Low-voltage power supply system for aircraft and aviation aircraft

Abstract

The utility model discloses a low-voltage power supply system for an aircraft and the aircraft, and relates to the field of aircrafts, and the system comprises at least two direct-current power supplies, at least two main bus bars, at least two emergency bus bars corresponding to the main bus bars in number, an emergency battery and a power interface. The main bus bars and the direct-current power supplies are connected in a one-to-one correspondence and on-off mode, and every two adjacent main bus bars are connected through a first switch; the emergency bus bars and the main bus bars are in one-to-one correspondence on-off connection, and every two adjacent emergency bus bars are connected through a second switch; the emergency battery is in on-off connection with each emergency bus bar; the power interface is in on-off connection with the at least one main bus bar, the power interface is used for being connected with an external power supply, and the power interface is further connected with the emergency battery so that the external power supply can be used for charging 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] The present application relates to the technical field of aviation aircraft, in particular to a low-voltage power supply system for an aircraft and an aviation aircraft. BACKGROUND

[0002] The low-voltage power supply system of the aviation aircraft is a system for providing low-voltage direct current to various electrical equipment. 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 problem of the low-voltage power supply system is that the power supply redundancy of the main bus bar and the emergency bus bar is insufficient, resulting in low power supply reliability. If a system failure occurs, important equipment will be powered off and fail, which will also affect flight safety. In addition, when the ground is maintained, the electrical energy on the aircraft is consumed, which limits the use of the aircraft, and the safety of ground maintenance is low. CONTENT OF THE UTILITY MODEL

[0003] The main purpose of the present application is to provide a low-voltage power supply system for an aircraft and an aviation aircraft, which aims to solve the technical problems of low power supply reliability of the aircraft in the related art, affecting flight safety, and low safety of ground maintenance.

[0004] To achieve the above-mentioned purpose, the present application provides a low-voltage power supply system for an aircraft, comprising at least two direct current power supplies, at least two main bus bars, at least two emergency bus bars corresponding to the number of main bus bars, an emergency battery and a power supply interface;

[0005] Wherein, each main bus bar is connected to each direct current power supply in a one-to-one 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 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 one-to-one manner. The power supply interface is connected to at least one main bus bar in a one-to-one manner, and the power supply interface is used to connect an external power supply. The power supply interface is also connected to the emergency battery to charge the emergency battery with the external power supply.

[0006] In an embodiment, the at least two direct current power supplies include a first direct current power supply and a second direct current 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.

[0007] The first main bus bar is connected with the first DC power source in an on-off manner, the second main bus bar is connected with the second DC power source in an on-off manner, the first main bus bar is connected with the second main bus bar through the first switch, the first emergency bus bar is connected with the first main bus bar in an on-off manner, the second emergency bus bar is connected with the second main bus bar in an on-off manner, the first emergency bus bar is connected with the second emergency bus bar through the second switch, the emergency battery is connected with the first emergency bus bar and the second emergency bus bar in an on-off manner, and the power interface is connected with the first main bus bar and the second main bus bar in an on-off manner.

[0008] In an embodiment, the system further comprises at least two fuses;

[0009] Each emergency bus bar is connected with the corresponding main bus bar through a fuse.

[0010] In an embodiment, the system further comprises a plurality of unidirectional conduction devices;

[0011] A unidirectional conduction device is connected between each main bus bar and the corresponding emergency bus bar, for limiting the current flow direction to be from the main bus bar to the emergency bus bar.

[0012] In an embodiment, a unidirectional conduction device is connected between the emergency battery and each emergency bus bar, for limiting the current flow direction to be from the emergency battery to the emergency bus bar.

[0013] In an embodiment, the unidirectional conduction device is a diode.

[0014] In an embodiment, the system further comprises a charger, which is integrated inside the emergency battery or is self-contained outside.

[0015] In an embodiment, each main bus bar is connected with a primary power-consuming device, each emergency bus bar is connected with a secondary power-consuming device, and each emergency bus bar is further connected with a tertiary power-consuming device, wherein the primary power-consuming device, the secondary power-consuming device and the tertiary power-consuming device are classified and determined according to the importance of each power-consuming device based on the working of the aircraft.

[0016] In an embodiment, a switch protection circuit is connected between each main bus bar and the primary power-consuming device, and between each emergency bus bar and the secondary power-consuming device.

[0017] In an embodiment, the switch protection circuit is a solid-state power controller circuit.

[0018] In an embodiment, a safety protection device is connected between each emergency bus bar and the tertiary power-consuming device.

[0019] In an embodiment, the safety protection device is a fuse or a circuit breaker.

[0020] In an embodiment, the direct current power supply is a voltage conversion device, a direct current generator or a battery pack.

[0021] In addition, to achieve the above object, the application further provides an aerial vehicle comprising the low-voltage power supply system for the aerial vehicle.

