CN110556917B - Continuous undetermined power source protection structure of aircraft generator controller GCU - Google Patents
Continuous undetermined power source protection structure of aircraft generator controller GCU Download PDFInfo
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- CN110556917B CN110556917B CN201810550495.3A CN201810550495A CN110556917B CN 110556917 B CN110556917 B CN 110556917B CN 201810550495 A CN201810550495 A CN 201810550495A CN 110556917 B CN110556917 B CN 110556917B
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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
- H02J9/08—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 requiring starting of a prime-mover
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Abstract
The invention discloses a continuous undetermined power source protection structure of an aircraft generator controller GCU, which comprises a generator controller GCU, wherein the generator controller GCU is used for sensing voltage and current at a generator breaker, and if the reactive power output of a generator is lower than a threshold value, the generator controller GCU executes continuous undetermined power source protection action. The invention has the beneficial effect of preventing unexpected parallel connection of a plurality of generators.
Description
Technical Field
The invention relates to a continuous undetermined power source protection structure of an aircraft generator controller GCU.
Background
The generator controller (Generator Control Unit, GCU) serves two functions, one to provide excitation regulation for the generator and the other to provide protection for the generator and the main power bus.
The traditional aircraft adopts a 115VAC/400Hz power supply system, the output frequency of the aircraft is constant, and a plurality of generators can be operated in parallel to improve the output power of a single generator, for example, in a power supply system of B474, a mode of parallel operation of 4 generators is adopted, as shown in figure 1. The multi-motor aircraft employs variable frequency starter generators (Variable FrequencyStart Generator, VFSG) which are operated independently of each other and are not connected in parallel under normal conditions due to the different output frequencies of the generators.
In a multi-motor aircraft architecture, the occurrence of an unexpected parallel connection of multiple generators is prevented so as to avoid the damage of the generators. For example, an unexpected closing of the connecting bus bar contacts may result in a parallel operation of multiple generators, also known as a continuous parallel power source (Sustained Parallel Source, SPS) condition.
Disclosure of Invention
The invention aims to solve the technical problem of preventing unexpected parallel connection of a plurality of generators and provides a continuous undetermined power source protection structure of a single-channel multi-electric aircraft generator controller GCU.
In order to achieve the purpose, the technical scheme of the invention is as follows: a continuous undetermined power source protection architecture for a single-channel multi-motor aircraft generator controller GCU includes,
the main generator GEN L is connected with a first end of a breaker L GCB, and a second end of the breaker L GCB is connected with a Bus bar L235VAC Bus;
the main generator GEN R is connected with a first end of a breaker R GCB, and a second end of the breaker R GCB is connected with a Bus bar R235VAC Bus;
the auxiliary generator APU GEN is connected with the first end of the breaker APB, the Bus bar L235VAC Bus is connected with the first end of the contactor L BTB, the Bus bar R235VAC Bus is connected with the first end of the contactor R BTB, and the second end of the contactor APB is respectively connected with the second end of the contactor L BTB and the second end of the contactor R BTB;
the main generator GEN L is provided with a generator controller L GCU, wherein the generator controller L GCU is used for sensing voltage and current at the breaker L GCB, and if the reactive power output of the main generator GEN L is lower than a first threshold value, the generator controller L GCU executes continuous undetermined power source protection action;
the main generator GEN R is provided with a generator controller R GCU, the generator controller R GCU is used for sensing voltage and current at the breaker R GCB, and if the reactive power output of the main generator GEN R is lower than a second threshold value, the generator controller R GCU executes continuous undetermined power source protection action;
the auxiliary generator APU GEN has a generator controller AGCU for sensing the voltage and current at the circuit breaker APB, and if the reactive power output of the auxiliary generator APU GEN is below a third threshold, the generator controller AGCU performs a continuous undetermined power source protection action.
As a preferred scheme of the continuous undetermined power source protection structure of the single-channel multi-motor aircraft generator controller GCU, the first threshold value, the second threshold value and the third threshold value are all 0.85.
