Closed high-voltage charging and distribution system of electric aircraft

Abstract

The utility model relates to the technical field of aviation, and discloses a closed high-voltage charging and distribution system of an electric aircraft. Loads are arranged in the system and comprise electric drives, and each electric drive comprises m power supply circuits; the n battery packs are connected in parallel and are used for providing electric energy for the load through the high-voltage charging and distribution box; the n bus bars are positioned in the high-voltage charging and distribution box and are correspondingly connected with the n battery packs respectively; the n bus bars enclose m closed circuits; the ith closed line is connected with the ith power supply circuit of the electric drive so as to supply power to the ith power supply circuit; the design safety margin and reliability of the system are greatly improved, so that the safe flight of the electric aircraft is ensured; meanwhile, through the high-voltage platform, current carrying of a high-voltage line is reduced so as to reduce the weight of the aircraft.

Description

TECHNICAL FIELD

[0001] The present disclosure relates to the field of aviation technology, and in particular to a closed high-voltage charging and power distribution system of an electric aircraft. BACKGROUND

[0002] With the development of new energy industry and people's pursuit of environmental protection, comfort, and cost performance, electric aircraft as a new energy product gradually develops in the field of aviation. Electric aircraft refers to an aircraft that relies on electric motors rather than traditional fuel to provide driving force. Taking an electric vertical take-off and landing aircraft (EVTOL) as an example, the EVTOL provides lift through one or more lift motor propellers to achieve vertical take-off and landing, and when it is vertically lifted to a certain height, the thrust motor propeller provides thrust, and the lift motor can stop working or be tilted to become a thrust motor. The EVTOL relies on high-voltage batteries (i.e. battery packs in the present application) to power the motor, rather than using traditional fuel to provide driving force for the aircraft. At this time, the EVTOL provides high-voltage electrical energy to high-voltage power components of the aircraft such as motors, air conditioners, warm air, DC-DC converters, etc. through multiple battery packs. The EVTOL has many advantages such as energy saving and environmental protection, near-zero emission, low noise and vibration level, good ride comfort, safety and reliability, simple structure, easy operation and use, good maintainability and economy, etc. It is not only environmentally friendly, but also creates a lot of economic value.

[0003] At present, there are few manned electric aircrafts that meet the safety airworthiness requirements. How to reliably distribute the high-voltage electrical energy of multiple battery packs to multiple different high-voltage electrical equipment under different flight conditions of the aircraft is a problem that needs to be solved in the design of the high-voltage charging and power distribution system of the electric aircraft. CONTENT OF THE INVENTION

[0004] Therefore, the present disclosure provides a closed high-voltage charging and power distribution system of an electric aircraft, which can realize redundant power distribution of multiple busbars and multiple loads, has sufficient safety design margin and reliability, and can also reduce the current carrying capacity of the high-voltage line through the high-voltage platform to reduce the weight of the aircraft.

[0005] In one aspect, the present disclosure provides a closed high-voltage charging and power distribution system of an electric aircraft, which comprises:

[0006] a load comprising electric drives, each electric drive comprising an m-way power supply circuit; wherein m is an integer greater than 1;

[0007] n battery packs connected in parallel to each other for providing electrical energy to the load through a high-voltage charging and power distribution box; wherein n is an integer greater than 1;

[0008] n bus bars in the high-voltage charging distribution box are connected with the n battery packs respectively; the n bus bars enclose m closed circuits; an ith closed circuit is connected with an ith power supply circuit of the electric drive to supply power to the ith power supply circuit; wherein, the i is a positive integer less than or equal to m, and m is an integer less than n.

[0009] Optionally, the different bus bars in each closed circuit are connected in a head-to-tail manner through first protection devices; the first protection device connected with each bus bar is used to cut off the connection between the bus bar and other bus bars in the case of abnormality of the circuit in which the bus bar is located.

[0010] Optionally, the electric drive includes a first electric drive for providing lift for the electric aircraft and symmetrically distributed on the wing of the electric aircraft.

[0011] Each bus bar in each closed circuit is connected with at least one pair of symmetric first electric drives.

