CN109273906B - Electromagnetic shielding structure for power socket sealing interface of aero-engine ignition device and installation method thereof - Google Patents
Electromagnetic shielding structure for power socket sealing interface of aero-engine ignition device and installation method thereof Download PDFInfo
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- CN109273906B CN109273906B CN201811224857.6A CN201811224857A CN109273906B CN 109273906 B CN109273906 B CN 109273906B CN 201811224857 A CN201811224857 A CN 201811224857A CN 109273906 B CN109273906 B CN 109273906B
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- bushing
- power supply
- ignition device
- filter
- power
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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
- H01R13/648—Protective earth or shield arrangements on coupling devices, e.g. anti-static shielding
- H01R13/658—High frequency shielding arrangements, e.g. against EMI [Electro-Magnetic Interference] or EMP [Electro-Magnetic Pulse]
- H01R13/6581—Shield structure
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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
- H01R13/46—Bases; Cases
- H01R13/502—Bases; Cases composed of different pieces
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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
- H01R13/46—Bases; Cases
- H01R13/52—Dustproof, splashproof, drip-proof, waterproof, or flameproof cases
- H01R13/5205—Sealing means between cable and housing, e.g. grommet
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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
- H01R13/46—Bases; Cases
- H01R13/52—Dustproof, splashproof, drip-proof, waterproof, or flameproof cases
- H01R13/5216—Dustproof, splashproof, drip-proof, waterproof, or flameproof cases characterised by the sealing material, e.g. gels or resins
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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
- H01R13/73—Means for mounting coupling parts to apparatus or structures, e.g. to a wall
- H01R13/74—Means for mounting coupling parts in openings of a panel
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01R—ELECTRICALLY-CONDUCTIVE CONNECTIONS; STRUCTURAL ASSOCIATIONS OF A PLURALITY OF MUTUALLY-INSULATED ELECTRICAL CONNECTING ELEMENTS; COUPLING DEVICES; CURRENT COLLECTORS
- H01R43/00—Apparatus or processes specially adapted for manufacturing, assembling, maintaining, or repairing of line connectors or current collectors or for joining electric conductors
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01R—ELECTRICALLY-CONDUCTIVE CONNECTIONS; STRUCTURAL ASSOCIATIONS OF A PLURALITY OF MUTUALLY-INSULATED ELECTRICAL CONNECTING ELEMENTS; COUPLING DEVICES; CURRENT COLLECTORS
- H01R43/00—Apparatus or processes specially adapted for manufacturing, assembling, maintaining, or repairing of line connectors or current collectors or for joining electric conductors
- H01R43/20—Apparatus or processes specially adapted for manufacturing, assembling, maintaining, or repairing of line connectors or current collectors or for joining electric conductors for assembling or disassembling contact members with insulating base, case or sleeve
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- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Chemical & Material Sciences (AREA)
- Dispersion Chemistry (AREA)
- Ignition Installations For Internal Combustion Engines (AREA)
- Details Of Connecting Devices For Male And Female Coupling (AREA)
Abstract
The invention provides an electromagnetic shielding structure for a power socket sealing interface of an aircraft engine ignition device and an installation method thereof, wherein the electromagnetic shielding structure comprises an aircraft engine ignition device shell, a power supply bushing, a nut and a filtering bushing; the power supply bushing penetrates through a mounting hole in the shell of the ignition device and then is fixed by argon arc welding, the power supply bushing is connected with a power socket outside the shell, the inner side of the shell is butted with a filtering bushing fixed on the filter, and a power supply wire penetrates through the power supply bushing and the filtering bushing from the power socket and then is connected with the filter and is sealed and fastened in the power socket through sealant; the power supply bushing is in butt joint with the filtering bushing and is fixed through a nut. The invention effectively prevents internal interference signals from being coupled to the power line for output, and also ensures that the sealing structure of the power socket is not damaged.
Description
Technical Field
The invention belongs to the field of aviation and aerospace engine ignition, and relates to a structural design of electromagnetic shielding of a power socket sealing interface of an engine ignition device.