[0022] The one or more technical solutions provided by the application have at least the following technical effects:

[0023] The application provides a low-voltage power supply system for an aerial vehicle, comprising at least two direct current power supplies, at least two main bus bars, at least two emergency bus bars corresponding to the number of main bus bars, an emergency battery and a power supply interface; in the system, each main bus bar is in turn connected to each direct current power supply in a manner that can be connected or disconnected, two adjacent main bus bars are connected through a first switch, so that each main bus bar has redundancy for power supply, thereby improving the power supply reliability of the main bus bar; each emergency bus bar is also in turn connected to each main bus bar in a manner that can be connected or disconnected, two adjacent emergency bus bars are connected through a second switch, and the emergency battery is connected to each emergency bus bar in a manner that can be connected or disconnected, so that each emergency bus bar has redundancy for power supply, thereby improving the power supply reliability of the emergency bus bar; when a short circuit fault occurs in a certain emergency bus bar, the power supply of the electrical equipment on the emergency bus bar can be cut off by disconnecting the corresponding connected main bus bar and the second switch, while other equipment can continue to work normally, so that only the safety margin of the aerial vehicle is reduced without causing flight safety accidents such as aerial vehicle crashes, thereby improving the power supply safety and flight safety of the system; the power supply interface is connected to at least one main bus bar in a manner that can be connected or disconnected, and the power supply interface is also connected to the emergency battery; the emergency battery can be charged by an external power supply, so that the ground power supply can be used alone during ground maintenance without consuming the power of the emergency battery and the power of the direct current power supply on the aerial vehicle, and high-voltage power supply is also not needed, thereby avoiding the inconvenience caused by consuming the limited power on the aerial vehicle, improving the safety of ground maintenance, and at the same time, reducing the capacity requirement of the emergency battery, thereby reducing the weight of the battery and improving the effective load performance of the aerial vehicle. BRIEF DESCRIPTION OF DRAWINGS

[0024] The accompanying drawings, which are incorporated into and form part of the specification, illustrate embodiments consistent with the application and, together with the specification, serve to explain the principles of the application.

[0025] In order to more clearly illustrate the technical solutions in the embodiments of the application or in the related art, the accompanying drawings needed to be used in the embodiments or related art description will be briefly introduced. Obviously, the accompanying drawings in the following description are only some embodiments of the application, and for those skilled in the art, other drawings can also be obtained from the structures shown in the drawings without creative labor.

[0026] Figure 1 is a system block diagram of a low voltage power supply system in the related art;

[0027] Figure 2 is a system block diagram of an embodiment of a low voltage power supply system for an aircraft according to the present application;

[0028] Figure 3 is a system block diagram of a specific example of a low voltage power supply system for an aircraft according to the present application.

[0029] The implementation, functional features and advantages of the present application will be further described with reference to the embodiments in conjunction with the accompanying drawings. DETAILED DESCRIPTION

[0030] The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all the embodiments of the present application. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative work fall within the scope of protection of the present application.

[0031] It should be noted that if the embodiments of the present application involve directional indications (such as up, down, left, right, front, back, etc.), the directional indications are only used to explain the relative positional relationship, movement condition, etc. between components in a certain posture, and if the certain posture changes, the directional indications also change accordingly. In addition, if the embodiments of the present application involve descriptions of “first”, “second”, etc., the descriptions of “first”, “second”, etc. are only for description purposes, and cannot be understood as indicating or implying the relative importance of the indicated technical features or implicitly indicating the number of the indicated technical features. Therefore, the features limited by “first”, “second” can explicitly or implicitly include at least one of the features. In addition, “and / or” or “and / or” appears throughout the text, which means that the three parallel schemes include A scheme, or B scheme, or A and B schemes are satisfied at the same time. In addition, the technical solutions of each embodiment can be combined with each other, but it must be based on the realization of those of ordinary skill in the art, and when the combination of technical solutions appears contradictory or unachievable, it should be considered that the combination of technical solutions does not exist, and is not within the scope of protection claimed by the present application.

[0032] The low voltage power supply system of the aircraft is a system that provides low voltage direct current to various electrical equipment. For example, the low voltage power supply system of the aircraft is a system that provides low voltage direct current to various electrical equipment. Figure 1A system block diagram of a low-voltage power supply system in the related art is shown, which mainly includes two sets of high-voltage distribution boxes, two main bus bars, an emergency bus bar and an emergency battery, the high-voltage distribution box is provided with a DCDC conversion module connected with the main bus bar in one-to-one manner, the DCDC conversion module converts high-voltage direct current on the aircraft into low-voltage direct current and provides the main bus bar, and the two DCDC conversion modules are communicatively connected to realize current sharing regulation. In the low-voltage power supply system, the main bus bar provides single redundancy power supply to the corresponding first type of electrical equipment, that is, power supply by the corresponding high-voltage distribution box, and the emergency bus bar provides three redundancy power supply to the corresponding second type of electrical equipment, that is, power supply by two sets of high-voltage distribution boxes or power supply by the emergency battery. However, the low-voltage power supply system still has some problems:

[0033] 1. Insufficient power supply redundancy of a single main bus bar

[0034] The power supply of a single main bus bar only comes from a corresponding DCDC conversion module, when the DCDC conversion module fails, the main bus bar has no power supply, the corresponding first type of electrical equipment will be powered off, resulting in device failure, and the power supply reliability is low;

