阅读说明：本技术 单通道多电飞机发电机控制器的联接汇流条差动保护功能结构 (connecting bus bar differential protection function structure of single-channel multi-electric aircraft generator controller ) 是由 万波 于 2018-05-31 设计创作，主要内容包括：本发明公开单通道多电飞机发电机控制器的联接汇流条差动保护功能结构,包含有,第一电流互感器,其用于检测接触器L BTB处的电流大小；第二电流互感器,其用于检测接触器R BTB处的电流大小；以及,第三电流互感器,其用于检测接触器APB处的电流大小；若第一电流互感器、第二电流互感器及第三电流互感器中有一者的电流比其余两者的电流之和大40A以上,则执行联接汇流条TB差动保护动作。本发明的有益效果在于,藉助上述结构,能够防止某一相出现接地故障。(the invention discloses a differential protection function structure of a connecting bus bar of a generator controller of a single-channel multi-electric-aircraft, which comprises a first current transformer, a second current transformer and a third current transformer, wherein the first current transformer is used for detecting the current at the position of a contactor L BTB; the second current transformer is used for detecting the current magnitude at the contactor R BTB; the third current transformer is used for detecting the current magnitude at the APB; if the current of one of the first current transformer, the second current transformer and the third current transformer is larger than the sum of the currents of the other two by more than 40A, the differential protection action of the connecting bus bar TB is executed. The invention has the beneficial effect that the structure can prevent a certain phase from generating ground fault.)

1. The connection Bus bar differential protection function structure of the generator controller of the single-channel multi-electric-aircraft comprises a main generator GEN R, a generator controller R GCU, a main generator GEN L, a generator controller L GCU, an auxiliary generator APU GEN, a generator controller A GCU, a connection Bus bar TB, a Bus bar L235VAC Bus and a Bus bar R235 VAC Bus, wherein the connection Bus bar TB is selectively powered by one of the Bus bar L235VAC Bus, the auxiliary generator APU GEN and the Bus bar R235 VAC Bus, the first end of the main generator GEN L is connected with a circuit breaker L GCB, and the second end of the circuit breaker L GCB is connected with the Bus bar L115 VAC Bus; the GEN R of the main generator is connected with the first end of the circuit breaker R GCB, and the second end of the circuit breaker R GCB is connected with the Bus bar R115 VAC Bus; the first end of the contactor L BTB is connected with a Bus bar L115 VAC Bus, the first end of the breaker APB is connected with an auxiliary generator APU GEN, the first end of the contactor R BTB is connected with a Bus bar R115 VAC Bus, the second end of the contactor L BTB is respectively connected with the second end of the breaker APB and the second end of the contactor R BTB, the utility model is characterized in that the contactor L BTB also comprises,

The first current transformer is used for detecting the current magnitude at the contactor L BTB;

the second current transformer is used for detecting the current magnitude at the contactor R BTB; and the number of the first and second groups,

the third current transformer is used for detecting the current magnitude at the APB;

if the current of one of the first current transformer, the second current transformer and the third current transformer is larger than the sum of the currents of the other two by more than 40A, the differential protection action of the connecting bus bar TB is executed.

2. the differential protection function structure of the connecting bus bar of the single-channel multi-electric-aircraft generator controller according to claim 1, wherein the differential protection action of the connecting bus bar TB comprises,

step S1, disconnect contactor L BTB and contactor R BTB;

in step S2, the generator controller agcu disables VR within 250ms, and disconnects the excitation of the auxiliary generator APU GEN and the circuit breaker APB.

Technical Field

the invention relates to a differential protection function structure of a connecting bus bar of a single-channel multi-electric-plane generator controller.

Background

the Generator Controller Unit (GCU) has two functions, one is to provide excitation regulation for the Generator and the other is to provide protection for the Generator and the main power bus.

in the protection function of a conventional GCU, differential protection is often ignored. Differential protection ensures that the current flowing into the distribution box is equal to the current flowing out of the distribution box to avoid a ground fault in one phase.

disclosure of Invention

The invention aims to solve the technical problem that a certain phase has a ground fault, and provides a novel connecting bus bar differential protection functional structure of a single-channel multi-electric-aircraft generator controller.

