CN208539638U - A kind of main ac power supply system of aviation aircraft - Google Patents
A kind of main ac power supply system of aviation aircraft Download PDFInfo
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- CN208539638U CN208539638U CN201721605966.3U CN201721605966U CN208539638U CN 208539638 U CN208539638 U CN 208539638U CN 201721605966 U CN201721605966 U CN 201721605966U CN 208539638 U CN208539638 U CN 208539638U
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Abstract
The utility model discloses a kind of main ac power supply systems of aviation aircraft.The main ac power supply system of the aviation aircraft includes the first main alternative electric generation circuit, the second main alternative electric generation circuit, circuit contactor, the first busbar, charging-discharging controller, battery and circuit breaker box；It wherein, is first busbar power supply according to circuit contactor position, the first main alternative electric generation circuit or the second main alternative electric generation circuit；First busbar is circuit breaker box power supply；The charging-discharging controller is for controlling the described first main alternative electric generation circuit or the second main alternative electric generation circuit as the battery charge or discharge；The battery is used to power for the circuit breaker box, and the battery can power when the battery contactor is connected to for first busbar.The application is mutually backups independently-powered framework using two, visualizes construction for electricity form, and intelligent accummulator charge and discharge control form greatly improves reliability, operability, maintainability.
Description
Technical field
The utility model relates to airplane power source technical field, more particularly to a kind of aviation aircraft with main Alternating Current Power Supply system
System.
Background technique
Country's helicopter largely uses main DC power-supply system at present, and exchange uses secondary power supply configuration shape, and part is straight
The machine of liter uses alternating current and direct current hybrid power supply form.Both the above power supply configuration is mainly used for small-sized, Medium Helicopter.It is used on machine
Electric equipment load is relatively fewer, and large-scale, ultra-large type helicopter is especially in the presence of since electrical equipment is larger as anti-deicing
When such large power-consuming equipment, helicopter generally uses main ac power supply system.
The main ac power supply system of the prior art does not use independently-powered framework, without using intelligent accummulator charge and discharge yet
Electric control form, reliability is low, complicated for operation, difficult in maintenance.
Thus, it is desirable to have a kind of technical solution overcomes or at least mitigates at least one drawbacks described above of the prior art.
Utility model content
Overcome the purpose of this utility model is to provide a kind of aviation aircraft with main ac power supply system or is at least subtracted
At least one drawbacks described above in the light prior art.
To achieve the above object, the utility model provides a kind of aviation aircraft main ac power supply system, the aviation
The main ac power supply system of aircraft includes the first main alternative electric generation circuit, the second main alternative electric generation circuit, circuit contactor, the
One busbar, charging-discharging controller, battery and circuit breaker box；
The first main alternative electric generation circuit and the described second main alternative electric generation circuit are converged by circuit contactor and first
Flow item connection；
First busbar is connect with the circuit breaker box；
The charging-discharging controller respectively with the described first main alternative electric generation circuit or the second main alternative electric generation circuit connection；
The battery is connect with the charging-discharging controller and circuit breaker box respectively, and the battery and described the
One busbar is connected by battery contactor；Wherein,
According to the circuit contactor position, the first main alternative electric generation circuit or the second main alternative electric generation circuit are institute
State the power supply of the first busbar；
First busbar is circuit breaker box power supply；
The charging-discharging controller is used to control the described first main alternative electric generation circuit or the second main alternative electric generation circuit is
The battery charge or discharge；
The battery is used to power for the circuit breaker box, and the battery can connect in the battery contactor
It powers when logical for first busbar.
Preferably, which is characterized in that the first main alternative electric generation circuit passes through with the described second main alternative electric generation circuit
The connection of fault contact device, when the fault contact device is connected, the first main alternative electric generation circuit main is exchanged with described second
Electricity-generating circuit connection.
