Low-voltage power supply control method and system for aircraft and aviation aircraft

Abstract

The invention discloses a low-voltage power supply control method and system for an aircraft and the aircraft, and relates to the field of the aircraft, and the system comprises at least two direct-current power supplies, at least two main bus bars, at least two emergency bus bars with the number corresponding to that of the main bus bars, a plurality of electric devices, at least one emergency battery and a power interface; the method comprises the steps that in a normal working state, a first switch between two adjacent main bus bars and a second switch between two adjacent emergency bus bars are controlled to be switched off, all the main bus bars are controlled to be connected with corresponding direct-current power sources, all the emergency bus bars are controlled to be connected with corresponding main bus bars, and power is supplied to all electric equipment; and in a ground maintenance state, the power interface is controlled to be connected with the main bus bar to supply power to all electric equipment, and an external power supply is utilized to charge the emergency battery. According to the invention, inconvenience to flight of the aircraft caused by consumption of limited electric energy on the aircraft can be avoided, and the safety of ground maintenance can be improved.

Description

Technical Field

[0001] This application relates to the technical field of aircraft, and particularly to a low-voltage power supply control method, system, and aircraft for an aircraft. Background Art

[0002] The low-voltage power supply system of an aircraft is a system that provides low-voltage direct current to various electrical devices. The low-voltage power supply system in the related art mainly includes a distribution box, a main bus bar, an emergency bus bar, and an emergency battery. The main problems existing in this low-voltage power supply system are that the power supply margin of the main bus bar and the emergency bus bar is insufficient, resulting in low power supply reliability. If the system fails, causing important devices to lose power and malfunction, it will also affect flight safety; and during ground maintenance, it consumes the electrical energy on the aircraft, resulting in limited use of the aircraft and low safety during ground maintenance. Summary of the Invention

[0003] The main purpose of this application is to provide a low-voltage power supply control method, system, and aircraft for an aircraft, aiming to solve the technical problems of low power supply reliability of the aircraft in the related art, which affects flight safety, and low safety during ground maintenance.

[0004] To achieve the above object, this application proposes a low-voltage power supply control method for an aircraft, which is applied to a low-voltage power supply system. The low-voltage power supply system includes at least two DC power sources, at least two main bus bars, at least two emergency bus bars corresponding to the number of main bus bars, a plurality of electrical devices respectively connected to each main bus bar and each emergency bus bar, at least one emergency battery, and a power interface connected to the emergency battery; the method includes:

[0005] In the normal working state of the low-voltage power supply system, control the first switch between adjacent two main bus bars and the second switch between adjacent two emergency bus bars to be disconnected;

[0006] Control each main bus bar to be connected to the corresponding DC power source, so that each DC power source supplies power to the corresponding connected electrical devices through the corresponding main bus bar;

[0007] Control the connection between each emergency bus bar and the emergency battery to be disconnected, and control each emergency bus bar to be connected to the corresponding main bus bar, so that each main bus bar supplies power to the corresponding connected electrical devices through the corresponding emergency bus bar;

[0008] In the ground maintenance state of the low-voltage power supply system, when the power interface is connected to an external power source, control the power interface to be connected to at least one main bus bar corresponding to it, and control the connection between at least one main bus bar and the corresponding DC power source to be disconnected, so that the external power source supplies power to at least one main bus bar and the corresponding emergency bus bar, and the external power source charges the emergency battery.

[0009] In one embodiment, the method further includes:

[0010] When a failure of any one of at least two DC power supplies is detected, controlling the disconnection of the connection between the failed DC power supply and the corresponding main busbar;

[0011] Controlling the closing of a first switch between the main busbar corresponding to the failed DC power supply and an adjacent main busbar, so that the adjacent DC power supply corresponding to the adjacent main busbar supplies power to the main busbar corresponding to the failed DC power supply through the adjacent main busbar and the first switch.

[0012] In one embodiment, the system further includes a plurality of unidirectional conduction devices, and each main busbar is connected to the corresponding emergency busbar through the unidirectional conduction device, for restricting the current flow direction to be from the main busbar to the emergency busbar; the method further includes:

[0013] When a failure of any one of at least two main busbars is detected, controlling the disconnection of the connection between the failed main busbar and the corresponding DC power supply;

[0014] Controlling the closing of a second switch between the emergency busbar corresponding to the failed main busbar and an adjacent emergency busbar, so that the adjacent DC power supply corresponding to the adjacent emergency busbar supplies power to the emergency busbar corresponding to the failed main busbar through the corresponding adjacent main busbar, the adjacent emergency busbar and the second switch.

[0015] In one embodiment, the system further includes a plurality of unidirectional conduction devices, and each main busbar is connected to the corresponding emergency busbar through the unidirectional conduction device, for restricting the current flow direction to be from the main busbar to the emergency busbar; the method further includes:

[0016] When a failure of one or more DC power supplies among at least two DC power supplies and / or a failure of one or more main busbars among at least two main busbars is detected, controlling the disconnection of the connection between the failed DC power supply and the corresponding main busbar, and / or controlling the disconnection of the connection between the failed main busbar and the corresponding DC power supply;

[0017] Controlling the connection of the emergency busbar corresponding to the failed DC power supply and / or the failed main busbar to the emergency battery, so that the emergency battery supplies power to the emergency busbar corresponding to the failed DC power supply and / or the failed main busbar respectively.

[0018] In one embodiment, the method further includes:

[0019] When a failure of any one of at least two emergency busbars is detected, controlling the disconnection of the connection between the failed emergency busbar and the corresponding main busbar, or automatically disconnecting through a fuse between the failed emergency busbar and the corresponding main busbar.

[0020] In one embodiment, the multiple electrical devices include primary electrical devices, secondary electrical devices, and tertiary electrical devices that are classified and determined in ascending order of importance based on the operation of the aircraft for each electrical device;

[0021] Controlling each main busbar to be connected to a corresponding DC power supply one by one, so that each DC power supply supplies power to the connected electrical devices through the corresponding main busbar, includes:

[0022] Controlling each main busbar to be connected to a corresponding DC power supply one by one, so that each DC power supply supplies power to the connected primary electrical devices through the corresponding main busbar;

[0023] Controlling each emergency busbar to be connected to a corresponding main busbar one by one, so that each main busbar supplies power to the connected electrical devices through the corresponding emergency busbar, includes:

[0024] Controlling each emergency busbar to be normally connected to a corresponding main busbar one by one, so that each main busbar supplies power to the connected secondary electrical devices and tertiary electrical devices respectively through the corresponding emergency busbar.

[0025] To achieve the above object, the present application also proposes a low-voltage power supply system for an aircraft, including at least two DC power supplies, at least two main busbars, at least two emergency busbars corresponding to the number of main busbars, and at least one emergency battery and a power interface;

[0026] Wherein, each main busbar is connected to each DC power supply in a switchable manner one by one, and two adjacent main busbars are connected through a first switch; each emergency busbar is connected to each main busbar in a switchable manner one by one, and two adjacent emergency busbars are connected through a second switch; the emergency battery is connected to each emergency busbar in a switchable manner; the power interface is connected to at least one main busbar in a switchable manner, and the power interface is used to connect to an external power supply. When the power interface is connected to the external power supply, the external power supply is used to supply power to at least one main busbar, and the power interface is also connected to the emergency battery to charge the emergency battery with the external power supply.

[0027] In one embodiment, the at least two DC power supplies include a first DC power supply and a second DC power supply, the at least two main busbars include a first main busbar and a second main busbar, and the at least two emergency busbars include a first emergency busbar and a second emergency busbar;

[0028] Among them, the first main busbar is connectable to the first DC power supply in a switchable manner, the second main busbar is connectable to the second DC power supply in a switchable manner, and the first main busbar is connected to the second main busbar through a first switch; the first emergency busbar is connectable to the first main busbar in a switchable manner, the second emergency busbar is connectable to the second main busbar in a switchable manner, and the first emergency busbar is connected to the second emergency busbar through a second switch; the emergency battery is respectively connectable to the first emergency busbar and the second emergency busbar in a switchable manner; the power interface is respectively connectable to the first main busbar and the second main busbar in a switchable manner.

[0029] In one embodiment, the system further includes at least two fuses, and each emergency busbar is connected to the corresponding main busbar through a fuse; and / or,

[0030] The system further includes a charger, and the charger is integrated inside the emergency battery or is self - contained outside; and / or,

[0031] The DC power supply is a voltage conversion device, a DC generator or a battery pack.

[0032] In one embodiment, the system further includes a plurality of unidirectional conduction devices;

[0033] A unidirectional conduction device is connected between each main busbar and the corresponding emergency busbar, for restricting the current flow direction to be from the main busbar to the emergency busbar.

[0034] In one embodiment, a unidirectional conduction device is connected between the emergency battery and each emergency busbar, for restricting the current flow direction to be from the emergency battery to the emergency busbar.

[0035] In one embodiment, the unidirectional conduction device is a diode.