[0012] Optionally, the electric drive includes a second electric drive; the second electric drive is used to provide thrust for the electric aircraft and symmetrically distributed on the tail of the electric aircraft.

[0013] The symmetric second electric drives connected to the same closed circuit are distributed in different bus bars in the closed circuit.

[0014] Optionally, the first closed circuit in the m closed circuits is connected with a charging structure; when the charging structure is connected with an external power supply, the battery pack connected through the first closed circuit is charged.

[0015] The first closed circuit is electrically connected with a second closed circuit to charge the battery pack connected through the second closed circuit by the first closed circuit.

[0016] The second closed circuit is other than the first closed circuit in the m closed circuits.

[0017] Optionally, the n bus bars and the electric drive are connected through second protection devices; the second protection device connected with each electric drive is used to cut off the connection between the electric drive and the bus bar in the case of abnormality of the circuit in which the electric drive is located.

[0018] Optionally, the load further includes at least two air conditioning devices and at least two DC converters; the at least two air conditioning devices are connected with different bus bars, and the at least two DC converters are connected with different bus bars.

[0019] Optionally, the load on each closed circuit is connected to the closed circuit based on the shortest circuit principle.

[0020] Optionally, the n battery packs are connected in parallel to provide a working DC voltage range of 500V-900V and a rated voltage of 800V for the high-voltage distribution box.

[0021] Optionally, the electric drive includes 4 pairs of first electric drives arranged symmetrically and 1 pair of second electric drives arranged symmetrically; the value of m is 2, and the high-voltage distribution box includes 2, each of which includes a closed circuit, each of which includes 4 bus bars, and the 4 bus bars are connected to the 4 pairs of first electric drives, respectively, and the 1 pair of second electric drives is distributed in different bus bars in the closed circuit.

[0022] By setting a load in the system, including an electric drive, each electric drive includes m power supply circuits; wherein m is an integer greater than 1; n battery packs connected in parallel, for providing power for the load through the high-voltage distribution box; wherein n is an integer greater than 1; and n bus bars in the high-voltage distribution box, connected to the n battery packs, respectively; n bus bars enclose m closed circuits; the ith closed circuit is connected to the ith power supply circuit of the electric drive to supply power to the ith power supply circuit; wherein i is a positive integer less than or equal to m, and m is an integer less than n; if one of the m closed circuits fails, the other power supply circuits of the electric drive can also be powered by other closed circuits, and different power supply circuits are arranged in different closed circuits. The failure of any closed circuit does not affect the normal operation of the electric drive, greatly improving the design safety margin, thereby ensuring the safe flight of the electric aircraft. At the same time, if a battery pack connected to a bus bar in a closed circuit fails, the battery packs connected to the other bus bars in the closed circuit can also power the closed circuit, thereby ensuring the safe flight of the electric aircraft. At the same time, if a bus bar in a closed circuit fails, the other bus bars can also normally distribute power, and the system has sufficient safety design margin and reliability, thereby ensuring the safe flight of the electric aircraft.

[0023] In addition, the high-voltage charging and distribution system not only has high-voltage distribution function, but also can contain high-voltage charging function, and the high-voltage distribution system can realize the setting of 800V DC voltage platform in the electric aircraft. Compared with 400V or 600V voltage platform, the current of high-voltage loop equipment can be reduced, and since the smaller the current is, the cross-sectional area of the electric wire in the electric aircraft can be smaller, thereby the weight of the high-voltage equipment can be greatly reduced. Taking the high-voltage wire harness as an example, the weight of the high-voltage wire harness can be reduced by nearly 40% compared with the 400V platform. In addition, the application of 800V DC high-voltage charging and distribution system in electric vertical take-off and landing aircraft fills the gap of EVTOL, which is conducive to the rapid development of EVTOL.

[0024] Other features and aspects of the present disclosure will become apparent from the following detailed description of example embodiments, taken in conjunction with the accompanying drawings. Attached Figure Description

[0025] The accompanying drawings, which are included in and form part of this specification, together with the specification, explain the principles of this disclosure.