[0035] 2. Single point failure of the emergency bus bar

[0036] The power supply of the emergency bus bar comes from the main bus bar and the emergency battery, and the power supply of the main bus bar comes from the corresponding DCDC conversion module, when the emergency bus bar is short-circuited, the voltage on the main bus bar and the emergency bus bar is pulled down, that is, if the emergency bus bar fails, even if the main bus bar is normal, the voltage on the main bus bar will also be pulled down, that is, there is a single point failure, which will cause all the first type of electrical equipment and the second type of electrical equipment to be powered off, resulting in device failure, and even the aircraft crashes, thereby affecting flight safety;

[0037] 3. When ground maintenance, the electrical energy on the aircraft is consumed, and the safety is low

[0038] When ground maintenance, the emergency battery needs to be connected to make the emergency bus bar have power, so that the second type of electrical equipment is powered on for maintenance and inspection, which will consume the electrical energy of the emergency battery; the high-voltage distribution box also needs to be connected to make the main bus bar have power, so that the first type of electrical equipment is powered on for maintenance and inspection, which will consume the high-voltage electrical energy of the aircraft; and when charging the emergency battery, the high-voltage distribution box is also used for charging, which will also consume the high-voltage electrical energy of the aircraft, so that the high-voltage electrical energy of the aircraft must be supplemented subsequently, otherwise the flight task may not be completed due to insufficient high-voltage electrical energy. In addition, during the foregoing ground maintenance process, the aircraft is in a high-voltage state, and the maintenance personnel are in such a high-voltage environment, which has the risk of high-voltage electric shock, resulting in low safety during ground maintenance.

[0039] To solve the above problems, the application provides a low-voltage power supply system for an aircraft and an aircraft.

[0040] The application provides a low-voltage power supply system for an aircraft.

[0041] In an embodiment of the application, referring to Figure 2 , Figure 2 FIG. 1 is a system block diagram of an embodiment of a low-voltage power supply system for an aircraft. The system can include 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, at least one emergency battery, and a power supply interface.

[0042] Each main bus bar is connected to each DC power source in a manner that can be turned on or off, and two adjacent main bus bars are connected through a first switch. Each emergency bus bar is connected to each main bus bar in a manner that can be turned on or off, and two adjacent emergency bus bars are connected through a second switch. The emergency battery is connected to each emergency bus bar in a manner that can be turned on or off. The power supply interface is connected to at least one main bus bar in a manner that can be turned on or off. The power supply interface is used to connect an external power source, and the power supply interface is also connected to the emergency battery to charge the emergency battery using the external power source.

[0043] It should be noted that the DC power source refers to a device or module that provides the required power for the operation of various electrical equipment on the aircraft, for example, it can provide 28VDC (direct current). The electrical equipment refers to the devices, apparatuses, and systems on the aircraft that need to obtain power from the low-voltage power supply system. The main bus bar and the emergency bus bar belong to two different levels of bus bars and are both power supply bus bars, but they supply power to different electrical equipment, and the specific electrical equipment can be divided into levels according to actual needs and connected to the main bus bar or the emergency bus bar, which is not limited here. The emergency battery refers to a battery device that supplies power to the emergency bus bar in the event of a DC power source failure or malfunction, main bus bar failure, etc. It can also provide the required power for the operation of various electrical equipment, such as 28VDC. The emergency battery can be one or multiple. When there are multiple emergency batteries, each emergency battery is connected to each emergency bus bar and connected to the power supply interface. The power supply interface refers to a power input interface provided on the aircraft to connect an external power source such as a ground power source. When maintaining on the ground, the external power source is used to supply power to one or more main bus bars connected to the power supply interface and to charge the emergency battery, so that the power of the power supply device on the aircraft does not need to be consumed.

[0044] It can be understood that in the system, each main bus bar can be powered by the corresponding DC power supply, can be powered by the DC power supply corresponding to other main bus bars, and can be powered by an external power supply connected by the power supply interface during ground maintenance. Each main bus bar can provide redundant power supply to the corresponding connected electrical equipment, thereby improving the power supply reliability of the main bus bar. Each emergency bus bar can be powered by the corresponding main bus bar, can be powered by the main bus bar corresponding to other emergency bus bars, can be powered by an emergency battery, and can be powered by an external power supply connected by the power supply interface through the main bus bar during ground maintenance. Each emergency bus bar can provide redundant power supply to the corresponding connected electrical equipment, thereby 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, and only the electrical equipment on the emergency bus bar is powered off, while other devices can remain normal. The operation only reduces the safety margin of the aircraft, but can avoid flight safety accidents such as aircraft crashes, thereby improving the power supply safety and flight safety of the system. During ground maintenance, an 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 on high voltage, and does not need to consume the electrical energy on the aircraft, thereby increasing the convenience and safety of the aircraft maintenance. At the same time, the capacity requirement of the emergency battery can also be reduced, thereby reducing the weight of the battery and improving the effective load performance of the aircraft.