Background
The ignition system is composed of an ignition device of the aircraft engine, an ignition cable and an ignition electric nozzle, and the ignition system ignites fuel-air mixed gas in the main/afterburning chamber in the ground and air starting processes of the aircraft engine. The ignition device converts direct current/alternating current provided by an aircraft engine controller for the ignition device into high-voltage pulse electricity, the ignition cable transmits the high-voltage pulse energy to the ignition electric nozzle, and the high-voltage pulse energy is punctured at the discharge end of the ignition electric nozzle to discharge to form an ignition flower. The performance of the ignition device directly influences the success or failure of the ground and air starting ignition of the engine, and the electromagnetic compatibility of the ignition device is related to the overall electromagnetic compatibility of the engine.
The existing aircraft engine ignition device adopts a nonlinear element and an energy storage element, so that the instantaneous value of power supply input current is very high, the waveform is seriously distorted and is in a pulse shape, and a differential mode interference signal is generated in a low-frequency band; in addition, the discharge tube generates strong electromagnetic radiation during discharge, and strong common-mode interference signals are generated on a power supply line. The electromagnetic interference signal is fed back to the controller connected with the ignition device through the power line, so that the internal logic signal of the controller is easy to be disordered, and the false alarm phenomenon is generated.
In order to solve the problem of false alarm of the controller caused by electromagnetic interference of the ignition device, a filter is usually added between a lead of an internal power input socket of the ignition device of the aircraft engine and a circuit of the ignition device, but an applicant finds that no matter how the filter is designed, a differential mode interference signal and a common mode interference signal are fed back to a power controller, so that the applicant searches for the problem from the structural design of the ignition device of the aircraft engine, and finds that after a power line inside a shell of the ignition device of the aircraft engine is connected with a lead of an input end of the filter, a power line inside the shell is not effectively shielded, the internal interference signal is coupled to the power line for direct output, and the electromagnetic compatibility of the ignition system is influenced. For this reason, the applicant considers that the filter is installed in a manner of being tightly attached to the aircraft engine ignition device shell during installation, but tests show that the aircraft engine ignition device power socket is fixed by a bushing welded on the aircraft engine ignition device shell due to the sealing performance and explosion-proof requirements of the aircraft engine ignition device power socket, welding beading is generated at the joint of the bushing and the shell during welding of the bushing, and the shell is deformed after welding, so that part of a power line inside the shell is exposed.
Disclosure of Invention
Aiming at the new technical problem discovered by the applicant for the first time, the applicant provides an electromagnetic shielding structure for a power socket sealing interface of an ignition device of an aircraft engine and an installation method thereof, so that the ignition device can effectively shield an internal exposed power line while ensuring the sealing requirement of a product, and internal interference signals are prevented from being coupled to the power line for output.
The technical scheme of the invention is as follows:
the electromagnetic shielding structure for the power socket sealing interface of the ignition device of the aircraft engine is characterized in that: the ignition device comprises an aeroengine ignition device shell, a power supply bushing, a nut and a filtering bushing; the power supply bushing penetrates through a mounting hole in the ignition device shell and then is fixed by argon arc welding; the power supply bushing is connected with the power socket through a fastener on the outer side of the ignition device shell, and the structure of the power supply bushing on the inner side of the ignition device shell is a hollow cylindrical structure and is provided with external threads; the hollow structure of the power supply bushing is a wire passing hole, and sealant is filled in the wire passing hole to seal and fasten the power supply wire and the power supply bushing; the filter bushing is provided with a mounting hole and is fixed on the filter shell through a fastener, an axial wire passing hole is formed in the filter bushing, the filter bushing is provided with an external thread, and anaerobic adhesive is arranged on the external thread; the filtering bushing is butted with the power supply bushing, and the outer diameters of butted sections are the same and are matched through threads; and the nut is arranged on the external thread of the opposite stage of the filtering bushing and the power supply bushing and is used for tightly connecting the filtering bushing and the power supply bushing.