[0026] Figure 1 A block diagram of an 800V DC high-voltage charging and distribution system in an electric vehicle according to an embodiment of the present disclosure is shown.

[0027] Figure 2 A block diagram of a closed high-voltage charging and distribution system for an electric aircraft according to an embodiment of the present disclosure is shown.

[0028] Figure 3 A power plant layout diagram of an electric vertical takeoff and landing aircraft according to an embodiment of the present disclosure is shown.

[0029] Figure 4 A block diagram of a closed high-voltage charging and distribution system for an electric aircraft according to an embodiment of the present disclosure is shown.

[0030] Figure 5 A block diagram of a closed high-voltage charging and distribution system for an electric aircraft according to another embodiment of the present disclosure is shown.

[0031] Figure 6 A block diagram of a closed high-voltage charging and distribution system for an electric aircraft according to yet another embodiment of the present disclosure is shown. Detailed Implementation

[0032] Various exemplary embodiments, features, and aspects of this disclosure will now be described in detail with reference to the accompanying drawings. The same reference numerals in the drawings denote elements that have the same or similar functions. Although various aspects of the embodiments are shown in the drawings, they are not necessarily drawn to scale unless specifically indicated otherwise.

[0033] The term “exemplary” as used herein means “serving as an example, embodiment, or illustration.” Any embodiment illustrated herein as “exemplary” is not necessarily to be construed as superior to or better than other embodiments.

[0034] Furthermore, to better illustrate this disclosure, numerous specific details are set forth in the following detailed description. Those skilled in the art will understand that this disclosure can be practiced without certain specific details. In some instances, methods, means, components, and circuits well known to those skilled in the art have not been described in detail in order to highlight the main points of this disclosure.

[0035] The high-voltage platform of an electric aircraft refers to the rated DC voltage at which all high-voltage equipment of an electric aircraft operates normally. This rated DC voltage is greater than the rated voltage of existing electric aircraft, for example, a rated voltage of 800VDC.

[0036] Currently, an 800V direct current high-voltage charging and distribution system is provided in an electric vehicle. The 800V direct current high-voltage charging and distribution system of the electric vehicle is centralized distribution, and a single bus bar is often used to supply power to all high-voltage loads of the vehicle. The direct current charging function has two forms according to the arrangement of the vehicle. One is that the external electric energy is directly input into the battery pack. The other is that the electric energy of the external power supply is distributed to the battery pack through a high-voltage distribution box, for example, as shown in Figure 1 Figure 1 It can be seen that the electric energy of the external power supply (including the electric energy of the direct current charging DC and / or the electric energy of the on-board charger (OBC)) is connected to the high-voltage charging and distribution box, and the high-voltage charging and distribution box distributes the electric energy to the high-voltage storage battery to charge the high-voltage storage battery. The electric energy of the high-voltage storage battery can also be supplied to the load in the electric vehicle through the high-voltage charging and distribution box, and the load includes an electric drive, a DCDC, an air conditioner (AC), a battery liquid heat (positive temperature coefficient thermistor (B-PTC)), a heater PTC, etc.

[0037] The centralized 800V direct current high-voltage charging and distribution system of the electric vehicle has the problem of energy or power function loss caused by single point failure in power distribution, and cannot meet the reliability and safety requirements of the electric aircraft. Therefore, the high-voltage charging and distribution system of the electric vehicle cannot be applied to the electric aircraft, and the high-voltage charging and distribution system of the manned electric aircraft needs a new design.

[0038] The present application provides a closed high-voltage charging and distribution system for an electric aircraft, which can meet the reliability and safety requirements of the electric aircraft, realize redundant power distribution of multiple bus bars and multiple loads, have sufficient safety design margin and reliability, and can also reduce the current carrying capacity of the high-voltage line through the high-voltage platform to reduce the weight of the aircraft.

[0039] Figure 2 A block diagram of a closed high-voltage charging and distribution system for an electric aircraft according to an embodiment of the present disclosure is shown. As shown in Figure 2 The system includes a load 210, an energy source system 220, and a high-voltage charging and distribution box 230.