In order to achieve the purpose, the technical scheme of the invention is as follows: the connection Bus bar differential protection function structure of the generator controller of the single-channel multi-electric-aircraft comprises a main generator GEN R, a generator controller R GCU, a main generator GENL, a generator controller L GCU, an auxiliary generator APU GEN, a generator controller A GCU, a connection Bus bar TB, a Bus bar L235VAC Bus and a Bus bar R235 VAC Bus, wherein the connection Bus bar TB is selectively powered by one of the Bus bar L235VAC Bus, the auxiliary generator GEAPU and the Bus bar R235 VAC Bus, the first end of the main generator GEN L is connected with a circuit breaker L GCB, and the second end of the circuit breaker L GCB is connected with the Bus bar L115 VAC Bus; the GEN R of the main generator is connected with the first end of the circuit breaker R GCB, and the second end of the circuit breaker R GCB is connected with the Bus bar R115 VAC Bus; the first end of the contactor L BTB is connected with a Bus bar L115 VAC Bus, the first end of the breaker APB is connected with an auxiliary generator APU GEN, the first end of the contactor RBTB is connected with a Bus bar R115 VAC Bus, the second end of the contactor L BTB is respectively connected with the second end of the breaker APB and the second end of the contactor R BTB, the utility model is characterized in that the contactor L BTB also comprises,

The first current transformer is used for detecting the current magnitude at the contactor L BTB;

the second current transformer is used for detecting the current magnitude at the contactor R BTB; and the number of the first and second groups,

The third current transformer is used for detecting the current magnitude at the APB;

If the current of one of the first current transformer, the second current transformer and the third current transformer is larger than the sum of the currents of the other two by more than 40A, the differential protection action of the connecting bus bar TB is executed.

as a preferred scheme of the connecting bus bar differential protection functional structure of the single-channel multi-electric-aircraft generator controller, the connecting bus bar TB differential protection action comprises,

Step S1, disconnect contactor L BTB and contactor R BTB;

In step S2, the generator controller agcu disables VR within 250ms, and disconnects the excitation of the auxiliary generator APU GEN and the circuit breaker APB.

Compared with the prior art, the invention has the beneficial effect that the structure can prevent a certain phase from generating ground fault.

In addition to the technical problems addressed by the present invention, the technical features constituting the technical solutions, and the advantageous effects brought by the technical features of the technical solutions described above, other technical problems solved by the present invention, other technical features included in the technical solutions, and advantageous effects brought 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 power system architecture of a single-channel multi-electric aircraft according to an embodiment of the invention.

FIG. 2 is a schematic diagram of a differential protection information collection point of the connection bus according to an embodiment of the present invention.

Detailed Description

the present invention will be described in further detail below with reference to specific embodiments and drawings. Here, the description of the embodiments is provided to help understanding of the present invention, but the present invention is not limited thereto. In addition, the technical features involved in the embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.

Referring to fig. 1, a differential protection architecture for a connecting bus of a single-channel multi-electric aircraft generator controller is shown. The system comprises a left variable-frequency main starting generator GEN L and a right variable-frequency main starting generator GEN R with the rated power of 225kVA, an APU starting generator with the rated power of 200kVA, and an RAT generator with the rated power of 50 kVA. There are also three external power sources, L FWD EP, R FWD EP and L AFT EP, respectively, the outlets of each of which can support a maximum of 90kVA of power. The rated voltages of the main starter generator, the APU starter generator and the RAT generator are all 235VAC, and the rated voltages of the three external power supplies are 115 VAC.

GEN L, GEN R and APU GEN are provided with respective generator breakers L GCB, R GCB and APB to control the switching of the generators, and in addition, the 3 generators are also provided with corresponding contactors L GNR, R GNR and A GNR to control the connection with a ground network.

The three external power supplies also have corresponding contactors for controlling the access of the power supplies, namely L EPC, R EPC and L AEPC.

The secondary power supply of the power supply system comprises 2 ATRUs with rated power of 150kVA, two ATUs with rated capacity of 60kVA and 4 TRUs with rated output current of 240A. Wherein, the ATRU converts 235VAC into +/-270VDC, and respectively outputs the +/-270VDC to the left and right buses for supplying power to multi-electrical loads (flight control actuation, electrical ring control and the like); the ATU converts 230VAC into 115VAC, and respectively outputs the 115VAC to the left and right 115VAC bus bars; the TRU converts 235VAC into 28VDC, and outputs the 28VDC normal bus bars and the 28VDC emergency bus bars to the left and right.

the power supply system has two batteries with the rated voltage of 28VDC and the capacity of 75Ah, namely a main battery and an APU battery, and the batteries can supply power to key electronic equipment before the aircraft generator is started. Meanwhile, the APU battery can also be used to start the APU.

the main generator GEN L is connected with the first end of the circuit breaker L GCB, and the second end of the circuit breaker L GCB is connected with the Bus bar L235VAC Bus;

the GEN R of the main generator is connected with the first end of the circuit breaker R GCB, and the second end of the circuit breaker R GCB is connected with the Bus bar R235 VAC Bus;

