High-voltage power distribution system based on hot backup power supply and aircraft

Abstract

The invention relates to a high-voltage power distribution system based on hot backup power supply and an aircraft. The high-voltage power distribution system comprises a surge protection branch, a load and at least two electric energy distribution branches, each electric energy distribution branch is configured to be connected with different power supply devices and distribute electric energy received from the power supply devices to corresponding loads; the load comprises a power propulsion mechanism; the power propulsion mechanism is connected with each electric energy distribution branch through the surge protection branch; the electric energy distribution branch comprises a first bus and a first isolation switch connected with the first bus, the first bus is configured to receive electric energy from power supply equipment, and the first isolation switch is connected between the first bus and the surge protection branch. According to the scheme provided by the invention, hot backup power supply can be ensured, and high-voltage power distribution stability and reliability can be met.

Description

Technical Field

[0001] The present application relates to the technical field of high-voltage power distribution, and in particular to a high-voltage power distribution system and an aircraft based on hot backup power supply. Background Art

[0002] When the aircraft is in operation, if a short circuit occurs in the propulsion system, a fast isolating switch is required to quickly isolate the short circuit point. If the disconnection speed of the fast isolating switch is too fast, then when there is a large difference between the fast isolating switches for hot backup power supply or the main and standby power distribution networks, it may cause a larger current when the fast isolating switch on one side is disconnected, resulting in a larger surge peak of the current in the circuit, which will cause the fast isolating switches on other normal power supply lines to be disconnected, leading to serious power loss. Summary of the invention

[0003] In order to solve or partially solve the problems existing in the related art, the present application provides a high-voltage power distribution system and an aircraft based on hot backup power supply.

[0004] In a first aspect, the present application provides a high-voltage power distribution system based on hot backup power supply, comprising a surge protection branch, a load and at least two electric energy distribution branches; each of the electric energy distribution branches is configured to connect to different power supply devices and distribute the electric energy received from the power supply devices to the corresponding loads; the load comprises a power propulsion mechanism, which is connected to each of the electric energy distribution branches through the surge protection branch; the electric energy distribution branch comprises a first bus and a first isolating switch connected to the first bus, the first bus is configured to receive electric energy from the power supply device, and the first isolating switch is connected between the first bus and the surge protection branch.

[0005] The technical solution provided by the present application, on the basis of hot backup power supply, sets a surge protection branch between the load and at least two power distribution branches, the power distribution branch is configured to connect different power supply devices, and distributes the electric energy received from the power supply equipment to the power propulsion mechanism in the corresponding load through the surge holding branch; when a fault occurs in the high-voltage distribution system, the first isolating switch of the abnormal power supply switches from a closed state to a cut-off state to prevent the fault from spreading, and the surge protection branch can suppress the large surge current caused by the state switching of the first isolating switch, and avoid the loss of power caused by the first isolating switch of the normal power supply being cut off, thereby achieving the high-voltage distribution stability of the hot backup power supply function of the power propulsion mechanism and the reliability of the fault isolation function.

[0006] In an optional embodiment, the power propulsion mechanism includes N power propulsion groups, the surge protection branch includes N surge protection units, the N power propulsion groups are connected one-to-one with the N surge protection units, each power propulsion group is connected to each of the power distribution branches through the corresponding surge protection unit, and N is a positive integer.

[0007] In an optional embodiment, the power thruster group includes two power thrusters, and both of the two power thrusters are connected to the surge protection unit via a second bus.

[0008] In an optional embodiment, in the power thruster group, two power thrusters are centrally symmetrically distributed on the aircraft.

[0009] In an optional implementation, the first busbar and / or the second busbar is a busbar.

[0010] In an optional embodiment, the propulsion device includes a propeller.

