High-redundancy, multi-transmission-path aircraft ac power distribution system and control method

Abstract

The present application relates to the aviation power distribution system, belongs to the alternating current power distribution system field.Proposed a kind of high redundancy, multiple transmission path aircraft alternating current power distribution system and control method, contactor includes No.1 generator to bus bar A contactor GCB1, No.1 generator to bus bar B contactor GCB2, No.2 generator to bus bar C contactor GCB3, No.2 generator to bus bar D contactor GCB4, conversion contactor BTB1~BTB5 And auxiliary generator contactor APB.In addition, bus bar power controller BPCU sends each control signal by the auxiliary normally closed contact of override switch, when communication signal reports exception, BPCU autonomous report fault or when actual working condition needs, the control signal of override switch can be sent by electrical display control box, to disconnect BPCU control signal, to be converted into manual hard-wire control.The aircraft alternating current power distribution system control logic of the present application is high in safety level, method strategy is stable, important load is long in grid-connected time and short in power transfer time, it is advanced in technology, and it is strong in universality.

Description

Technical Field

[0001] This invention relates to aircraft power distribution systems, specifically to an AC power distribution system and control method. It includes a highly redundant, multi-path aircraft AC power distribution system. Background Technology

[0002] Currently, aircraft AC power distribution systems typically design generators with only one direct power supply busbar, or multiple generators share a central busbar for backup. Furthermore, the logic design of aircraft AC power distribution systems generally categorizes generator states into two types: Normal 1 and Fault 0. When a generator is in Fault 0, the power distribution system first disconnects the contactor of the only busbar connected to the faulty generator, and then supplies power to the disconnected busbar through other generators in Normal 1. This control method causes temporary power outages for all equipment connected to the busbar on the same side as the faulty generator, posing a significant safety hazard for critical equipment. Moreover, current aircraft AC power distribution systems only define power supply priorities, transmitting power to disconnected busbars according to the power supply order, but do not design busbar priority. This means that when the power provided by the entire aircraft AC power distribution network is less than the power demand of all equipment connected to the busbars, overload problems and disconnection of critical loads can easily occur. Current methods for controlling aircraft AC power distribution systems aim to improve the completeness and redundancy of the aircraft power distribution network. These methods either enhance the reliability of the BPCU itself or increase the number of BPCUs in the power distribution network to achieve the system's primary / backup characteristics. However, when system communication problems occur or when special operating conditions of the actual aircraft require it, the safety and rapid response are not high. Summary of the Invention

[0003] Technical solution

[0004] A high-redundancy, multi-transmission-path aircraft AC power distribution system is disclosed. The front end of the architecture comprises a power source with two main AC generators (left generator L_GEN and right generator R_GEN) and an auxiliary power generation unit (APU). The middle section of the architecture consists of contactor and busbar assemblies for the power source. These assemblies include busbars A, B, C, and D; two left generator contactors GCB1 and GCB2; two right generator contactors GCB3 and GCB4; and an auxiliary power generation unit contactor APB. The front end of busbar A is connected to the rear end of the left generator contactor GCB1, and the front end of busbar B is connected to the rear end of the left generator contactor GCB2. The front end of busbar C is connected to the rear end of the right generator contactor GCB3, and the front end of busbar D is connected to the rear end of the right generator contactor GCB4. The rear end of the structure consists of a transfer contactor, a busbar power controller BPCU, an override switch, and an electrical display and control box. The front ends of transfer contactors BTB1 to BTB4 are connected to the rear ends of busbars A to D, and then connected to transfer contactor BTB5. The rear end of auxiliary generator unit contactor APB is connected to BTB5. The control signal line of BPCU is first connected to the control terminal of all contactors through the override switch. The acquisition signal line of BPCU is directly connected to the auxiliary contacts of the contactors and busbars A to D.