[0036] In one embodiment, each main busbar is correspondingly connected to a first - level electrical device, and each emergency busbar is correspondingly connected to a second - level and / or third - level electrical device, wherein the first - level electrical device, the second - level electrical device and the third - level electrical device are classified and determined according to the importance of each electrical device based on the operation of the aircraft, from low to high.

[0037] In one embodiment, a switch protection circuit is connected between the main busbar and the first - level electrical device and between the emergency busbar and the second - level electrical device; and / or,

[0038] A safety protection device is connected between the emergency busbar and the third - level electrical device.

[0039] In one embodiment, the switch protection circuit is a solid - state power controller circuit; and / or,

[0040] The safety protection device is a fuse or a circuit breaker.

[0041] In addition, to achieve the above object, the present application further provides an aircraft, including the low-voltage power supply system for the aircraft as described above.

[0042] One or more technical solutions proposed by the present application have at least the following technical effects:

[0043] A low-voltage power supply control method for an aircraft is proposed, which is applied to a low-voltage power supply system. The system includes at least two DC power supplies, at least two main busbars, at least two emergency busbars corresponding to the number of main busbars, a plurality of electrical equipment respectively connected to each main busbar and each emergency busbar, an emergency battery and a power supply interface; in the normal working state of the low-voltage power supply system, control the first switch between adjacent two main busbars and the second switch between adjacent two emergency busbars to be disconnected, and control the main busbars to be connected to the DC power supplies, so that the DC power supplies supply power to the corresponding connected electrical equipment through the main busbars. Also control the connection between the emergency busbars and the emergency battery to be disconnected, and the emergency busbars to be connected to the main busbars, so that the main busbars supply power to the corresponding connected electrical equipment through the emergency busbars, which can provide at least two independent power supplies for a plurality of electrical equipment respectively to ensure the stable operation of the system; the first switch and the second switch can be turned on and off as needed, so that each main busbar and emergency busbar have redundant power supply, improving the power supply reliability; in the ground maintenance state of the low-voltage power supply system, when the power supply interface is connected to an external power supply, control the power supply interface to be connected to the main busbars, and control the connection between the main busbars and the DC power supplies to be disconnected, so that the external power supply supplies power to the main busbars and the corresponding emergency busbars, and uses the external power supply to charge the emergency battery. It can use the ground power supply alone during ground maintenance without consuming the electrical energy of the emergency battery and the DC power supply on the aircraft, and without applying high voltage, avoiding the inconvenience to the flight of the aircraft caused by consuming the limited electrical energy on the aircraft, improving the safety of ground maintenance. At the same time, it can also reduce the capacity requirement for the emergency battery, thereby reducing the battery weight and improving the effective payload performance of the aircraft. Description of the Drawings

[0044] The drawings here are incorporated into the specification and form a part of this specification, showing embodiments consistent with the present application, and are used together with the specification to explain the principles of the present application.

[0045] To more clearly illustrate the technical solutions in the embodiments of the present application or related technologies, the following will briefly introduce the drawings required for use in the description of the embodiments or related technologies. Obviously, the drawings in the following description are only some embodiments of the present application. For those of ordinary skill in the art, without creative efforts, other drawings can be obtained based on the structures shown in these drawings.

[0046] Figure 1It is a system block diagram of a low-voltage power supply system in the related art;

[0047] Figure 2 It is a system block diagram of an embodiment of the low-voltage power supply system for an aircraft in the present application;

[0048] Figure 3 It is a system block diagram of a specific example of the low-voltage power supply system for an aircraft in the present application;

[0049] Figure 4 It is a schematic flowchart of an embodiment of the low-voltage power supply control method for an aircraft in the present application.

[0050] The realization of the purpose of the present application, functional characteristics and advantages will be further described with reference to the embodiments and the accompanying drawings. Detailed implementation manners

[0051] Next, the technical solutions in the embodiments of the present application will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present application. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present application.

[0052] It should be noted that if there are directional indications (such as up, down, left, right, front, back...) involved in the embodiments of the present application, the directional indications are only used to explain the relative position relationship and movement conditions between components in a specific posture. If the specific posture changes, the directional indications will also change accordingly. In addition, if there are descriptions such as "first" and "second" in the embodiments of the present application, the descriptions of "first" and "second" are only for descriptive purposes and cannot be understood as indicating or implying their relative importance or implicitly indicating the quantity of the indicated technical features. Thus, the features defined with "first" and "second" may explicitly or implicitly include at least one of such features. In addition, if "and / or" or "and / or" appears throughout the text, its meaning includes three parallel solutions. Taking "A and / or B" as an example, it includes solution A, solution B, or the solution where A and B are satisfied simultaneously. In addition, the technical solutions between the embodiments can be combined with each other, but it must be based on the fact that those of ordinary skill in the art can implement it. When the combination of technical solutions is contradictory or cannot be implemented, it should be considered that such a combination of technical solutions does not exist and is not within the protection scope required by the present application.

[0053] The low-voltage power supply system of an aircraft is a system that provides low-voltage direct current to various electrical devices. For example Figure 1The following is a system block diagram of a low-voltage power supply system in the related art. The low-voltage power supply system mainly includes two sets of high-voltage distribution boxes, two main busbars, an emergency busbar, and an emergency battery. A DCDC conversion module connected one-to-one with the main busbar is provided in the high-voltage distribution box. The DCDC conversion module converts the high-voltage direct current on the aircraft into low-voltage direct current and supplies it to the main busbar, and the two DCDC conversion modules are communicatively connected to achieve current sharing regulation. In this low-voltage power supply system, the main busbar provides single-redundancy power supply to the corresponding first-type electrical equipment, that is, it is powered by the corresponding high-voltage distribution box, and the emergency busbar provides triple-redundancy power supply to the corresponding second-type electrical equipment, that is, it can be powered by two sets of high-voltage distribution boxes or by the emergency battery. However, there are still some problems in this low-voltage power supply system:

[0054] 1. The power supply redundancy of a single main busbar is insufficient

[0055] The power supply of a single main busbar only comes from a corresponding DCDC conversion module. When this DCDC conversion module fails, the main busbar has no power supply, and the corresponding first-type electrical equipment will lose power, resulting in equipment failure and low power supply reliability;

[0056] 2. There is a single-point failure in the emergency busbar

[0057] The power supply of the emergency busbar comes from the main busbar and the emergency battery, and the power supply of the main busbar comes from the corresponding DCDC conversion module. When the emergency busbar is short-circuited, the voltages on the main busbar and the emergency busbar are pulled down. That is to say, if the emergency busbar fails, even if the main busbar is normal, the voltage on the main busbar will also be pulled down accordingly, that is, there is a single-point failure, which will cause all the first-type electrical equipment and the second-type electrical equipment to lose power, resulting in equipment failure and even the crash of the aircraft, thus affecting flight safety;

[0058] 3. During ground maintenance, it consumes the electrical energy on the aircraft and has low safety

[0059] During ground maintenance, it is necessary to connect the emergency battery to make the emergency busbar powered so that the second-type electrical equipment can be powered on for maintenance inspection, which will consume the electrical energy of the emergency battery; it is also necessary to connect the high-voltage distribution box to make the main busbar powered so that the first-type electrical equipment can be powered on for maintenance inspection, which will consume the high-voltage electrical energy of the aircraft; and when charging the emergency battery, it is also charged by using the high-voltage distribution box, which will also consume the high-voltage electrical energy of the aircraft. Therefore, it is necessary to replenish the high-voltage electrical energy for the aircraft later, otherwise the flight mission may not be completed due to insufficient high-voltage electrical energy. In addition, during the aforementioned ground maintenance process, the aircraft is in a high-voltage state, and maintenance personnel are in this high-voltage environment, there are risks such as high-voltage electric shock, resulting in low safety during ground maintenance.

[0060] In view of the above problems, the present application provides a low-voltage power supply control method, system and aircraft for an aircraft. The present application and the following embodiments will be described below with reference to the accompanying drawings.

[0061] The present application proposes a low-voltage power supply system for an aircraft.

[0062] In an embodiment of the present application, referring to Figure 2 , Figure 2 FIG. 10 is a system block diagram of an embodiment of a low-voltage power supply system for an aircraft. The system may include at least two DC power supplies, at least two main busbars, at least two emergency busbars corresponding to the number of main busbars, and at least one emergency battery and a power interface.

[0063] Among them, each main busbar is connectable to and disconnectable from each DC power supply in a one-to-one correspondence, and adjacent two main busbars are connected by a first switch; each emergency busbar is connectable to and disconnectable from each main busbar in a one-to-one correspondence, and adjacent two emergency busbars are connected by a second switch; the emergency battery is connectable to and disconnectable from each emergency busbar; the power interface is connectable to and disconnectable from at least one main busbar. The power interface is used to connect an external power supply. When the power interface is connected to the external power supply, the external power supply is used to supply power to at least one main busbar. The power interface is also connected to the emergency battery to charge the emergency battery with the external power supply.