[0045] In a possible implementation, with continuous reference to Figure 2 , the at least two DC power supplies can include a first DC power supply and a second DC power supply, the at least two main bus bars can include a first main bus bar and a second main bus bar, and the at least two emergency bus bars can include a first emergency bus bar and a second emergency bus bar.

[0046] The first main bus bar is in an on-off connection with the first DC power supply, the second main bus bar is in an on-off connection with the second DC power supply, the first main bus bar is connected with the second main bus bar through the first switch, the first emergency bus bar is in an on-off connection with the first main bus bar, the second emergency bus bar is in an on-off connection with the second main bus bar, the first emergency bus bar is connected with the second emergency bus bar through the second switch, the emergency battery is in an on-off connection with the first emergency bus bar and the second emergency bus bar respectively, and the power supply interface is in an on-off connection with the first main bus bar and the second main bus bar respectively.

[0047] It should be noted that the on-off connection refers to the on-off control of the connection between the devices or circuits, which can be realized by using contactors, circuit breakers, controllable switches and other switching devices, switching circuits or chips. In this embodiment, the first main bus bar is connected with the first DC power supply through the contactor C1, the second main bus bar is connected with the second DC power supply through the contactor C2, the emergency battery is connected with the first emergency bus bar through the contactor C7, the emergency battery is also connected with the second emergency bus bar through the contactor C8, the power interface is connected with the first main bus bar through the contactor C2, and the power interface is also connected with the second main bus bar through the contactor C3. The first switch and the second switch can also be contactors, circuit breakers, controllable switches and other switching devices. In this embodiment, the first switch and the second switch are both realized by contactors, the first main bus bar is connected with the second main bus bar through the contactor C5, and the first emergency bus bar is connected with the second emergency bus bar through the contactor C6.

[0048] It can be understood that the contactor C5 between the two main bus bars, on the basis that the first DC power supply supplies power to the first main bus bar and the second DC power supply supplies power to the second main bus bar, when the first DC power supply fails and the first main bus bar has no power supply, causing the connected electrical equipment to power off, the contactor C5 can be closed, so that the two main bus bars are connected with each other. At this time, the first main bus bar can take power from the second DC power supply; when the second DC power supply fails, the second main bus bar can take power from the first DC power supply, that is, the main bus bar has double redundancy power supply. When there are more DC power supplies and more main bus bars, the power supply redundancy of each main bus bar will be more, solving the problem of insufficient power supply redundancy of the main bus bar, and preventing single failure from causing system failure.

[0049] It can be understood that the contactor C6 between the two emergency bus bars, on the basis that the first DC power supply supplies power to the first main bus bar and the second DC power supply supplies power to the second main bus bar, when the first main bus bar is short-circuited and fails, the connected electrical equipment is powered off, and the first emergency bus bar cannot take power from the first main bus bar. At this time, the contactor C6 can be closed, so that the first emergency bus bar is connected with the second emergency bus bar to take power from the second main bus bar; when the second main bus bar is short-circuited and fails, the second emergency bus bar can take power from the first main bus bar. Alternatively, when the first emergency bus bar cannot take power from the first main bus bar, it can also take power from the emergency battery. Therefore, the problem of insufficient power supply redundancy of the emergency bus bar is also solved.

[0050] In this embodiment, the two main bus bars can be connected, the main bus bar has double redundancy power supply, so that the connected electrical equipment has double redundancy power supply, the power supply redundancy of these devices is increased, and the safety of the aircraft is improved.

[0051] In a possible implementation, continuing to refer to Figure 2 The system can further include at least two fuses; each emergency bus bar is connected to the corresponding main bus bar through the fuse.

[0052] It should be noted that the on-off connection can be actively or passively implemented to connect or disconnect when needed. In this embodiment, the on-off connection between the emergency bus bar and the main bus bar is implemented by using the fuse. Specifically, the first emergency bus bar is connected to the first main bus bar through the fuse F1, and the second emergency bus bar is connected to the second main bus bar through the fuse F2.

[0053] It can be understood that the contactor C6 is arranged between the two emergency bus bars, and in combination with the fuse F1 and the fuse F2, when the first emergency bus bar is short-circuited, the voltage of the first emergency bus bar is pulled down, and the power supply equipment thereof will be powered off. At this time, the fuse F1 is fused, and the voltage on the first main bus bar will not be affected, and the power supply equipment connected to the first main bus bar can work normally, and the contactor C6 can be disconnected, and the power supply equipment connected to the second emergency bus bar and the second main bus bar can also work normally, so that only the power supply equipment connected to the first emergency bus bar is powered off, and other equipment works normally. This situation only reduces the flight safety margin of the aircraft, and does not seriously cause the aircraft to crash, thereby avoiding the single-point failure of the emergency bus bar.

[0054] In this embodiment, the two emergency bus bars can be connected, and the fuse is arranged between the emergency bus bar and the main bus bar as a protection device. When a single emergency bus bar fails, the power supply equipment on the other three bus bars will not be affected, and the aircraft can continue to fly, thereby improving the safety and reliability of the aircraft.

