CN108054977B - Main power feeder line power supply system and method for reducing direct current starting power generation of airplane - Google Patents
Main power feeder line power supply system and method for reducing direct current starting power generation of airplane Download PDFInfo
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- CN108054977B CN108054977B CN201711250016.8A CN201711250016A CN108054977B CN 108054977 B CN108054977 B CN 108054977B CN 201711250016 A CN201711250016 A CN 201711250016A CN 108054977 B CN108054977 B CN 108054977B
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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
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- Control Of Eletrric Generators (AREA)
Abstract
The invention relates to a main power feeder line power supply system and a method for reducing direct current starting power generation of an airplane, wherein the system structure is as follows: the first double-pole double-throw switch, the starting controller and the second double-pole double-throw switch are arranged at two ends of a main power feeder used for supplying power between the starting controller and the three-phase alternating-current starting generator, and the main power feeder is multiplexed by controlling the first double-pole double-throw switch, the starting controller and the second double-pole double-throw switch in the restarting and power generation stages, so that the number of the main power feeders is reduced. The invention has the beneficial effects that: by adopting the technical scheme, the invention realizes the multiplexing of the main power feeder, reduces the number of the main power feeders, improves the power density of the starting power generation system, reduces the cable consumption of the main power feeder by 40 percent and can achieve the aim of reducing the weight of the airplane.
Description
Technical Field
The invention relates to an aircraft power supply system, a direct current starting power generation system and cable connection, in particular to a main power feeder line power supply system and a method for reducing direct current starting power generation of an aircraft, which are applied to the aircraft, particularly but not limited to civil aircrafts.
Background
The direct current starting power generation system is a system which starts an engine by using direct current electric energy and generates the direct current electric energy in a power generation stage. The direct current starting power generation system respectively adopts two sets of different control devices to respectively realize the starting and power generation functions in the starting and power generation stages. In the starting stage, a three-phase bridge type driving circuit and a microprocessor are adopted to convert direct current electric energy into three-phase alternating current electric energy, the three-phase alternating current electric energy is input into a three-phase alternating current generator to generate torque to drive an engine, and in the power generation stage, a three-phase rectification bridge type circuit arranged in the generator is adopted to rectify the electric energy generated by the three-phase alternating current generator into direct current electric energy to be output to a power load.
In the existing direct current starting system, cables used in a starting stage and a generating stage cannot be multiplexed, and two sets of independent cables are required to be adopted for electric energy transmission respectively. On a large civil aircraft, because the generator is positioned in an engine hanging cabin, and a controller and electric equipment in a starting stage are positioned in the middle cabin of the aircraft, the length of each main power feeder line is not less than 30 meters, and under the conditions that a direct current starting power generation system has larger power and longer electric energy transmission distance, the increase of the number of main power feeder line cables can obviously increase the weight of the system and reduce the power density.
The connection mode of the main power feeder of the current direct current starting power generation system is shown as figure 1, the schematic diagram of the system structure of the prior scheme is shown as figure 2,
it can be seen that there are five main power feeders used in the existing solutions. The inability to multiplex between main power feeds creates long distance redundancy and a severe increase in weight of the cable. The scheme needs to achieve the purposes of reducing the number of main power feeders and reducing the weight of the main power feeders through the improvement of an internal connection framework of the starting power generation system.
Disclosure of Invention
In order to solve the above problems, an object of the present invention is to provide a power supply system capable of reducing the number of main power feeders of a dc start power generation system, thereby achieving the purpose of reducing the weight of the main power feeders and reducing the number of main power feeders of an aircraft dc start power generation system with a simple structure.
The technical scheme of the invention is as follows: a power supply system for reducing main power feeders of airplane direct current starting power generation comprises a starting controller, a three-phase bridge rectifier, a direct current load and a three-phase alternating current starting generator, wherein a first double-pole double-throw switch and a starting controller are arranged at one end of the starting controller, a second double-pole double-throw switch is arranged at one end of the three-phase alternating current starting generator, the first double-pole double-throw switch and the starting controller are connected with the second double-pole double-throw switch and the three-phase alternating current starting generator through 3 main power feeders, and the multiplexing of the main power feeders in the starting and power generation stages is realized by controlling the first double-pole double-throw switch, a control contactor and the second double-pole double-throw switch, so that the number of the main power feeders is reduced.