[0064] It should be noted that the DC power supply refers to a device or module that provides electrical energy required for the operation of various electrical devices on the aircraft. For example, it can provide 28VDC (direct current). Among them, the electrical device refers to a device, apparatus and system on the aircraft that needs to obtain electrical energy from this low-voltage power supply system. The main busbar and the emergency busbar belong to different two levels of busbars, and both belong to the power supply busbars, but the electrical devices they supply power to are different. The specific electrical devices supplied with power can be connected to the main busbar or the emergency busbar after being classified according to actual needs, and no specific limitation is made here. The emergency battery refers to a battery device that supplies power to the emergency busbar when a DC power supply fails or malfunctions, or the main busbar fails, etc. It can also provide electrical energy required for the operation of various electrical devices, such as 28VDC. The emergency battery can be one or more. When there are multiple emergency batteries, each emergency battery is connected to each emergency busbar and is also connected to the power interface. The power interface refers to a power input interface provided on the aircraft for connecting an external power supply such as a ground power supply, so as to supply power to one or more main busbars connected to the power interface with the external power supply and charge the emergency battery with the external power supply during ground maintenance, so as not to consume the electrical energy of the power supply device on the aircraft.

[0065] It can be understood that in this system, each main bus bar can be powered by the corresponding DC power supply, or by the DC power supply corresponding to other main bus bars, or by the external power supply connected through the power interface during ground maintenance. Each main bus bar can provide redundant power supply to the connected electrical equipment, improving the power supply reliability of the main bus bar. Each emergency bus bar can be powered by the corresponding main bus bar, or by the main bus bar corresponding to other emergency bus bars, or by the emergency battery, and can also be powered by the external power supply connected through the power interface through the main bus bar during ground maintenance. Each emergency bus bar can provide redundant power supply to the connected electrical equipment, improving the power supply reliability of the emergency bus bar. At the same time, when a short-circuit fault occurs in a certain emergency bus bar, the corresponding connected main bus bar and the second switch can be disconnected, only causing the electrical equipment on this emergency bus bar to lose power, while other equipment can still operate normally. This operation only reduces the safety margin of the aircraft, but can avoid flight safety accidents such as aircraft crashes, improving the power supply safety and flight safety of the system. During ground maintenance, the external power supply can be used to supply power to each electrical equipment and charge the emergency battery. The aircraft does not need to be powered by high voltage and does not need to consume the electrical energy on the aircraft, increasing the convenience and safety of aircraft maintenance. At the same time, it can also reduce the capacity requirement for the emergency battery, thereby reducing the battery weight and improving the effective payload performance of the aircraft.

[0066] In a feasible implementation manner, with continued reference to Figure 2 , at least two DC power supplies may include a first DC power supply and a second DC power supply, at least two main bus bars may include a first main bus bar and a second main bus bar, and at least two emergency bus bars may include a first emergency bus bar and a second emergency bus bar.

[0067] Among them, the first main bus bar is connectable and disconnectable to the first DC power supply, the second main bus bar is connectable and disconnectable to the second DC power supply, and the first main bus bar is connected to the second main bus bar through a first switch; the first emergency bus bar is connectable and disconnectable to the first main bus bar, the second emergency bus bar is connectable and disconnectable to the second main bus bar, and the first emergency bus bar is connected to the second emergency bus bar through a second switch; the emergency battery is respectively connectable and disconnectable to the first emergency bus bar and the second emergency bus bar; the power interface is respectively connectable and disconnectable to the first main bus bar and the second main bus bar.

[0068] It should be noted that the switchable connection means that the connection between two devices is controlled to be turned on or off by the on-off state of a device or circuit. Specifically, it can be implemented by using switching devices such as contactors, circuit breakers, and controllable switches, switching circuits, or chips. In this embodiment, for example, the first main busbar is connected to the first DC power supply through a contactor C1, the second main busbar is connected to the second DC power supply through a contactor C2, the emergency battery is connected to the first emergency busbar through a contactor C7, the emergency battery is also connected to the second emergency busbar through a contactor C8, the power interface is connected to the first main busbar through a contactor C2, and the power interface is also connected to the second main busbar through a contactor C3. The first switch and the second switch can also be switching devices such as contactors, circuit breakers, and controllable switches. In this embodiment, both the first switch and the second switch are implemented by using contactors. The first main busbar is connected to the second main busbar through a contactor C5, and the first emergency busbar is connected to the second emergency busbar through a contactor C6.

[0069] It can be understood that, based on the first DC power supply supplying power to the first main busbar and the second DC power supply supplying power to the second main busbar, when the first DC power supply fails and the first main busbar loses power, causing the electrical equipment connected thereto to lose power, the contactor C5 between the two main busbars can be closed to connect the two main busbars to each other. At this time, the first main busbar can obtain power from the second DC power supply. When the second DC power supply fails, similarly, the second main busbar can obtain power from the first DC power supply, that is, the main busbar has dual-redundancy power supply. When there are more DC power supplies and more main busbars, the power supply redundancy of each main busbar will be greater, solving the problem of insufficient power supply redundancy of the main busbar and preventing the system from failing due to a single fault.

[0070] It can be understood that, based on the first DC power supply supplying power to the first main busbar and the second DC power supply supplying power to the second main busbar, when the first main busbar fails due to a short circuit and the electrical equipment connected thereto loses power, and the first emergency busbar cannot obtain power from the first main busbar, the contactor C6 between the two emergency busbars can be closed to connect the first emergency busbar to the second emergency busbar, and the first emergency busbar can obtain power from the second main busbar. When the second main busbar fails due to a short circuit, similarly, the second emergency busbar can obtain power from the first main busbar. Optionally, when the first emergency busbar cannot obtain power from the first main busbar, it can also obtain power from the emergency battery. Therefore, the problem of insufficient power supply redundancy of the emergency busbar is also solved.

[0071] In this embodiment, the two main busbars can be connected, and the main busbar has dual-redundancy power supply, so that the electrical equipment connected thereto has dual-redundancy power supply, increasing the power supply redundancy of these devices and improving the safety of the aircraft.

[0072] In a feasible implementation manner, continue to refer to Figure 2 , the system may further include at least two fuses, and each emergency bus bar is connected to the corresponding main bus bar through a fuse.

[0073] It should be noted that the connectable and disconnectable connection can be achieved actively or passively to correspondingly connect the connection when needed or disconnect the connection when needed. In this embodiment, the connectable and disconnectable connection between the emergency bus bar and the main bus bar is realized by using a fuse. Specifically, the first emergency bus bar is connected to the first main bus bar through fuse F1, and the second emergency bus bar is connected to the second main bus bar through fuse F2.

[0074] It can be understood that a contactor C6 is arranged between the two emergency bus bars. Combining fuse F1 and fuse F2, when the first emergency bus bar is short-circuited, the voltage of the first emergency bus bar is pulled down, and the electrical equipment powered by it will lose power. At this time, fuse F1 melts, which will not affect the voltage on the first main bus bar. The electrical equipment powered by the first main bus bar can keep working normally, and the contactor C6 can be disconnected. The electrical equipment powered by the second emergency bus bar and the second main bus bar can also keep working normally, so that only the electrical equipment powered by the first emergency bus bar loses power, and other equipment works normally. This situation will only reduce the flight safety margin of the aircraft, but will not be serious enough to cause the aircraft to crash. Therefore, the single-point failure of the emergency bus bar is avoided.

[0075] In this implementation manner, the two emergency bus bars can be connected. There is a fuse as a protection device between the emergency bus bar and the main bus bar line. When a single emergency bus bar fails, it will not affect the electrical equipment on the other three bus bars, and the aircraft can continue to fly, improving the safety and reliability of the aircraft.

[0076] In a feasible implementation manner, continue to refer to Figure 2 , the system may further include a charger, and the charger can be integrated inside the emergency battery or be self-contained outside.

[0077] It should be noted that when the charger is integrated with the emergency battery, the connection between the power interface and the emergency battery is that one end of the power interface is connected to the emergency battery through the charger, as Figure 2 shown. The other end of the power interface can be directly connected to an external power source. This setting method improves the convenience of the power connection operation during ground maintenance; when the charger is independent of the emergency battery and is self-contained, one end of the power interface can be directly connected to the emergency battery, and the other end of the power interface is connected to the external power source through the charger. This setting method can reduce the weight of the emergency battery, reduce the weight of the entire aircraft, and is more conducive to improving the flight performance of the aircraft.

[0078] In a feasible implementation manner, the DC power supply can be a voltage conversion device, a DC generator, or a battery pack.

[0079] It should be noted that the voltage conversion device refers to a device that obtains electric energy and then converts it into low-voltage direct current for output. For example, a DCDC conversion power supply that obtains high-voltage direct current from a high-voltage distribution box, performs high-voltage DC / DC conversion, and converts the high-voltage direct current into low-voltage direct current for output. Another example is an ACDC conversion power supply that obtains alternating current from an AC power source, performs AC-DC conversion to obtain high-voltage direct current, and then converts the high-voltage direct current into low-voltage direct current for output, or directly converts alternating current into low-voltage direct current for output. In practical applications, it can be selected according to needs, and no specific limitation is made here; the DC generator refers to a generator that can directly generate and output low-voltage direct current; the battery pack refers to a battery pack that can convert alternating current into low-voltage direct current for output or directly provide low-voltage direct current.