Preferably, the described first main alternative electric generation circuit includes:
First generator busbar；
First vertoro, the input terminal of first vertoro are connect with first generator busbar；
First contactor, the input terminal of the first contactor are connect with the output end of first vertoro；
First vertoro busbar, the first vertoro busbar is connect with the first contactor and institute
The first vertoro busbar is stated to connect by the circuit contactor with first busbar；Wherein,
First vertoro is used to the three-phase alternating current that the first generator busbar provides becoming direct current, and
First busbar is passed to by the first vertoro busbar.
Preferably, the described second main alternative electric generation circuit includes:
Second generator busbar；
Second vertoro, the input terminal of second vertoro are connect with second generator busbar；
Second contactor, the input terminal of the second contactor are connect with the output end of second vertoro；
Second vertoro busbar, the second vertoro busbar by the circuit contactor with it is described
The connection of first busbar；Wherein,
First vertoro is used to the three-phase alternating current that the first generator busbar provides becoming direct current, and
First busbar is passed to by the first vertoro busbar.
Preferably, the first vertoro busbar and the second vertoro busbar pass through the failure
Contactor connection.
Preferably, circuit breaker box busbar and the direct busbar of battery are provided in the circuit breaker box；It is described disconnected
Road device box busbar is connect with first busbar；The direct busbar of battery is connect with the battery.
The aviation aircraft of the application is with main ac power supply system when the Helicopter AC system failure, and battery is as standby
Part power supply is emergency set power supply on machine.The application is mutually backups independently-powered framework using two, visualization power supply stand configuration
Formula, intelligent accummulator charge and discharge control form, greatly improves reliability, operability, maintainability.It is easy to alleviate pilot's note
Burden.Conducive to flight.
Detailed description of the invention
Fig. 1 is the structural representation according to the main ac power supply system of aviation aircraft of the utility model first embodiment
Figure.
Appended drawing reference:
| 1 | Circuit contactor | 9 | First vertoro |
| 2 | First busbar | 10 | First contactor |
| 3 | Charging-discharging controller | 11 | First vertoro busbar |
| 4 | Battery | 12 | Second generator busbar |
| 5 | Circuit breaker box | 13 | Second vertoro |
| 6 | Battery relay | 14 | Second contactor |
| 7 | Fault contact device | 15 | Second vertoro busbar |
| 8 | First generator busbar | 16 | Circuit breaker box busbar |
| 17 | The direct busbar of battery |
Specific embodiment
To keep the purposes, technical schemes and advantages of the utility model implementation clearer, below in conjunction with the utility model
Attached drawing in embodiment, is further described in more detail the technical scheme in the embodiment of the utility model.In the accompanying drawings, from beginning
Same or similar element or element with the same or similar functions are indicated to same or similar label eventually.Described reality
Applying example is the utility model a part of the embodiment, instead of all the embodiments.Below with reference to the embodiment of attached drawing description
It is exemplary, it is intended to for explaining the utility model, and should not be understood as limiting the present invention.It is practical new based on this
Embodiment in type, every other implementation obtained by those of ordinary skill in the art without making creative efforts
Example, fall within the protection scope of the utility model.The embodiments of the present invention are described in detail with reference to the accompanying drawing.
In the description of the present invention, it should be understood that term " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or positional relationship of the instructions such as "left", "right", "vertical", "horizontal", "top", "bottom" "inner", "outside" is based on attached drawing institute
The orientation or positional relationship shown, is merely for convenience of describing the present invention and simplifying the description, rather than indication or suggestion is signified
Device or element must have a particular orientation, be constructed and operated in a specific orientation, therefore should not be understood as to this is practical
The limitation of novel protected range.
Fig. 1 is the structural representation according to the main ac power supply system of aviation aircraft of the utility model first embodiment
Figure.