[0011] In an optional embodiment, the surge protection unit includes a single anti-surge device or two anti-surge devices; if the surge protection unit includes a single anti-surge device, one end of the anti-surge device is connected to each of the power distribution branches, and the other end is connected to the power propulsion group; if the surge protection unit includes at least two anti-surge devices, one end of each of the anti-surge devices is connected to one of the power distribution branches, and the other end is connected to the power propulsion group.

[0012] In an optional implementation, the first isolating switch is a fast isolating switch, including at least one of a solid-state relay, a transistor, and a field effect transistor.

[0013] In an optional implementation, the output ends of any two of the first busbars are connected via a second isolating switch, and the input ends are each connected to one of the power supply devices.

[0014] A second aspect of the present application provides an aircraft, comprising a high-voltage power distribution system based on hot backup power supply as described above.

[0015] It should be understood that the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the present application. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] The above and other objects, features and advantages of the present application will become more apparent by describing in more detail the exemplary embodiments of the present application in conjunction with the accompanying drawings, wherein the same reference numerals generally represent the same components in the exemplary embodiments of the present application.

[0017] Figure 1 It is a structural schematic diagram of a high-voltage power distribution system based on hot backup power supply shown in this application;

[0018] Figure 2 It is a schematic diagram of the system architecture of a high-voltage power distribution system based on hot backup power supply shown in this application;

[0019] Figure 3 It is another system architecture schematic diagram of a high-voltage power distribution system based on hot backup power supply shown in the present application. DETAILED DESCRIPTION

[0020] The embodiments of the present application will be described in more detail below with reference to the accompanying drawings. Although the embodiments of the present application are shown in the accompanying drawings, it should be understood that the present application can be implemented in various forms and should not be limited by the embodiments described herein. On the contrary, these embodiments are provided to make the present application more thorough and complete, and to fully convey the scope of the present application to those skilled in the art.

[0021] The terms used in this application are for the purpose of describing specific embodiments only and are not intended to limit this application. The singular forms of "a", "said" and "the" used in this application and the appended claims are also intended to include plural forms unless the context clearly indicates other meanings. It should also be understood that the term "and / or" used herein refers to and includes any or all possible combinations of one or more associated listed items.

[0022] It should be understood that although the terms "first", "second", "third", etc. may be used in this application to describe various information, this information should not be limited to these terms. These terms are only used to distinguish the same type of information from each other. For example, without departing from the scope of this application, the first information may also be referred to as the second information, and similarly, the second information may also be referred to as the first information. Thus, the features defined as "first" and "second" may explicitly or implicitly include one or more of the features. In the description of this application, the meaning of "multiple" is two or more, unless otherwise clearly and specifically defined.

[0023] In the related art, when a high-voltage power distribution system fails, such as a short circuit in the propulsion system during aircraft operation, a fast isolating switch is required to quickly isolate the short-circuit point. However, if the fast isolating switch cuts off too quickly, then when there is a large difference between the fast isolating switches for hot backup power supply or between the main and standby power distribution networks, the surge peak in the circuit may be larger, thereby causing the fast isolating switches on other normal power supply lines to be cut off, resulting in serious power loss.

[0024] In response to the above problems, the present application provides a high-voltage power distribution system based on hot backup power supply, which can ensure hot backup power supply and meet the stability and reliability of high-voltage power distribution.

[0025] The technical solution of the present application is described in detail below with reference to the accompanying drawings.

[0026] Figure 1 It is a structural schematic diagram of a high-voltage power distribution system based on hot backup power supply shown in this application.

[0027] See also Figure 1 The present application shows a high-voltage power distribution system based on hot backup power supply, which is applied to an aircraft. The high-voltage power distribution system includes a surge protection branch, a load and at least two power distribution branches.

[0028] Each power distribution branch is configured to connect different power supply devices and distribute the power received from the power supply devices to the corresponding loads. The power distribution branch includes a first bus and a first isolating switch connected to the first bus, the first bus is configured to receive power from the power supply device, and the first isolating switch is connected between the first bus and the surge protection branch.