As a preferred solution of the continuous undetermined power source protection structure of the single-channel multi-motor aircraft generator controller GCU, the Bus bar L235VAC Bus is connected to the first end of the contactor L ATUC, the second end of the contactor L ATUC is connected to the power conversion device L ATU, which is in turn connected to the first end of the contactor L BSB, and the second end of the contactor L BSB is connected to the Bus bar L115 VAC Bus;
the Bus bar R235VAC Bus is connected with the first end of the contactor R ATUC, the second end of the contactor R ATUC is connected with the electric energy conversion device R ATU, the electric energy conversion device R ATU is connected with the first end of the contactor R BSB, and the second end of the contactor R BSB is connected with the Bus bar R115 VAC Bus;
the ground power supply LFWD EP is connected with a first end of the contactor L EPC, and a second end of the contactor L EPC is connected with a first end of the contactor LBSB;
the ground power supply R FWD EP is connected with a first end of the contactor R EPC, and a second end of the contactor R EPC is connected with a first end of the contactor RBSB;
the Bus bar L115 VAC Bus is connected with a first end of a contactor LacT, a second end of the contactor LacT is connected with a first end of a contactor RacT, and a second end of the contactor RacT is connected with the Bus bar R115 VAC Bus;
the second end of the contactor L ATUC is connected to the first end of the contactor L TRU Rly, the second end of the contactor L TRU Rly is connected to the power converter TRU L, which in turn is connected to the Bus bar L28 VDC Bus;
the second end of the contactor R ATUC is connected to the first end of the contactor R TRU Rly, the second end of which is connected to the power conversion means TRU R, which in turn is connected to the Bus bar R28 VDC Bus;
the Bus bar L28 VDC Bus is connected with a first end of a contactor LdcT, a second end of the contactor LdcT is connected with a first end of a contactor RdcT, and a second end of the contactor RdcT is connected with the Bus bar R28 VDC Bus;
the second end of the contactor L ATUC is connected with the first end of the contactor E1 TRU ISO oly, the second end of the contactor E1 TRU ISORly is respectively connected with the power conversion device TRU E1 and the first end of the contactor E1 TRU oly, the power conversion device TRU E1 is connected with the first end of the Bus bar ESS1 28VDC Bus, the second end of the contactor ESS ISO oly is connected with the Bus bar ESS235VAC Bus, the Bus bar ESS235VAC Bus is connected with the power conversion device TRU E2, and the power conversion device TRU E2 is connected with the Bus bar ESS2 28VDC Bus;
the generator GEN RAT is connected with a first end of a contactor RCB, and a second end of the contactor RCB is connected with a bus ESS235 VACBus;
the busbar ESS1 28VDC Bus is connected with the first end of the contactor E1T, the second end of the contactor E1T is connected with the first end of the contactor E2T, and the second end of the contactor E2T is connected with the busbar ESS2 28VDC Bus;
bus ESS1, 28VDC Bus, is connected to a first end of contactor MBR, and a second end of contactor MBR is connected to Bus HotBB 1;
the bus bar Hot BB2 is connected with a first end of a contactor SPUC, a second end of the contactor SPUC is connected with an SPU, the SPU is connected with a first end of a contactor SPUB, and a second end of the contactor SPUB is connected with an autotransformer rectifier ATRU R;
the Bus bar L235VAC Bus is connected with a first end of a contactor L ATRUC, a second end of the contactor L ATRUC is connected with an autotransformer rectifier ATRU L, and the autotransformer rectifier ATRU L is connected with the Bus bar L270 VDC Bus;
the Bus bar R235VAC Bus is connected with a first end of a contactor R ATRUC, a second end of the contactor R ATRUC is connected with an autotransformer rectifier ATRU R, and the autotransformer rectifier ATRU R is connected with the Bus bar R270 VDC Bus;
the external power supply laft EP is connected to a first terminal of a contactor laxpc, and a second terminal of the contactor laxpc is connected to an autotransformer rectifier ATRU L.
