CN104518478B - A kind of discharge mechanism of aircraft power system - Google Patents
A kind of discharge mechanism of aircraft power system Download PDFInfo
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- CN104518478B CN104518478B CN201310460303.7A CN201310460303A CN104518478B CN 104518478 B CN104518478 B CN 104518478B CN 201310460303 A CN201310460303 A CN 201310460303A CN 104518478 B CN104518478 B CN 104518478B
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- contact
- relay
- contactor
- moving together
- aircraft power
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Abstract
The invention belongs to aircraft power system, the present invention provides a kind of discharge mechanism of aircraft power system, including：Fuse, contactor, switch, the first relay and the second relay；Fuse one terminates aircraft power supply, and the fuse other end is connected with contactor moving together contact one end；The contactor moving together contact other end is connected with the electrical equipment of preparation unloading；One coil contact of contactor is connected with the fuse other end；Another coil contact of contactor is connected with one end of the moving together contact of the first relay；The other end of the moving together contact of first relay is connected with one end of the moving together contact of the second relay；Coil contact one end of first relay is connected with right generator main contactor, and the coil contact other end of the first relay is connected with aircraft power supply negative terminal.
Description
Technical field
The invention belongs to aircraft power system, it is related to a kind of discharge mechanism of aircraft power system.
Background technology
Current aircraft non-transformer system uninstallation function, when aircraft power system breaks down, because power consumption is big
In power-supply system power supply capacity, some unessential big power consumption equipment on aircraft are such as uninstalled not in time, it is possible to damaged and flown
The electricity system of machine.
The content of the invention
The purpose of the present invention：A kind of discharge mechanism of aircraft power system is proposed, pilot can be made rapidly to unload
Carry the larger equipment of power consumption on aircraft.
Technical scheme：A kind of discharge mechanism of aircraft power system, including：Fuse, contactor, switch,
First relay and the second relay；
Fuse one terminates aircraft power supply, and the fuse other end is connected with contactor moving together contact one end；Contactor dynamic circuit connector
The contact other end is connected with the electrical equipment of preparation unloading；One coil contact of contactor is connected with the fuse other end；
Another coil contact of contactor is connected with one end of the moving together contact of the first relay；The moving together contact of first relay it is another
One end is connected with one end of the moving together contact of the second relay；Coil contact one end of first relay is contacted with right generator main
Device is connected, and the coil contact other end of the first relay is connected with aircraft power supply negative terminal；The moving together contact of second relay it is another
One end passes through the first contact portion of diode and switch, coil contact one end of the second relay and left generator main contactor
Connection, the coil contact other end of the second relay is connected with aircraft power supply negative terminal；Born with aircraft power supply second contact of switch
End connection, the 3rd contact of switch passes through another coil contact portion of diode and the contactor；The contactor
The coil contact portion that another coil contact passes through diode and this contactor.
Advantages of the present invention：When aircraft power system breaks down, a kind of aircraft power system that the present invention is provided
Discharge mechanism can uninstall the larger equipment of power consumption on aircraft automatically, and protection aircraft power supply is without prejudice.
Brief description of the drawings：
Fig. 1 is relay construction schematic diagram used in the present invention；
Fig. 2 is a kind of discharge mechanism structural representation of aircraft power system of the invention.
Embodiment：
The present invention is described in further detail below in conjunction with the accompanying drawings.
As shown in figure 1, relay is typically the closed device being made up of coil and several groups of dynamic circuit connector parts, and coil and dynamic circuit connector
The position that part is connected with outer lead is generally termed coil contact and moving together contact, and usual 1 group of dynamic circuit connector part is touched by 3 dynamic circuit connectors
Point composition.X1 and X2 in Fig. 1 are coil contact, and moving together contact 1,2 and 3 constitutes one group of dynamic circuit connector part, moving together contact 4,5 and 6
Constitute another group of dynamic circuit connector part.
A kind of discharge mechanism for aircraft power system that the present invention is provided, as shown in Fig. 2 including：Fuse 85p, contact
Device 86p, switch 89p, the first relay 36p and the second relay 35p；
Fuse 85p mono- terminates aircraft power supply, and the fuse 85p other ends are connected with contactor 86p moving together contact one end；Connect
The tentaculum 86p moving together contact other end is connected with the electrical equipment of preparation unloading；Mono- coil contact of contactor 86p and the fusing
The device 85p other ends are connected；Another coil contact of contactor 86p is connected with one end of the first relay 36p moving together contact；The
The other end of one relay 36p moving together contact is connected with one end of the second relay 35p moving together contact；First relay
36p coil contact one end is connected with right generator main contactor, the first relay 36p the coil contact other end and aircraft electricity
Source negative terminal () connection；The other end of second relay 35p moving together contact is touched by diode 90p with the first of switch 89p
Point connection, the second relay 35p coil contact one end is connected with left generator main contactor, the second relay 35p coil
The contact other end is connected with aircraft power supply negative terminal；Switch 89p the second contact is connected with aircraft power supply negative terminal, switchs the of 89p
Another coil contact portion that three contacts pass through the diode 88p and contactor 86p；The contactor 86p another
The coil contact portion that coil contact passes through diode 87p and this contactor.