[0029] In at least one embodiment, the number of power distribution branches is two, one is the main power distribution branch, and the other is the backup power distribution branch. The input end of the main power distribution branch is connected to the main power supply, and the input end of the backup power distribution branch is connected to the backup power supply, wherein the main power supply and the backup power supply can be hot-backed up to each other. The power distribution branch is centered on the first bus, and may specifically include the first bus and a first isolating switch connected to the first bus, and the first bus includes an input end and multiple output ends. The input end of one of the first busbars is connected to the main power supply or the backup power supply, an output end is connected to the corresponding load, an output end is connected to the surge protection branch through the first isolating switch, and an output end is connected to the output end of another first busbar through the second isolating switch.

[0030] It is understandable that the loads connected to the output ends of the two first busbars can be completely the same, or partially the same and partially different. If the power supply status of the main and backup power supplies is the same, then the loads connected to the output ends of the two first busbars can be completely the same. If the power supply status of the main power supply is higher than that of the backup power supply, then the same load connected to the first busbars in the main and backup power distribution branches can be a load that affects flight safety, such as DCDC, while loads that do not affect flight safety can be connected to the output end of the first busbar in the main power distribution branch or the backup power distribution branch according to demand, such as air conditioning.

[0031] And, the load includes a power propulsion mechanism, which is connected to each power distribution branch through a surge protection branch.

[0032] In at least one embodiment, one of the loads may be a power propulsion mechanism. As the power part of the aircraft, the power propulsion mechanism has a need for redundant power supply. Therefore, the main and standby power supplies of this embodiment can be hot-backed up to each other to provide hot-backup power supply for the power propulsion mechanism, ensuring that the power propulsion mechanism does not lose power during operation. The main and standby power supplies supply power to the power propulsion mechanism through the main and standby power distribution branches, and the power propulsion mechanism provides mechanical driving force for the aircraft, thereby realizing the lifting and lowering of the aircraft. Therefore, in this embodiment, there are a main current loop and a standby current loop. Assuming that the main current loop fails, the first isolating switch in the main current loop switches from a closed state to a cut-off state to avoid the spread of the fault, and the surge protection branch can suppress the large surge current caused by the state switching of the first isolating switch, avoiding the loss of power caused by the normal power supply of the first isolating switch being cut off, thereby achieving the high-voltage power distribution stability of the hot backup power supply function of the power propulsion mechanism and the reliability of the fault isolation function.

[0033] In some embodiments, the power propulsion mechanism includes N power propeller groups, the surge protection branch includes N surge protection units, the N power propeller groups are connected to the N surge protection units in a one-to-one correspondence, each power propeller group is connected to each power distribution branch through a corresponding surge protection unit, and N is a positive integer. In this embodiment, one power propeller group is equipped with one surge protection unit, and the power propellers are grouped and equipped with surge protection units, which can be broken down into pieces. When a power propeller group fails, it can be disconnected as a whole under the action of the two first isolation switches corresponding to the power propeller group without affecting other power propeller groups, thereby ensuring the power of the aircraft.

[0034] Further, the power propeller group includes two power propellers, both of which are connected to the surge protection unit via the second busbar. Also, in the power propeller group, the two power propellers are centrally symmetrically distributed on the aircraft. The power propellers include propellers.

[0035] In this embodiment, each power propulsion group has two propellers, and the current input of these two propellers is obtained by secondary distribution of the current output of the first busbar through the second busbar, and the two propellers are centrally symmetrically distributed on the aircraft. Assuming there are four groups of eight propellers, then these eight propellers are distributed in a ring, and the two propellers in each group are symmetrically distributed about the center point of the ring, thereby ensuring that when the propeller power in the same group is lost, the overall power balance can still be maintained. Among them, each propeller is adapted to the motor, and the current output by the main and standby power supplies enters the stator winding of the motor to generate a rotating magnetic field, driving the rotor winding of the motor to drive the propeller to rotate, thereby providing power for the aircraft.