[0005] The key feature is that the busbar power controller (BPCU) first controls each contactor in the AC power distribution system through the normally closed contact of the overcurrent switch. The BPCU directly collects the analog signals of busbars A to D and the discrete signals of each contactor, and transmits the data in real time with the electrical display and control box via signal lines. When the electrical display and control box determines that the communication signal is reported abnormally, the BPCU reports a fault autonomously, or the actual working condition requires it, it can manually send the control terminal signal of the overcurrent switch through the electrical display and control box to disconnect the control signal line of the BPCU from the entire AC power distribution system. Then, it controls and protects each contactor through the hard wiring of the electrical display and control box.

[0006] The power distribution system architecture for the two main AC generators is designed with busbars A through D. Each AC generator outputs two channels, each equipped with an independent contactor to control the power transmission of its respective busbar. When a generator fails and cannot output power, the BPCU directly controls the contactor on the same side of the failed generator to disconnect from the grid, and the generator on the opposite side switches power to the disconnected busbar. When generator power decreases, the BPCU collects the generator status in real time and, based on the busbar priority level, prioritizes disconnecting the contactor of the lower priority busbar on the same side, while the higher priority busbar continues to be powered by the generator until the generator power on the same side decreases to an insufficient level to support the normal operation of the connected busbar. This achieves the characteristics of long grid connection time, short power switching time, and rapid fault isolation for critical loads in the aircraft power distribution network.

[0007] A highly redundant, multi-transmission-path aircraft AC power distribution control method includes several forms:

[0008] For Form 1, the control steps for different generator qualities are as follows:

[0009] 1. The BPCU detects that generator L_GEN and right generator R_GEN are operating normally and provides a 28VDC signal to the positive terminals of the coils of the two left generator contactors GCB1 and GCB2, and the two right generator contactors GCB3 and GCB4, causing the contactors to close. At this time, busbars A and B are powered by L_GEN, and busbars C and D are powered by R_GEN.

[0010] 2. When the BPCU detects that the quality of a single main generator has deteriorated to the point that its power is insufficient to supply the full load of the two busbars on the same side, but can only supply the load of one busbar, the air display control box collects the generator status signal at this time and feeds it back to the BPCU through the signal line. The BPCU disconnects the GCB of the channel where the low-priority busbar is located according to the priority level of the busbar on the same side where the generator with deteriorated quality is located. At this time, the generator with deteriorated quality only supplies power to the high-priority busbar on the same side.

[0011] 3. When a single main generator fails and cannot be connected to the grid, the electrical display and control box will feed back the collected generator status signal to the BPCU, and the BPCU will shut down the two GCBs corresponding to the faulty generator;

[0012] 4. When both main generators fail and neither can be connected to the grid, the electrical display and control box will feed back the collected generator status signals to the BPCU. The BPCU will disconnect all GCBs and provide a 28VDC signal to the positive terminal of the APB coil, causing its contactor to close. At this time, the APU auxiliary power generation unit will be connected to the grid.

[0013] Form 2, the control steps after a GCB is decommissioned are as follows:

[0014] 1. When the contactor to be de-energized is GCB1, the BPCU provides a 28VDC signal to the positive terminals of the coils of BTB1 and BTB2 to close the contactor. At this time, busbar A is powered by L_GEN through busbar B.

[0015] 2. When the contactor being deactivated is GCB2, the BPCU does not provide an additional 28VDC signal.

[0016] 3. When the contactor to be de-energized is GCB3 or GCB4, the BPCU provides a 28VDC signal to the positive terminal of the coil of BTB2, BTB3, BTB5 or BTB2, BTB4, BTB5, causing the contactor to close. At this time, busbar C or busbar D is powered by L_GEN through busbar B.

[0017] For Form 3, the control steps after the two GCBs on the same side of the generator are disconnected from the grid are as follows:

[0018] 1. When the contactors to be disconnected are GCB1 and GCB2, the BPCU provides a 28VDC signal to the positive terminals of the coils of BTB1, BTB4, and BTB5 to close the contactors. At this time, busbar A is powered by R_GEN through busbar D.