The installation method of the electromagnetic shielding structure is characterized in that: the method comprises the following steps:
step 1: installing a power socket on a power supply bushing, leading a power line into the shell of the ignition device of the aero-engine through a power supply bushing wire passing hole, filling sealant into the power supply bushing, and sealing and fastening the power line and the power supply bushing;
step 2: the nut is screwed on the external thread at the tail part of the power socket through the power line;
and step 3: the power line penetrates through a filtering bush fixed on the filter and is connected with the input end of the filter through a lead inside the filter;
and 4, step 4: coating anaerobic adhesive on the external thread of the filtering bush;
and 5: after the power supply bushing and the filter bushing are aligned, the nut is screwed on the filter bushing until the joint of the power supply bushing and the filter bushing is located at the center of the nut.
Advantageous effects
According to the electromagnetic shielding structure of the power socket sealing interface of the aircraft engine ignition device, the original exposed voltage line in the ignition device shell passes through the shielding structure formed by the power bushing, the nut and the filtering bushing, so that the internal interference signal is effectively prevented from being coupled to the power line for output, and the sealing structure of the power socket is ensured not to be damaged.
Additional aspects and advantages of the invention will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of the invention.
Drawings
The above and/or additional aspects and advantages of the present invention will become apparent and readily appreciated from the following description of the embodiments, taken in conjunction with the accompanying drawings of which:
FIG. 1: the existing power socket and the filter are connected schematically;
FIG. 2: the electromagnetic shielding structure of the invention;
FIG. 3: a power supply bushing structure schematic diagram;
FIG. 4: the structure of the filtering bush is shown schematically.
Wherein: 1. a power socket; 2. a bushing; 3. a housing; 4. a power line; 5. a filter; 6. a power supply bushing; 7. a nut; 8. and a filtering liner.
Detailed Description
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention.
As shown in fig. 2, the electromagnetic shielding structure for the aircraft engine ignition device power socket sealing interface comprises an aircraft engine ignition device shell, a power supply bushing, a nut and a filter bushing; the power supply bushing penetrates through a mounting hole in the ignition device shell and then is fixed by argon arc welding; the power supply bushing is connected with the power socket through a fastener on the outer side of the ignition device shell, and the structure of the power supply bushing on the inner side of the ignition device shell is a hollow cylindrical structure and is provided with external threads; the hollow structure of the power supply bushing is a wire passing hole, and sealant is filled in the wire passing hole to seal and fasten the power supply wire and the power supply bushing; the filter bushing is provided with a mounting hole and is fixed on the filter shell through a fastener, an axial wire passing hole is formed in the filter bushing, the filter bushing is provided with an external thread, and anaerobic adhesive is arranged on the external thread; the filtering bushing is butted with the power supply bushing, and the outer diameters of butted sections are the same and are matched through threads; and the nut is arranged on the external thread of the opposite stage of the filtering bushing and the power supply bushing and is used for tightly connecting the filtering bushing and the power supply bushing.
The installation method of the electromagnetic shielding structure comprises the following steps:
step 1: installing a power socket on a power supply bushing, leading a power line into the shell of the ignition device of the aero-engine through a power supply bushing wire passing hole, filling sealant into the power supply bushing, and sealing and fastening the power line and the power supply bushing;
step 2: the nut is screwed on the external thread at the tail part of the power socket through the power line;
and step 3: the power line penetrates through a filtering bush fixed on the filter and is connected with the input end of the filter through a lead inside the filter;
and 4, step 4: coating anaerobic adhesive on the external thread of the filtering bush;
and 5: after the power supply bushing and the filter bushing are aligned, the nut is screwed on the filter bushing until the joint of the power supply bushing and the filter bushing is located at the center of the nut.
The electromagnetic shielding structure in the embodiment is applied to an internal electromagnetic shielding structure of a Q/DHZ-49B ignition device, wherein the central wire passing hole diameter of a power supply bushing is 6mm, and the external thread is M10; the central wire passing aperture of the filtering bushing is 6mm, and the external thread is M10; the nut internal thread is M10mm, and the length is 12 mm. The Q/DHZ-49B ignition device designed according to the electromagnetic shielding structure design method provided by the invention is verified to be qualified in the test results of the CE102 and the RE102 in electromagnetic compatibility through an electromagnetic compatibility test.
Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made in the above embodiments by those of ordinary skill in the art without departing from the principle and spirit of the present invention.