[0036] The first busbar and / or the second busbar is a busbar. Generally speaking, a busbar refers to a conductor that collects and distributes electrical energy in an electric power system, has a large current carrying capacity, and has the functions of collecting electrical energy, distributing electrical energy and connecting equipment. Specifically, it can be a busbar. As an efficient electrical connection component, the busbar can simplify wiring installation and provide a centralized connection point for multiple branch lines in the circuit, making the circuit wiring clearer and simpler. The compact design of the busbar can also realize multiple electrical connections in a limited space, thereby improving the utilization of the internal space of the aircraft.

[0037] In some optional embodiments, the surge protection unit includes a single anti-surge device or two anti-surge devices; if the surge protection unit includes a single anti-surge device, one end of the anti-surge device is connected to each power distribution branch, and the other end is connected to the power propeller group; if the surge protection unit includes at least two anti-surge devices, one end of each anti-surge device is connected to a power distribution branch, and the other end is connected to the power propeller group. In this embodiment, a second bus is connected to both first disconnectors through an anti-surge device. Adding a surge protection unit upstream of the busbar corresponding to each power propeller group can suppress possible surge currents and avoid the first disconnector of normal power supply being cut off, so as to ensure that the power supply characteristics of the distribution network are within the normal working range of each node. Optionally, the anti-surge device can be a filter that can directly suppress current mutations, or it can be an actively controlled low-resistance path that performs shunting when necessary, or it can be other electronic components that can absorb surge currents.

[0038] And, the first isolating switch is a fast isolating switch, including at least one of a solid-state relay, a transistor, and a field effect transistor. The fast isolating switch can be a single or composite form of components such as a solid-state relay, a transistor, and a field effect transistor. The fast isolating switch works in the on and off mode, and has the advantages of fast cutting speed, low loss, light weight, high reliability, and recoverability after cutting. Among them, the switching action of the fast isolating switch is usually triggered by a large current flowing through the switch. When the fast isolating switch is cut off, due to its fast cutting characteristics, there is often a large surge current in the circuit, which may cause the fast isolating switch on other normal power supply lines to be cut off, resulting in more serious power loss.

[0039] Furthermore, the output ends of any two first busbars are connected through a second isolating switch, and the input ends are each connected to a power supply device. The second isolating switch is a fast isolating switch, and each power supply device is used as a group. There is at least one fast isolating switch between every two power supply units as isolation. Specifically, the output end of the busbar corresponding to one power supply unit is connected to the output end of the busbar corresponding to another power supply unit through the fast isolating switch. And, in practice, the power supply device can be a battery or other component that can provide electrical energy plus an electromechanical relay, and the electromechanical relay can control the power on and off of the entire high-voltage power distribution system before and after the flight.

[0040] In the present application, the application of a high-voltage power distribution system on a helicopter is taken as an example, and the high-voltage power distribution system of the present application is described in more detail with reference to the accompanying drawings.

[0041] For pure electric helicopters with vertical take-off and landing, the high-voltage power distribution system has the characteristics of high voltage and concentrated load. Compared with the low-voltage power distribution system, the peak values ​​of voltage and current surges are larger, the electromagnetic compatibility is more difficult, and the characteristics of each node when considered individually and when considered in combination in the distribution network are also more different, making it a huge challenge to meet the stability and reliability requirements of the high-voltage power distribution system.

[0042] like Figure 2 As shown, it is a schematic diagram of the system architecture of the high-voltage power distribution system provided in an embodiment of the present application. The high-voltage power distribution system includes two power supply units, three groups of six power propulsion units, other load units excluding the power propulsion units, fault isolation switches, bus bars, high-voltage cables, and surge protection units. The fault isolation switch may be a fast isolation switch or a non-fast isolation switch, and the non-fast isolation switch may be an ordinary fuse or a circuit breaker, wherein the fault isolation switch between the two power supply units is the second isolation switch K2, and the fault isolation switch between the second bus bar M2 close to the power propulsion unit and the first bus bar M1 close to the power supply unit is the first isolation switch K1, and the first isolation switch and the second isolation switch K2 are both fast isolation switches, and the remaining switches that need to use the fault isolation switch may be non-fast isolation switches.

