CN108054977A - Reduce the main Power feed electric power system and method for aircraft DC starting-generating - Google Patents
Reduce the main Power feed electric power system and method for aircraft DC starting-generating Download PDFInfo
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- CN108054977A CN108054977A CN201711250016.8A CN201711250016A CN108054977A CN 108054977 A CN108054977 A CN 108054977A CN 201711250016 A CN201711250016 A CN 201711250016A CN 108054977 A CN108054977 A CN 108054977A
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02P—CONTROL OR REGULATION OF ELECTRIC MOTORS, ELECTRIC GENERATORS OR DYNAMO-ELECTRIC CONVERTERS; CONTROLLING TRANSFORMERS, REACTORS OR CHOKE COILS
- H02P25/00—Arrangements or methods for the control of AC motors characterised by the kind of AC motor or by structural details
- H02P25/16—Arrangements or methods for the control of AC motors characterised by the kind of AC motor or by structural details characterised by the circuit arrangement or by the kind of wiring
- H02P25/30—Arrangements or methods for the control of AC motors characterised by the kind of AC motor or by structural details characterised by the circuit arrangement or by the kind of wiring the motor being controlled by a control effected upon an ac generator supplying it
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02P—CONTROL OR REGULATION OF ELECTRIC MOTORS, ELECTRIC GENERATORS OR DYNAMO-ELECTRIC CONVERTERS; CONTROLLING TRANSFORMERS, REACTORS OR CHOKE COILS
- H02P9/00—Arrangements for controlling electric generators for the purpose of obtaining a desired output
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02P—CONTROL OR REGULATION OF ELECTRIC MOTORS, ELECTRIC GENERATORS OR DYNAMO-ELECTRIC CONVERTERS; CONTROLLING TRANSFORMERS, REACTORS OR CHOKE COILS
- H02P2101/00—Special adaptation of control arrangements for generators
- H02P2101/30—Special adaptation of control arrangements for generators for aircraft
Abstract
A kind of main Power feed electric power system for reducing aircraft DC starting-generating of the present invention and method, the system structure are：By the way that the both ends that the main Power feed of power supply is used between starter controller and three-phase alternating current starter-generator are set the first single-pole double-throw switch (SPDT), starting control contactor and the second single-pole double-throw switch (SPDT), restart and be multiplexed with power generating stage by the way that the first single-pole double-throw switch (SPDT), starting control contactor and the second single-pole double-throw switch (SPDT) is controlled to realize main Power feed, reduce the quantity of main Power feed.The beneficial effects of the invention are as follows：Due to the adoption of the above technical scheme, the present invention, which realizes, realizes main Power feed multiplexing, reduces main Power feed quantity, improves starting-generating system power-density, reduces 40% main Power feed cable dosage, can reach the purpose of aircraft loss of weight.
Description
Technical field
The present invention relates to aircraft electrical power supply system, DC start electricity generation system, cable connection more particularly to one kind to be applied to one
Kind of aircraft, specific to but be not limited to main Power feed electric power system and the side of the reduction aircraft DC starting-generating of aircarrier aircraft
Method.
Background technology
DC start electricity generation system refer to direct current energy start engine, be what power generating stage sent direct current energy
System.DC start electricity generation system is respectively adopted two sets of different control devices with power generating stage in starting and realizes starting and hair respectively
Electricity Functional.It is defeated that direct current energy is converted to by threephase AC electric energy using three-phase bridge driving circuit and microprocessor in starting stage
Enter to generation torque drive engine in threephase alternator, it is whole using the three-phase for being built in generator in power generating stage
Stream bridge circuit exports electric energy rectification that threephase alternator is sent to using electric loading for direct current energy.
Direct current is risen in system at present, for that cannot be multiplexed between starting stage and the cable of power generating stage, need to be adopted respectively
The transmission of electric energy is carried out with two sets of separate cables.In Large Civil Aircraft, since generator is located in engine pod, start
The controller and electrical equipment in stage are at aircraft middle deck position, and therefore, every main Power feed length is not less than 30 meters,
DC start electricity generation system power is larger, in the case that electric energy transmission range is longer, the increase meeting of main Power feed number of cables
System weight is dramatically increased, reduces power density.
The main Power feed connection mode of DC start electricity generation system is as shown in Figure 1, the system structure of existing scheme at present
Schematic diagram as shown in Fig. 2,
It can be seen that main Power feed has five used by existing scheme.It cannot be multiplexed between main Power feed and cause electricity
The serious increase of the long range redundancy and weight of cable.This programme need to be reached by the improvement of the internal connection architecture of starting-generating system
To main Power feed radical is reduced, the purpose of main Power feed weight is reduced.