Further, the specific structure of the system is as follows: one end of the starting controller is connected with a direct-current starting power supply, the other end of the starting controller is respectively connected with the 2 nd contact of the first double-pole double-throw switch and one end of the starting controller, the direct-current load is connected with the 1 st contact of the first double-pole double-throw switch, wherein one end of each of the 2 main power feeders is connected with one end of the first double-pole double-throw switch, the other end of each main power feeder is connected with one end of the second double-pole double-throw switch, one end of the other main power feeder is connected with the other end of the starting controller, the other end of the other main power feeder is connected with the three-phase alternating-current starting generator, the three-phase AC starting generator is connected with the 2 nd contact of the second double-pole double-throw switch, the three-phase bridge rectifier is connected with the 1 st contact of the second double-pole double-throw switch, and the three-phase bridge rectifier is connected with the three-phase AC starting generator.
The system further comprises a double-pole double-throw switch controller and a current sensor, wherein the current sensor is arranged on the main power feeder and connected with the double-pole double-throw switch controller, and the double-pole double-throw switch controller is respectively connected with the first double-pole double-throw switch, the starting controller and the second double-pole double-throw switch in a control mode.
Further, the double-pole double-throw switch controller comprises an AC/DC module, a resistor R1, a resistor R2, a resistor R3, a resistor R4, a resistor R5, a resistor R6, a resistor R7, a resistor R8, a resistor R9, a resistor R10, a resistor R11, a resistor R12, a resistor R13, a resistor R14, a resistor R15, a resistor R16, a resistor R17, a resistor R18, a resistor R19, a resistor R20, a resistor R21, a resistor R22, a diode D1, a diode D2, a diode D3, a diode D4, a diode D5, a diode D6, a diode D7, a diode D8, a diode D9, a capacitor C1, a capacitor C2, an operational amplifier V1, an operational amplifier V2, an operational amplifier V3 and a signal controller;
one end of the resistor R4 and one end of the diode D1 both receive an A-phase voltage signal, the other end of the R4 is connected with one end of the diode D4, and the other end of the diode D1 is connected with one end of the resistor R1; one end of the resistor R5 and one end of the diode D2 both receive a B-phase voltage signal, the other end of the resistor R5 is connected with one end of the diode D5, and the other end of the diode D2 is connected with one end of the resistor R2; one end of each of the R6 and D3 receives a C-phase voltage signal, the other end of the resistor R6 is connected to one end of a diode D6, the other end of the D3 is connected to one end of the resistor R2, the other ends of the diode D4, the diode D5 and the diode D6 are connected to the negative input of an operational amplifier V1, the other ends of the resistor R1, the resistor R2 and the resistor R3 are connected to one end of the resistor R12, one ends of the capacitor C1 and the resistor R7 are connected to one end of the resistor R12, the other ends of the capacitor C1 and the resistor R7 are grounded, the other end of the resistor R12 is connected to one end of the resistor R13, the other end of the resistor R13 is connected to the positive input of the operational amplifier V2, one end of the resistor R19 is connected to the positive input of the operational amplifier V2, and the other end is connected to ground;
one end of the resistor R14 is connected to one end of the resistor R13, the other end of the resistor R14 is connected to the output of the operational amplifier V1 and one end of the resistor R16, the other end of the resistor R16 is connected to the positive input of the operational amplifier V1 and one end of the resistor R17, and the other end of the resistor R17 is grounded;
one end of the resistor R7 and one end of the diode D7 receive a phase current signal of A, the other end of the resistor R7 is grounded, one end of the resistor R8 and one end of the diode D8 receive a phase current signal of B, the other end of the resistor R8 is grounded, one end of the resistor R9 and one end of the diode D9 receive a phase current signal of C, the other end of the resistor R9 is grounded, the other ends of the diode D7, the diode D8 and the diode D9 are connected with one end of the resistor R11, the other end of the resistor R11 is connected with one end of the resistor R20, the other end of the resistor R20 is connected with the negative input of the operational amplifier V3, one ends of the capacitor C2 and the resistor R18 are connected with one end of the resistor R20, and the other ends of the capacitor C2 and the resistor;
the output of the operational amplifier V3 is connected to one end of the resistor R21, the other end of the resistor R21 is connected to the negative input of the operational amplifier V2, the output of the operational amplifier V2 is connected to one end of the resistor R22, and the other end of the resistor R22 is connected to the signal controller.