[0043] As an important load of a helicopter, the power propulsion unit (propeller) usually has a demand for redundant power supply and cannot tolerate long-term power supply interruption. Its backup power supply line is usually hot backup. All power propulsion units are grouped according to symmetrical positions on the aircraft, with two in each group. Two power supplies are used for each group, and the two first isolating switches K1 are in a closed state at the same time to achieve hot backup power supply. The purpose of setting all the first isolating switches K1 is to ensure that when a power propulsion unit in any group has a short circuit or open circuit fault, it can be effectively isolated by the first isolating switch K1 to avoid the spread of the fault and ensure the normal operation of the power propulsion units in the remaining groups. Among them, the first isolating switch K1 is a fast isolating switch, and its action is usually triggered by a large current flowing through the switch. When the fast isolating switch is cut off, due to its fast cut-off characteristics, especially when there are reasonable hardware differences between the fast isolating switches and differences between the main and standby power distribution networks, there will be a large surge current in the circuit, which may cause the fast isolating switches on other normal power supply lines to be cut off, and ultimately cause more serious power loss. Except for other load units of the power propulsion unit, the corresponding power supply unit is connected according to the actual backup relationship, and the second isolating switch K2 is used to provide protection.

[0044] An anti-surge unit is added upstream of the second bus M2 of each power propulsion unit group to suppress possible surge current and avoid the first isolating switch K1 of normal power supply being cut off, while protecting the power supply characteristics of the distribution system within the normal working range of each node.

[0045] Therefore, the embodiment of the present application can realize the rapid disconnection of the first isolating switch K1, and when there are reasonable hardware differences between the first isolating switches K1 of the hot backup power supply and there are differences between the main and standby power distribution networks, the reliability of the hot backup power supply function and the fault isolation function can be guaranteed.

[0046] It should be noted that the number of power propulsion units is not unique, and can be the above three groups or four groups, such as Figure 3 shown.

[0047] The present application also provides an aircraft and corresponding embodiments.

[0048] like Figure 1 As shown, an embodiment of the present application provides an aircraft, including the above-mentioned high-voltage power distribution system based on hot backup power supply.

[0049] Taking the aircraft as a helicopter as an example, the helicopter includes a high voltage power distribution system based on hot backup power supply. Figure 1 As shown, the high-voltage power distribution system includes a surge protection branch, a load and at least two power distribution branches.

[0050] Each power distribution branch is configured to connect different power supply devices and distribute the power received from the power supply devices to the corresponding loads. The power distribution branch includes a first bus and a first isolating switch connected to the first bus, the first bus is configured to receive power from the power supply device, and the first isolating switch is connected between the first bus and the surge protection branch.

[0051] In at least one embodiment, the number of power distribution branches is two, one is the main power distribution branch, and the other is the backup power distribution branch. The input end of the main power distribution branch is connected to the main power supply, and the input end of the backup power distribution branch is connected to the backup power supply, wherein the main power supply and the backup power supply can be hot-backed up to each other. The power distribution branch is centered on the first bus, and may specifically include the first bus and a first isolating switch connected to the first bus, and the first bus includes an input end and multiple output ends. The input end of one of the first busbars is connected to the main power supply or the backup power supply, an output end is connected to the corresponding load, an output end is connected to the surge protection branch through the first isolating switch, and an output end is connected to the output end of another first busbar through the second isolating switch.

[0052] It is understandable that the loads connected to the output ends of the two first busbars can be completely the same, or partially the same and partially different. If the power supply status of the main and backup power supplies is the same, then the loads connected to the output ends of the two first busbars can be completely the same. If the power supply status of the main power supply is higher than that of the backup power supply, then the same load connected to the first busbars in the main and backup power distribution branches can be a load that affects flight safety, such as DCDC, while loads that do not affect flight safety can be connected to the output end of the first busbar in the main power distribution branch or the backup power distribution branch according to demand, such as air conditioning.