[0080] Exemplarily, the DC power supply is a DCDC conversion power supply that converts high-voltage direct current into low-voltage direct current (such as 28 VDC). The DCDC conversion power supply has functions such as output overvoltage protection, undervoltage protection, overcurrent protection, and short-circuit protection. It can detect the voltage of the low-voltage direct current at the front end of the main busbar. When the voltage is too high or too low, the contactor between the DCDC conversion power supply and the main busbar can be actively disconnected to ensure that general electrical equipment on the main busbar is not damaged, achieving the effect of protecting the electrical equipment at the rear end.

[0081] The low-voltage power supply system for an aircraft provided in this embodiment includes at least two DC power sources, at least two main busbars, at least two emergency busbars corresponding to the number of main busbars, an emergency battery, and a power interface. In this system, each main busbar is connected to each DC power source in a switchable manner, and adjacent two main busbars are connected through a first switch, so that each main busbar has redundant power supply. In addition to being powered by its corresponding DC power source, when the DC power source fails, the adjacent two main busbars can be connected by turning on the first switch, and the DC power source connected to the adjacent main busbar supplies power, which improves the power supply reliability of the main busbar. Each emergency busbar is also connected to each main busbar in a switchable manner, and adjacent two emergency busbars are connected through a second switch. The emergency battery is connected to each emergency busbar in a switchable manner, so that each emergency busbar has redundant power supply, including being powered by its corresponding main busbar and the emergency battery, which improves the power supply reliability of the emergency busbar. When a short-circuit fault occurs in a certain emergency busbar, the power-consuming equipment on this emergency busbar can be powered off by disconnecting the corresponding main busbar and the second switch, while other equipment can still work normally, so that only the safety margin of the aircraft is reduced and flight safety accidents such as aircraft crashes will not occur, which improves the power supply safety and flight safety of the system. The power interface is connected to at least one main busbar in a switchable manner, and the power interface is also connected to the emergency battery. The external power supply is used to charge the emergency battery, and the ground power supply can be used alone during ground maintenance without consuming the electric energy of the emergency battery and DC power source on the aircraft, and there is no need to apply high voltage, which avoids the inconvenience to the flight of the aircraft caused by consuming the limited electric energy on the aircraft, improves the safety of ground maintenance, and at the same time, can also reduce the capacity requirement for the emergency battery, thereby reducing the battery weight and improving the effective load performance of the aircraft.

[0082] In another embodiment of the present application, with continued reference to Figure 2 , the system may further include a plurality of unidirectional conduction devices.

[0083] Unidirectional conduction devices are connected between each main busbar and the corresponding emergency busbar to limit the current flow direction from the main busbar to the emergency busbar; unidirectional conduction devices are connected between the emergency battery and each emergency busbar to limit the current flow direction from the emergency battery to the emergency busbar.

[0084] It should be noted that the unidirectional conduction device can be an electronic device such as a diode, thyristor, triac, etc. The diode can include ordinary diodes, Schottky diodes, tunnel diodes, PIN diodes, Zener diodes, etc. Here, an ordinary diode with a lower cost is preferably used, which has the unidirectional conduction characteristic and will not break down reversely.

[0085] Exemplarily, taking the unidirectional conduction device as an ordinary diode as an example, as Figure 2 In the system shown, four unidirectional conduction diodes D1 - D4 can be included. The positive electrode of diode D1 is connected to fuse F1, and the negative electrode of diode D1 is connected to the first emergency busbar; the positive electrode of diode D2 is connected to fuse F2, and the negative electrode of diode D2 is connected to the second emergency busbar; the positive electrode of diode D3 is connected to the emergency battery, and the negative electrode of diode D3 is connected to the first emergency busbar; the positive electrode of diode D4 is connected to the emergency battery, and the negative electrode of diode D4 is connected to the second emergency busbar.

[0086] It can be understood that the diode between the main busbar and the emergency busbar can ensure that while the main busbar supplies power to the electrical equipment on it, it also supplies power to the corresponding emergency busbar, enabling the electrical equipment on the emergency busbar to work properly; it can also prevent the emergency battery from supplying power to the main busbar through the emergency busbar when the DC power supply fails and the emergency battery supplies power to the emergency busbar to ensure the normal operation of the electrical equipment on it, that is, it will not consume extra electrical energy to supply power to the electrical equipment on the main busbar, thus avoiding the rapid consumption of the emergency battery's power and shortening the emergency power supply time of the aircraft. Therefore, this system can ensure the stable operation of the electrical equipment on the emergency busbar in an emergency state, improve the power supply reliability of such electrical equipment, and reduce the capacity requirement for the emergency battery. Furthermore, it can reduce the battery weight and improve the effective payload performance of the aircraft. And the diode between the emergency battery and the emergency busbar can prevent the main busbar from uncontrollably charging the emergency battery through the emergency busbar, resulting in overcharging of the emergency battery, thus keeping the emergency battery in a dangerous state.

[0087] In this embodiment, by utilizing the unidirectional conduction performance of the diode to limit the current flow direction between the main busbar and the emergency busbar and the current flow direction between the emergency battery and the emergency busbar, the power supply reliability of the electrical equipment can be ensured, the capacity requirement for the emergency battery can be reduced, and overcharging of the emergency battery can also be avoided, improving the safety and stability of the system.

[0088] In a feasible embodiment, continue to refer to Figure 2 , in this system, each main busbar is correspondingly connected to the primary electrical equipment, and each emergency busbar is correspondingly connected to the secondary and / or tertiary electrical equipment, where the primary electrical equipment, secondary electrical equipment, and tertiary electrical equipment are classified and determined according to the importance of each electrical equipment based on the operation of the aircraft, from low to high.

[0089] It should be noted that primary electrical equipment refers to general electrical equipment, which may include equipment that improves flight conditions without affecting flight missions and safety; secondary electrical equipment refers to important electrical equipment, which may include equipment necessary for the aircraft to complete flight missions; and tertiary electrical equipment refers to critical electrical equipment, which may include equipment necessary for the safe flight and landing of the aircraft.

[0090] Exemplarily, as Figure 2 shown in the system, the first main busbar and the second main busbar are respectively connected to the primary electrical equipment, the first emergency busbar and the second emergency busbar are respectively connected to the secondary electrical equipment, and the first emergency busbar and the second emergency busbar are also respectively connected to the tertiary electrical equipment.

[0091] In a specific embodiment, with continued reference to Figure 2 , in this system, a switch protection circuit is connected between the main busbar and the primary electrical equipment and between the emergency busbar and the secondary electrical equipment.

[0092] Exemplarily, as Figure 2 shown in the system, a switch protection circuit is connected between the first main busbar and the primary electrical equipment and between the second main busbar and the primary electrical equipment; a switch protection circuit is connected between the first emergency busbar and the corresponding secondary electrical equipment and between the second emergency busbar and the corresponding secondary electrical equipment.

[0093] Among them, the switch protection circuit can be a solid-state power controller (SSPC: Solid-State Power Controller) circuit. The SSPC is used to provide switch on / off, overcurrent protection, and short-circuit protection. When necessary, the SSPC can be turned off to protect the safety of the electrical equipment, improving the power supply reliability and safety of the system.

[0094] In a specific embodiment, with continued reference to Figure 2 , in this system, a safety protection device is connected between the emergency busbar and the tertiary electrical equipment.

[0095] Exemplarily, as Figure 2 shown in the system, a safety protection device is connected between the first emergency busbar and the tertiary electrical equipment and between the second emergency busbar and the tertiary electrical equipment.

[0096] Among them, the safety protection device can be a fuse or a circuit breaker. The fuse can play the role of overcurrent protection and short-circuit protection.

[0097] It can be understood that both the SSPC and the fuse are light in weight, which can avoid increasing the overall weight of the aircraft. For the third-level electrical equipment, using a fuse in the power distribution channel can improve its reliability. For the first-level and second-level electrical equipment, using an SSPC in the power distribution channel can control its on / off and can actively disconnect when necessary to ensure the flight of the aircraft, further improving the reliability and safety of the aircraft.

[0098] The low-voltage power supply system for an aircraft provided in this embodiment can be designed according to the characteristics of the all-electric aircraft and has the characteristics of redundancy, multi-level, high reliability, and light weight.

[0099] Exemplarily, as Figure 3 shown is the system block diagram of a specific example of the low-voltage power supply system. The low-voltage power supply system of this embodiment will be described in detail below with this specific example:

[0100] The electrical equipment is divided into general electrical equipment, important electrical equipment, and critical electrical equipment. Both DC power supplies adopt DCDC conversion power supplies. The two main busbars are defined as the left main busbar and the right main busbar, and the two emergency busbars are defined as the left emergency busbar and the right emergency busbar. The specific connection relationship is combined with the previous description and can be seen in Figure 3 shown, and will not be elaborated here.