Another object of the present invention is to provide a power supply control method for the system for reducing the main power feeder for dc start power generation of an aircraft, which specifically includes the following steps:
when starting, the starting controller inverts the direct current energy input by the direct current starting power supply into three-phase alternating current electric energy, and the three-phase alternating current generator generates torque to drive the engine to rotate to a starting rotating speed by switching the first double-pole double-throw switch and closing the starting controller;
during power generation, the three-phase alternating-current generator generates three-phase alternating current, the first double-pole double-throw switch and the second double-pole double-throw switch are switched, and the starting controller is switched off at the same time, so that the three-phase alternating current is rectified into direct-current electric energy through the three-phase rectifying bridge circuit and is transmitted to the direct-current load end through the main power feeder.
Further, the method comprises the following specific steps:
when the starting controller is started, the direct current electric energy output by the direct current starting power supply is transmitted to the starting controller in the starting controller shell, the starting controller inverts the direct current electric energy into three-phase alternating current electric energy, the contact of the first double-pole double-throw switch is poked to the 2 nd contact, the contact of the second double-pole double-throw switch is poked to the 2 nd contact, meanwhile, the starting controller is closed, the three-phase alternating current output by the starting controller enters the three-phase alternating current starting generator in the three-phase alternating current starting generator shell through three main power feeders, and the three-phase alternating current generator generates torque to drive the engine to rotate to the starting rotating speed.
Further, during power generation, the three-phase alternating-current generator generates three-phase alternating-current electric energy, the contacts of the first double-pole double-throw switch are respectively pushed to the 1 st contact, the contacts of the second double-pole double-throw switch are pushed to the 1 st contact, the starting controller is turned off at the same time, the three-phase alternating-current electric energy is controlled to be input into a three-phase rectification bridge circuit in the shell of the three-phase alternating-current starting generator, the three-phase rectification bridge circuit rectifies the three-phase alternating current into direct-current electric energy, and the direct-current electric energy enters a direct-current load end through two.
Further, the invention also provides a power supply automatic control method of the power supply system, which specifically comprises the following steps that the double-pole double-throw switch controller obtains the three-phase voltage V on the main power feeder line in a cable direct connection mode0Obtaining a three-phase current value I on the main power feeder line through a current sensor arranged on the main power feeder line, and obtaining a reference voltage value V of an A-phase loop through an AC/DC module in the double-pole double-throw switch controller1(ii) a By comparing the circuit with a three-phase voltage V0And comparing, and realizing automatic switching of the first double-pole double-throw switch and the second double-pole double-throw switch according to the conditions met by comparison.
Further, the comparison requires a condition to be satisfied:
when the voltage value V on the main power feeder line0When the voltage is smaller than the power generation allowable value, the first double-pole double-throw switch is kept at 1 position;
when the voltage value V of the main power feeder line0And when the voltage is larger than the power generation allowable value, the first double-pole double-throw switch is switched to be at 2 bits.
The invention has the beneficial effects that: by adopting the technical scheme, the system changes the architecture of the existing direct-current starting power generation system, and the double-pole double-throw switch is added in the generator and the controller of the direct-current starting power generation system, so that the multiplexing of the main power feeder line in the starting and power generation stages is realized. The control loop of the double-pole double-throw switch is added in the motor shell, the automatic switching of the double-pole double-throw switch is realized, the multiplexing of the main power feeder is realized by adopting a control strategy according to the framework, the power density of a starting power generation system is improved, the consumption of the main power feeder cable is reduced by 40%, and the purpose of reducing the weight of an airplane can be achieved.
Drawings
Fig. 1 is a schematic diagram of a connection structure of a dc start power generation system in an existing aircraft.
Fig. 2 is a schematic structural diagram of a dc start power generation system in the prior art.
Fig. 3 is a schematic diagram of a connection structure of a dc starting power generation system in the technical solution of the present invention.
Fig. 4 is a schematic structural diagram of a power supply system of the dc start power generation system in the technical solution of the present invention.
Fig. 5 is a schematic structural diagram of another embodiment of the power supply system of the present invention.
Fig. 6 is an electrical schematic diagram of the controller of the double pole double throw switch of the present invention.
In the figure: 5. the starting control device comprises an engine, 10 a three-phase alternating current starting generator shell, 110 a three-phase alternating current starting generator, 111 a three-phase bridge rectifier built in the three-phase alternating current starting generator, 215 a direct current load, 30 a starting controller shell, 31 a starting controller, 32 a direct current starting power supply, 50 a main power feeder through which current flows in a power generation stage, 51 a main power feeder through which current flows in the starting stage, 40 a power generation control contactor, 41 a starting controller, 43 a first double-pole double-throw switch, 44 a second double-pole double-throw switch, 60 a main power feeder and 70 a double-pole double-throw switch controller.
Detailed Description
The technical scheme of the invention is further explained by combining the attached drawings.
As shown in fig. 3-4, the power supply system for reducing the main power feeder of the direct current start power generation of the aircraft of the invention comprises a start controller, a three-phase bridge rectifier, a direct current load and a three-phase alternating current start generator, wherein the system is provided with a first double-pole double-throw switch and a start controller at one end of the start controller, and a second double-pole double-throw switch at one end of the three-phase alternating current start generator, the first double-pole double-throw switch and the start controller are connected with the second double-pole double-throw switch and the three-phase alternating current start generator through 3 main power feeders, and the multiplexing of the main power feeders in the start and power generation stages is realized by controlling the first double-pole double-throw switch, a control contactor and the second double-pole double-throw switch, so as to reduce.
The system has the specific structure that one end of the starting controller is connected with a direct-current starting power supply, the other end of the starting controller is respectively connected with the 2 nd contact of the first double-pole double-throw switch and one end of the starting controller, the direct-current load is connected with the 1 st contact of the first double-pole double-throw switch, wherein one end of each of the 2 main power feeders is connected with one end of the first double-pole double-throw switch, the other end of each main power feeder is connected with one end of the second double-pole double-throw switch, one end of the other main power feeder is connected with the other end of the starting controller, the other end of the other main power feeder is connected with the three-phase alternating-current starting generator, the three-phase AC starting generator is connected with the 2 nd contact of the second double-pole double-throw switch, the three-phase bridge rectifier is connected with the 1 st contact of the second double-pole double-throw switch, and the three-phase bridge rectifier is connected with the three-phase AC starting generator.
A control method of the power supply system for reducing the main power feeder of the airplane direct current starting power generation specifically comprises the following steps:
when starting, the starting controller inverts the direct current energy input by the direct current starting power supply into three-phase alternating current electric energy, and the three-phase alternating current generator generates torque to drive the engine to rotate to a starting rotating speed by switching the first double-pole double-throw switch and closing the starting controller;
during power generation, the three-phase alternating-current generator generates three-phase alternating current, the first double-pole double-throw switch and the second double-pole double-throw switch are switched, and the starting controller is switched off at the same time, so that the three-phase alternating current is rectified into direct-current electric energy through the three-phase rectifying bridge circuit and is transmitted to the direct-current load end through the main power feeder.
When the starting is carried out, the direct-current electric energy output by the direct-current starting power supply is transmitted to a starting controller in a shell of the starting controller, the starting controller inverts the direct-current electric energy into three-phase alternating-current electric energy, a contact of a first double-pole double-throw switch is dialed to a 2 nd contact, a contact of a second double-pole double-throw switch is dialed to the 2 nd contact, meanwhile, the starting controller is closed, so that three-phase alternating-current electric energy output by the starting controller enters a three-phase alternating-current starting generator in the shell of the three-phase alternating-current starting generator through three main power feeders, and the three-phase alternating-current generator generates torque to drive an engine to rotate;
during power generation, the three-phase alternating-current generator generates three-phase alternating-current electric energy, the contacts of the first double-pole double-throw switch are respectively shifted to the 1 st contact, the contacts of the second double-pole double-throw switch are shifted to the 1 st contact, the starting controller is turned off at the same time, the three-phase alternating-current electric energy is controlled to be input into a three-phase rectification bridge circuit in a shell of the three-phase alternating-current starting generator, the three-phase rectification bridge circuit rectifies the three-phase alternating current into direct-current electric energy, and the direct-current electric energy enters a direct-current load end through.
As shown in fig. 5 to 6, the system further includes a double-pole double-throw switch controller and a current sensor, the current sensor is disposed on the main power feeder and connected to the double-pole double-throw switch controller, and the double-pole double-throw switch controller is respectively connected to the first double-pole double-throw switch, the start controller and the second double-pole double-throw switch.
The double-pole double-throw switch controller comprises an AC/DC module, a resistor R1, a resistor R2, a resistor R3, a resistor R4, a resistor R5, a resistor R6, a resistor R7, a resistor R8, a resistor R9, a resistor R10, a resistor R11, a resistor R12, a resistor R13, a resistor R14, a resistor R15, a resistor R16, a resistor R17, a resistor R18, a resistor R19, a resistor R20, a resistor R21, a resistor R22, a diode D1, a diode D2, a diode D3, a diode D4, a diode D5, a diode D6, a diode D7, a diode D8, a diode D9, a capacitor C1, a capacitor C2, an operational amplifier V1, an operational amplifier V2, an operational amplifier V3 and a signal controller;
one end of the resistor R4 and one end of the diode D1 both receive an A-phase voltage signal, the other end of the R4 is connected with one end of the D4, and the other end of the D1 is connected with one end of the resistor R1; one end of the resistor R5 and one end of the diode D2 both receive a B-phase voltage signal, the other end of the resistor R5 is connected with one end of the diode D5, and the other end of the diode D2 is connected with one end of the resistor R2; one end of each of the R6 and D3 receives a C-phase voltage signal, the other end of the resistor R6 is connected to one end of a diode D6, the other end of the D3 is connected to one end of the resistor R2, the other ends of the diode D4, the diode D5 and the diode D6 are connected to the negative input of an operational amplifier V1, the other ends of the resistor R1, the resistor R2 and the resistor R3 are connected to one end of the resistor R12, one ends of the capacitor C1 and the resistor R7 are connected to one end of the resistor R12, the other ends of the capacitor C1 and the resistor R7 are grounded, the other end of the resistor R12 is connected to one end of the resistor R13, the other end of the resistor R13 is connected to the positive input of the operational amplifier V2, one end of the resistor R19 is connected to the positive input of the operational amplifier V2, and the other end is connected to ground;
one end of the resistor R14 is connected to one end of the resistor R13, the other end of the resistor R14 is connected to the output of the operational amplifier V1 and one end of the resistor R16, the other end of the resistor R16 is connected to the positive input of the operational amplifier V1 and one end of the resistor R17, and the other end of the resistor R17 is grounded;
one ends of the resistors R7 and D7 receive a phase-a current signals, the other end of the resistor R7 is grounded, one ends of the resistor R8 and the diode D8 receive B phase-B current signals, the other end of the resistor R8 is grounded, one ends of the resistor R9 and the diode D9 receive C phase-C current signals, the other end of the resistor R9 is grounded, the other ends of the diode D7, the diode D8 and the diode D9 are all connected with one end of the resistor R11, the other end of the resistor R11 is connected with one end of the resistor R20, the other end of the resistor R20 is connected with the negative input of the operational amplifier V3, one ends of the capacitor C2 and the resistor R18 are both connected with one end of the resistor R20, and the other ends of the capacitor C2 and the resistor R18 are grounded, respectively;
the output of the operational amplifier V3 is connected to one end of the resistor R21, the other end of the resistor R21 is connected to the negative input of the operational amplifier V2, the output of the operational amplifier V2 is connected to one end of the resistor R22, and the other end of the resistor R22 is connected to the signal controller.
The automatic power supply control method adopting the power supply system specifically comprises the following steps that the double-pole double-throw switch controller obtains the three-phase voltage V on the main power feeder line in a cable direct connection mode0The main power is obtained by a current sensor arranged on the main power feederObtaining a reference voltage value V of an A-phase loop through an AC/DC module inside the double-pole double-throw switch controller according to a three-phase current value I on a feeder line1(ii) a By comparing the circuit with a three-phase voltage V0And comparing, and realizing automatic switching of the first double-pole double-throw switch and the second double-pole double-throw switch according to the conditions met by comparison.
The comparison needs to satisfy the conditions:
when the voltage value V on the main power feeder line0When the voltage is smaller than the power generation allowable value, the first double-pole double-throw switch is kept at 1 position;
when the voltage value of the main power feeder is larger than a power generation allowable value (the power generation allowable value is a voltage value which can enable the three-phase alternating-current generator to generate torque to drive the engine to rotate to a starting rotating speed), the first double-pole double-throw switch is switched to be at 2 bits.
While one embodiment of the present invention has been described in detail, the description is only a preferred embodiment of the present invention and should not be taken as limiting the scope of the invention. All equivalent changes and modifications made within the scope of the present invention shall fall within the scope of the present invention.
Claims (7)
1. A power supply system for reducing main power feeders of airplane direct current starting power generation is disclosed, the system comprises a starting controller, a three-phase bridge rectifier, a direct current load and a three-phase alternating current starting generator, and is characterized in that a first double-pole double-throw switch is arranged on one side of the starting controller, a second double-pole double-throw switch is arranged on one side of the three-phase alternating current starting generator, the first double-pole double-throw switch and the starting controller are connected with the second double-pole double-throw switch and the three-phase alternating current starting generator through 3 main power feeders, and the multiplexing of the main power feeders in the starting and power generation stages is realized by controlling the first double-pole double-throw switch, a control contactor and the second double-pole double-throw switch, so that the number of the main power feeders;
one end of the starting controller is connected with a direct-current starting power supply, the other end of the starting controller is respectively connected with the 2 nd contact of the first double-pole double-throw switch and one end of the control contactor, the direct-current load is connected with the 1 st contact of the first double-pole double-throw switch, wherein one end of each of 2 main power feeders is connected with one end of the first double-pole double-throw switch, the other end of each main power feeder is connected with one end of the second double-pole double-throw switch, one end of the other main power feeder is connected with the other end of the starting controller through a control contactor, the other end of the other main power feeder is connected with the three-phase alternating-current starting generator, the three-phase AC starting generator is connected with the 2 nd contact of the second double-pole double-throw switch, the three-phase bridge rectifier is connected with the 1 st contact of the second double-pole double-throw switch, and the three-phase bridge rectifier is connected with the three-phase AC starting generator.
2. The power supply system of claim 1, further comprising a double pole double throw switch controller and a current sensor, said current sensor being disposed on said main power feed line and connected to said double pole double throw switch controller, said double pole double throw switch controller being in control connection with a first double pole double throw switch, a start controller and a second double pole double throw switch, respectively.
3. The power supply system of claim 2, wherein the double-pole double-throw switch controller comprises an AC/DC module, a resistor R1, a resistor R2, a resistor R3, a resistor R4, a resistor R5, a resistor R6, a resistor R7, a resistor R8, a resistor R9, a resistor R10, a resistor R11, a resistor R12, a resistor R13, a resistor R14, a resistor R15, a resistor R16, a resistor R17, a resistor R18, a resistor R19, a resistor R20, a resistor R21, a resistor R22, a diode D1, a diode D2, a diode D3, a diode D4, a diode D5, a diode D6, a capacitor C6, an operational amplifier V6 and a signal controller;
one end of the resistor R4 and one end of the diode D1 both receive an A-phase voltage signal, the other end of the R4 is connected with one end of the diode D4, and the other end of the diode D1 is connected with one end of the resistor R1; one end of the resistor R5 and one end of the diode D2 both receive a B-phase voltage signal, the other end of the resistor R5 is connected with one end of the diode D5, and the other end of the diode D2 is connected with one end of the resistor R2; one end of the resistor R6 and one end of the diode D3 both receive a C-phase voltage signal, the other end of the resistor R6 is connected with one end of the diode D6, the other end of the resistor D3 is connected with one end of the resistor R3, the other ends of the diode D4, the diode D5 and the diode D6 are connected with the negative input of the operational amplifier V1, the other ends of the resistor R1, the resistor R2 and the resistor R3 are connected with one end of the resistor R12, one ends of the capacitor C1 and the resistor R7 are connected with one end of the resistor R12, the other ends of the capacitor C1 and the resistor R7 are grounded, the other end of the resistor R12 is connected with one end of the resistor R13, the other end of the resistor R13 is connected with the positive input of the operational amplifier V2, one end of the resistor R19 is connected with the positive input of the operational amplifier V2, and the other end is connected with the ground;