[0053] And, the load includes a power propulsion mechanism, which is connected to each power distribution branch through a surge protection branch.

[0054] In at least one embodiment, one of the loads may be a power propulsion mechanism. As the power part of the aircraft, the power propulsion mechanism has a need for redundant power supply. Therefore, the main and standby power supplies of this embodiment can be hot-backed up to each other to provide hot-backup power supply for the power propulsion mechanism, ensuring that the power propulsion mechanism does not lose power during operation. The main and standby power supplies supply power to the power propulsion mechanism through the main and standby power distribution branches, and the power propulsion mechanism provides mechanical driving force for the aircraft, thereby realizing the lifting and lowering of the aircraft. Therefore, in this embodiment, there are a main current loop and a standby current loop. Assuming that the main current loop fails, the first isolating switch in the main current loop switches from a closed state to a cut-off state to avoid the spread of the fault, and the surge protection branch can suppress the large surge current caused by the state switching of the first isolating switch, avoiding the loss of power caused by the normal power supply of the first isolating switch being cut off, thereby achieving the high-voltage power distribution stability of the hot backup power supply function of the power propulsion mechanism and the reliability of the fault isolation function.

[0055] In some embodiments, the power propulsion mechanism includes N power propeller groups, the surge protection branch includes N surge protection units, the N power propeller groups are connected to the N surge protection units in a one-to-one correspondence, each power propeller group is connected to each power distribution branch through a corresponding surge protection unit, and N is a positive integer. In this embodiment, one power propeller group is equipped with one surge protection unit, and the power propellers are grouped and equipped with surge protection units, which can be broken down into pieces. When a power propeller group fails, it can be disconnected as a whole under the action of the two first isolation switches corresponding to the power propeller group without affecting other power propeller groups, thereby ensuring the power of the aircraft.

[0056] Further, the power propeller group includes two power propellers, both of which are connected to the surge protection unit via the second busbar. Also, in the power propeller group, the two power propellers are centrally symmetrically distributed on the aircraft. The power propellers include propellers.

[0057] In this embodiment, each power propulsion group has two propellers, and the current input of these two propellers is obtained by secondary distribution of the current output of the first busbar through the second busbar, and the two propellers are centrally symmetrically distributed on the aircraft. Assuming there are four groups of eight propellers, then these eight propellers are distributed in a ring, and the two propellers in each group are symmetrically distributed about the center point of the ring, thereby ensuring that when the propeller power in the same group is lost, the overall power balance can still be maintained. Among them, each propeller is adapted to the motor, and the current output by the main and standby power supplies enters the stator winding of the motor to generate a rotating magnetic field, driving the rotor winding of the motor to drive the propeller to rotate, thereby providing power for the aircraft.

[0058] The first busbar and / or the second busbar is a busbar. Generally speaking, a busbar refers to a conductor that collects and distributes electrical energy in an electric power system, has a large current carrying capacity, and has the functions of collecting electrical energy, distributing electrical energy and connecting equipment. Specifically, it can be a busbar. As an efficient electrical connection component, the busbar can simplify wiring installation and provide a centralized connection point for multiple branch lines in the circuit, making the circuit wiring clearer and simpler. The compact design of the busbar can also realize multiple electrical connections in a limited space, thereby improving the utilization of the internal space of the aircraft.