[0101] Based on Figure 3 the low-voltage power supply system, two levels of busbars are designed. Each level of busbar has two busbars, namely the left and right main busbars and the left and right emergency busbars. The main busbar can provide dual-redundancy power supply for general electrical equipment from two DCDC conversion power supplies. The emergency busbar can provide triple-redundancy power supply for important electrical equipment and critical electrical equipment from two DCDC conversion power supplies and an emergency battery, improving the power supply redundancy of the electrical equipment and increasing the flight safety of the aircraft.

[0102] During normal operation, the left DCDC conversion power supply and the right DCDC conversion power supply output low-voltage direct current, which are respectively connected to the left and right main busbars through the closed contactors C1 and C4. The left main busbar supplies power to the left general electrical equipment and the left emergency busbar, and the right main busbar supplies power to the right general electrical equipment and the right emergency busbar. That is, the left DCDC conversion power supply supplies power to the left general electrical equipment, the left important electrical equipment, and the left critical electrical equipment, and the right DCDC conversion power supply supplies power to the right general electrical equipment, the right important electrical equipment, and the right critical electrical equipment. At this time, all the electrical equipment of the aircraft has normal power supply.

[0103] When a single DCDC conversion power supply fails, the contactor C5 can be switched on, and all electrical equipment is powered by another DCDC conversion power supply. For example, when the left DCDC conversion power supply fails, the left main busbar loses power, the left general electrical equipment loses power, and the left emergency busbar can only be powered by the emergency battery. Specifically, the emergency battery outputs low-voltage direct current, which is connected to the left emergency busbar through the switched-on contactor C7 to supply power to the left important electrical equipment and the left critical electrical equipment. At this time, the contactor C5 can be closed, and the left and right main busbars are connected to each other. The low-voltage direct current output by the right DCDC conversion power supply can be transmitted to the left main busbar through the right main busbar and the contactor C5. That is, the left main busbar draws power from the right DCDC conversion power supply, the left general electrical equipment resumes power supply, and the power supply of the left emergency busbar is switched from the emergency battery to the left main busbar. At this time, the right DCDC conversion power supply supplies power to all electrical equipment. Similarly, when the right DCDC conversion power supply fails, the contactor C5 can also be closed to make the right main busbar draw power from the left DCDC conversion power supply, and the left DCDC conversion power supply supplies power to all electrical equipment. This ensures the dual-redundancy power supply provided by the main busbar to the general electrical equipment and the emergency busbar.

[0104] When any main busbar fails, such as when the left main busbar is short-circuited, the corresponding left general electrical equipment loses power, and the left emergency busbar loses one power supply redundancy, resulting in a reduction in the power supply redundancy of the left important electrical equipment and the left critical electrical equipment. However, by disconnecting the first switch connected between the two main busbars, that is, the contactor C5, the right general electrical equipment, the right important electrical equipment, and the right critical electrical equipment can be kept working normally, thus avoiding the crash of the aircraft. Therefore, the overall safety of the aircraft can be prevented from being reduced.

[0105] Based on Figure 3 In the low-voltage power supply system, the left emergency busbar is powered by the left main busbar and the emergency battery, and the right emergency busbar is powered by the right main busbar and the emergency battery. The two emergency busbars are connected by a contactor C6. The left emergency busbar supplies power to the left important electrical equipment and the left critical electrical equipment, and the right emergency busbar supplies power to the right important electrical equipment and the right critical electrical equipment.

[0106] When the left main busbar fails, or fuse F1 fails, or diode D1 fails, the left emergency busbar is powered by the emergency battery. Due to the capacity limitation of the emergency battery, the operating time of the left important electrical equipment and the left critical electrical equipment will be shorter. At this time, contactor C6 can be closed, and the left and right emergency busbars are connected to each other, so that the left emergency busbar draws power from the right main busbar through the right emergency busbar. The right main busbar is powered by the right DCDC conversion power supply. At this time, the right DCDC conversion power supply supplies power to all electrical equipment. Similarly, when the right main busbar fails, or fuse F2 fails, or diode D2 fails, contactor C6 is closed, and the right emergency busbar can also draw power from the left main busbar, so that the left DCDC conversion power supply supplies power to all electrical equipment. This ensures a triple-redundancy power supply provided by the emergency busbar to the critical electrical equipment and the important electrical equipment.

[0107] When any emergency busbar fails, such as when the left emergency busbar is short-circuited, the corresponding left critical electrical equipment and left important electrical equipment lose power. However, the second switch, i.e., contactor C6, connected between the two emergency busbars can be opened, so that the right important electrical equipment and right critical electrical equipment can operate normally, thus avoiding the crash of the aircraft. Therefore, the safety of the aircraft can be guaranteed. In addition, when the left emergency busbar is short-circuited, the voltage of the left emergency busbar is pulled down, and the left important electrical equipment and left critical electrical equipment lose power. Fuse F1 blows, which does not affect the voltage on the left main busbar, and thus does not affect the operation of the left general electrical equipment. That is, only the left important electrical equipment and left critical electrical equipment lose power at this time, and other equipment operates normally. When the right emergency busbar is short-circuited, the situation is the same, which will not be elaborated here.

[0108] As Figure 3 shown, in this example, a ground power supply is connected to the power supply interface. The ground power supply is connected to the left and right main busbars through contactors C2 and C3 respectively. During ground maintenance, the ground power supply can be used to supply power to all electrical equipment on the aircraft without applying high voltage, ensuring the safety of the maintenance personnel's operating environment and not consuming the low-voltage electrical energy (including the electrical energy of the emergency battery) and high-voltage electrical energy on the aircraft, which is convenient for ground maintenance of the aircraft. Moreover, the ground power supply can be used to charge the emergency battery through a charger, which does not consume the high-voltage electrical energy on the aircraft and can also save the charging time of the emergency battery.

[0109] Based on the above specific description, it is sufficient to prove that the low-voltage power supply system of this embodiment indeed has the effects of improving the power supply redundancy of the main busbar, adding an emergency busbar to avoid single-point failures, and not consuming the electrical energy of the aircraft and ensuring the safety of ground maintenance operations during ground maintenance.

[0110] This application also proposes a low-voltage power supply control method for an aircraft, which can be applied to the low-voltage power supply system in any of the above embodiments.

[0111] In one embodiment, the low-voltage power supply system specifically includes at least two DC power supplies, at least two main busbars, at least two emergency busbars corresponding to the number of main busbars, a plurality of electrical equipment respectively connected to each main busbar and each emergency busbar, at least one emergency battery, and a power interface connected to the emergency battery; Refer to Figure 4 , Figure 4 FIG.

[0112] is a schematic flow chart of a low-voltage power supply control method for an aircraft. The low-voltage power supply control method may include steps S100 to S310:

[0113] It should be noted that the control device that executes this control method may be independent of the low-voltage power supply system, or may be a control module or controller configured inside the low-voltage power supply system. The execution entity may be specifically connected to switch devices, modules, or devices that can be connected and disconnected to different components in the low-voltage power supply system, and perform on-off control on these switches to adjust different working modes of the low-voltage power supply system.

[0114] In the low-voltage power supply system, a device for detecting the system state or a device for manually adjusting the system state by the user may also be configured, which may include fault detection of each component in the system and on-off detection of each connection state. The system state may include a normal working state, a ground maintenance state, a fault emergency state, etc. Among them, the fault emergency state may be specifically divided into multiple specific fault state detection results according to different detected fault situations, which are not specifically limited here.

[0115] Step S210, in the normal working state of the low-voltage power supply system, control the first switch between adjacent two main busbars and the second switch between adjacent two emergency busbars to be disconnected;

[0116] Step S220, control each main busbar to be connected to the corresponding DC power supply one by one, so that each DC power supply supplies power to the corresponding connected electrical equipment through the corresponding main busbar;

[0117] Step S230, control the connection between each emergency busbar and the emergency battery to be disconnected, and control each emergency busbar to be connected to the corresponding main busbar one by one, so that each main busbar supplies power to the corresponding connected electrical equipment through the corresponding emergency busbar.

[0118] It should be noted that each main bus bar is connected to each DC power supply in a one-to-one and switchable manner, and adjacent two main bus bars are connected through a first switch; each emergency bus bar is connected to each main bus bar in a one-to-one and switchable manner, and adjacent two emergency bus bars are connected through a second switch; the emergency battery is connected to each emergency bus bar in a switchable manner; the power interface is connected to at least one main bus bar in a switchable manner and is also connected to the emergency battery. On this premise, when the system status detection information is an instruction to switch to the normal working state, that is, when it is necessary to control the low-voltage power supply system to enter the normal working state, the first switch and the second switch can be controlled to be disconnected, each main bus bar is connected to each DC power supply, each emergency bus bar is connected to each main bus bar, the connection between the emergency bus bar and the emergency battery is disconnected, and of course, the connection between the main bus bar and the power interface is also disconnected. In this way, the DC power supply supplies power to the general electrical equipment connected thereto through the main bus bar, and the DC power supply supplies power to the important electrical equipment and key electrical equipment connected thereto through the main bus bar and the emergency bus bar.