[0019] 2. When the contactors being de-energized are GCB3 and GCB4, the BPCU provides a 28VDC signal to the positive terminals of the coils of BTB2, BTB3, and BTB5, causing the contactors to close. At this time, busbar C is powered by L_GEN through busbar B.

[0020] Form 4, the control steps after the two GCBs on opposite sides of the generator are disconnected from the grid are as follows:

[0021] 1. When the contactors being de-energized are GCB1 and GCB3, the BPCU provides a 28VDC signal to the positive terminals of the coils of BTB1, BTB2, BTB3, and BTB4 to close the contactors. At this time, busbar A is powered by L_GEN through busbar B, and busbar C is powered by R_GEN through busbar D.

[0022] 2. When the contactors to be de-energized are GCB1 and GCB4, the BPCU provides a 28VDC signal to the positive terminals of the coils of BTB1 and BTB2, causing the contactors to close. At this time, busbar A is powered by L_GEN through busbar B. 3. When the contactors to be de-energized are GCB2 and GCB3, the BPCU provides a 28VDC signal to the positive terminals of the coils of BTB3 and BTB4, causing the contactors to close. At this time, busbar C is powered by R_GEN through busbar D. 4. When the contactors to be de-energized are GCB2 and GCB4, the BPCU does not provide an additional 28VDC signal.

[0023] After the BPCU acquires discrete and analog signals, it transmits them to the controller for logic operations. After 20ms, it sends control signals to the relevant contactors to prevent short-term parallel connection of AC power. In addition, the action response time of each contactor is within 20ms. The entire AC power distribution network needs to control up to 4 contactors at the same time. Therefore, the power distribution architecture completes the power transfer in no more than 100ms.

[0024] Technical effect

[0025] This solution refines generator quality specifications and increases the number of busbars connected to a single generator. Considering both fault (0) and normal (1) states, it also addresses generator power reduction. In response to power fluctuations, an autonomous control strategy deactivates lower-priority busbars while ensuring higher-priority busbars remain connected until generator power drops below the required level for the connected busbars. This extends the connection time for critical loads and improves the safety level of the aircraft's AC power distribution system architecture. Furthermore, the solution defines busbar priorities. In the event of a power distribution network failure, deactivation is performed on busbars on the same side of the faulty generator in ascending order of priority, while connection is performed in descending order of priority across the entire power distribution system. Based on this, a high-redundancy, multi-channel aircraft AC power distribution system control strategy is established, enabling rapid power transfer and preventing short-term parallel connection of AC power sources. This solution connects the BPCU control signal to the relay auxiliary normally closed contact. The relay's operation signal is manually activated, while the BPCU's acquired signal is directly transmitted to the electrical control and display box via the power distribution network. When onboard personnel determine through the electrical control and display box that a communication signal is reported abnormally, the BPCU is autonomously reporting a fault, or the actual operating condition requires it, they can manually send a control signal to the overriding switch via the electrical control and display box to disconnect the BPCU's control signal line from the entire AC power distribution system. Then, the contactors are controlled and protected via the hardwired wiring of the electrical control and display box, greatly improving the safety margin and sophistication of the aircraft's AC power distribution network. This solution combines dynamic generator status monitoring, busbar priority levels, and the combined module of the BPCU and overriding switch in the power distribution network to design a stable and versatile system architecture control method. Attached Figure Description

[0026] Figure 1 It is an aircraft AC power distribution system architecture that includes BPCU control signals;

[0027] Figure 2 It is an aircraft AC power distribution system architecture that includes signals acquired by the BPCU;

[0028] Figure 3 This is a typical control flowchart of an aircraft AC power distribution system. Detailed Implementation

[0029] The present invention will be further described below with reference to embodiments. The following description represents only a portion of the embodiments of the present invention, not all of them. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without inventive effort are within the scope of protection of the present invention.