[0055] In a possible implementation, continuing to refer to Figure 2 The system can further include a charger, which can be arranged inside the emergency battery in an integrated manner or arranged outside in a self-contained manner.

[0056] It should be noted that when the charger is integrated with the emergency battery, the connection between the power supply interface and the emergency battery is that one end of the power supply interface is connected to the emergency battery through the charger. As shown in Figure 2 The other end of the power supply interface can be directly connected to the external power supply. This arrangement improves the convenience of power connection operation during ground maintenance. When the charger is independent of the emergency battery and self-contained, one end of the power supply interface can be directly connected to the emergency battery, and the other end of the power supply interface is connected to the external power supply through the charger. This arrangement can reduce the weight of the emergency battery, reduce the weight of the entire aircraft, and more favorably improve the flight performance of the aircraft.

[0057] The low-voltage power supply system for the aircraft provided by the embodiment comprises 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, an emergency battery and a power supply interface. In the system, each main bus bar is connected to each DC power source in a one-to-one correspondence and can be connected or disconnected, two adjacent main bus bars are connected through a first switch, so that each main bus bar has redundancy for power supply. In addition to the power supply from the DC power source corresponding to the main bus bar, when the DC power source fails, the adjacent two main bus bars are connected by turning on the first switch, and the adjacent main bus bar is powered by the DC power source corresponding to the adjacent main bus bar, thereby improving the power supply reliability of the main bus bar. Each emergency bus bar is connected to each main bus bar in a one-to-one correspondence and can be connected or disconnected, two adjacent emergency bus bars are connected through a second switch, and the emergency battery is connected to each emergency bus bar in a connectable or disconnectable manner. Each emergency bus bar has redundancy for power supply, including power supply from the main bus bar corresponding to the emergency bus bar and the emergency battery, thereby improving the power supply reliability of the emergency bus bar. When a short-circuit fault occurs in a certain emergency bus bar, the power supply of the electrical equipment on the emergency bus bar is turned off by disconnecting the corresponding main bus bar and the second switch, while other equipment can continue to work normally, thereby reducing the safety margin of the aircraft without causing flight safety accidents such as aircraft crashes, improving the power supply safety and flight safety of the system. The power supply interface is connected to at least one main bus bar in a connectable or disconnectable manner, and the power supply interface is also connected to the emergency battery. The external power source is used to charge the emergency battery. The ground power supply can be used independently during ground maintenance without consuming the power of the emergency battery and the DC power source on the aircraft, and high-voltage power supply is not required. The consumption of limited power on the aircraft is avoided, the safety of ground maintenance is improved, the capacity requirement of the emergency battery is reduced, the weight of the battery is reduced, and the effective load performance of the aircraft is improved.

[0058] In another embodiment of the present application, with reference to Figure 2 , the system can further comprise a plurality of unidirectional conduction devices.

[0059] The unidirectional conduction device is connected between each main bus bar and the corresponding emergency bus bar for limiting the current flow direction from the main bus bar to the emergency bus bar. The unidirectional conduction device is connected between the emergency battery and each emergency bus bar for limiting the current flow direction from the emergency battery to the emergency bus bar.

[0060] It should be noted that the unidirectional conduction device can be a diode, a thyristor, a three-terminal bidirectional silicon-controlled silicon, etc. The diode can include a general diode, a Schottky diode, a tunnel diode, a PIN diode, a Zener diode, etc. Here, a general diode with lower cost is preferred, which has a unidirectional conduction characteristic and will not be reverse breakdown.

[0061] For example, taking a common diode as an example of a unidirectional conducting device, such as... Figure 2 The system shown may include four unidirectional diodes D1-D4. The anode of diode D1 is connected to fuse F1, and the cathode of diode D1 is connected to the first emergency busbar. The anode of diode D2 is connected to fuse F2, and the cathode of diode D2 is connected to the second emergency busbar. The anode of diode D3 is connected to the emergency battery, and the cathode of diode D3 is connected to the first emergency busbar. The anode of diode D4 is connected to the emergency battery, and the cathode of diode D4 is connected to the second emergency busbar.

[0062] Understandably, the diodes between the main bus and the emergency bus ensure that the main bus supplies power to the corresponding emergency bus while simultaneously powering the equipment on it, allowing the equipment on the emergency bus to operate normally. Furthermore, in the event of a DC power failure, when the emergency battery powers the emergency bus to ensure the equipment on it continues to operate, the diodes prevent the emergency battery from supplying power to the main bus through the emergency bus. This avoids unnecessary energy consumption for the equipment on the main bus, preventing the emergency battery from depleting too quickly and shortening the aircraft's emergency power supply time. Therefore, this system ensures stable operation of the equipment on the emergency bus in emergency situations, improves the power supply reliability of such equipment, and reduces the capacity requirements of the emergency battery, thereby reducing battery weight and improving the aircraft's effective payload capacity. The diodes between the emergency battery and the emergency bus prevent uncontrolled charging of the emergency battery by the main bus through the emergency bus, which could lead to overcharging and put the emergency battery in a dangerous state.