The content of the invention
To solve the above-mentioned problems, the purpose of the present invention is to propose to a kind of main work(that can reduce DC start electricity generation system
Rate feeder line radical, so as to achieve the purpose that reduce main Power feed weight and reduction aircraft DC starting-generating system simple in structure
The electric power system for main Power feed quantity of uniting.
The technical scheme is that：A kind of electric power system for the main Power feed for reducing aircraft DC starting-generating, institute
Stating system includes starter controller, three-phase bridge rectifier, DC load and three-phase alternating current starter-generator, which is rising
Movement controller one end sets the first single-pole double-throw switch (SPDT) and starting control contactor, is set in three-phase alternating current starter-generator one end
Second single-pole double-throw switch (SPDT), first single-pole double-throw switch (SPDT) and starting control contactor pass through 3 main Power feeds and second
Single-pole double-throw switch (SPDT) is connected with three-phase alternating current starter-generator, by controlling the first single-pole double-throw switch (SPDT), control contactor and the
The main Power feed of realization of two single-pole double-throw switch (SPDT)s starts the multiplexing with power generating stage, reduces the quantity of main Power feed.
Further, the concrete structure of the system is：Described starter controller one end is connected with DC start power supply, the other end
One end with the 2nd contact of first single-pole double-throw switch (SPDT) and the starting control contactor is connected respectively, and the direct current is born
The 1st contact portion with first single-pole double-throw switch (SPDT) is carried, wherein 2 described main Power feed one end and first hilted broadsword
One end connection of commutator, the other end are connected with one end of second single-pole double-throw switch (SPDT), another main power feedback
The other end connection of starting control contactor described in one end of line, the other end are connected with the three-phase alternating current starter-generator, institute
State the 2nd contact portion of three-phase alternating current starter-generator and second single-pole double-throw switch (SPDT), the three-phase bridge rectifier with
1st contact portion of second single-pole double-throw switch (SPDT), the three-phase bridge rectifier and the three-phase alternating current starter-generator
Connection.
Further, which further includes single-pole double-throw switch (SPDT) controller and current sensor, and the current sensor is set
It is connected in the main Power feed, and with the single-pole double-throw switch (SPDT) controller, the single-pole double-throw switch (SPDT) controller difference
It controls and connects with the first single-pole double-throw switch (SPDT), starting control contactor and the second single-pole double-throw switch (SPDT).
Further, the single-pole double-throw switch (SPDT) controller includes AC/DC modules, resistance R1, resistance R2, resistance R3, resistance
R4, resistance R5, resistance R6, resistance R7, resistance R8, resistance R9, resistance R10, resistance R11, resistance R12, resistance R13, resistance
R14, resistance R15, resistance R16, resistance R17, resistance R18, resistance R19, resistance R20, resistance R21, resistance R22, diode
D1, diode D2, diode D3, diode D4, diode D5, diode D6, diode D7, diode D8, diode D9, electricity
Hold C1, capacitance C2, operational amplifier V1, operational amplifier V2, operational amplifier V3 and signal controller；
Wherein, one end of the resistance R4 and diode D1 receives A phase voltage signals, and the R4 other ends are with diode D4's
One end connects, and the other end of the diode D1 is connected with one end of the resistance R1；The one of the resistance R5 and diode D2
End receives B phase voltage signals, and the other end of the resistance R5 is connected with one end of diode D5, and the diode D2's is another
End is connected with one end of the resistance R2；One end of the R6 and D3 receives C phase voltage signals, the other end of the resistance R6
It is connected with one end of diode D6, the other end of the D3 is connected with one end of the resistance R2, the diode D4, diode
Negative input of the other end of D5 and diode D6 with operational amplifier V1 is connected, the resistance R1, resistance R2 and resistance R3's
The one end of the other end with the resistance R12 is connected, the one end of one end of the capacitance C1 and resistance R7 with the resistance R12
The other end of connection, the capacitance C1 and resistance R7 are grounded, one end of the other end of the resistance R12 and the resistance R13
Connection, the other end of the resistance R13 are connected with the positive input of the operational amplifier V2, one end of the resistance R19 and institute
The positive input for stating operational amplifier V2 is connected, and the other end is connected to the ground；
The resistance R14's is connected with one end of the resistance R13, and the other end of the resistance R14 is put respectively with the computing
Big device V1 outputs are connected with one end of the resistance R16, and the other end of the resistance R16 is respectively with the operational amplifier V1's
Positive input is connected with one end of resistance R17, the other end ground connection of the resistance R17；
The resistance R7 and D7 one end receive A phase current signals, the other end ground connection of the resistance R7, the resistance R8 and two poles
Pipe D8 one end receives A phase current signals, and the other end ground connection of the resistance R8, the resistance R9 and diode D9 one end receive A
Phase current signal, the other end ground connection of the resistance R9, the other end of the diode D7, diode D8 and diode D9 with
One end connection of the resistance R11, the other end of the resistance R11 are connected with one end of the resistance R20, the resistance R20
The other end be connected with the negative input of the operational amplifier V3, one end of the capacitance C2 and resistance R18 with the computing
The negative input of amplifier V3 is connected, and the other end of the capacitance C2 and resistance R18 are grounded respectively；
The output of the operational amplifier V3 is connected with described resistance R21 one end, the other end of the R21 and the operation amplifier
The negative input connection of device V2, the output of the operational amplifier V2 are connected with one end of the resistance R22, and the resistance R22 is another
One end is connected with the signal controller.