[0040] ​Energy system 220 is used to provide electrical power to the electric aircraft. In this embodiment, energy system 220 includes n battery packs connected in parallel and is used to provide electrical power to load 210 through high-voltage charging and distribution box 230. n is an integer greater than 1. In this embodiment, the n battery packs provide a DC high-voltage voltage, which is greater than the rated voltage of existing electric aircraft, such as a high-voltage voltage of 800V. At this time, the n battery packs connected in parallel can provide a high-voltage platform with an operating DC voltage range of 500V to 900V and a rated voltage of 800V to the high-voltage charging and distribution box 230.

[0041] Load 210 is the electrical equipment in the electric aircraft. Load 210 includes at least the power unit of the electric aircraft, which includes an electric propulsion system and an electric lift system. The electric propulsion system provides thrust to the electric aircraft, and the electric lift system provides lift. The electric propulsion system and the electric lift system include an electric drive and a propulsion component. The propulsion component can be a propeller or a fan of the electric aircraft, which generates power through rotation to enable flight. The electric drive is connected to the propulsion component and is used to convert electrical energy into mechanical energy to drive the propulsion component, thereby enabling flight of the electric aircraft. The electric drive includes a motor and an electronic speed controller (ESC). The motor is an electric motor that drives the propulsion component to rotate, converting electrical energy into mechanical energy to propel the aircraft. The ESC is an electronic device that controls the speed and torque of the motor. The ESC receives commands from the flight control system to adjust the power supply to the motor, thereby controlling the speed and flight attitude of the aircraft.

[0042] In this embodiment, the electric drive includes a first electric drive for an electric lift system and a second electric drive for an electric propulsion system. The first electric drive provides lift to the electric aircraft and is symmetrically distributed on the arms of the electric aircraft. The second electric drive provides thrust to the electric aircraft and is symmetrically distributed on the tail of the electric aircraft.

[0043] For example: Reference Figure 3 The diagram shows the power plant layout of an electric vertical takeoff and landing (EVTOL) aircraft. This EVTOL aircraft has a compound wing configuration, and its power plant consists of two electric propulsion systems and eight electric lift systems. M1 to M8 are electric lift systems, each comprising four symmetrically arranged pairs of first electric drives. Along the central axis of the EVTOL aircraft, pairs of first electric drives for M1 and M3 are symmetrically arranged on the inner fuselage arm; pairs of first electric drives for M2 and M4 are symmetrically arranged on the inner fuselage arm; pairs of first electric drives for M5 and M7 are symmetrically arranged on the outer fuselage arm; and pairs of first electric drives for M6 and M8 are symmetrically arranged on the outer fuselage arm. M9 and M10 are electric thrust systems, each comprising one symmetrically arranged pair of second electric drives. Along the central axis of the EVTOL aircraft, pairs of second electric drives for M9 and M10 are symmetrically arranged on the tail section.

[0044] In this embodiment, in order to improve the safety and reliability of the electric aircraft, each electric drive includes m power supply circuits, so that when an abnormality occurs in one of the power supply circuits, power supply can still be achieved through another power supply circuit; m is an integer greater than 1. The value of m can be 2, or other values greater than 2, and the number of power supply circuits is not limited in this embodiment.

[0045] Optionally, the load 210 further includes a DCDC and / or a climate control device. The DCDC is used to convert the high-voltage power output by the high-voltage charging and distribution box 230 into low-voltage power (such as 24V) required by the low-voltage battery, to supply power to the low-voltage system of the aircraft.

[0046] The climate control device includes but is not limited to: a high-voltage air conditioning device, a high-voltage heating and ventilation device, and / or a high-voltage battery thermal management device, etc., and the climate control device is used to provide a suitable temperature for the passenger cabin and the battery pack of the electric aircraft.

[0047] Optionally, the closed high-voltage charging and distribution system further includes a charging structure connected to an external power source for charging the battery pack. Exemplarily, the charging structure is a direct current charging seat, thereby providing a high-voltage direct current charging interface for the electric aircraft, at this time, the external power source can be connected to the direct current charging seat through a charging gun, and the battery pack is charged through the high-voltage charging and distribution box 230. Among them, the external power source and the charging gun do not belong to the airborne equipment of the electric aircraft, and the external power source can be a new energy charging pile to provide charging energy for the aircraft.

