CN203607813U - Electronic device for ground fault protection of three-phase aeronautical relay - Google Patents
Electronic device for ground fault protection of three-phase aeronautical relay Download PDFInfo
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- CN203607813U CN203607813U CN201320624919.9U CN201320624919U CN203607813U CN 203607813 U CN203607813 U CN 203607813U CN 201320624919 U CN201320624919 U CN 201320624919U CN 203607813 U CN203607813 U CN 203607813U
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- 238000009434 installation Methods 0.000 claims description 7
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- 230000002159 abnormal effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
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Abstract
The utility model discloses an electronic device for the ground fault protection of a three-phase aeronautical relay, and relates to the technical field of aeronautics and astronautics. The device comprises a relay contact, a fault current detection board, an induction magnet ring, and a relay coil. The fault current detection board is connected with a power supply through a relay coil. The fault current detection board is also connected with the induction magnet ring. The induction magnet ring is provided with the relay contact in a penetration manner. The relay coil is also connected with the relay contact. According to the utility model, the fault current detection board and a conventional aeronautical relay are integrated into the all-in-one device, and only a mutual inductor and an electric circuit board need to be embedded into the housing of the conventional aeronautical relay. The device provided by the utility model is small in size, is convenient for application and maintenance, and does not affect the mechanical and electrical interfaces of a conventional relay.
Description
Technical field
The utility model relates to field of aerospace technology, be specifically related to a kind of three-phase aeronautical relay earth fault protection electronic installation.
Background technology
Three-phase aeronautical relay is the switch electric component for controlling three-phase aviation load break-make.On aircraft, typical threephase load comprises oil fuel booster pump, kitchen oven, sewage pump etc.In the time occurring that threephase load is uneven, the lighter understands scaling loss contact, load, and severe one can cause electrical fire, affects flight safety.There are some defects in current three-phase aeronautical relay on the market:
1, aeronautical relay is one of important electric device on airborne vehicle, and traditional aeronautical relay is that electromagnetic mechanical type structure belongs to passive on-off type device, no ground failure protection function.
2, the current domestic manufacturer that there is no the aeronautical relay with earth fault protection function
3, the earth fault protection on aircraft adopts traditional relay and the acting in conjunction of external earth-fault detector electronics to go to realize more, and its shortcoming is that complex structure safeguards inconvenient, is not easy to test.The purpose of this utility model is to provide a kind of novel aeronautical relay that traditional relay and ground fault detection device is integrated into one, is convenient to install, safeguards and tests.
Utility model content
For the deficiency existing in prior art, the utility model object is to be to provide a kind of three-phase aeronautical relay earth fault protection electronic installation, has volume little, and O&M is convenient, and does not affect traditional relay machinery, electric interfaces.
To achieve these goals; the utility model is to realize by the following technical solutions: three-phase aeronautical relay earth fault protection electronic installation; comprise relay contact, fault current detection plate, reaction magnetic ring and relay coil; fault current detection plate is connected with power supply by relay coil; fault current detection plate is also connected with reaction magnetic ring; in reaction magnetic ring, be equipped with relay contact, relay coil is also connected with relay contact.
As preferably, described fault current detection plate, reaction magnetic ring are all embedded in casing of relay.
When failure detector circuit of the present utility model detects and has abnormal current in reaction magnetic ring, can automatic block system relay coil current, thus break contact is realized load earth fault protection.
The utility model is the device that ground fault detection device and traditional aeronautical relay are become one, and only instrument transformer and electronic circuit board need to be embedded in traditional aeronautical relay housing.Have volume little, O&M is convenient, and does not affect traditional relay machinery, electric interfaces.
Accompanying drawing explanation
Describe the utility model in detail below in conjunction with the drawings and specific embodiments;
Fig. 1 is structural representation of the present utility model.
Embodiment
For technological means, creation characteristic that the utility model is realized, reach object and effect is easy to understand, below in conjunction with embodiment, further set forth the utility model.