[0030] Example 1

[0031] The objective of this invention can be achieved through the following technical solutions:

[0032] The aircraft AC power distribution system architecture including BPCU control signals designed in this invention is as follows: Figure 1 As shown, the front end of this architecture is the power source, containing two AC main generators, namely the left generator L_GEN and the right generator R_GEN, and one auxiliary power generation unit (APU). The middle section of the architecture contains the contactor protection device and busbars for the power source. These components include busbars A, B, C, and D, containing two left generator contactors GCB1 and GCB2, two right generator contactors GCB3 and GCB4, and one auxiliary power generation unit contactor APB. The front end of busbar A is connected to the rear end of the left generator contactor GCB1, and the front end of busbar B is connected to... The rear end of the left generator contactor GCB2 is connected, the front end of busbar C is connected to the rear end of the right generator contactor GCB3, and the front end of busbar D is connected to the rear end of the right generator contactor GCB4. The rear end of the structure consists of transfer contactors, BPCU, overriding switches, and an electrical display and control box. The front ends of transfer contactors BTB1 to BTB4 are connected to the rear ends of busbars A to D respectively, and then connected to transfer contactor BTB5. The rear end of the auxiliary generator unit contactor APB is connected to BTB5. The control signal line of the BPCU is first connected to the control terminals of all contactors through the overriding switch. The aircraft AC power distribution system architecture, including the BPCU signal acquisition, is as follows. Figure 2 As shown, the BPCU's acquisition signal line is directly connected to the contactor's auxiliary contacts and busbars A to D.

[0033] First, the BPCU controls each contactor in the AC power distribution system through the normally closed contacts of the overcurrent control switch. The BPCU directly collects the analog signals of busbars A to D and the discrete signals of each contactor, and transmits the data in real time with the electrical display and control box through signal lines. The electrical display and control box determines whether the analog or discrete signals reported by the BPCU are abnormal or, according to the actual working conditions, can manually send the control terminal signal of the overcurrent control switch through the electrical display and control box to disconnect the BPCU's control signal line from the entire AC power distribution system. Then, the contactors are controlled and protected through the hard wiring of the electrical display and control box.

[0034] Then, busbars A through D are prioritized, with loads on busbar A designated as critical loads, loads on busbar C as general loads, loads on busbar D as ordinary loads, and loads on busbar B as backup loads. The priority order of the busbars from highest to lowest is: busbar A, busbar C, busbar D, and busbar B. When a generator at the front end of the power distribution system fails, the BPCU performs grid disconnection control according to the priority order of the busbars on the same side of the failed generator from lowest to highest, and performs grid connection control of the transfer contactors at the back end of the power distribution system according to the priority order of the busbars in the entire power distribution system from highest to lowest.