The main ac power supply system of aviation aircraft as shown in Figure 1 includes the first main alternative electric generation circuit, the second main friendship
Flow electricity-generating circuit, circuit contactor 1, the first busbar 2, charging-discharging controller 3, battery 4 and circuit breaker box 5；
First main alternative electric generation circuit and the second main alternative electric generation circuit are connected by circuit contactor 1 and the first busbar 2
It connects；
First busbar 2 is connect with circuit breaker box 5；
Charging-discharging controller 3 respectively with the first main alternative electric generation circuit or the second main alternative electric generation circuit connection；
Battery 4 is connect with the charging-discharging controller 3 and circuit breaker box 5 respectively, and the battery 4 and first converges
Item 2 is flowed to connect by battery contactor 6；Wherein,
According to circuit contactor position, the first main alternative electric generation circuit or the second main alternative electric generation circuit are the first busbar
2 power supplies；
First busbar 2 is the power supply of circuit breaker box 5；
Charging-discharging controller 3 is for controlling the first main alternative electric generation circuit or the second main alternative electric generation circuit as the electric power storage
Pond charge or discharge；
Battery is used to power for circuit breaker box 5, and battery 4 can be the when the battery contactor 6 is connected to
The power supply of one busbar.
The aviation aircraft of the application is with main ac power supply system when the Helicopter AC system failure, and battery is as standby
Part power supply is emergency set power supply on machine.Direct current itself uses two to be mutually backups independently-powered framework, visualization power supply stand configuration
Formula, intelligent accummulator charge and discharge control form, greatly improves reliability, operability, maintainability.It is easy to alleviate pilot's note
Burden.Conducive to flight.
Referring to Fig. 1, in the present embodiment, the first main alternative electric generation circuit is connect with the second main alternative electric generation circuit by failure
Tentaculum 7 connects, when fault contact device 7 is connected, the first main alternative electric generation circuit and the second main alternative electric generation circuit communication.
Referring to Fig. 1, in the present embodiment, the first main alternative electric generation circuit includes the first generator busbar 8, first
Vertoro 9, first contactor 10 and the first vertoro busbar 11.
The input terminal of first vertoro 9 is connect with the first generator busbar 8；
The input terminal of first contactor 10 is connect with the output end of the first vertoro 9；
First vertoro busbar 11 is connect with first contactor 10 and the first vertoro busbar 11 passes through
Circuit contactor 1 is connect with the first busbar 2；Wherein,
First vertoro is used to the three-phase alternating current that the first generator busbar provides becoming direct current, and passes through
First vertoro busbar passes to first busbar.
Referring to Fig. 1, in the present embodiment, the second main alternative electric generation circuit becomes including the second generator busbar 12, second
Press rectifier 13, second contactor 14 and the second vertoro busbar 15.
The input terminal of second vertoro 13 is connect with the second generator busbar 12；
The input terminal of the second contactor 14 is connect with the output end of the second vertoro；
Second vertoro busbar 15 is connect by circuit contactor 1 with the first busbar 2；Wherein,
First vertoro is used to the three-phase alternating current that the first generator busbar provides becoming direct current, and passes through
First vertoro busbar passes to first busbar.
Referring to Fig. 1, in the present embodiment, the first vertoro busbar 11 and the second vertoro busbar 15 are logical
Cross the connection of fault contact device 7.
Referring to Fig. 1, it is provided with circuit breaker box busbar 16 in the present embodiment, in circuit breaker box and battery directly converges
Flow item 17；Circuit breaker box busbar is connect with the first busbar；The direct busbar of battery is connect with the battery.
Finally it is noted that above embodiments are only to illustrate the technical solution of the utility model, rather than it is limited
System.Although the utility model is described in detail with reference to the foregoing embodiments, those skilled in the art should be managed
Solution: it is still possible to modify the technical solutions described in the foregoing embodiments, or to part of technical characteristic into
Row equivalent replacement；And these are modified or replaceed, various embodiments of the utility model that it does not separate the essence of the corresponding technical solution
The spirit and scope of technical solution.