The auxiliary generator APU GEN is connected with the first end of the circuit breaker APB, the Bus bar L235VAC Bus is connected with the first end of the contactor L BTB, the Bus bar R235 VAC Bus is connected with the first end of the contactor R BTB, and the second end of the contactor APB is connected with the second end of the contactor L BTB and the second end of the contactor R BTB respectively;

the Bus bar L235VAC Bus is connected with a first end of a contactor L ATUC, a second end of the contactor L ATUC is connected with an electric energy conversion device L ATU, the electric energy conversion device L ATU is connected with a first end of a contactor L BSB, and a second end of the contactor L BSB is connected with the Bus bar L115 VAC Bus;

The Bus bar R235 VAC Bus is connected with a first end of a contactor R ATUC, a second end of the contactor R ATUC is connected with an electric energy conversion device R ATU, the electric energy conversion device R ATU is connected with a first end of a contactor R BSB, and a second end of the contactor R BSB is connected with the Bus bar R115 VAC Bus;

A ground power supply L FWD EP is connected with a first end of a contactor L EPC, and a second end of the contactor L EPC is connected with a first end of a contactor L BSB;

A ground power supply R FWD EP is connected with a first end of a contactor R EPC, and a second end of the contactor R EPC is connected with a first end of a contactor R BSB;

the Bus bar L235VAC Bus is connected with the first end of the contactor LacT, the second end of the contactor LacT is connected with the first end of the contactor RacT, and the second end of the contactor RacT is connected with the Bus bar R235 VAC Bus;

The second end of the contactor L ATUC is connected with the first end of the contactor L TRU Rly, the second end of the contactor L TRU Rly is connected with the power conversion device TRU L, and the power conversion device TRU L is connected with the Bus bar L28 VDC Bus;

the second end of the contactor R ATUC is connected with the first end of the contactor R TRU Rly, the second end of the contactor R TRU Rly is connected with the power conversion device TRU R, and the power conversion device TRU R is connected with 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 Rly, the second end of the contactor E1 TRU ISO Rly is respectively connected with the first ends of a power conversion device TRU 1 and a contactor E1 TRU Rly, the power conversion device TRU 1 is further connected with the first end of a Bus bar ESS 128 VDC Bus, the second end of the contactor ESS ISO Rly is connected with a Bus bar ESS 235VAC Bus, the Bus bar ESS 235VAC Bus is connected with a power conversion device TRU 2, and the power conversion device TRU E2 is further connected with the Bus bar ESS 228 VDC 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 bar ESS 235VAC Bus;

Bus ESS 128 VDC Bus is connected to the first terminal of contact E1T, the second terminal of contact E1T is connected to the first terminal of contact E2T, and the second terminal of contact E2T is connected to Bus ESS 228 VDC Bus;

Bus ESS 128 VDC Bus is connected to a first terminal of contactor MBR, and a second terminal of contactor MBR is connected to Bus Hot BB 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 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 R235 VAC Bus is connected with the first end of the contactor R ATRUC, the second end of the contactor R ATRUC is connected with the autotransformer rectifier ATRU R, and the autotransformer rectifier ATRU R is connected with the Bus bar R270 VDC Bus;

an external power supply L AFT EP is connected with a first end of a contactor L AEPC, and a second end of the contactor L AEPC is connected with an autotransformer rectifier ATRU L;

Referring to fig. 2, an information collection site for differential protection of a link bus is shown.

Three sets of CTs, a first current transformer, a second current transformer and a third current transformer, respectively, for monitoring and protecting the connecting bus bar are placed in the P100, P200 and P150 distribution cabinets, respectively. The outputs from the three CTs are connected to a resistor, and normally the sum of the output current from one distribution box and the input current from the other two distribution boxes is zero, so that the differential voltage generated across the resistor is 0.

When the current of one acquisition CT is more than 40A larger than the sum of the other two CT currents, the bus bar differential protection (TBDP) is connected to act:

1) the left and right main channels GCU will disconnect the L/R BTB;

2) The agcu will disable VR within 250ms, disconnecting the generator excitation and APB.

The software latency of the L/R GCU may be set to 210ms, i.e., it acts after the differential protection condition persists for 210 ms.

The foregoing merely represents embodiments of the present invention, which are described in some detail and detail, and therefore should not be construed as limiting the scope of the invention. It should be noted that, for a person skilled in the art, several variations and modifications can be made without departing from the inventive concept, which falls within the scope of the present invention. Therefore, the protection scope of the present patent shall be subject to the appended claims.