It is a further object of the present invention to provide the confessions of the system of the main Power feed of above-mentioned reduction aircraft DC starting-generating
Electric control method, this method specifically include following steps：
At the start, the direct current energy inversion of DC start power input is threephase AC electric energy by starter controller, by cutting
The first single-pole double-throw switch (SPDT) and the first single-pole double-throw switch (SPDT) are changed, starting control contactor is closed at, makes threephase alternator
Torque drive engine rotation is generated to starting speed；
In power generation, threephase alternator sends three-phase alternating current, switches the first single-pole double-throw switch (SPDT) and the second single-pole double throw
Switch, simultaneously switch off starting control contactor, make three-phase alternating current by three phase rectifier bridge-type circuit rectifies be direct current energy, lead to
It crosses main Power feed and is conveyed to DC load end.
Further, this method concretely comprises the following steps：
It is described at the start, the direct current energy that DC start power supply exports is delivered to the starting control in starter controller casing
Direct current energy inversion is threephase AC electric energy by device, the starter controller, and the contact of the first single-pole double-throw switch (SPDT) is allocated to 2
It puts, the contact of the second single-pole double-throw switch (SPDT) is allocated to 2 positions, is closed at starting control contactor so that starter controller is defeated
The three-phase alternating current gone out is started by three main Power feeds into the three-phase alternating current in three-phase alternating current starter-generator casing
Generator, threephase alternator generate torque drive engine rotation to starting speed.
Further, in power generation, threephase alternator sends threephase AC electric energy, respectively by the first single-pole double-throw switch (SPDT)
Contact be allocated to 1 position, the contact of the second single-pole double-throw switch (SPDT) is allocated to 1 position, simultaneously switches off starting control contactor, control
Threephase AC electric energy is inputted into the three phase rectifier bridge-type circuit in three-phase alternating current starter-generator casing, three phase rectifier bridge-type
Three-phase alternating current electric rectification is direct current energy by circuit, and is passed through two main Power feeds and entered DC load end.
Further, the present invention also provides the power supply autocontrol method of the electric power system, following steps are specifically included,
The single-pole double-throw switch (SPDT) controller obtains the three-phase voltage V in main Power feed by the direct-connected mode of cable0, by being arranged on
Current sensor in main Power feed obtains the three-phase electricity flow valuve I in main Power feed, passes through the single-pole double-throw switch (SPDT) control
AC/DC modules obtain the reference voltage value V in A phases circuit inside device processed1；By comparing circuit and three-phase voltage V0It is compared, root
The automatic switching of the first single-pole double-throw switch (SPDT) and the second single-pole double-throw switch (SPDT) is realized according to the condition for comparing satisfaction.
Further, the condition for relatively needing to meet:
As the voltage value V in main Power feed0During less than power generation permissible value, the first single-pole double-throw switch (SPDT) is kept to be in 1；
As the voltage value V of main Power feed0During more than power generation permissible value, the first single-pole double-throw switch (SPDT) of switching is in 2.
The beneficial effects of the invention are as follows：Due to the adoption of the above technical scheme, system of the invention sends out existing DC start
The framework of electric system is changed, and adding single-pole double throw inside the generator and controller of DC start electricity generation system opens
It closes, realizes main Power feed and start the multiplexing with power generating stage.The control of single-pole double-throw switch (SPDT) is added in motor case
Circuit processed realizes the automatic switching of single-pole double-throw switch (SPDT) and realizes main power using a kind of control strategy according to this framework and presents
The multiplexing of line improves starting-generating system power-density, reduces 40% main Power feed cable dosage, can reach aircraft
The purpose of loss of weight.
Description of the drawings
Fig. 1 is the DC start electricity generation system connecting line construction schematic diagram in existing aircraft.