[0063] In this embodiment, the unidirectional conduction performance of the diode is used to limit the current flow between the main busbar and the emergency busbar, as well as the current flow between the emergency battery and the emergency busbar. This ensures the reliability of the power supply to the equipment, reduces the capacity requirements of the emergency battery, and also avoids overcharging of the emergency battery, thereby improving the safety and stability of the system.

[0064] In one feasible implementation, continue to refer to Figure 2 In this system, each main busbar is connected to a corresponding primary electrical device, and each emergency busbar is connected to a corresponding secondary and / or tertiary electrical device. The primary, secondary, and tertiary electrical devices are classified and determined from low to high according to the importance of each electrical device based on the operation of the aircraft.

[0065] It should be noted that the first power equipment refers to general power equipment, which can include equipment for improving flight conditions without affecting flight tasks and safety; the second power equipment refers to important power equipment, which can include equipment necessary for the aircraft to complete the flight task; and the third power equipment refers to critical power equipment, which can include equipment necessary for the aircraft to safely fly and land.

[0066] As shown in the system, Figure 2 the first main bus bar and the second main bus bar are respectively connected with the first power equipment, the first emergency bus bar and the second emergency bus bar are respectively connected with the second power equipment, and the first emergency bus bar and the second emergency bus bar are respectively connected with the third power equipment.

[0067] In a specific embodiment, continuing to refer to Figure 2 , in the system, the main bus bar and the first power equipment are connected with the switch protection circuit, and the emergency bus bar and the second power equipment are connected with the switch protection circuit.

[0068] As shown in the system, Figure 2 the first main bus bar and the second main bus bar are respectively connected with the first power equipment, the first emergency bus bar and the second emergency bus bar are respectively connected with the second power equipment, and the first emergency bus bar and the second emergency bus bar are respectively connected with the third power equipment.

[0069] The switch protection circuit can be a solid-state power controller (SSPC) circuit, which 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 power equipment, thereby improving the power supply reliability and safety of the system.

[0070] In a specific embodiment, continuing to refer to Figure 2 , in the system, the emergency bus bar and the third power equipment are connected with the safety protection device.

[0071] As shown in the system, Figure 3 the first emergency bus bar and the second emergency bus bar are respectively connected with the third power equipment.

[0072] The safety protection device can be a fuse or a circuit breaker. The fuse can play a role in overcurrent protection and short circuit protection.

[0073] Understandably, both SSPCs and fuses are lightweight, which avoids increasing the overall weight of the aircraft. For tertiary electrical equipment, using fuses in the power distribution channel can improve its reliability. For primary and secondary electrical equipment, using SSPCs in the power distribution channel can control its on / off state and can actively disconnect when necessary to ensure the aircraft's flight, further improving the aircraft's reliability and safety.

[0074] In one feasible implementation, the DC power supply can be a voltage conversion device, a DC generator, or a battery pack.

[0075] It should be noted that a voltage conversion device refers to a device that acquires electrical energy and then converts it into low-voltage direct current before outputting it. For example, it may acquire high-voltage direct current from a high-voltage distribution box, perform a high-voltage DC / DC conversion, and output a DC-DC converter that converts the high-voltage direct current into low-voltage direct current. Another example is to acquire AC power from an AC power source, perform an AC-DC conversion to obtain high-voltage direct current, and then convert the high-voltage direct current into low-voltage direct current before outputting an AC-DC converter. Alternatively, it may directly convert AC power to obtain low-voltage direct current before outputting an AC-DC converter. In practical applications, the appropriate device can be selected as needed, and no specific limitation is made here. A DC generator refers to a generator that can directly generate and output low-voltage direct current. A battery pack refers to a battery pack that can convert AC power into low-voltage direct current before outputting it or directly provide low-voltage direct current.

[0076] For example, the DC power supply is a DC-DC converter that converts high-voltage DC to low-voltage DC (such as 28VDC). The DC-DC converter has functions such as output overvoltage protection, undervoltage protection, overcurrent protection, and short-circuit protection. It can detect the voltage of the low-voltage DC at the front end of the main busbar. When the voltage is too high or too low, it can actively disconnect the contactor between the DC-DC converter and the main busbar to ensure that the general electrical equipment on the main busbar is not damaged, thus achieving the effect of protecting the downstream electrical equipment.

[0077] The low-voltage power supply system for aircraft provided in this embodiment can be designed according to the characteristics of all-electric aircraft, and features redundancy, multi-level, high reliability, and light weight.

[0078] For example, such as Figure 3 The diagram shown is a system block diagram of a specific example of a low-voltage power supply system. The low-voltage power supply system of this embodiment will be described in detail below using this specific example:

[0079] The electrical equipment is categorized into general electrical equipment, important electrical equipment, and critical electrical equipment. Both DC power supplies use DC-DC converters. The two main busbars are defined as the left and right main busbars, and the two emergency busbars are defined as the left and right emergency busbars. Specific connection relationships are described above and can be found in the reference section.Figure 3 As shown, it will not be elaborated further here.