[0059] In some optional embodiments, the surge protection unit includes a single anti-surge device or two anti-surge devices; if the surge protection unit includes a single anti-surge device, one end of the anti-surge device is connected to each power distribution branch, and the other end is connected to the power propeller group; if the surge protection unit includes at least two anti-surge devices, one end of each anti-surge device is connected to a power distribution branch, and the other end is connected to the power propeller group. In this embodiment, a second bus is connected to both first disconnectors through an anti-surge device. Adding a surge protection unit upstream of the busbar corresponding to each power propeller group can suppress possible surge currents and avoid the first disconnector of normal power supply being cut off, so as to ensure that the power supply characteristics of the distribution network are within the normal working range of each node. Optionally, the anti-surge device can be a filter that can directly suppress current mutations, or it can be an actively controlled low-resistance path that performs shunting when necessary, or it can be other electronic components that can absorb surge currents.

[0060] And, the first isolating switch is a fast isolating switch, including at least one of a solid-state relay, a transistor, and a field effect transistor. The fast isolating switch can be a single or composite form of components such as a solid-state relay, a transistor, and a field effect transistor. The fast isolating switch works in the on and off mode, and has the advantages of fast cutting speed, low loss, light weight, high reliability, and recoverability after cutting. Among them, the switching action of the fast isolating switch is usually triggered by a large current flowing through the switch. When the fast isolating switch is cut off, due to its fast cutting characteristics, there is often a large surge current in the circuit, which may cause the fast isolating switch on other normal power supply lines to be cut off, resulting in more serious power loss.

[0061] Furthermore, the output ends of any two first busbars are connected through a second isolating switch, and the input ends are each connected to a power supply device. The second isolating switch is a fast isolating switch, and each power supply device is used as a group. There is at least one fast isolating switch between every two power supply units as isolation. Specifically, the output end of the busbar corresponding to one power supply unit is connected to the output end of the busbar corresponding to another power supply unit through the fast isolating switch. And, in practice, the power supply device can be a battery or other component that can provide electrical energy plus an electromechanical relay, and the electromechanical relay can control the power on and off of the entire high-voltage power distribution system before and after the flight.

[0062] In the present application, the application of a high-voltage power distribution system on a helicopter is taken as an example, and the high-voltage power distribution system of the present application is described in more detail with reference to the accompanying drawings.

[0063] For pure electric helicopters with vertical take-off and landing, the high-voltage power distribution system has the characteristics of high voltage and concentrated load. Compared with the low-voltage power distribution system, the peak values ​​of voltage and current surges are larger, the electromagnetic compatibility is more difficult, and the characteristics of each node when considered individually and when considered in combination in the distribution network are also more different, making it a huge challenge to meet the stability and reliability requirements of the high-voltage power distribution system.

[0064] like Figure 2 As shown, it is a schematic diagram of the system architecture of the high-voltage power distribution system provided in an embodiment of the present application. The high-voltage power distribution system includes two power supply units, three groups of six power propulsion units, other load units excluding the power propulsion units, fault isolation switches, bus bars, high-voltage cables, and surge protection units. The fault isolation switch may be a fast isolation switch or a non-fast isolation switch, and the non-fast isolation switch may be an ordinary fuse or a circuit breaker, wherein the fault isolation switch between the two power supply units is the second isolation switch K2, and the fault isolation switch between the second bus bar M2 close to the power propulsion unit and the first bus bar M1 close to the power supply unit is the first isolation switch K1, and the first isolation switch and the second isolation switch K2 are both fast isolation switches, and the remaining switches that need to use the fault isolation switch may be non-fast isolation switches.

[0065] As an important load of a helicopter, the power propulsion unit (propeller) usually has a demand for redundant power supply and cannot tolerate long-term power supply interruption. Its backup power supply line is usually hot backup. All power propulsion units are grouped according to symmetrical positions on the aircraft, with two in each group. Two power supplies are used for each group, and the two first isolating switches K1 are in a closed state at the same time to achieve hot backup power supply. The purpose of setting all the first isolating switches K1 is to ensure that when a power propulsion unit in any group has a short circuit or open circuit fault, it can be effectively isolated by the first isolating switch K1 to avoid the spread of the fault and ensure the normal operation of the power propulsion units in the remaining groups. Among them, the first isolating switch K1 is a fast isolating switch, and its action is usually triggered by a large current flowing through the switch. When the fast isolating switch is cut off, due to its fast cut-off characteristics, especially when there are reasonable hardware differences between the fast isolating switches and differences between the main and standby power distribution networks, there will be a large surge current in the circuit, which may cause the fast isolating switches on other normal power supply lines to be cut off, and ultimately cause more serious power loss. Except for other load units of the power propulsion unit, the corresponding power supply unit is connected according to the actual backup relationship, and the second isolating switch K2 is used to provide protection.