Fig. 2 is the DC start power generation system structure schematic diagram in prior art.
Fig. 3 is the DC start electricity generation system connecting line construction schematic diagram in technical solution of the present invention.
Fig. 4 is the electric power system structure diagram of the DC start electricity generation system in technical solution of the present invention.
Fig. 5 is the structure diagram of the electric power system another specific embodiment of the present invention.
Fig. 6 is the electrical structure schematic diagram of single-pole double-throw switch (SPDT) controller in the present invention.
In figure：
5. engine, 10. three-phase alternating current starter-generator casings, 110. three-phase alternating current starter-generators, 111. three-phase alternating currents rise
Three-phase bridge rectifier, 215. DC loads, 30. starter controller casings, 31. starter controllers built in dynamic generator, 32
For DC start power supply, main power feedback that main Power feed that 50. power generating stage electric currents flow through, 51. starting stage electric currents flow through
Line, 40. Generation Control contactors, 41. be starting control contactor, 43. first single-pole double-throw switch (SPDT)s, 44. second single-pole double throws
Switch, 60. main Power feeds, 70 be single-pole double-throw switch (SPDT) controller.
Specific embodiment
Technical scheme is described further below in conjunction with the accompanying drawings.
As Figure 3-Figure 4, a kind of electric power system for the main Power feed for reducing aircraft DC starting-generating of the present invention, institute
Stating system includes starter controller, three-phase bridge rectifier, DC load and three-phase alternating current starter-generator, which is rising
Movement controller one end sets the first single-pole double-throw switch (SPDT) and starting control contactor, is set in three-phase alternating current starter-generator one end
Second single-pole double-throw switch (SPDT), first single-pole double-throw switch (SPDT) and starting control contactor pass through 3 main Power feeds and second
Single-pole double-throw switch (SPDT) is connected with three-phase alternating current starter-generator, by controlling the first single-pole double-throw switch (SPDT), control contactor and the
The main Power feed of realization of two single-pole double-throw switch (SPDT)s starts the multiplexing with power generating stage, reduces the quantity of main Power feed.
The system volume concrete structure is that described starter controller one end is connected with DC start power supply, the other end respectively with
2nd contact of first single-pole double-throw switch (SPDT) is connected with one end of the starting control contactor, the DC load and institute
The 1st contact portion of the first single-pole double-throw switch (SPDT) is stated, wherein 2 described main Power feed one end are opened with first single-pole double throw
One end connection of pass, the other end are connected with one end of second single-pole double-throw switch (SPDT), and the one of another main Power feed
The other end of the starting control contactor is held to connect, the other end is connected with the three-phase alternating current starter-generator, the three-phase
Exchange the 2nd contact portion of starter-generator and second single-pole double-throw switch (SPDT), the three-phase bridge rectifier and described the
1st contact portion of two single-pole double-throw switch (SPDT)s, the three-phase bridge rectifier are connected with the three-phase alternating current starter-generator.
A kind of control method of the electric power system of the main Power feed of above-mentioned reduction aircraft DC starting-generating, this method tool
Body comprises the following steps：
At the start, the direct current energy inversion of DC start power input is threephase AC electric energy by starter controller, by cutting
The first single-pole double-throw switch (SPDT) and the first single-pole double-throw switch (SPDT) are changed, starting control contactor is closed at, makes threephase alternator
Torque drive engine rotation is generated to starting speed；
In power generation, threephase alternator sends three-phase alternating current, switches the first single-pole double-throw switch (SPDT) and the second single-pole double throw
Switch, simultaneously switch off starting control contactor, make three-phase alternating current by three phase rectifier bridge-type circuit rectifies be direct current energy, lead to
It crosses main Power feed and is conveyed to DC load end.
It is described at the start, the direct current energy that DC start power supply exports is delivered to the starting in starter controller casing
Direct current energy inversion is threephase AC electric energy by controller, the starter controller, and the contact of the first single-pole double-throw switch (SPDT) is dialled
To 2 positions, the contact of the second single-pole double-throw switch (SPDT) is allocated to 2 positions, is closed at starting control contactor so that starting control
The three-phase alternating current of device output enters the three-phase alternating current in three-phase alternating current starter-generator casing by three main Power feeds
Starter-generator, threephase alternator generate torque drive engine rotation to starting speed；
In power generation, threephase alternator sends threephase AC electric energy, and the contact of the first single-pole double-throw switch (SPDT) is allocated to 1 respectively
The contact of second single-pole double-throw switch (SPDT) is allocated to 1 position by position, simultaneously switches off starting control contactor, controls three-phase alternating current
Can be in input to three phase rectifier bridge-type circuit in three-phase alternating current starter-generator casing, three phase rectifier bridge-type circuit is by three-phase
AC rectification is direct current energy, and passes through two main Power feeds and enter DC load end.