[0119] Exemplarily, referring to the Figure 2 low-voltage power supply system shown, in the normal working state of the low-voltage power supply system, control C2, C3, C5, C6, C7 and C8 to be disconnected, and control C1 and C4 to be connected, that is, the first DC power supply is connected to the first main bus bar, the second DC power supply is connected to the second main bus bar, and the fuses F1 and F2 work normally, that is, the first main bus bar is connected to the first emergency bus bar, and the second main bus bar is connected to the second emergency bus bar. At this time, all electrical equipment can work normally.

[0120] Step S310, in the ground maintenance state of the low-voltage power supply system, when the power interface is connected to an external power supply, control the power interface to be connected to at least one main bus bar corresponding to it, and control the connection between at least one main bus bar and the corresponding DC power supply to be disconnected, so that the external power supply supplies power to at least one main bus bar and the corresponding emergency bus bar, and the external power supply charges the emergency battery.

[0121] It should be noted that when the system status detection information is an instruction to switch to the ground maintenance state, that is, when it is necessary to control the low-voltage power supply system to enter the ground maintenance state, after connecting the external power supply to the power interface, for the main busbar that has a switchable connection relationship with the power interface, it may be one main busbar or all the main busbars. However many there are, for at least one main busbar that is switchably connected to the power interface, the connection between the at least one main busbar and its corresponding DC power supply can be controlled to be disconnected, and the at least one main busbar can be controlled to be connected to the power interface, so that the external power supply supplies power to the at least one main busbar, and the at least one main busbar supplies power to the corresponding emergency busbar one by one. Thus, the electrical equipment on the at least one main busbar and the electrical equipment on the emergency busbar no longer consume the electrical energy of the DC power supply. The external power supply can not only supply power to the electrical equipment that needs to remain in the working state during ground maintenance, but also charge the emergency battery. For specific details, reference can be made to the description of the foregoing embodiments, which will not be elaborated here.

[0122] Exemplarily, referring to the Figure 2 low-voltage power supply system shown, in the ground maintenance state of the low-voltage power supply system, control C1, C4, C5, C6, C7, and C8 to be disconnected, control C2 and C3 to be connected, and F1 and F2 work normally. At this time, the power supply for all electrical equipment comes from the external power supply connected to the power interface. Optionally, if only the second main busbar has a switchable connection relationship with the power interface, and the first main busbar only has a switchable connection with the first DC power supply, during ground maintenance, the first switch such as Figure 2 C5 can be controlled to be connected, so that the external power supply supplies power to the corresponding first-level electrical equipment through C3 and the second main busbar, supplies power to the corresponding first-level electrical equipment through C3, the second main busbar, and the first main busbar in sequence, supplies power to the corresponding second-level and third-level electrical equipment through C3, the second main busbar, F2, and the second emergency busbar in sequence, and supplies power to the corresponding second-level and third-level electrical equipment through C3, the second main busbar, the first main busbar, F1, and the first emergency busbar in sequence. At this time, the power supply for all electrical equipment also comes from the external power supply.

[0123] It should be noted that this step S310 can be directly executed after step S100 to directly control the system working mode, or can be executed after executing steps S210 - S230 to realize the switching control of the system working mode. No specific limitation is made here.

[0124] In a specific implementation manner, the multiple electrical equipment in the low-voltage power supply system may include first-level electrical equipment, second-level electrical equipment, and third-level electrical equipment determined by dividing the levels from low to high according to the importance of each electrical equipment based on the operation of the aircraft.

[0125] Step S220 may include: controlling each main bus bar to be connected to a corresponding DC power supply one by one, so that each DC power supply supplies power to the first-level electrical equipment connected correspondingly through the corresponding main bus bar;

[0126] Step S230 may include: controlling each emergency bus bar to be normally connected to a corresponding main bus bar one by one, so that each main bus bar supplies power to the second-level electrical equipment and the third-level electrical equipment connected correspondingly through the corresponding emergency bus bar respectively.

[0127] For the low-voltage power supply control method for an aircraft provided in this embodiment, in the normal working state of the low-voltage power supply system, the first switch between two adjacent main bus bars and the second switch between two adjacent emergency bus bars are controlled to be disconnected, and the main bus bar is controlled to be connected to the DC power supply, so that the DC power supply supplies power to the electrical equipment connected correspondingly through the main bus bar. It also controls the connection between the emergency bus bar and the emergency battery to be disconnected, and the emergency bus bar is connected to the main bus bar, so that the main bus bar supplies power to the electrical equipment connected correspondingly through the emergency bus bar, and at least two groups of independent power supplies can be provided to multiple electrical equipment respectively to ensure the stable operation of the system; the first switch and the second switch can be turned on and off as needed, so that each main bus bar and emergency bus bar have redundant power supplies, improving the power supply reliability; in the ground maintenance state of the low-voltage power supply system, when the power interface is connected to an external power supply, the power interface is controlled to be connected to the main bus bar, and the connection between the main bus bar and the DC power supply is controlled to be disconnected, so that the external power supply supplies power to the main bus bar and the corresponding emergency bus bar, and the external power supply is used to charge the emergency battery. It can use the ground power supply alone during ground maintenance without consuming the electrical energy of the emergency battery and the DC power supply on the aircraft, and without applying high voltage, avoiding the inconvenience to the flight of the aircraft caused by consuming the limited electrical energy on the aircraft, improving the safety of ground maintenance. At the same time, it can also reduce the capacity requirement for the emergency battery, thereby reducing the battery weight and improving the effective load performance of the aircraft.

[0128] In another embodiment, the low-voltage power supply control method for an aircraft may further include steps S411 to S412:

[0129] Step S411, when it is detected that any one of at least two DC power supplies fails, controlling the connection between the faulty DC power supply and the corresponding main bus bar to be disconnected;

[0130] Step S412, controlling the first switch between the main bus bar corresponding to the faulty DC power supply and the adjacent main bus bar to be closed, so that the adjacent DC power supply corresponding to the adjacent main bus bar supplies power to the main bus bar corresponding to the faulty DC power supply through the adjacent main bus bar and the first switch.

[0131] It should be noted that each main busbar in the low-voltage power supply system has redundant power supply. When a certain DC power supply fails, the connection between the faulty DC power supply and its corresponding main busbar can be controlled to be disconnected, and the first switch between the main busbar corresponding to the faulty DC power supply and the adjacent main busbar can be controlled to close; at this time, the second switch can remain open, and the main busbar corresponding to the faulty DC power supply and the adjacent main busbar are both powered by the adjacent DC power supply. The main busbar corresponding to the faulty DC power supply, its corresponding emergency busbar, the adjacent main busbar, and the electrical equipment connected to their corresponding emergency busbars are all powered, that is, all electrical equipment is powered, so as to keep all electrical equipment working normally.

[0132] Exemplarily, referring to the low-voltage power supply system as Figure 2 shown, when the first DC power supply fails, C1 can be controlled to open and C5 to close. The second DC power supply supplies power to the right-side primary electrical equipment connected thereto through C4 and the second main busbar, supplies power to the left-side primary electrical equipment connected thereto through C4, the second main busbar, C5, and the first main busbar, supplies power to the right-side secondary and tertiary electrical equipment connected thereto through C4, the second main busbar, F2, and the second emergency busbar, and also supplies power to the left-side secondary and tertiary electrical equipment connected thereto through C4, the second main busbar, C5, the first main busbar, F1, and the first emergency busbar. All electrical equipment can work normally.

[0133] In a feasible implementation manner, the low-voltage power supply system may further include a plurality of unidirectional conduction devices. Each main busbar is connected to the corresponding emergency busbar through the unidirectional conduction device, which is used to limit the current flow direction to be from the main busbar to the emergency busbar; correspondingly, the low-voltage power supply control method for the aircraft may further include steps S421 to S422:

[0134] Step S421, when any main busbar among at least two main busbars is detected to fail, control the connection between the faulty main busbar and the corresponding DC power supply to be disconnected;

[0135] Step S422, control the second switch between the emergency busbar corresponding to the faulty main busbar and the adjacent emergency busbar to close, so that the adjacent DC power supply corresponding to the adjacent emergency busbar supplies power to the emergency busbar corresponding to the faulty main busbar through the corresponding adjacent main busbar, adjacent emergency busbar, and the second switch.