the resistor R14 is connected to one end of the resistor R13, the other end of the resistor R14 is connected to the output of the operational amplifier V1 and one end of the resistor R16, the other end of the resistor R16 is connected to the positive input of the operational amplifier V1 and one end of the resistor R17, and the other end of the resistor R17 is grounded;
one end of the resistor R7 and one end of the diode D7 receive a phase current signal of A, the other end of the resistor R7 is grounded, one end of the resistor R8 and one end of the diode D8 receive a phase current signal of B, the other end of the resistor R8 is grounded, one end of the resistor R9 and one end of the diode D9 receive a phase current signal of C, the other end of the resistor R9 is grounded, the other ends of the diode D7, the diode D8 and the diode D9 are connected with one end of the resistor R11, the other end of the resistor R11 is connected with one end of the resistor R20, the other end of the resistor R20 is connected with the negative input of the operational amplifier V3, one ends of the capacitor C2 and the resistor R18 are connected with one end of the resistor R20, and the other ends of the capacitor C2 and the resistor;
the output of the operational amplifier V3 is connected to one end of the resistor R21, the other end of the resistor R21 is connected to the negative input of the operational amplifier V2, the output of the operational amplifier V2 is connected to one end of the resistor R22, and the other end of the resistor R22 is connected to the signal controller.
4. A power supply control method for a power supply system of a main power feed line for reducing aircraft dc start up power generation according to claim 1, the method comprising in particular the steps of:
when starting, the starting controller inverts the direct current input by the direct current starting power supply into three-phase alternating current, simultaneously switches the first double-pole double-throw switch and the second double-pole double-throw switch, and simultaneously closes the control contactor, so that the three-phase alternating current starting generator generates torque to drive the engine to rotate to a starting rotating speed;
during power generation, the three-phase alternating-current starting generator generates three-phase alternating current, the first double-pole double-throw switch and the second double-pole double-throw switch are switched, and the control contactor is switched off, so that the three-phase alternating current is rectified into direct current through the three-phase bridge rectifier and is transmitted to the direct-current load end through the main power feeder.
5. The power supply control method according to claim 4, wherein at the time of starting, the direct current output by the direct current starting power supply is transmitted to the starting controller, the starting controller inverts the direct current into three-phase alternating current, the contact of the first double-pole double-throw switch is pushed to the 2 nd contact, the contact of the second double-pole double-throw switch is pushed to the 2 nd contact, and meanwhile, the control contactor is closed, so that the three-phase alternating current output by the starting controller enters the three-phase alternating current starting generator through three main power feeders.
6. The power supply control method according to claim 4, wherein, during power generation, the three-phase ac starting generator generates three-phase ac power to respectively shift the contact of the first double-pole double-throw switch to the 1 st contact and shift the contact of the second double-pole double-throw switch to the 1 st contact, and simultaneously, the control contactor is opened.
7. An automatic power supply control method using the power supply system according to claim 2, characterized by specifically comprising the following stepsThe method comprises the following steps that the double-pole double-throw switch controller obtains a three-phase voltage V on a main power feeder line in a cable direct connection mode0Obtaining a three-phase current value I on the main power feeder line through a current sensor arranged on the main power feeder line, and obtaining a reference voltage value V of an A-phase loop through an AC/DC module in the double-pole double-throw switch controller1(ii) a By comparing the circuit with a three-phase voltage V0And comparing, and realizing automatic switching of the first double-pole double-throw switch and the second double-pole double-throw switch according to the conditions met by comparison.
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| 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 |
| 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 |
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| 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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| CN108054977B true CN108054977B (en) | 2020-06-02 |
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| 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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| CN108054977A (en) | 2018-05-18 |
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