[0080] based on Figure 3 The low-voltage power supply system is designed with two busbars. Each busbar consists of two main busbars (left and right) and two emergency busbars (left and right). The main busbars provide dual-redundancy power to general electrical equipment, sourced from two DC-DC converters. The emergency busbars provide triple-redundancy power to important and critical electrical equipment, sourced from two DC-DC converters and an emergency battery. This improves the power supply redundancy of the equipment and enhances the flight safety of the aircraft.

[0081] During normal operation, the left and right DC-DC converters output low-voltage DC power, which is connected to the left and right main busbars respectively through the contactors C1 and C4. The left main busbar supplies power to the left general electrical equipment and the left emergency busbar, while the right main busbar supplies power to the right general electrical equipment and the right emergency busbar. In other words, the left DC-DC converter supplies power to the left general electrical equipment, the left important electrical equipment, and the left critical electrical equipment, while the right DC-DC converter supplies power to the right general electrical equipment, the right important electrical equipment, and the right critical electrical equipment. At this time, all electrical equipment of the aircraft has normal power supply.

[0082] When a single DC-DC converter fails, contactor C5 can be switched on to supply power to all electrical equipment from another DC-DC converter. For example, when the left DC-DC converter fails, the left main busbar is de-energized, and the left general-use equipment loses power. The left emergency busbar can only be powered by the emergency battery. Specifically, the emergency battery outputs low-voltage DC power, which is connected to the left emergency busbar through the connected contactor C7 to supply power to the left important and critical equipment. At this time, contactor C5 can be closed to connect the left and right main busbars. The low-voltage DC power output from the right DC-DC converter can be transmitted to the left main busbar through the right main busbar and contactor C5. That is, the left main busbar draws power from the right DC-DC converter, the left general-use equipment is powered again, and the left emergency busbar switches from being powered by the emergency battery to being powered by the left main busbar. At this time, the right DC-DC converter supplies power to all equipment. Similarly, when the right DC-DC converter fails, contactor C5 can also be closed to allow the right main busbar to draw power from the left DC-DC converter, and the left DC-DC converter supplies power to all equipment. This ensures that the main busbar provides redundant power to general electrical equipment and the emergency busbar.

[0083] When any one of the main bus bars fails, such as the left main bus bar short-circuits, the corresponding left general electrical equipment is powered off, and the left emergency bus bar has one less power supply redundancy, causing the power supply redundancy of the left important electrical equipment and the left critical electrical equipment to decrease, but the first switch connected between the two main bus bars, i.e., the contactor C5, can be disconnected, so that the right general electrical equipment, the right important electrical equipment and the right critical electrical equipment remain normal work, thereby avoiding causing the aircraft to crash, and thus the overall safety of the aircraft can be avoided.

[0084] Based on the low-voltage power supply system Figure 3 , the left emergency bus bar is powered by the left main bus bar and the emergency battery, the right emergency bus bar is powered by the right main bus bar and the emergency battery, the two emergency bus bars are connected by a contactor C6, the left emergency bus bar supplies power to the left important electrical equipment and the left critical electrical equipment, and the right emergency bus bar supplies power to the right important electrical equipment and the right critical electrical equipment.

[0085] When the left main bus bar fails or the fuse F1 fails or the diode D1 fails, the left emergency bus bar is powered by the emergency battery, and due to the capacity limitation of the emergency battery, the working time of the left important electrical equipment and the left critical electrical equipment will be shorter; at this time, the contactor C6 can be closed, and the left and right emergency bus bars are connected to each other, so that the left emergency bus bar takes power from the right main bus bar through the right emergency bus bar, and the right main bus bar 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 bus bar fails or the fuse F2 fails or the diode D2 fails, the contactor C6 is connected, and the right emergency bus bar can also take power from the left main bus bar, so that the left DCDC conversion power supply supplies power to all electrical equipment. It ensures that the emergency bus bar provides three-redundancy power supply to the critical electrical equipment and the important electrical equipment.

[0086] When any one of the emergency bus bars fails, such as the left emergency bus bar short-circuits, the corresponding left critical electrical equipment and left important electrical equipment are powered off, but the second switch connected between the two emergency bus bars, i.e., the contactor C6, can be disconnected, so that the right important electrical equipment and the right critical electrical equipment remain normal work, thereby avoiding causing the aircraft to crash, and thus the aircraft can be ensured to have a certain safety; in addition, when the left emergency bus bar short-circuits, the voltage of the left emergency bus bar is pulled down, the left important electrical equipment and the left critical electrical equipment are powered off, and the fuse F1 is blown, which does not affect the voltage on the left main bus bar, so as not to affect the work of the left general electrical equipment, i.e., only the left important electrical equipment and the left critical electrical equipment are powered off at this time, and other equipment are normal; when the right emergency bus bar short-circuits, similarly, details are not repeated here.