[0035] Then, with the left generator L_GEN and the right generator R_GEN operating normally, the BPCU provides a 28VDC signal to the positive terminals of the coils of the two left generator contactors GCB1 and GCB2, and the two right generator contactors GCB3 and GCB4, causing the contactors to close. At this time, busbars A and B are powered by L_GEN, and busbars C and D are powered by L_GEN. When the quality of a single main generator degrades to the point that its power is insufficient to supply the full load of the two busbars on the same side, but can only supply the load of one busbar, the electrical display and control box collects the generator status signal at this time and feeds it back to the BPCU through the signal line. The BPCU then adjusts the signal based on the quality degradation. The priority level of the busbar on the same side where the generator is located is determined, and the GCB of the channel where the lower priority busbar is located is disconnected. At this time, the generator with degraded quality only supplies power to the higher priority busbar on the same side. When a single main generator fails and cannot be connected to the grid, the electrical control box feeds back the collected generator status signal to the BPCU, and the BPCU shuts down the two GCBs corresponding to the failed generator. When both main generators fail and cannot be connected to the grid, the electrical control box feeds back the collected generator status signal to the BPCU, the BPCU disconnects all GCBs and provides a 28VDC signal to the positive terminal of the APB coil, causing its contactor to close. At this time, the APU auxiliary power generation unit is connected to the grid. The strategy for decommissioning a GCB in the back-end architecture of the aircraft AC power distribution system is as follows: When the decommissioned contactor is GCB1, the BPCU provides a 28VDC signal to the positive terminals of the coils of BTB1 and BTB2, causing the contactors to close. At this time, bus A is powered by L_GEN through bus B. When the decommissioned contactor is GCB2, the BPCU does not provide an additional 28VDC signal. When the decommissioned contactor is GCB3, the BPCU provides a 28VDC signal to the positive terminals of the coils of BTB2, BTB3, and BTB5, causing the contactors to close. At this time, bus C is powered by L_GEN through bus B. When the decommissioned contactor is GCB4, the BPCU provides a 28VDC signal to the positive terminals of the coils of BTB3, BTB4, and BTB5, causing the contactors to close. At this time, bus D is powered by L_GEN through bus B. The strategy for the aircraft AC power distribution system backend after the deactivation of two GCBs on the same side is as follows: When the deactivated contactors are GCB1 and GCB2, the BPCU provides a 28VDC signal to the positive terminals of the coils of BTB1, BTB4, and BTB5 to close the contactors. At this time, busbar A is powered by R_GEN through busbar D. When the deactivated contactors are GCB3 and GCB4, the BPCU provides a 28VDC signal to the positive terminals of the coils of BTB2, BTB3, and BTB5 to close the contactors. At this time, busbar C is powered by L_GEN through busbar B.The strategy for the aircraft AC power distribution system backend after the deactivation of two GCBs on opposite sides of the generator is as follows: When the deactivated contactors are GCB1 and GCB3, the BPCU provides a 28VDC signal to the positive terminals of the coils of BTB1, BTB2, BTB3, and BTB4, causing the contactors to close. At this time, busbar A is powered by L_GEN through busbar B, and busbar C is powered by R_GEN through busbar D; when the deactivated contactors are GCB1 and GCB4, the BPCU provides 2 An 8VDC signal is sent to the positive terminals of the coils of BTB1 and BTB2 to close their contactors. At this time, busbar A is powered by L_GEN through busbar B. When the contactors to be de-energized are GCB2 and GCB3, the BPCU provides a 28VDC signal to the positive terminals of the coils of BTB3 and BTB4 to close their contactors. At this time, busbar C is powered by R_GEN through busbar D. When the contactors to be de-energized are GCB2 and GCB4, the BPCU does not provide an additional 28VDC signal. The strategy for the aircraft AC power distribution system backend after the decommissioning of the three GCBs is as follows: When the decommissioned contactors are GCB1, GCB2, and GCB3, the BPCU provides a 28VDC signal to the positive terminals of the coils of BTB1, BTB4, and BTB5 to close the contactors. At this time, busbar A is powered by R_GEN through busbar D. When the decommissioned contactors are GCB1, GCB2, and GCB4, the BPCU does not provide an additional 28VDC signal. When the decommissioned contactors are GCB1, GCB3, and GCB4, the BPCU provides a 28VDC signal to the positive terminals of the coils of BTB1 and BTB2 to close the contactors. At this time, busbar A is powered by L_GEN through busbar B. When the decommissioned contactors are GCB2, GCB3, and GCB4, the BPCU does not provide an additional 28VDC signal.

[0036] Finally, after the BPCU acquires the discrete and analog signals, it transmits them to the controller for logic operations. After 20ms, it sends control signals to the relevant contactors to prevent short-term parallel connection of AC power. In addition, the action response time of each contactor is within 20ms. The entire AC power distribution network needs to control up to 4 contactors at the same time. Therefore, the power distribution architecture completes the power transfer in no more than 100ms.