Claims (2)
1. The utility model provides an electromagnetic shield structure that is used for aeroengine ignition supply socket to seal interface which characterized in that: the ignition device comprises an aeroengine ignition device shell, a power supply bushing, a nut and a filtering bushing; the power supply bushing penetrates through a mounting hole in the ignition device shell and then is fixed by argon arc welding; the power supply bushing is connected with the power socket through a fastener on the outer side of the ignition device shell, and the structure of the power supply bushing on the inner side of the ignition device shell is a hollow cylindrical structure and is provided with external threads; the hollow structure of the power supply bushing is a wire passing hole, and sealant is filled in the wire passing hole to seal and fasten the power supply wire and the power supply bushing; the filter bushing is provided with a mounting hole and is fixed on the filter shell through a fastener, an axial wire passing hole is formed in the filter bushing, the filter bushing is provided with an external thread, and anaerobic adhesive is arranged on the external thread; the filtering bushing is butted with the power supply bushing, and the outer diameters of butted sections are the same and are matched through threads; and the nut is arranged on the external thread of the butt joint section of the filtering bushing and the power supply bushing, and the filtering bushing and the power supply bushing are fixedly connected.
2. The method of installing an electromagnetic shielding structure for a sealed interface of an aircraft engine ignition device power outlet of claim 1, wherein: the method comprises the following steps:
step 1: installing a power socket on a power supply bushing, leading a power line into the shell of the ignition device of the aero-engine through a power supply bushing wire passing hole, filling sealant into the power supply bushing, and sealing and fastening the power line and the power supply bushing;
step 2: the nut is screwed on the external thread at the tail part of the power supply bush through the power line;
and step 3: the power line penetrates through a filtering bush fixed on the filter and is connected with the input end of the filter through a lead inside the filter;
and 4, step 4: coating anaerobic adhesive on the external thread of the filtering bush;
and 5: after the power supply bushing and the filter bushing are aligned, the nut is screwed on the filter bushing until the joint of the power supply bushing and the filter bushing is located at the center of the nut.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811224857.6A CN109273906B (en) | 2018-10-19 | 2018-10-19 | Electromagnetic shielding structure for power socket sealing interface of aero-engine ignition device and installation method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811224857.6A CN109273906B (en) | 2018-10-19 | 2018-10-19 | Electromagnetic shielding structure for power socket sealing interface of aero-engine ignition device and installation method thereof |
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| Publication Number | Publication Date |
|---|---|
| CN109273906A CN109273906A (en) | 2019-01-25 |
| CN109273906B true CN109273906B (en) | 2020-01-14 |
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| CN201811224857.6A Active CN109273906B (en) | 2018-10-19 | 2018-10-19 | Electromagnetic shielding structure for power socket sealing interface of aero-engine ignition device and installation method thereof |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113525530B (en) * | 2021-07-21 | 2022-06-28 | 湖北三江航天万峰科技发展有限公司 | Multifunctional interface window of special vehicle cabin |
| CN114709675A (en) * | 2021-12-13 | 2022-07-05 | 陕西航空电气有限责任公司 | Electromagnetic compatibility shielding bush of power socket |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| EP2093846B1 (en) * | 2008-02-20 | 2011-08-17 | VEGA Grieshaber KG | Conductor lead through, housing apparatus and method for manufacturing a conductor lead through |
| CN201781095U (en) * | 2010-07-20 | 2011-03-30 | 上海航天科工电器研究院有限公司 | Connecting component of cable shielding layer |
| US9391393B2 (en) * | 2012-11-08 | 2016-07-12 | Delphi Technologies, Inc. | Connector backshell having multiple cable exit configurations |
| EP2822105A1 (en) * | 2013-02-05 | 2015-01-07 | Amphenol Corporation | Coupling system for electrical connector assembly |
| CN203445582U (en) * | 2013-08-28 | 2014-02-19 | 上海蓝科电气有限公司 | Cable waterproof joint with electromagnetic shielding function |
| CN205179621U (en) * | 2015-11-25 | 2016-04-20 | 成都中亚港利科技集团有限公司 | Power cord shield assembly |
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