As shown in Fig. 5-Fig. 6, which further includes single-pole double-throw switch (SPDT) controller and current sensor, the current sense
Device is arranged in the main Power feed, and is connected with the single-pole double-throw switch (SPDT) controller, the single-pole double-throw switch (SPDT) control
Device controls with the first single-pole double-throw switch (SPDT), starting control contactor and the second single-pole double-throw switch (SPDT) connect respectively.
The single-pole double-throw switch (SPDT) controller control includes AC/DC modules, resistance R1, resistance R2, resistance R3, resistance R4, electricity
Hinder R5, resistance R6, resistance R7, resistance R8, resistance R9, resistance R10, resistance R11, resistance R12, resistance R13, resistance R14, electricity
Hinder R15, resistance R16, resistance R17, resistance R18, resistance R19, resistance R20, resistance R21, resistance R22, diode D1, two poles
Pipe D2, diode D3, diode D4, diode D5, diode D6, diode D7, diode D8, diode D9, capacitance C1, electricity
Hold C2, operational amplifier V1, operational amplifier V2, operational amplifier V3 and signal controller；
Wherein, one end of the resistance R4 and diode D1 receives one end company of A phase voltage signals, the R4 other ends and D4
It connects, the other end of the D1 is connected with one end of the resistance R1；One end of the resistance R5 and diode D2 receives B phases
Voltage signal, the other end of the resistance R5 are connected with one end of diode D5, the other end and the electricity of the diode D2
Hinder one end connection of R2；One end of the R6 and D3 receives C phase voltage signals, the other end and the diode D6 of the resistance R6
One end connection, the other end of the D3 is connected with one end of the resistance R2, the diode D4, diode D5 and diode
Negative input of the other end of D6 with operational amplifier V1 is connected, the other end of the resistance R1, resistance R2 and resistance R3 with
The one end of one end of one end connection of the resistance R12, the capacitance C1 and resistance R7 with the resistance R12 is connected, described
The other end of capacitance C1 and resistance R7 are grounded, and the other end of the resistance R12 is connected with one end of the resistance R13, described
The other end of resistance R13 is connected with the positive input of the operational amplifier V2, one end and the operation amplifier of the resistance R19
The positive input of device V2 is connected, and the other end is connected to the ground；
The resistance R14's is connected with one end of the R13, the other end of the resistance R14 respectively with the operational amplifier
V1 outputs are connected with one end of the resistance R16, and the other end of the resistance R16 is just defeated with the operational amplifier V1 respectively
Enter and connected with one end of resistance R17, the other end ground connection of the resistance R17；
The resistance R7 and D7 one end receive A phase current signals, the other end ground connection of the resistance R7, the resistance R8 and two poles
Pipe D8 one end receives A phase current signals, and the other end ground connection of the resistance R8, the resistance R9 and diode D9 one end receive A
Phase current signal, the other end ground connection of the resistance R9, the other end of the diode D7, diode D8 and diode D9 with
One end connection of the resistance R11, the other end of the resistance R11 are connected with one end of the resistance R20, the resistance R20
The other end be connected with the negative input of the operational amplifier V3, one end of the capacitance C2 and resistance R18 with the computing
The negative input of amplifier V3 is connected, and the other end of the capacitance C2 and resistance R18 are grounded respectively；
The output of the operational amplifier V3 is connected with described resistance R21 one end, the other end of the R21 and the operation amplifier
The negative input connection of device V2, the output of the operational amplifier V2 are connected with one end of the resistance R22, and the resistance R22 is another
One end is connected with the signal controller.
A kind of power supply autocontrol method using above-mentioned electric power system specifically includes following steps, the single-pole double throw
Switch controller obtains the three-phase voltage V in main Power feed by the direct-connected mode of cable0, by being arranged in main Power feed
Current sensor obtain the three-phase electricity flow valuve I in main Power feed, pass through the single-pole double-throw switch (SPDT) controller inside AC/DC
Module obtains the reference voltage value V in A phases circuit1；By comparing circuit and three-phase voltage V0It is compared, according to comparing satisfaction
Condition realizes the automatic switching of the first single-pole double-throw switch (SPDT) and the second single-pole double-throw switch (SPDT).
The condition for relatively needing to meet:
As the voltage value V in main Power feed0During less than power generation permissible value, the first single-pole double-throw switch (SPDT) is kept to be in 1；
When the voltage value of main Power feed is more than power generation permissible value（The power generation permissible value is that can produce threephase alternator
Torque drive engine rotation is given birth to the voltage value of starting speed）When, the first single-pole double-throw switch (SPDT) of switching is in 2.