[0037] It will be understood by those skilled in the art that, unless otherwise defined, all terms used herein (including technical and scientific terms) have the same meaning as commonly understood by one of ordinary skill in the art to which this invention pertains. It should also be understood that terms such as those defined in general dictionaries should be understood to have the meaning consistent with their meaning in the context of the prior art, and should not be interpreted in an idealized or overly formal sense unless defined as herein. The specific embodiments described above further illustrate the purpose, technical solutions, and beneficial effects of the present invention. It should be understood that the above descriptions are merely specific embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A high-redundancy, multiple transmission path aircraft AC power distribution system, characterized by: The front end of the architecture is the power supply, which includes two main AC generators, namely the left generator L_GEN and the right generator R_GEN, and one auxiliary power generation unit (APU). The middle section of the architecture contains the contactors and busbar assemblies for the power supply. These assemblies include busbar A, busbar B, busbar C, busbar D, two left generator contactors GCB1 and GCB2, two right generator contactors GCB3 and GCB4, and one auxiliary power generation unit contactor APB. The front end of busbar A is connected to the rear end of the left generator contactor GCB1, and the front end of busbar B is connected to the left generator contactor R_GEN. The rear end of generator contactor GCB2 is connected, the front end of busbar C is connected to the rear end of right generator contactor GCB3, and the front end of busbar D is connected to the rear end of right generator contactor GCB4. The rear end of the structure consists of a transfer contactor, busbar power controller BPCU, overpass switch, and electrical display and control box. The front ends of transfer contactors BTB1~BTB4 are connected to the rear ends of busbars A~D respectively, and then connected to transfer contactor BTB5. The rear end of auxiliary generator unit contactor APB is connected to BTB5. The control signal line of BPCU first passes through the overpass switch... The BPCU is then connected to the control terminals of all contactors. Its signal acquisition line is directly connected to the auxiliary contacts of the contactors and busbars A through D. The BPCU first controls each contactor in the AC power distribution system through the normally closed contacts of the overload switch. The BPCU directly acquires the analog signals from busbars A through D and the discrete signals from each contactor, and transmits the data in real time to the electrical display and control box via signal lines. The electrical display and control box determines whether communication signals are reported abnormally, the BPCU reports a fault autonomously, or if the actual operating conditions require manual intervention. The gas display and control box sends the control terminal signal of the over-control switch to disconnect the control signal line of the BPCU from the entire AC power distribution system. Then, the contactors are controlled and protected through the hard wiring of the electrical display and control box. The power distribution system architecture of the two main AC generators is designed with busbars A to D, where each AC generator outputs two channels, and each channel is equipped with an independent contactor to control the power transmission of its respective busbar. When a generator fails and cannot output power, the BPCU directly controls the contactor on the same side of the faulty generator to disconnect from the grid, and the generator on the opposite side switches the power to the disconnected busbar. When generator power decreases, the BPCU collects the generator status in real time and, based on the bus priority level, prioritizes disconnecting the contactors of the lower priority busbars on the same side. The higher priority busbars continue to be powered by the generator until the generator power on the same side decreases to a level insufficient to support the normal operation of the grid-connected busbars. This achieves the characteristics of long grid connection time, short power transfer time, and rapid fault isolation for important loads in the aircraft power distribution network.

2. A high-redundancy, multi-transmission-path aircraft AC power distribution control method based on the system of claim 1, characterized in that, It includes four forms: Form 1 controls different generator qualities; Form 2 controls one GCB after it is de-registered; Form 3 controls two GCBs on the same side of the generator after they are de-registered; and Form 4 controls two GCBs on opposite sides of the generator after they are de-registered.