[0136] It should be noted that each emergency busbar in the low-voltage power supply system has redundant power supply. When a certain main busbar fails, the connection between the faulty main busbar and its corresponding DC power supply can be controlled to be disconnected, and the second switch between the emergency busbar corresponding to the faulty main busbar and the adjacent emergency busbar can be controlled to close. At this time, the first switch can remain open. The emergency busbar corresponding to the faulty main busbar and the adjacent emergency busbar are both powered by the adjacent main busbar, and the adjacent main busbar is powered by the corresponding adjacent DC power supply. That is, there will be no current on the faulty main busbar, and its corresponding DC power supply will not work either. The emergency busbar corresponding to the faulty main busbar, the adjacent main busbar, and its corresponding adjacent emergency busbar all have power supply. That is, except for the electrical equipment connected to the faulty main busbar without power supply, other electrical equipment all have power supply, so that the normal operation of most equipment can be maintained.

[0137] Exemplarily, referring to the low-voltage power supply system as Figure 2 shown, when a short-circuit fault occurs in the first main busbar and the voltage of the first main busbar is pulled down, C1 can be controlled to disconnect and C6 to close. The second DC power supply supplies power to the right-side primary electrical equipment connected thereto through C4 and the second main busbar, supplies power to the right-side secondary and tertiary electrical equipment connected thereto through C4, the second main busbar, F2, and the second emergency busbar, and also supplies power to the left-side secondary and tertiary electrical equipment connected thereto through C4, the second main busbar, F2, the second emergency busbar, C6, and the first emergency busbar. At this time, because the first main busbar is connected to the first emergency busbar through the diode D1 and the diode D1 conducts unidirectionally, the current on the first emergency busbar will not flow back to the first main busbar. Therefore, except for the left-side primary electrical equipment without power supply, most other equipment has power supply, and most electrical equipment can operate normally. In particular, the important and critical electrical equipment corresponding to the two emergency busbars can ensure normal operation.

[0138] In another feasible implementation manner, the low-voltage power supply system may further include a plurality of unidirectional conduction devices. Each main busbar is connected to the corresponding emergency busbar through the unidirectional conduction device to limit the current flow direction to be from the main busbar to the emergency busbar. Correspondingly, the low-voltage power supply control method for the aircraft may further include steps S431 to S432:

[0139] Step S431, when it is detected that one or more of at least two DC power supplies fail and / or one or more of at least two main busbars fail, control the connection between the faulty DC power supply and the corresponding main busbar to be disconnected, and / or control the connection between the faulty main busbar and the corresponding DC power supply to be disconnected;

[0140] Step S432: Control the emergency bus corresponding to the faulty DC power supply and / or the faulty main bus to be connected to the emergency battery, so that the emergency battery supplies power to the emergency bus corresponding to the faulty DC power supply and / or the faulty main bus respectively.

[0141] It should be noted that when one or more DC power supply faults, one or more main bus faults, or one or more DC power supply faults and one or more main bus faults are detected, the connection between the faulty DC power supply and the corresponding main bus can be controlled to be disconnected, or the connection between the faulty main bus and the corresponding DC power supply can be controlled to be disconnected. At the same time, control the emergency bus corresponding to the faulty DC power supply or the faulty main bus to be connected to the emergency battery; at this time, the first switch and the second switch can remain disconnected. The main bus corresponding to the faulty DC power supply has no power supply, and the faulty main bus has no power supply. However, the emergency bus corresponding to the faulty DC power supply and / or the faulty main bus is powered by the emergency battery. The complete subsystem where the DC power supply and the main bus have no faults can maintain normal operation. Except for the electrical equipment connected to the main bus corresponding to the faulty DC power supply and the electrical equipment connected to the faulty main bus having no power supply, other electrical equipment has power supply, and the normal operation of important equipment and key equipment can be maintained. At the same time, because each main bus is connected to each emergency bus through a unidirectional conduction device, when the emergency battery supplies power to the emergency bus, the current on the emergency bus will not flow to the main bus. That is, in the subsystem powered by the emergency battery, general electrical equipment has no power supply, and important and key electrical equipment can operate normally.

[0142] Exemplarily, referring to the low-voltage power supply system as Figure 2 shown, when the first DC power supply and the second DC power supply faults, or the first main bus and the second main bus faults are detected, C1 and C4 can be controlled to be disconnected, and C5 and C6 can be controlled to be disconnected. Since there is no current on the main bus, the emergency bus cannot obtain power from the main bus. At this time, C7 and C8 can be controlled to be connected, and the first emergency bus and the second emergency bus are both powered by the emergency battery, and the corresponding connected left-side secondary and tertiary electrical equipment and right-side secondary and tertiary electrical equipment all have power supply. At this time, due to the unidirectional conduction function of diode D1 and diode D2, the current of the first emergency bus will not flow to the first main bus, and the current of the second emergency bus will not flow to the second main bus. Therefore, except for the left and right first-level electrical equipment having no power supply, other second-level and third-level electrical equipment all have power supply, that is, all important and key electrical equipment can operate normally, ensuring the flight safety of the aircraft.

[0143] It should be noted that the above steps S411-412, steps S421-422, and steps S431-432 can be directly executed after step S100 respectively to achieve direct control of the system working mode, or can be executed after executing steps S210-S230 to achieve switching control of the system working mode. Specifically, they are emergency measures for faults detected during the normal operation of the system, that is, switching from the normal working state to the emergency state for faults, and no specific limitation is made here.

[0144] In a feasible implementation, the low-voltage power supply control method for the aircraft may further include step S510:

[0145] Step S510, when it is detected that any one of at least two emergency busbars fails, control the disconnection of the connection between the faulty emergency busbar and the corresponding main busbar, or automatically disconnect through the fuse between the faulty emergency busbar and the corresponding main busbar.

[0146] It should be noted that when the connection between the main busbar and the emergency busbar is realized by a controllable switch for on-off connection, specifically control the disconnection of the connection between the faulty emergency busbar and the corresponding main busbar, and the disconnection at this time is passive disconnection; when the connection between the main busbar and the emergency busbar is a fuse connection, then the connection between the faulty emergency busbar and the corresponding main busbar can be disconnected by the automatic disconnection of the fuse, and the disconnection at this time is active disconnection. At this time, the connection between the faulty emergency busbar and the emergency battery remains disconnected, but the main busbar corresponding to the faulty emergency busbar can still be powered by the corresponding DC power supply. Except for the electrical equipment connected to the faulty emergency busbar without power supply, other electrical equipment has power supply, and most equipment can maintain normal operation.

[0147] Exemplarily, referring to the Figure 2 low-voltage power supply system shown, when it is detected that the first emergency busbar fails, F1 fuses due to overcurrent caused by the fault. At this time, C5 and C6 can remain disconnected. Except for the electrical equipment connected to the first emergency busbar without power supply, the electrical equipment connected to the first main busbar, the second main busbar, and the second emergency busbar all have power supply.

[0148] It can be understood that when a short-circuit fault occurs in a certain emergency busbar, by disconnecting the corresponding main busbar and disconnecting the second switch, the electrical equipment on the emergency busbar loses power, while other equipment can maintain normal operation, so that only the safety margin of the aircraft is reduced and no flight safety accidents such as the crash of the aircraft will occur, improving the power supply safety and flight safety of the system.

[0149] It should be noted that the specific structure of the low-voltage power supply system in the low-voltage power supply control method for an aircraft and the beneficial effects that can be brought can be referred to the embodiments of the above low-voltage power supply system. Since this low-voltage power supply control method can adopt all the technical solutions of the above embodiments of the low-voltage power supply system, it has at least all the beneficial effects brought by the technical solutions of the above embodiments, and will not be elaborated one by one here.

[0150] This application also proposes an aircraft. The aircraft includes a low-voltage power supply system for the aircraft. Among them, this low-voltage power supply system can implement the low-voltage power supply control method for the aircraft in the above embodiments.

[0151] It should be noted that the specific structure of the low-voltage power supply system for the aircraft refers to the above embodiments. Since this aircraft adopts all the technical solutions of the above embodiments, it has at least all the beneficial effects brought by the technical solutions of the above embodiments, and will not be elaborated one by one here.

[0152] This application also proposes a storage medium, specifically a computer-readable storage medium, with computer-readable program instructions (i.e., computer programs) stored thereon. The computer-readable program instructions are used to execute the steps of the low-voltage power supply control method for the aircraft in the above embodiments.

[0153] The computer-readable storage medium provided by this application can be, for example, a USB flash drive, but is not limited to electrical, magnetic, optical, electromagnetic, infrared, or semiconductor systems or devices, or any combination of the above. More specific examples of the computer-readable storage medium may include, but are not limited to: portable computer disks with electrical connections of one or more wires, hard disks, random access memory (RAM), read-only memory (ROM), erasable programmable read-only memory (EPROM) or flash memory, optical fibers, portable compact disk read-only memory (CD-ROM), optical storage devices, magnetic storage devices, and so on, or any suitable combination of the above. In this embodiment, the computer-readable storage medium can be any tangible medium that contains or stores a program, which can be used by an instruction execution system or device, or both in combination. The program code contained on the computer-readable storage medium can be transmitted by any appropriate medium, including but not limited to: wires, optical cables, RF (Radio Frequency), and so on, or any suitable combination of the above.