One embodiment of the present of invention is described in detail above, but the content is only the preferable implementation of the present invention
Example, it is impossible to be construed as limiting the practical range of the present invention.All all the changes and improvements made according to the present patent application scope
Deng, should all still belong to the present invention patent covering scope within.
Claims (9)
1. it is a kind of reduce aircraft DC starting-generating main Power feed electric power system, the system comprises starter controller,
Three-phase bridge rectifier, DC load and three-phase alternating current starter-generator, which is characterized in that the system is in starter controller one
End sets the first single-pole double-throw switch (SPDT) and starting control contactor, sets the second hilted broadsword double in three-phase alternating current starter-generator one end
Throw switch, first single-pole double-throw switch (SPDT) and starting control contactor are opened by 3 main Power feeds with the second single-pole double throw
Pass is connected with three-phase alternating current starter-generator, by controlling the first single-pole double-throw switch (SPDT), control contactor and the second single-pole double throw
The main Power feed of realization of switch starts the multiplexing with power generating stage, reduces the quantity of main Power feed.
2. electric power system according to claim 1, which is characterized in that described starter controller one end and DC start power supply
Connection, the one end of the other end respectively with the 2nd contact of first single-pole double-throw switch (SPDT) and the starting control contactor are connected,
The DC load and the 1st contact portion of first single-pole double-throw switch (SPDT), wherein 2 described main Power feed one end and institute
One end connection of the first single-pole double-throw switch (SPDT) is stated, the other end is connected with one end of second single-pole double-throw switch (SPDT), another institute
State the other end connection of starting control contactor described in one end of main Power feed, the other end and the three-phase alternating current starting-generating
Machine connects, the 2nd contact portion of the three-phase alternating current starter-generator and second single-pole double-throw switch (SPDT), the three-phase bridge
1st contact portion of rectifier and second single-pole double-throw switch (SPDT), the three-phase bridge rectifier rise with the three-phase alternating current
Dynamic generator connection.
3. electric power system according to claim 2, which is characterized in that the system further include single-pole double-throw switch (SPDT) controller and
Current sensor, the current sensor are arranged in the main Power feed, and are connected with the single-pole double-throw switch (SPDT) controller
Connect, the single-pole double-throw switch (SPDT) controller respectively with the first single-pole double-throw switch (SPDT), starting control contactor and the second single-pole double throw
Switch control connection.
4. electric power system according to claim 3, which is characterized in that the single-pole double-throw switch (SPDT) controller includes AC/DC
Module, resistance R1, resistance R2, resistance R3, resistance R4, resistance R5, resistance R6, resistance R7, resistance R8, resistance R9, resistance R10,
Resistance R11, resistance R12, resistance R13, resistance R14, resistance R15, resistance R16, resistance R17, resistance R18, resistance R19, resistance
R20, resistance R21, resistance R22, diode D1, diode D2, diode D3, diode D4, diode D5, diode D6, two
Pole pipe D7, diode D8, diode D9, capacitance C1, capacitance C2, operational amplifier V1, operational amplifier V2, operational amplifier V3
And signal controller；
Wherein, one end of the resistance R4 and diode D1 receives A phase voltage signals, and the R4 other ends are with diode D4's
One end connects, and the other end of the diode D1 is connected with one end of the resistance R1；The one of the resistance R5 and diode D2
End receives B phase voltage signals, and the other end of the resistance R5 is connected with one end of diode D5, and the diode D2's is another
End is connected with one end of the resistance R2；One end of the R6 and D3 receives C phase voltage signals, the other end of the resistance R6
It is connected with one end of diode D6, the other end of the D3 is connected with one end of the resistance R2, the diode D4, diode
Negative input of the other end of D5 and diode D6 with operational amplifier V1 is connected, the resistance R1, resistance R2 and resistance R3's
The one end of the other end with the resistance R12 is connected, the one end of one end of the capacitance C1 and resistance R7 with the resistance R12
The other end of connection, the capacitance C1 and resistance R7 are grounded, one end of the other end of the resistance R12 and the resistance R13
Connection, the other end of the resistance R13 are connected with the positive input of the operational amplifier V2, one end of the resistance R19 and institute
The positive input for stating operational amplifier V2 is connected, and the other end is connected to the ground；
The resistance R14's is connected with one end of the resistance R13, and the other end of the resistance R14 is put respectively with the computing
Big device V1 outputs are connected with one end of the resistance R16, and the other end of the resistance R16 is respectively with the operational amplifier V1's
Positive input is connected with one end of resistance R17, the other end ground connection of the resistance R17；
The resistance R7 and D7 one end receive A phase current signals, the other end ground connection of the resistance R7, the resistance R8 and two poles
Pipe D8 one end receives A phase current signals, and the other end ground connection of the resistance R8, the resistance R9 and diode D9 one end receive A
Phase current signal, the other end ground connection of the resistance R9, the other end of the diode D7, diode D8 and diode D9 with
One end connection of the resistance R11, the other end of the resistance R11 are connected with one end of the resistance R20, the resistance R20
The other end be connected with the negative input of the operational amplifier V3, one end of the capacitance C2 and resistance R18 with the computing
The negative input of amplifier V3 is connected, and the other end of the capacitance C2 and resistance R18 are grounded respectively；
The output of the operational amplifier V3 is connected with described resistance R21 one end, the other end of the R21 and the operation amplifier
The negative input connection of device V2, the output of the operational amplifier V2 are connected with one end of the resistance R22, and the resistance R22 is another
One end is connected with the signal controller.
5. a kind of system for the main Power feed that aircraft DC starting-generating is reduced according to 1 or 2 any one of them of claim
Method for controlling power supply, which is characterized in that this method specifically includes following steps：
At the start, the direct current energy inversion of DC start power input is threephase AC electric energy by starter controller, by cutting
The first single-pole double-throw switch (SPDT) and the first single-pole double-throw switch (SPDT) are changed, starting control contactor is closed at, makes threephase alternator
Torque drive engine rotation is generated to starting speed；
In power generation, threephase alternator sends three-phase alternating current, switches the first single-pole double-throw switch (SPDT) and the second single-pole double throw
Switch, simultaneously switch off starting control contactor, make three-phase alternating current by three phase rectifier bridge-type circuit rectifies be direct current energy, lead to
It crosses main Power feed and is conveyed to DC load end.
6. method for controlling power supply according to claim 5, which is characterized in that it is described at the start, by DC start power supply
The direct current energy of output is delivered to the starter controller in starter controller casing, and the starter controller is by direct current energy inversion
For threephase AC electric energy, the contact of the first single-pole double-throw switch (SPDT) is allocated to 2 positions, the contact of the second single-pole double-throw switch (SPDT) is allocated to
2 positions are closed at starting control contactor so that the three-phase alternating current of starter controller output passes through three main Power feeds
Into the three-phase alternating current starter-generator in three-phase alternating current starter-generator casing, threephase alternator generates torque drive
Engine rotation is to starting speed.
7. method for controlling power supply according to claim 5, which is characterized in that in power generation, threephase alternator is sent
The contact of first single-pole double-throw switch (SPDT) is allocated to 1 position by threephase AC electric energy respectively, and the contact of the second single-pole double-throw switch (SPDT) is dialled
To 1 position, starting control contactor is simultaneously switched off, control threephase AC electric energy is inputted in three-phase alternating current starter-generator casing
In interior three phase rectifier bridge-type circuit, three-phase alternating current electric rectification is direct current energy by three phase rectifier bridge-type circuit, and passes through two
Main Power feed enters DC load end.
8. a kind of power supply autocontrol method using electric power system as claimed in claim 3, which is characterized in that specifically include
Following steps, the single-pole double-throw switch (SPDT) controller obtain the three-phase voltage V in main Power feed by the direct-connected mode of cable0,
The three-phase electricity flow valuve I in main Power feed is obtained by the current sensor being arranged in main Power feed, passes through the hilted broadsword
AC/DC modules obtain the reference voltage value V in A phases circuit inside commutator controller1；By comparing circuit and three-phase voltage V0
It is compared, the automatic switching of the first single-pole double-throw switch (SPDT) and the second single-pole double-throw switch (SPDT) is realized according to the condition for comparing satisfaction.
9. method for controlling power supply according to claim 8, which is characterized in that the condition for relatively needing to meet:
As the voltage value V in main Power feed0During less than power generation permissible value, the first single-pole double-throw switch (SPDT) is kept to be in 1；
As the voltage value V of main Power feed0During more than power generation permissible value, the first single-pole double-throw switch (SPDT) of switching is in 2.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711250016.8A CN108054977B (en) | 2017-12-01 | 2017-12-01 | Main power feeder line power supply system and method for reducing direct current starting power generation of airplane |
| PCT/CN2017/114789 WO2019104749A1 (en) | 2017-12-01 | 2017-12-06 | Main power feeder-based power supply system and method for reducing direct-current starting power generation of aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201711250016.8A CN108054977B (en) | 2017-12-01 | 2017-12-01 | Main power feeder line power supply system and method for reducing direct current starting power generation of airplane |
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| Publication Number | Publication Date |
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| CN108054977A true CN108054977A (en) | 2018-05-18 |
| CN108054977B CN108054977B (en) | 2020-06-02 |
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| CN201711250016.8A Active CN108054977B (en) | 2017-12-01 | 2017-12-01 | Main power feeder line power supply system and method for reducing direct current starting power generation of airplane |
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| CN (1) | CN108054977B (en) |
| WO (1) | WO2019104749A1 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113708679A (en) * | 2021-08-24 | 2021-11-26 | 中国商用飞机有限责任公司 | Cable time-sharing multiplexing circuit and method for aircraft starting power generation system |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0881738A2 (en) * | 1997-05-29 | 1998-12-02 | STMicroelectronics, Inc. | Generator powered electrically heated catalyst system |
| CN101535611A (en) * | 2006-11-15 | 2009-09-16 | 三菱电机株式会社 | Hybrid engine assist system for vehicle |
| CN203278379U (en) * | 2013-05-27 | 2013-11-06 | 宋立明 | Starting system of emergency power-generation vehicle |
| CN104539023A (en) * | 2015-01-19 | 2015-04-22 | 东北电力大学 | Wind power generation and power supply system based on grid power complementation |
| CN204538971U (en) * | 2015-01-15 | 2015-08-05 | 山东艾诺仪器有限公司 | A kind of electrical network analog power with direct current output function |
| CN106915316A (en) * | 2017-02-27 | 2017-07-04 | 东风汽车公司 | For the power-supply system and power control method of idling start and stop vehicle |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP4761370B2 (en) * | 2006-03-20 | 2011-08-31 | 本田技研工業株式会社 | Control device for motor generator for motorcycle |
| CN102545754B (en) * | 2012-02-29 | 2014-04-16 | 南京航空航天大学 | Winding open circuit type permanent magnet double-salient-pole starting power generation system |
| CN103684127B (en) * | 2013-11-28 | 2016-02-17 | 南京航空航天大学 | A kind of combined type brushless DC start generator system and control method thereof |
| CN107683565B (en) * | 2015-03-09 | 2020-09-18 | 新电元工业株式会社 | Starting power generation device and starting power generation method |
| CN104935143B (en) * | 2015-03-18 | 2018-09-07 | 中国科学院电工研究所 | A kind of starter generator |
| CN104767466B (en) * | 2015-04-21 | 2017-08-18 | 山东理工大学 | The starting-generating system that a kind of winding automatically switches |
| CN107276482B (en) * | 2017-07-17 | 2019-07-19 | 南京航空航天大学 | A kind of starting of starting/generating system/power generation soft handover method |
-
2017
- 2017-12-01 CN CN201711250016.8A patent/CN108054977B/en active Active
- 2017-12-06 WO PCT/CN2017/114789 patent/WO2019104749A1/en active Application Filing
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0881738A2 (en) * | 1997-05-29 | 1998-12-02 | STMicroelectronics, Inc. | Generator powered electrically heated catalyst system |
| CN101535611A (en) * | 2006-11-15 | 2009-09-16 | 三菱电机株式会社 | Hybrid engine assist system for vehicle |
| CN203278379U (en) * | 2013-05-27 | 2013-11-06 | 宋立明 | Starting system of emergency power-generation vehicle |
| CN204538971U (en) * | 2015-01-15 | 2015-08-05 | 山东艾诺仪器有限公司 | A kind of electrical network analog power with direct current output function |
| CN104539023A (en) * | 2015-01-19 | 2015-04-22 | 东北电力大学 | Wind power generation and power supply system based on grid power complementation |
| CN106915316A (en) * | 2017-02-27 | 2017-07-04 | 东风汽车公司 | For the power-supply system and power control method of idling start and stop vehicle |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113708679A (en) * | 2021-08-24 | 2021-11-26 | 中国商用飞机有限责任公司 | Cable time-sharing multiplexing circuit and method for aircraft starting power generation system |
| WO2023024371A1 (en) * | 2021-08-24 | 2023-03-02 | 中国商用飞机有限责任公司 | Time division multiplexing circuit and method for cables of starting-generation system of aircraft |
| CN113708679B (en) * | 2021-08-24 | 2023-05-09 | 中国商用飞机有限责任公司 | Cable time-sharing multiplexing circuit and method for aircraft starting power generation system |
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| Publication number | Publication date |
|---|---|
| WO2019104749A1 (en) | 2019-06-06 |
| CN108054977B (en) | 2020-06-02 |
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