (en) * | 2017-11-30 | 2018-06-29 | 四川泛华航空仪表电器有限公司 | A kind of face contacts conveying type firing cable interface limiting device |
| CN209762481U (en) * | 2019-04-12 | 2019-12-10 | 郑州三金石油设备制造有限公司 | Universal pipeline cutting sleeve type joint assembly |
| CN110492297A (en) * | 2019-08-22 | 2019-11-22 | 沈阳兴华航空电器有限责任公司 | A kind of end connecting of rigid cable |
| CN211088559U (en) * | 2019-11-15 | 2020-07-24 | 陕西航空电气有限责任公司 | Aviation ignition cable high reliability shell fragment jack structure |
| CN210743654U (en) * | 2019-11-28 | 2020-06-12 | 沈阳兴华航空电器有限责任公司 | Aerospace engine is with high temperature resistant cable |
| CN213661178U (en) * | 2020-09-07 | 2021-07-09 | 江苏泰普特电气仪表有限公司 | Armored double-seal explosion-proof cable stuffing box |
| CN112377309A (en) * | 2020-11-13 | 2021-02-19 | 四川泛华航空仪表电器有限公司 | Repairable aeroengine ignition electric nozzle device |
| CN112636068A (en) * | 2020-12-18 | 2021-04-09 | 陕西航空电气有限责任公司 | Ignition cable contact pin type connecting structure |
| CN112993881A (en) * | 2021-03-16 | 2021-06-18 | 国家电网有限公司 | Wire joint insulation processing device |
Non-Patent Citations (1)
| Title |
|---|
| 航空插头及专用拆卸工具设计;周开华;李志华;;舰船电子工程;20100220(第02期);全文 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114336144A (en) | 2022-04-12 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103244773B (en) | Quick connector for gas conveying bellows | |
| EP2541702B1 (en) | Plug cap | |
| CN101702477A (en) | Tail clamping and locking mechanism of low-frequency electric connector | |
| CN201533090U (en) | Tail clamping and locking mechanism of low-frequency electric connector | |
| CN114336144B (en) | Aeroengine ignition cable interface structure | |
| CN201570605U (en) | N-type pin RF coaxial connector of adaption 7D-FB type coaxial cable | |
| CN204538329U (en) | A kind of novel without jack connector jockey | |
| CN206041062U (en) | Electrical connector housing subassembly and use this shells assembly's electric connector | |
| CN105958249B (en) | A kind of electric connector | |
| CN205828685U (en) | The high voltage cable connector of bonding structure | |
| CN209822988U (en) | High-reliability electric connector tail accessory | |
| CN210867391U (en) | Motor casing convenient to cable installation | |
| CN201061039Y (en) | Braided shield outer conductor radio frequency coaxial cable connector | |
| CN205846687U (en) | Metal-rubber shielded joint | |
| CN105958254B (en) | Electric connector housing component and the electric connector using the housing unit | |
| CN217109438U (en) | Lamp holder not easy to loosen | |
| CN206211094U (en) | Super-pressure connector | |
| CN220401036U (en) | Anti-deformation SMA cable assembly | |
| CN113969839B (en) | Aeroengine ignition cable sealing structure | |
| CN217215309U (en) | Middle-high voltage connector | |
| CN203857720U (en) | Receiver-drier housing | |
| CN206806591U (en) | A kind of rainproof electric connector | |
| CN214336428U (en) | Cable fixing head and shielded cable | |
| CN219999016U (en) | Waterproof gram head | |
| CN203532208U (en) | Air compressor for electric bus |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |