CN107919725A - A kind of airplane power source control box using Interleaved control configuration - Google Patents
A kind of airplane power source control box using Interleaved control configuration Download PDFInfo
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- CN107919725A CN107919725A CN201711136065.9A CN201711136065A CN107919725A CN 107919725 A CN107919725 A CN 107919725A CN 201711136065 A CN201711136065 A CN 201711136065A CN 107919725 A CN107919725 A CN 107919725A
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- contactor
- engine controller
- contact device
- load contact
- connects
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J9/00—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting
- H02J9/04—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which the distribution system is disconnected from the normal source and connected to a standby source
- H02J9/06—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which the distribution system is disconnected from the normal source and connected to a standby source with automatic change-over, e.g. UPS systems
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- Business, Economics & Management (AREA)
- Emergency Management (AREA)
- Engineering & Computer Science (AREA)
- Power Engineering (AREA)
- Supply And Distribution Of Alternating Current (AREA)
- Control Of Vehicle Engines Or Engines For Specific Uses (AREA)
Abstract
The present invention proposes a kind of airplane power source control box using Interleaved control configuration, including left connection contactor, right connection contactor, left load contact device, right load contact device, ground power supply contactor and current transformer group, left connection contactor connects the right engine controller of airplane power source, right connection contactor connects the left engine controller of airplane power source, left load contact device connects left engine controller, and right load contact device connects right engine controller；And when binary channels is each independently-powered, left connection contactor and right connection contactor are in closure state；By the present invention in that the control logic novel circuit configuration of Interleaved control is used, solve one kind (losing the control to contactor) failure problems on former model aircraft, change and optimize the structure of logic control, left and right passage conversion zero defect conversion is reached, it is ensured that a hair passage is powered to full machine.
Description
Technical field
The invention belongs to aviation power system control technology field, is related to a kind of alternating current of binary channels aircraft electrical power supply system
The Interleaved control novel circuit configuration of source control box, the control circuit for aviation power system.
Background technology
Certain aircraft uses the AC power supply system for the non-parallel operation being made of two power channels, can be set to aircraft electricity consumption
Available electricity.Each power channel is made of a generator and an engine controller.Each passage is thrown with generator
Net control function, has defencive function, power channel conversion and power-supply system self-checking function.Two power channels, ground electricity
Source monitoring device and power control box collectively constitute aircraft binary channels alternating current power-generating system, after which is made of these devices,
It is required that when there is a certain channel load or power supply failure, control box disconnects the side, realizes that single channel is powered for full machine.
But there are a kind of situation for existing changeover control logic：When the control failure to contactor occurs losing in a wing passage
When (such as engine controller failure itself, other unit failures such as generator, mutual inductor, the feeder line of power channel disconnect
Deng), control signal can not be sent at this time and disconnects contactor, is only capable of disconnecting the load contact device of the wing passage, led to not
The Bus Tie Contactor of the wing passage is disconnected, then causes the busbar of faulty channel can not connect fault-free passage, that
In this case, this side of faulty channel will be unable to connect the power supply that normal channel provides, and lead to not realize that a hair leads to
Road powers to full machine.Current changeover control logic is thus used, if engine controller failure, power supply will be caused logical
Disconnection fault on the machine that road can not be changed and occurred.
The content of the invention
This mistake that the present invention usually occurs when being changed by analyzing current aviation power system binary channels, designs one
The power control box of kind of Interleaved control logic, to control the dual channel source system of current this mainstream, perfect power-supply system
Control relay protective scheme, also improve the fault tolerant electrical power supply ability under electric power system fault condition.And due to aircraft generating system
Composition is substantially similar, and twin-channel aircraft generating system is used for other, is using Interleaved control logic proposed by the present invention
Power control box after, can be realized by way of controlling this passage main contactor to connect contactor with his passage and staggeredly controlled
System, improves fault tolerant electrical power supply ability.
The technical scheme is that：
A kind of airplane power source control box using Interleaved control configuration, including left connection contactor, right connection contact
Device, left load contact device, right load contact device, ground power supply contactor and current transformer group；It is characterized in that：Left connection
Contactor connects the right engine controller of airplane power source, and right engine controller connects contactor and provides break-make control letter to the left
Number；Right connection contactor connects the left engine controller of airplane power source, and left engine controller, which connects to the right contactor and provides, to be led to
Disconnected control signal；Left load contact device connects left engine controller, and right load contact device connects right engine controller；And work as
When binary channels is each independently-powered, left connection contactor and right connection contactor are in closure state；Left connection contactor
Normally-closed contact one end is connected with right generator, and normally-closed contact one end of right connection contactor is connected with left generator；Left load connects
Normally opened contact one end of tentaculum and common one end of left connection contactor connect, normally opened contact one end of right load contact device
Connected with common one end of right connection contactor；Left load contact device meets the left engine controller of airplane power source, Zuo Fa
Load contact device provides break-make control signal to electric machine controller to the left, and when left engine controller failure, left load contact
Device is transformed into off-state by closure state automatically；Right load contact device connects the right engine controller of airplane power source, right power generation
Load contact device provides break-make control signal to machine controller to the right, and when right engine controller failure, right load contact device
Automatically off-state is transformed into by closure state.
Beneficial effect
By the present invention in that having used the control logic novel circuit configuration of Interleaved control, solves one kind on former model aircraft
(losing the control to contactor) failure problems, change and optimize the structure of logic control, have reached left and right passage conversion nothing
Mistake is changed, it is ensured that a hair passage is powered to full machine.
The additional aspect and advantage of the present invention will be set forth in part in the description, and will partly become from the following description
Obtain substantially, or recognized by the practice of the present invention.
Brief description of the drawings
The above-mentioned and/or additional aspect and advantage of the present invention will become in the description from combination accompanying drawings below to embodiment
Substantially and it is readily appreciated that, wherein：
Fig. 1：When binary channels is independently-powered, the wiring of control box and contactor location diagram；
Fig. 2：Left channel failure (including engine controller failure), when right passage is powered for full machine, the wiring of control box
And contactor location diagram.
Embodiment
The embodiment of the present invention is described below in detail, the embodiment is exemplary, it is intended to for explaining the present invention, and
It is not considered as limiting the invention.
This mistake that the present invention usually occurs when being changed by analyzing current aviation power system binary channels, designs one
The power control box of kind of Interleaved control logic, to control the dual channel source system of current this mainstream, perfect power-supply system
Control relay protective scheme, also improve the fault tolerant electrical power supply ability under electric power system fault condition.And due to aircraft generating system
Composition is substantially similar, and twin-channel aircraft generating system is used for other, is using Interleaved control logic proposed by the present invention
Power control box after, can be realized by way of controlling this passage main contactor to connect contactor with his passage and staggeredly controlled
System, improves fault tolerant electrical power supply ability.
Specific airplane power source control box, including left connection contactor, right connection contactor, left load contact device, the right side are negative
Carry contactor, ground power supply contactor and current transformer group.
As shown in Figure 1, left connection contactor connects the right engine controller of airplane power source, right engine controller connects to the left
Connect contactor and break-make control signal is provided；Right connection contactor connects the left engine controller of airplane power source, left generator control
Device connects to the right contactor and provides break-make control signal.
Left load contact device connects left engine controller, and right load contact device connects right engine controller；And when double
When passage is each independently-powered, left connection contactor and right connection contactor are in closure state.
It is left connection contactor normally-closed contact one end be connected with right generator, it is right connection contactor normally-closed contact one end and
Left generator is connected；Normally opened contact one end of left load contact device and common one end of left connection contactor connect, and the right side is negative
The normally opened contact one end and common one end of right connection contactor for carrying contactor connect.
Left load contact device connects the left engine controller of airplane power source, and load contact device carries left engine controller to the left
For break-make control signal, and when left engine controller failure, left load contact device is transformed into disconnection by closure state automatically
State；Right load contact device connects the right engine controller of airplane power source, and load contact device provides right engine controller to the right
Break-make control signal, and when right engine controller failure, right load contact device is transformed into disconnection shape by closure state automatically
State.