[0154] The computer-readable storage medium provided by the present application stores computer-readable program instructions (i.e., computer programs) for executing the above-mentioned low-voltage power supply control method for an aircraft. Its beneficial effects are the same as those of the low-voltage power supply control method for an aircraft provided in the above embodiments, and will not be elaborated here.

[0155] The above are only partial embodiments of the present application, and do not limit the patent scope of the present application. Any equivalent structural transformation made by using the content of the specification and drawings of the present application under the technical concept of the present application, or any direct / indirect application in other related technical fields, is included in the patent protection scope of the present application.

Claims

1. A low voltage power supply control method for an aircraft, characterized in that: The method is applied to a low-voltage power supply system, which includes at least two DC power supplies, at least two main bus bars, at least two emergency bus bars corresponding to the number of the main bus bars, a plurality of electrical devices respectively connected to the main bus bars and the emergency bus bars, at least one emergency battery, and a power supply interface connected to the emergency battery; the method includes: Under the normal working state of the low-voltage power supply system, controlling the first switch between two adjacent main bus bars and the second switch between two adjacent emergency bus bars to be disconnected; Controlling each of the main bus bars to be connected to each of the corresponding DC power supplies, so that each of the DC power supplies supplies power to the corresponding connected electrical equipment through the corresponding main bus bar; Controlling the connection between each of the emergency bus bars and the emergency battery to be disconnected, and controlling each of the emergency bus bars to be connected to the corresponding main bus bars, so that each of the main bus bars supplies power to the correspondingly connected electrical equipment through the corresponding emergency bus bars; In the ground maintenance state of the low-voltage power supply system, when the power interface is connected to an external power supply, the power interface is controlled to be connected to at least one corresponding main bus, and the connection between the at least one main bus and the corresponding DC power supply is controlled to be disconnected, so that the external power supply supplies power to the at least one main bus and the corresponding emergency bus, and the external power supply charges the emergency battery.

2. The low voltage power supply control method for an aircraft according to claim 1, characterized in that: The method further comprises: When a fault of any one of the at least two DC power supplies is detected, controlling the faulty DC power supply to be disconnected from the corresponding main bus bar; The first switch between the main bus corresponding to the faulty DC power supply and the adjacent main bus is controlled to be closed, so that the adjacent DC power supply corresponding to the adjacent main bus supplies power to the main bus corresponding to the faulty DC power supply through the adjacent main bus and the first switch.

3. The low voltage power supply control method for an aircraft according to claim 1, characterized in that: The system further comprises a plurality of unidirectional conducting devices, each of the main bus bars is connected to the corresponding emergency bus bar through the unidirectional conducting device, and is used to limit the current flow direction to flow from the main bus bar to the emergency bus bar; The method further comprises: When a fault is detected in any one of the at least two main bus bars, controlling the faulty main bus bar to be disconnected from the corresponding DC power supply; The second switch between the emergency bus corresponding to the faulty main bus and the adjacent emergency bus is controlled to close, so that the adjacent DC power supply corresponding to the adjacent emergency bus supplies power to the emergency bus corresponding to the faulty main bus through the corresponding adjacent main bus, the adjacent emergency bus and the second switch.

4. The low voltage power supply control method for an aircraft according to claim 1, characterized in that: The system further comprises a plurality of unidirectional conducting devices, each of the main bus bars is connected to the corresponding emergency bus bar through the unidirectional conducting device, and is used to limit the current flow direction to flow from the main bus bar to the emergency bus bar; The method further comprises: When it is detected that one or more of the at least two DC power supplies fail and / or one or more of the at least two main bus bars fail, controlling the failed DC power supply to be disconnected from the corresponding main bus bar, and / or controlling the failed main bus bar to be disconnected from the corresponding DC power supply; The faulty DC power supply and / or the emergency bus bar corresponding to the faulty main bus bar are controlled to be connected to the emergency battery, so that the emergency battery supplies power to the faulty DC power supply and / or the emergency bus bar corresponding to the faulty main bus bar respectively.

5. The low voltage power supply control method for an aircraft according to claim 1, characterized in that: The method further comprises: When a fault of any one of the at least two emergency bus bars is detected, the faulty emergency bus bar is controlled to be disconnected from the corresponding main bus bar, or a fuse between the faulty emergency bus bar and the corresponding main bus bar is automatically disconnected.

6. The low voltage power supply control method for an aircraft according to any one of claims 1 to 5, characterized in that: The plurality of electrical consumers include primary electrical consumers, secondary electrical consumers and tertiary electrical consumers, which are graded from low to high according to the importance of each electrical consumer based on the work of the aircraft; The controlling each of the main bus bars to be connected to each of the corresponding DC power supplies so that each of the DC power supplies supplies power to the corresponding connected electrical equipment through the corresponding main bus bar comprises: Controlling each of the main bus bars to be connected to each of the corresponding DC power supplies, so that each of the DC power supplies supplies power to the correspondingly connected primary power-consuming equipment through the corresponding main bus bar; Controlling each of the emergency bus bars to be connected to each of the corresponding main bus bars so that each of the main bus bars supplies power to the correspondingly connected electrical equipment through the corresponding emergency bus bar, comprising: Each of the emergency bus bars is controlled to be normally connected with each of the corresponding main bus bars, so that each of the main bus bars supplies power to the correspondingly connected secondary power-consuming equipment and the tertiary power-consuming equipment through the corresponding emergency bus bars.

7. A low voltage power supply system for an aircraft, characterized in that: It includes at least two DC power supplies, at least two main bus bars, at least two emergency bus bars corresponding to the number of the main bus bars, and at least one emergency battery and power supply interface; Among them, each of the main buses can be connected and disconnected with each of the DC power supplies in a one-to-one correspondence, and two adjacent main buses are connected through a first switch; each of the emergency buses can be connected and disconnected with each of the main buses in a one-to-one correspondence, and two adjacent emergency buses are connected through a second switch; the emergency battery can be connected and disconnected with each of the emergency buses; the power interface can be connected and disconnected with at least one main bus, and the power interface is used to connect an external power supply. When the power interface is connected to an external power supply, the external power supply is used to power at least one main bus, and the power interface is also connected to the emergency battery so that the emergency battery can be charged by the external power supply.

8. The low voltage power supply system for an aircraft according to claim 7, characterized in that: The at least two DC power supplies include a first DC power supply and a second DC power supply, the at least two main bus bars include a first main bus bar and a second main bus bar, and the at least two emergency bus bars include a first emergency bus bar and a second emergency bus bar; Among them, the first main bus is connectable and disconnectable to the first DC power supply, the second main bus is connectable and disconnectable to the second DC power supply, and the first main bus is connected to the second main bus through the first switch; the first emergency bus is connectable and disconnectable to the first main bus, the second emergency bus is connectable and disconnectable to the second main bus, and the first emergency bus is connected to the second emergency bus through the second switch; the emergency battery is connectable and disconnectable to the first emergency bus and the second emergency bus respectively; the power interface is connectable and disconnectable to the first main bus and the second main bus respectively.

9. The low voltage power supply system for an aircraft according to claim 7, characterized in that: The system further comprises at least two fuses, each of the emergency bus bars being connected to the corresponding main bus bar via the fuse; and / or, The system further comprises a charger, which is integrated inside the emergency battery or is independently arranged outside the emergency battery; and / or, The DC power source is a voltage conversion device, a DC generator or a battery pack.

10. The low voltage power supply system for an aircraft according to claim 7, characterized in that: The system also includes a plurality of unidirectional conductive devices; The unidirectional conductive device is connected between each of the main bus bars and the corresponding emergency bus bar, and is used to limit the current flow from the main bus bar to the emergency bus bar.

11. The low voltage power supply system for an aircraft according to claim 10, characterized in that: The unidirectional conductive device is connected between the emergency battery and each of the emergency bus bars, and is used to limit the current flow from the emergency battery to the emergency bus bars.

12. The low voltage power supply system for an aircraft according to any one of claims 7 to 11, characterized in that: Each of the main buses is connected to a corresponding primary power consumer, and each of the emergency buses is connected to a corresponding secondary and / or tertiary power consumer, wherein the primary power consumers, the secondary power consumers and the tertiary power consumers are graded from low to high according to the importance of each power consumer based on the operation of the aircraft.

13. The low voltage power supply system for an aircraft according to claim 12, characterized in that: A switch protection circuit is connected between the main bus bar and the primary power-consuming equipment and between the emergency bus bar and the secondary power-consuming equipment; and / or, A safety protection device is connected between the emergency bus bar and the third-level electrical equipment.

14. The low voltage power supply system for an aircraft according to claim 13, characterized in that: The switch protection circuit is a solid-state power controller circuit; and / or, The safety protection device is a fuse or a circuit breaker.

15. An aviation vehicle, characterized in that: The low voltage power supply system for an aircraft comprises the low voltage power supply system for an aircraft according to any one of claims 7 to 14.

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