[0066] An anti-surge unit is added upstream of the second bus M2 of each power propulsion unit group to suppress possible surge current and avoid the first isolating switch K1 of normal power supply being cut off, while protecting the power supply characteristics of the distribution system within the normal working range of each node.

[0067] Therefore, the embodiment of the present application can realize the rapid disconnection of the first isolating switch K1, and when there are reasonable hardware differences between the first isolating switches K1 of the hot backup power supply and there are differences between the main and standby power distribution networks, the reliability of the hot backup power supply function and the fault isolation function can be guaranteed.

[0068] It should be noted that the number of power propulsion units is not unique, and can be the above three groups or four groups, such as Figure 3 shown.

[0069] The embodiments of the present application have been described above, and the above description is exemplary, not exhaustive, and is not limited to the disclosed embodiments. Many modifications and changes will be apparent to those of ordinary skill in the art without departing from the scope and spirit of the described embodiments. The selection of terms used herein is intended to best explain the principles of the embodiments, practical applications, or improvements to the technology in the market, or to enable other persons of ordinary skill in the art to understand the embodiments disclosed herein.

Claims

1. A high voltage power distribution system based on hot backup power supply, characterized in that: It includes a surge protection branch, a load and at least two power distribution branches; Each of the electric energy distribution branches is configured to connect to different power supply devices and distribute the electric energy received from the power supply devices to corresponding loads; The load includes a power propulsion mechanism, and the power propulsion mechanism is connected to each of the power distribution branches through the surge protection branch; The electric energy distribution branch includes a first busbar and a first isolating switch connected to the first busbar, the first busbar is configured to receive electric energy from a power supply device, and the first isolating switch is connected between the first busbar and the surge protection branch.

2. The system according to claim 1, characterized in that The power propulsion mechanism includes N power propulsion groups, and the surge protection branch includes N surge protection units. The N power propulsion groups are connected to the N surge protection units in a one-to-one correspondence. Each power propulsion group is connected to each of the power distribution branches through the corresponding surge protection unit, and N is a positive integer.

3. The system according to claim 2, characterized in that The power thruster group includes two power thrusters, and both of the two power thrusters are connected to the surge protection unit via a second bus.

4. The system according to claim 3, characterized in that In the power thruster group, the two power thrusters are centrally symmetrically distributed on the aircraft.

5. The system according to claim 3, characterized in that The first busbar and / or the second busbar is a busbar.

6. The system according to claim 3, characterized in that The power propulsion device includes a propeller.

7. The system according to claim 2, characterized in that The surge protection unit includes a single surge protection device or two surge protection devices; If the surge protection unit includes a single surge protection device, one end of the surge protection device is connected to each of the power distribution branches, and the other end is connected to the power propulsion unit; If the surge protection unit includes at least two surge protection devices, one end of each of the surge protection devices is connected to one of the power distribution branches, and the other end is connected to the power propulsion unit.

8. The system according to claim 1, characterized in that The first isolating switch is a fast isolating switch, including at least one of a solid-state relay, a transistor, and a field effect transistor.

9. The system according to claim 1, characterized in that The output ends of any two of the first busbars are connected via a second isolating switch, and the input ends are each connected to one of the power supply devices.

10. An aircraft, characterized in that: It comprises a high voltage power distribution system based on hot backup power supply as described in any one of claims 1 to 9.

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