3. A high-redundancy, multiple transmission path aircraft AC power distribution control method according to claim 2, wherein, For Form 1, the control steps for different generator qualities are as follows: (1) The BPCU detects that generator L_GEN and right generator R_GEN are in normal operation and provides a 28VDC signal to the positive terminals of the coils of the two left generator contactors GCB1 and GCB2 and the two right generator contactors GCB3 and GCB4, causing the contactors to close. At this time, busbar A and busbar B are powered by L_GEN, and busbar C and busbar D are powered by R_GEN. (2) When the BPCU detects that the quality of a single main generator has deteriorated to the point that its power is insufficient to supply the full load of the two busbars on the same side, but can be used by the load of one busbar, the electrical display and control box detects the generator status signal at this time and feeds it back to the BPCU through the signal line. The BPCU disconnects the GCB of the channel where the low-priority busbar is located according to the priority level of the busbar on the same side where the generator with deteriorated quality is located. At this time, the generator with deteriorated quality only supplies power to the high-priority busbar on the same side. (3) When a single main generator fails and cannot be connected to the grid, the electrical display and control box will feed back the collected generator status signal to the BPCU, and the BPCU will shut down the two GCBs corresponding to the main generator; (4) When both main generators fail and neither can be connected to the grid, the electrical display and control box will feed back the collected generator status signal to the BPCU. The BPCU will disconnect all GCBs and provide a 28VDC signal to the positive terminal of the APB coil, causing its contactor to close. At this time, the APU auxiliary power generation unit is connected to the grid.

4. A high-redundancy, multiple transmission path aircraft AC power distribution control method in accordance with claim 2 characterized by, Form 2, the control steps after a GCB is decommissioned are as follows: (1) When the contactor to be de-energized is GCB1, BPCU provides a 28VDC signal to the positive terminals of the coils of BTB1 and BTB2 to close the contactor. At this time, busbar A is powered by L_GEN through busbar B. (2) When the contactor being deactivated is GCB2, the BPCU does not provide an additional 28VDC signal. (3) When the contactor to be de-energized is GCB3 or GCB4, the BPCU provides a 28VDC signal to the positive terminal of the coil of BTB2, BTB3, BTB5 or BTB2, BTB4, BTB5, so that the contactor is closed. At this time, bus bar C or bus bar D is powered by L_GEN through bus bar B.

5. A high-reliability, multiple transmission path aircraft AC power distribution control method according to claim 2 wherein, For Form 3, the control steps after the two GCBs on the same side of the generator are disconnected from the grid are as follows: (1) When the contactors to be de-energized are GCB1 and GCB2, the BPCU provides a 28VDC signal to the positive terminals of the coils of BTB1, BTB4 and BTB5 to close the contactors. At this time, busbar A is powered by R_GEN through busbar D. (2) When the contactors to be de-energized are GCB3 and GCB4, the BPCU provides a 28VDC signal to the positive terminals of the coils of BTB2, BTB3 and BTB5 to close the contactors. At this time, busbar C is powered by L_GEN through busbar B.

6. A high-redundancy, multiple transmission path aircraft AC power distribution control method according to claim 2 wherein, Form 4, the control steps after the two GCBs on opposite sides of the generator are disconnected from the grid are as follows: (1) When the contactors to be de-energized are GCB1 and GCB3, the BPCU provides a 28VDC signal to the positive terminals of the coils of BTB1, BTB2, BTB3 and BTB4 to close the contactors. At this time, busbar A is powered by L_GEN through busbar B and busbar C is powered by R_GEN through busbar D. (2) When the contactors to be de-energized are GCB1 and GCB4, the BPCU provides a 28VDC signal to the positive terminals of the coils of BTB1 and BTB2 to close the contactors. At this time, busbar A is powered by L_GEN through busbar B. (3) When the contactors to be de-energized are GCB2 and GCB3, the BPCU provides a 28VDC signal to the positive terminals of the coils of BTB3 and BTB4 to close the contactors. At this time, busbar C is powered by R_GEN through busbar D. (4) When the contactors being deactivated are GCB2 and GCB4, the BPCU does not provide an additional 28VDC signal. After the BPCU acquires discrete and analog signals, it transmits them to the controller for logic operations. After 20ms, it sends control signals to the relevant contactors to prevent short-term parallel connection of AC power. In addition, the action response time of each contactor is within 20ms. The entire AC power distribution network needs to control up to 4 contactors at the same time. Therefore, the power distribution architecture completes the power transfer in no more than 100ms.

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