[0087] As ​As shown, the power interface is connected with a ground power supply in this example, the ground power supply is connected to the left and right main bus bars 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 using high-voltage power, ensuring the safety of the operating environment of the maintenance personnel, and without consuming low-voltage power (including emergency battery power) and high-voltage power on the aircraft, facilitating ground maintenance of the aircraft; and the ground power supply can be used to charge the emergency battery through the charger, without consuming high-voltage power on the aircraft, and can also save the charging time of the emergency battery.

[0088] Based on the above specific description, it is sufficient to prove that the low-voltage power supply system of the embodiment indeed has the effects of improving the power supply margin of the main bus bar, increasing the emergency bus bar to avoid single-point failure, and not consuming the power of the aircraft during ground maintenance and ensuring the safety of ground maintenance operation.

[0089] The application also provides an aircraft. The aircraft comprises the low-voltage power supply system for the aircraft.

[0090] It should be noted that the specific structure of the low-voltage power supply system for the aircraft refers to the above embodiments, since the aircraft adopts all the technical solutions of the above embodiments, it at least has all the beneficial effects brought by the technical solutions of the above embodiments, which will not be repeated here.

[0091] The above is only part of the embodiments of the application, and does not limit the patent scope of the application, any equivalent structural transformation made by using the content of the specification and drawings, or direct / indirect application in other related technical fields is included in the patent protection scope of the application.

Claims

1. A low-voltage power supply system for an aircraft, characterized in that The system comprises at least two direct current power sources, at least two main bus bars, at least two emergency bus bars corresponding to the number of main bus bars, an emergency battery and a power source interface; The main bus bars are connected to the direct current power sources in a switchable manner, and two adjacent main bus bars are connected through a first switch; the emergency bus bars are connected to the main bus bars in a switchable manner, and two adjacent 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 source interface is connected to at least one main bus bar in a switchable manner, and is used for connecting an external power source; the power source interface is also connected to the emergency battery, so that the external power source is used to charge the emergency battery.

2. The low-voltage power supply system for an aircraft as claimed in claim 1, characterized in that The at least two direct current power sources comprise a first direct current power source and a second direct current power source, and the at least two main bus bars comprise a first main bus bar and a second main bus bar, and the at least two emergency bus bars comprise a first emergency bus bar and a second emergency bus bar; The first main bus bar is connected to the first direct current power source in a switchable manner, the second main bus bar is connected to the second direct current power source in a switchable manner, and the first main bus bar is connected to the second main bus bar through the first switch; the first emergency bus bar is connected to the first main bus bar in a switchable manner, the second emergency bus bar is connected to the second main bus bar in a switchable manner, and the first emergency bus bar is connected to the second emergency bus bar through the second switch; the emergency battery is connected to the first emergency bus bar and the second emergency bus bar in a switchable manner; and the power source interface is connected to the first main bus bar and the second main bus bar in a switchable manner.

3. The low-voltage power supply system for an aircraft of claim 1, wherein, The system further comprises at least two fuses; Each emergency bus bar is connected to the corresponding main bus bar through the fuse.

4. The low-voltage power supply system for an aircraft of claim 1, wherein, The system further comprises a plurality of unidirectional conduction devices; The unidirectional conduction device is connected between each main bus bar and the corresponding emergency bus bar, and is used to limit the current flow direction to be from the main bus bar to the emergency bus bar.

5. The low-voltage power supply system for an aircraft as claimed in claim 4, characterized in that The unidirectional conduction device is connected between the emergency battery and each emergency bus bar, and is used to limit the current flow direction to be from the emergency battery to the emergency bus bar.

6. The low-voltage power supply system for an aircraft as claimed in claim 5, characterized in that The unidirectional conduction device is a diode.

7. The low-voltage power supply system for an aircraft of claim 1, wherein, The system further comprises a charger, which is integrated inside the emergency battery or is self-contained outside.

8. Low voltage power supply system for an aircraft according to any of claims 1 to 7, characterized in that Each main bus bar is connected to a primary electrical equipment, each emergency bus bar is connected to a secondary electrical equipment, and each emergency bus bar is further connected to a tertiary electrical equipment, wherein the primary electrical equipment, the secondary electrical equipment and the tertiary electrical equipment are classified and determined in grades according to the importance of each electrical equipment based on the working of an aircraft.

9. The low-voltage power supply system for an aircraft of claim 8, wherein, A switch protection circuit is connected between the main bus bar and the primary electrical equipment, and between the emergency bus bar and the secondary electrical equipment.

10. The low-voltage power supply system for an aircraft of claim 9, wherein, The switch protection circuit is a solid-state power controller circuit.

11. The low-voltage power supply system for an aircraft of claim 8, wherein, A safety protection device is connected between the emergency bus bar and the tertiary electrical equipment.

12. The low-voltage power supply system for an aircraft of claim 11, wherein, The safety protection device is a fuse or a circuit breaker.

13. Low voltage power supply system for an aircraft according to any of claims 1 to 7, characterized in that The direct current power source is a voltage conversion device, a direct current generator or a battery pack.

14. An aircraft, characterized in that A low-voltage power supply system for an aircraft comprising a low-voltage power supply system according to any one of claims 1 to 13.

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