Claims (6)
1. a kind of main ac power supply system of aviation aircraft, which is characterized in that the main Alternating Current Power Supply system of the aviation aircraft
System includes the first main alternative electric generation circuit, the second main alternative electric generation circuit, circuit contactor (1), the first busbar (2), charge and discharge
Electric controller (3), battery (4) and circuit breaker box (5)；
The first main alternative electric generation circuit and the described second main alternative electric generation circuit pass through circuit contactor (1) and the first confluence
Item (2) connection；
First busbar (2) connect with the circuit breaker box (5)；
The charging-discharging controller (3) respectively with the described first main alternative electric generation circuit or the second main alternative electric generation circuit connection；
The battery (4) connect with the charging-discharging controller (3) and circuit breaker box (5) respectively, and the battery (4)
It is connect with first busbar (2) by battery contactor (6)；Wherein,
According to the circuit contactor position, the first main alternative electric generation circuit or the second main alternative electric generation circuit are described the
One busbar (2) power supply；
First busbar (2) is the circuit breaker box (5) power supply；
The charging-discharging controller (3) is institute for controlling the described first main alternative electric generation circuit or the second main alternative electric generation circuit
State battery charge or discharge；
The battery is used to power for the circuit breaker box (5), and the battery (4) can be in the battery contactor
(6) it powers when being connected to for first busbar.
2. the main ac power supply system of aviation aircraft as described in claim 1, which is characterized in that the first main exchange hair
Circuit is connect with the described second main alternative electric generation circuit by fault contact device (7), is connected in the fault contact device (7)
When, the first main alternative electric generation circuit and the described second main alternative electric generation circuit communication.
3. the main ac power supply system of aviation aircraft as claimed in claim 2, which is characterized in that the first main exchange hair
Circuit includes:
First generator busbar (8)；
First vertoro (9), the input terminal of first vertoro (9) and first generator busbar (8)
Connection；
First contactor (10), the output end of the input terminal of the first contactor (10) and first vertoro (9)
Connection；
First vertoro busbar (11), the first vertoro busbar (11) and the first contactor (10)
Connection and the first vertoro busbar (11) pass through the circuit contactor (1) and first busbar (2) even
It connects；Wherein,
First vertoro is used to the three-phase alternating current that the first generator busbar provides becoming direct current, and passes through
First vertoro busbar passes to first busbar.
4. the main ac power supply system of aviation aircraft as claimed in claim 3, which is characterized in that the second main exchange hair
Circuit includes:
Second generator busbar (12)；
Second vertoro (13), the input terminal and second generator busbar of second vertoro (13)
(12) it connects；
Second contactor (14), the input terminal of the second contactor (14) and the output end of second vertoro connect
It connects；
Second vertoro busbar (15), the second vertoro busbar (15) pass through the circuit contactor
(1) it is connect with first busbar (2)；Wherein,
First vertoro is used to the three-phase alternating current that the first generator busbar provides becoming direct current, and passes through
First vertoro busbar passes to first busbar.
5. the main ac power supply system of aviation aircraft as claimed in claim 4, which is characterized in that first Transformer Rectifier
Device busbar (11) is connect with the second vertoro busbar (15) by the fault contact device (7).
6. the main ac power supply system of aviation aircraft as claimed in claim 5, which is characterized in that set in the circuit breaker box
It is equipped with circuit breaker box busbar (16) and the direct busbar of battery (17)；The circuit breaker box busbar and described first converges
Flow item connection；The direct busbar of battery is connect with the battery.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721605966.3U CN208539638U (en) | 2017-11-27 | 2017-11-27 | A kind of main ac power supply system of aviation aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721605966.3U CN208539638U (en) | 2017-11-27 | 2017-11-27 | A kind of main ac power supply system of aviation aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208539638U true CN208539638U (en) | 2019-02-22 |
Family
ID=65399778
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721605966.3U Active CN208539638U (en) | 2017-11-27 | 2017-11-27 | A kind of main ac power supply system of aviation aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN208539638U (en) |
-
2017
- 2017-11-27 CN CN201721605966.3U patent/CN208539638U/en active Active
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