Wherein, fuse 85P rated operational currents 200A.Contactor 86P rated voltages：28V, rated current：200A.After
Electrical equipment 35P and 36P rated voltage：28V, rated current：5A, coil resistance：290Ω.Diode 87P, 88P and 90P are specified just
It is 1A to operating current.
When aircraft power system normal work, when switch 89P is placed in " normal " position, 89P 1 and 3 contactings are switched,
Relay 35P and relay 36P coils are in running order, and relay 35P is connected with relay 36P moving together contact 5 with 6,
Contactor 86P coils contact 3 is connected, and contactor 86P work, electrical equipment is powered；
When aircraft power system failure, when switch 89P is placed in " normal " position, at relay 35P or relay 36P coils
In off position, relay 35P or relay 36P moving together contact 5 and 6 are disconnected, and contactor 86P coil contact 3 is broken
Open, contactor 86P does not work, discharge mechanism automatically cuts off the power supply of electrical equipment；
When aircraft power system failure, switch 89P can be also placed at " off " position, switch 89P by pilot
In neutral condition, contactor 86P coil contact 3 is disconnected, and contactor 86P does not work, and discharge mechanism hand off electricity consumption is set
Standby power supply；
Switch 89P is placed in " on " position, 89P 1 and 2 contactings, the contactor 86P quilt of coil contact 3 are switched
It is forcibly turned on, contactor 86P work, electrical equipment is powered (ground energization inspection of this function for aircraft electrical equipment
Look into).
Claims (1)
1. a kind of discharge mechanism of aircraft power system, it is characterised in that including：Fuse, contactor, switch, the first relay
Device and the second relay；
Fuse one terminates aircraft power supply, and the fuse other end is connected with contactor moving together contact one end；Contactor moving together contact
The other end is connected with the electrical equipment of preparation unloading；One coil contact of contactor is connected with the fuse other end；Contact
Another coil contact of device is connected with one end of the moving together contact of the first relay；The other end of the moving together contact of first relay
It is connected with one end of the moving together contact of the second relay；Coil contact one end of first relay connects with right generator main contactor
Connect, the coil contact other end of the first relay is connected with aircraft power supply negative terminal；The other end of the moving together contact of second relay
By the first contact portion of diode and switch, coil contact one end of the second relay connects with left generator main contactor
Connect, the coil contact other end of the second relay is connected with aircraft power supply negative terminal；Second contact of switch and aircraft power supply negative terminal
Connection, the 3rd contact of switch passes through another coil contact portion of diode and the contactor；The contactor it is another
The coil contact portion that one coil contact passes through diode and this contactor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310460303.7A CN104518478B (en) | 2013-09-30 | 2013-09-30 | A kind of discharge mechanism of aircraft power system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310460303.7A CN104518478B (en) | 2013-09-30 | 2013-09-30 | A kind of discharge mechanism of aircraft power system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104518478A CN104518478A (en) | 2015-04-15 |
| CN104518478B true CN104518478B (en) | 2017-08-25 |
Family
ID=52793390
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310460303.7A Active CN104518478B (en) | 2013-09-30 | 2013-09-30 | A kind of discharge mechanism of aircraft power system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104518478B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113328426B (en) * | 2021-06-30 | 2023-06-02 | 江西洪都航空工业集团有限责任公司 | Nacelle, radar power supply control circuit of coach machine |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO1999052090A1 (en) * | 1998-04-06 | 1999-10-14 | Antti Kaarnamo | Method for switching off a power supply in a dangerous situation and a corresponding safeguarding arrangement |
| CN200976576Y (en) * | 2006-12-07 | 2007-11-14 | 林华木 | Plane solid state relay for short circuit and overload protection |
| CN202678927U (en) * | 2012-07-13 | 2013-01-16 | 广东广业云硫矿业有限公司 | Electric shovel handle safety control system |
-
2013
- 2013-09-30 CN CN201310460303.7A patent/CN104518478B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO1999052090A1 (en) * | 1998-04-06 | 1999-10-14 | Antti Kaarnamo | Method for switching off a power supply in a dangerous situation and a corresponding safeguarding arrangement |
| CN200976576Y (en) * | 2006-12-07 | 2007-11-14 | 林华木 | Plane solid state relay for short circuit and overload protection |
| CN202678927U (en) * | 2012-07-13 | 2013-01-16 | 广东广业云硫矿业有限公司 | Electric shovel handle safety control system |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104518478A (en) | 2015-04-15 |
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