With reference to Fig. 1; this embodiment is by the following technical solutions: three-phase aeronautical relay earth fault protection electronic installation; comprise relay contact 1, fault current detection plate 2, reaction magnetic ring 3 and relay coil 4; fault current detection plate 2 is connected with power supply by relay coil 4; fault current detection plate 2 is also connected with reaction magnetic ring 3; in reaction magnetic ring 3, be equipped with relay contact 1, relay coil 4 is also connected with relay contact 1.
It should be noted that described fault current detection plate 2, reaction magnetic ring 3 are all embedded in casing of relay.
Three main contactss of this embodiment relay are all through reaction magnetic ring 3; in the time occurring that a certain ground connection of load or three AC load are uneven; induction coil on magnet ring can sense unsymmetrical current; detected by fault current detection plate 2; 4 power-off of control relay coil, to protect load.
This embodiment is the device that ground fault detection device and traditional aeronautical relay are become one, and only instrument transformer and electronic circuit board need to be embedded in traditional aeronautical relay housing.Have volume little, O&M is convenient, and does not affect traditional relay machinery, electric interfaces.
More than show and described basic principle of the present utility model and principal character and advantage of the present utility model.The technical staff of the industry should understand; the utility model is not restricted to the described embodiments; that in above-described embodiment and specification, describes just illustrates principle of the present utility model; do not departing under the prerequisite of the utility model spirit and scope; the utility model also has various changes and modifications, and these changes and improvements all fall within the scope of claimed the utility model.The claimed scope of the utility model is defined by appending claims and equivalent thereof.
Claims (2)
1. three-phase aeronautical relay earth fault protection electronic installation; it is characterized in that; comprise relay contact (1), fault current detection plate (2), reaction magnetic ring (3) and relay coil (4); fault current detection plate (2) is connected with power supply by relay coil (4); fault current detection plate (2) is also connected with reaction magnetic ring (3); in reaction magnetic ring (3), be equipped with relay contact (1), relay coil (4) is also connected with relay contact (1).
2. three-phase aeronautical relay earth fault protection electronic installation according to claim 1, is characterized in that, described fault current detection plate (2), reaction magnetic ring (3) are all embedded in casing of relay.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320624919.9U CN203607813U (en) | 2013-10-10 | 2013-10-10 | Electronic device for ground fault protection of three-phase aeronautical relay |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320624919.9U CN203607813U (en) | 2013-10-10 | 2013-10-10 | Electronic device for ground fault protection of three-phase aeronautical relay |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203607813U true CN203607813U (en) | 2014-05-21 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320624919.9U Expired - Lifetime CN203607813U (en) | 2013-10-10 | 2013-10-10 | Electronic device for ground fault protection of three-phase aeronautical relay |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203607813U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| TWI773479B (en) * | 2021-08-10 | 2022-08-01 | 上銀科技股份有限公司 | Relay safety system and robot arm controller |
-
2013
- 2013-10-10 CN CN201320624919.9U patent/CN203607813U/en not_active Expired - Lifetime
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| TWI773479B (en) * | 2021-08-10 | 2022-08-01 | 上銀科技股份有限公司 | Relay safety system and robot arm controller |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C56 | Change in the name or address of the patentee | ||
| CP03 | Change of name, title or address |
Address after: 300300, Dongli District, Tianjin Ping Ying Road, 8, services, Binhai Committee, room 3091 Patentee after: TIANJIN VATAPLE HANGYI PHOTOELECTRIC TECHNOLOGY Co.,Ltd. Address before: Room 3 building B-301-1 No. 6 A block 300000 in Tianjin District of Dongli City Huaming Industrial Park HuaFeng Road Patentee before: TIANJIN HANGYI PHOTOELECTRIC SCIENCE & TECHNOLOGY Co.,Ltd. |
|
| CX01 | Expiry of patent term |
Granted publication date: 20140521 |
|
| CX01 | Expiry of patent term |