As the optimized scheme of the continuous undetermined power source protection structure of the single-channel multi-motor aircraft generator controller GCU, the main generator GEN L and the main generator GEN R are variable-frequency generators with rated power of 225kVA and rated voltage of 235 VAC; the auxiliary generator APU GEN is a variable-frequency generator with rated power of 200kVA and rated voltage of 235 VAC; the generator GEN RAT is a variable-frequency generator with rated power of 50kVA and rated voltage of 235 VAC; the rated voltage of the ground power supply LFWD EP, the ground power supply R FWD EP and the third external power supply LAFT EP is 115VAC; the rated power of the autotransformer rectifier ATU L and the autotransformer rectifier ATU R are 150kVA, the rated capacities of the electric energy conversion device L ATU and the electric energy conversion device R ATU are 60kVA, and the rated output currents of the power conversion device TRU L, the power conversion device TRU R, the power conversion device TRU 1 and the power conversion device TRU E2 are 240A; the storage battery Main BAT and the storage battery APU BAT are both storage batteries with rated voltage of 28VDC and capacity of 75 Ah.
Compared with the prior art, the invention has the beneficial effects that:
1. preventing unintended multiple generators from being connected in parallel.
2. 235VAC bus bars were introduced to replace 115VAC bus bars of conventional aircraft, with increased power levels.
3. A 270VDC voltage level was introduced for regulating the speed of large motors (air conditioning compressors, etc.).
4. The number of external power supply sockets is changed from 1 socket of a traditional airplane to 2 sockets, and meanwhile, the voltage level and the capacity of an emergency power supply RAT are increased, and the original 115VAC 30kVA is changed into 235VAC 50kVA.
In addition to the technical problems, features constituting the technical solutions and advantageous effects caused by the technical features of the technical solutions described above, other technical problems that the present invention can solve, other technical features included in the technical solutions and advantageous effects caused by the technical features will be described in further detail with reference to the accompanying drawings.
Drawings
Fig. 1 is a schematic diagram of a prior art structure.
Fig. 2 is a schematic structural view of an embodiment of the present invention.
Fig. 3 is a schematic diagram of a continuous undetermined power source protection information collection point according to an embodiment of the present invention.
FIG. 4 is a control logic diagram of a power generation controller in an embodiment of the invention.
Description of the embodiments
The invention will be described in further detail below with reference to the drawings by means of specific embodiments. The description of these embodiments is provided to assist understanding of the present invention, but is not to be construed as limiting the present invention. In addition, the technical features of the embodiments of the present invention described below may be combined with each other as long as they do not collide with each other.
The embodiment relates to a novel continuous undetermined power source protection structure of a single-channel multi-motor aircraft generator controller GCU. The power control system comprises left and right 2 variable-frequency main starting generators GEN L and GEN R with rated power of 225kVA, an APU starting generator with rated power of 200kVA and a RAT generator with rated power of 50kVA. There are also three external power sources, L FWD EP, R FWD EP and L AFT EP, respectively, each of which sockets can support a maximum of 90kVA of power. The main starter generator, the APU starter generator and the RAT generator are all rated at 235VAC, and the three external sources are rated at 115VAC. The GEN L, GEN R, and APU GEN each have respective generator breakers LGCB, rgcb, and APB to control switching of the generators, and the 3 generators have corresponding contactors lgnr, RGNR, and agnr to control connection to the ground network. The three external power sources also have corresponding contactor control power accesses, namely L EPC, R EPC and L AEPC.
The secondary power supply of the power supply system includes 2 ATRUs rated at 150kVA, two ATUs rated at 60kVA, and 4 TRUs rated at 240A. Wherein the ATRU converts 235VAC into +/-270VDC, and outputs the +/-270VDC to left and right paths of +/-270VDC bus bars respectively for supplying power to multiple electric loads (fly control action, electric loop control and the like); the ATU converts 230VAC into 115VAC and outputs the 115VAC to left and right paths of 115VAC bus bars respectively; the TRU converts 235VAC to 28VDC and outputs to left and right 28VDC normal bus bars and left and right 28VDC emergency bus bars, respectively.
The power supply system has two batteries, a main battery and an APU battery, rated at 28VDC and having a capacity of 75Ah, which can power critical electronics before the aircraft generator is started. At the same time, the APU battery can also be used to start the APU.
Referring to FIG. 2, the main generator GEN L is connected to a first end of a circuit breaker L GCB, and a second end of the circuit breaker L GCB is connected to a Bus bar L235VAC Bus.
The main generator GEN R is connected to a first end of the circuit breaker R GCB, and a second end of the circuit breaker R GCB is connected to the Bus bar R235VAC Bus.
The auxiliary generator APU GEN is connected with the first end of the breaker APB, the Bus bar L235VAC Bus is connected with the first end of the contactor LBTB, the Bus bar R235VAC Bus is connected with the first end of the contactor R BTB, and the second end of the contactor APB is respectively connected with the second end of the contactor L BTB and the second end of the contactor R BTB.
The main generator GEN L has a generator controller L GCU for sensing the voltage current at the circuit breaker LGCB (as shown in fig. 3).
The main generator GEN R has a generator controller R GCU for sensing the voltage current at the circuit breaker RGCB (as shown in fig. 3).
The auxiliary generator APU GEN has a generator controller agcu for sensing the voltage current at the circuit breaker APB (as shown in fig. 3).
The Bus bar L235VAC Bus is connected to a first end of the contactor L ATUC, a second end of the contactor L ATUC is connected to the power conversion device L ATU, which is in turn connected to a first end of the contactor L BSB, and a second end of the contactor L BSB is connected to the Bus bar L115 VAC Bus.
The Bus bar R235VAC Bus is connected to a first end of the contactor R ATUC, a second end of the contactor R ATUC is connected to the power conversion device R ATU, which is in turn connected to a first end of the contactor R BSB, and a second end of the contactor R BSB is connected to the Bus bar R115 VAC Bus.
The ground power supply L FWD EP is connected to a first end of the contactor L EPC, and a second end of the contactor L EPC is connected to a first end of the contactor L BSB.
The ground power supply R FWD EP is connected to a first terminal of the contactor R EPC, and a second terminal of the contactor R EPC is connected to a first terminal of the contactor R BSB.
The Bus bar L115 VAC Bus is connected with a first end of a contactor LacT, a second end of the contactor LacT is connected with a first end of a contactor RacT, and a second end of the contactor RacT is connected with the Bus bar R115 VAC Bus.
The second end of the contactor L ATUC is connected to the first end of the contactor L TRU Rly, which is connected to the power converter TRU L, which in turn is connected to the Bus bar L28 VDC Bus.
The second end of the contactor R gluc is connected to the first end of the contactor R TRU Rly, the second end of the contactor R TRU Rly is connected to the power conversion device TRU R, which in turn is connected to the Bus bar R28 VDC Bus.
The Bus bar L28 VDC Bus is connected to a first end of the contactor LdcT, a second end of the contactor LdcT is connected to a first end of the contactor RdcT, and a second end of the contactor RdcT is connected to the Bus bar R28 VDC Bus.
The second end of the contactor L ATUC is connected to the first end of the contactor E1 TRU ISO oly, the second end of the contactor E1 TRU ISO oly is connected to the power conversion device TRU E1 and the first end of the contactor E1 TRU oly, the power conversion device TRU E1 is connected to the first end of the Bus bar ESS1 28VDC Bus, the second end of the contactor ESS ISO oly is connected to the Bus bar ESS235VAC Bus, the Bus bar ESS235VAC Bus is connected to the power conversion device TRU E2, and the power conversion device TRU E2 is connected to the Bus bar ESS2 28VDC Bus.
The generator GEN RAT is connected to a first end of the contactor RCB and a second end of the contactor RCB is connected to the Bus ESS235VAC Bus.
The Bus bar ESS1 28VDC Bus is connected to the first end of the contactor E1T, the second end of the contactor E1T is connected to the first end of the contactor E2T, and the second end of the contactor E2T is connected to the Bus bar ESS2 28VDC Bus.
Bus ESS1, 28VDC Bus, is connected to a first terminal of contactor MBR, and a second terminal of contactor MBR is connected to Bus Hot BB 1.
Bus bar Hot BB2 is connected to a first terminal of contactor SPUC, a second terminal of contactor SPUC is connected to SPU, SPU is connected to a first terminal of contactor SPUB, and a second terminal of contactor SPUB is connected to autotransformer rectifier ATRU R.
The Bus bar L235VAC Bus is connected to a first end of the contactor L ATRUC, a second end of which is connected to an autotransformer rectifier ATRU L, which in turn is connected to the Bus bar L270 VDC Bus.
Bus bar R235VAC Bus is connected to a first end of contactor R ATRUC, a second end of contactor R ATRUC is connected to autotransformer rectifier ATRU R, which in turn is connected to Bus bar R270 VDC Bus.
The external power supply laft EP is connected to a first terminal of a contactor laxpc, and a second terminal of the contactor laxpc is connected to an autotransformer rectifier ATRU L.
In a multi-motor aircraft architecture, the occurrence of an unexpected parallel connection of multiple generators is prevented so as to avoid the damage of the generators. For example, an unexpected closing of the connecting bus bar contacts may result in a parallel operation of multiple generators, also known as a continuous parallel power source (Sustained Parallel Source, SPS) condition.
Unexpected parallel connection conditions may cause a lot of damage, such as beat frequency, where one of the two parallel generators is used as a load of the other, and the two parallel generators are operated in an operation mode of the motor to continuously consume power instead of output power, thereby causing damage to the generators.
The sustained undetermined power source protection (Sustained Unexpected Source Protection, SUSP) is typically determined by detecting the reactive output of the generator, which normally has an upper limit, and upon occurrence of a SUSP condition, a generator will draw excess reactive power, and the GCU can determine whether a SUSP condition has occurred by detecting whether the reactive power output of the generator exceeds a threshold.
The power factor of a normal generator is 0.85 hysteresis, which results in a decrease in power factor when the reactive power output increases. When the power factor drops below 0.8, it is considered that a continuously undetermined power source is present, i.e. the SPS condition is met, the GCU will implement protection after a delay of 2 s.
The protection control logic for the continuously undeniated power source is shown in fig. 4.
The foregoing has outlined rather broadly the more detailed description of the invention in order that the detailed description thereof that follows may be better understood, and in order that the present invention may be better understood. It should be noted that it will be apparent to those skilled in the art that several variations and modifications can be made without departing from the spirit of the invention, which are all within the scope of the invention. Accordingly, the scope of protection of the present invention is to be determined by the appended claims.
Claims (3)
1. A continuous undetermined power source protection architecture for an aircraft generator controller GCU, comprising,
the main generator GEN L is connected with a first end of a breaker L GCB, and a second end of the breaker L GCB is connected with a Bus bar L235VAC Bus;
the main generator GEN R is connected with a first end of a breaker R GCB, and a second end of the breaker R GCB is connected with a Bus bar R235VAC Bus;
the auxiliary generator APU GEN is connected with the first end of the breaker APB, the Bus bar L235VAC Bus is connected with the first end of the contactor L BTB, the Bus bar R235VAC Bus is connected with the first end of the contactor R BTB, and the second end of the contactor APB is respectively connected with the second end of the contactor L BTB and the second end of the contactor R BTB;
the main generator GEN L is provided with a generator controller L GCU, wherein the generator controller L GCU is used for sensing voltage and current at the breaker L GCB, and if the reactive power output of the main generator GEN L is lower than a first threshold value, the generator controller L GCU executes continuous undetermined power source protection action;
the main generator GEN R is provided with a generator controller R GCU, the generator controller R GCU is used for sensing voltage and current at the breaker R GCB, and if the reactive power output of the main generator GEN R is lower than a second threshold value, the generator controller R GCU executes continuous undetermined power source protection action;
the auxiliary generator APU GEN has a generator controller AGCU for sensing the voltage and current at the circuit breaker APB, and if the reactive power output of the auxiliary generator APU GEN is below a third threshold, the generator controller AGCU performs a continuous undetermined power source protection action;
the Bus bar L235VAC Bus is connected with the first end of the contactor L ATUC, the second end of the contactor L ATUC is connected with the electric energy conversion device L ATU, the electric energy conversion device L ATU is connected with the first end of the contactor L BSB, and the second end of the contactor L BSB is connected with the Bus bar L115 VAC Bus;
the Bus bar R235VAC Bus is connected with the first end of the contactor R ATUC, the second end of the contactor R ATUC is connected with the electric energy conversion device R ATU, the electric energy conversion device R ATU is connected with the first end of the contactor R BSB, and the second end of the contactor R BSB is connected with the Bus bar R115 VAC Bus;
the ground power supply LFWD EP is connected with a first end of the contactor L EPC, and a second end of the contactor L EPC is connected with a first end of the contactor LBSB;
the ground power supply R FWD EP is connected with a first end of the contactor R EPC, and a second end of the contactor R EPC is connected with a first end of the contactor RBSB;
the Bus bar L115 VAC Bus is connected with a first end of a contactor LacT, a second end of the contactor LacT is connected with a first end of a contactor RacT, and a second end of the contactor RacT is connected with the Bus bar R115 VAC Bus;
the second end of the contactor L ATUC is connected to the first end of the contactor L TRU Rly, the second end of the contactor L TRU Rly is connected to the power converter TRU L, which in turn is connected to the Bus bar L28 VDC Bus;
the second end of the contactor R ATUC is connected to the first end of the contactor R TRU Rly, the second end of which is connected to the power conversion means TRU R, which in turn is connected to the Bus bar R28 VDC Bus;
the Bus bar L28 VDC Bus is connected with a first end of a contactor LdcT, a second end of the contactor LdcT is connected with a first end of a contactor RdcT, and a second end of the contactor RdcT is connected with the Bus bar R28 VDC Bus;
the second end of the contactor L ATUC is connected with the first end of the contactor E1 TRU ISO oly, the second end of the contactor E1 TRU ISORly is respectively connected with the power conversion device TRU E1 and the first end of the contactor E1 TRU oly, the power conversion device TRU E1 is connected with the first end of the Bus bar ESS1 28VDC Bus, the second end of the contactor ESS ISO oly is connected with the Bus bar ESS235VAC Bus, the Bus bar ESS235VAC Bus is connected with the power conversion device TRU E2, and the power conversion device TRU E2 is connected with the Bus bar ESS2 28VDC Bus;
the generator GEN RAT is connected with a first end of a contactor RCB, and a second end of the contactor RCB is connected with a bus ESS235 VACBus;
the busbar ESS1 28VDC Bus is connected with the first end of the contactor E1T, the second end of the contactor E1T is connected with the first end of the contactor E2T, and the second end of the contactor E2T is connected with the busbar ESS2 28VDC Bus;
bus ESS1, 28VDC Bus, is connected to a first end of contactor MBR, and a second end of contactor MBR is connected to Bus HotBB 1;
the bus bar Hot BB2 is connected with a first end of a contactor SPUC, a second end of the contactor SPUC is connected with an SPU, the SPU is connected with a first end of a contactor SPUB, and a second end of the contactor SPUB is connected with an autotransformer rectifier ATRU R;
the Bus bar L235VAC Bus is connected with a first end of a contactor L ATRUC, a second end of the contactor L ATRUC is connected with an autotransformer rectifier ATRU L, and the autotransformer rectifier ATRU L is connected with the Bus bar L270 VDC Bus;
the Bus bar R235VAC Bus is connected with a first end of a contactor R ATRUC, a second end of the contactor R ATRUC is connected with an autotransformer rectifier ATRU R, and the autotransformer rectifier ATRU R is connected with the Bus bar R270 VDC Bus;
the external power supply laft EP is connected to a first terminal of a contactor laxpc, and a second terminal of the contactor laxpc is connected to an autotransformer rectifier ATRU L.
2. The continuous undetermined power source protection architecture for an aircraft generator controller GCU according to claim 1, wherein the first, second, and third thresholds are all 0.85.
3. The structure of claim 1, wherein the main generator GEN L and the main generator GEN R are variable frequency generators rated at 225kVA and rated at 235 VAC; the auxiliary generator APU GEN is a variable-frequency generator with rated power of 200kVA and rated voltage of 235 VAC; the generator GEN RAT is a variable-frequency generator with rated power of 50kVA and rated voltage of 235 VAC; the rated voltage of the ground power supply LFWD EP, the ground power supply R FWD EP and the third external power supply L AFT EP is 115VAC; the rated power of the autotransformer rectifier ATU L and the autotransformer rectifier ATU R are 150kVA, the rated capacities of the electric energy conversion device L ATU and the electric energy conversion device R ATU are 60kVA, and the rated output currents of the power conversion device TRU L, the power conversion device TRU R, the power conversion device TRU 1 and the power conversion device TRU E2 are 240A; the storage battery Main BAT and the storage battery APUBAT are both storage batteries with rated voltage of 28VDC and capacity of 75 Ah.
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