As shown in Fig. 2, when the failure mode of left engine controller is to lose control to contactor (when power channel
Other unit failures such as generator, mutual inductor, feeder line disconnection etc.), engine controller can disconnect negative according to set logic
Contactor GCB and connection contactor BTB are carried, so that it is guaranteed that realizing that right power channel is powered for binary channels.It is achieved that single-pass
Its passage can power to full machine under road either component failure, any failure mode, solve engine controller from principle
Power-off caused by failure, solves this kind of failure problems.
The electric power system at utmost ensure that unilateral generator supplies full machine electricity consumption when aircraft power supply binary channels is changed.
Due to the use of the control logic of Interleaved control, the event of conversion error when solving the failure of traditional dual channel electric power system single channel
Barrier problem, optimizes the structure of logic control, has reached left and right passage conversion zero defect conversion.Aircraft bilateral using the present invention
Road electric power system, can effectively shield this on the premise of not changing miscellaneous part and also not increasing system complexity and weight
A kind of failure, improves the reliability of product, and the perfect control relay protective scheme of power-supply system, also improves electric power system failure
In the case of fault tolerant electrical power supply ability.Carried out using certain type AC power control box of the invention in the electric power system of aircraft
Use, passage caused by engine controller failure is not changed to be resolved completely with outage problem, the failure of electric power system
Rate significantly reduces, and does not cause the change of other matching components.
Although the embodiment of the present invention has been shown and described above, it is to be understood that above-described embodiment is example
Property, it is impossible to limitation of the present invention is interpreted as, those of ordinary skill in the art are not departing from the principle of the present invention and objective
In the case of above-described embodiment can be changed within the scope of the invention, change, replace and modification.
Claims (1)
1. a kind of airplane power source control box using Interleaved control configuration, including left connection contactor, right connection contactor, a left side are negative
Carry contactor, right load contact device, ground power supply contactor and current transformer group；It is characterized in that：Left connection contactor
The right engine controller of airplane power source is connect, right engine controller connects contactor and provides break-make control signal to the left；Right company
The left engine controller that contactor connects airplane power source is connect, left engine controller connects to the right contactor and provides break-make control letter
Number；Left load contact device connects left engine controller, and right load contact device connects right engine controller；And when binary channels is each
From it is independently-powered when, it is left connection contactor and it is right connection contactor be in closure state；The normally-closed contact of left connection contactor
One end is connected with right generator, and normally-closed contact one end of right connection contactor is connected with left generator；Left load contact device it is normal
Open contact one end and common one end of left connection contactor connects, normally opened contact one end and the right connection of right load contact device
Common one end connection of contactor；Left load contact device connects the left engine controller of airplane power source, left generator control
Load contact device provides break-make control signal to device to the left, and when left engine controller failure, left load contact device automatically by
Closure state is transformed into off-state；Right load contact device connects the right engine controller of airplane power source, right engine controller
Load contact device provides break-make control signal to the right, and when right engine controller failure, right load contact device is automatically by closing
Conjunction state is transformed into off-state.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711136065.9A CN107919725B (en) | 2017-11-16 | 2017-11-16 | Aviation power supply control box adopting staggered control configuration |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711136065.9A CN107919725B (en) | 2017-11-16 | 2017-11-16 | Aviation power supply control box adopting staggered control configuration |
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| CN107919725A true CN107919725A (en) | 2018-04-17 |
| CN107919725B CN107919725B (en) | 2021-01-05 |
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| CN201711136065.9A Active CN107919725B (en) | 2017-11-16 | 2017-11-16 | Aviation power supply control box adopting staggered control configuration |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110844094A (en) * | 2019-10-25 | 2020-02-28 | 天津航空机电有限公司 | Double-channel aviation digital power supply control method |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110844094A (en) * | 2019-10-25 | 2020-02-28 | 天津航空机电有限公司 | Double-channel aviation digital power supply control method |
| CN110844094B (en) * | 2019-10-25 | 2022-10-11 | 天津航空机电有限公司 | Double-channel aviation digital power supply control method |
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| Publication number | Publication date |
|---|---|
| CN107919725B (en) | 2021-01-05 |
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