[0048] In this embodiment, the electric aircraft further includes a vehicle control unit (VCU). The VCU is used to control the high-voltage distribution and high-voltage charging and discharging of the electric aircraft.

[0049] Specifically, when the electric aircraft is in a charging state, the high-voltage power of the external power source is connected to the aircraft direct current charging seat through the charging gun, the VCU is used to communicate with the external power source, and after successful communication, the VCU controls the high-voltage charging and distribution box 230 and the internal devices of the battery pack to connect the charging loop, and the high-voltage charging current enters the multiple battery packs of the energy system 220 from the external power source through the high-voltage charging and distribution box 230, to charge the battery packs. At the same time, the high-voltage charging current can also provide high-voltage power for the high-voltage devices of the whole machine, to realize the charging and discharging of the electric aircraft at the same time.

[0050] When the electric aircraft is in a high-voltage and non-charging state, the VCU is used to control the high-voltage discharging current to be distributed from the energy system 220 to the load 210, such as the high-voltage electrical propulsion system, the electrical lift system, the DCDC, the climate control system, and other high-voltage electrical devices of the whole machine.

[0051] The high-voltage charging and distribution box 230 is used for managing and distributing high-voltage electric energy. In this embodiment, the high-voltage charging and distribution box 230 has n busbars, so that the high-voltage charging and distribution box 230 obtains high-voltage electric energy of the battery pack through the busbars and distributes the high-voltage electric energy to the load 210 through the busbars, thereby ensuring efficient and stable transmission of the high-voltage electric energy.

[0052] The number of busbars is determined based on the number of battery packs, at this time, n busbars are respectively connected with n battery packs, and n busbars enclose m closed circuits; the i-th closed circuit is connected with the i-th power supply circuit of the electric drive to supply power to the i-th power supply circuit. i is a positive integer less than or equal to m, and m is an integer less than n.

[0053] In the formula, the closed circuit means that each busbar in the circuit is connected in series (or connected end to end), and a closed circuit is formed by connecting the first busbar and the last busbar in series.

[0054] For example, referring to Figure 4 , if the value of n is 8 and the value of m is 2. At this time, 8 busbars are numbered 1-8 in Figure 4 , and correspondingly, 8 battery packs, i.e. battery pack B1 to battery pack B8 in Figure 4 , constitute the energy system 220 of the electric aircraft in Figure 2 . According to Figure 4 , each busbar is respectively connected with one battery pack. The high-voltage charging and distribution box 230 includes two, i.e. high-voltage charging and distribution box 1 and high-voltage charging and distribution box 2, wherein busbars 1-4 are arranged in the high-voltage charging and distribution box 1, and busbars 1-4 are respectively connected with battery packs B1-B4; busbars 1-4 form a closed circuit to supply power to the A power supply circuit of each electric drive M1-M8, M9, M10. Busbars 5-8 are arranged in the high-voltage charging and distribution box 2, and busbars 5-8 are respectively connected with battery packs B5-B8; busbars 5-8 form another closed circuit to supply power to the B power supply circuit of each electric drive M1-M8, M9, M10. As shown in Figure 4 , each busbar in each closed circuit is connected in series, connected end to end, and encloses a closed circuit.

[0055] Figure 4 In the above embodiment, n is 8 and m is 2, but in actual implementation, n and m can also have other values, and the present embodiment does not limit the values of n and m.

[0056] At this time, if one of the m closed circuits fails, the other closed circuits can also supply power to the other power supply circuits of the electric drive. Different power supply circuits are arranged on different closed circuits. The failure of any closed circuit does not affect the normal operation of the electric drive, greatly improving the design safety margin, thereby ensuring the safe flight of the electric aircraft. At the same time, if a battery pack connected to a busbar in a closed circuit fails, other battery packs connected to busbars in the closed circuit can also supply power to the closed circuit, thereby ensuring the safe flight of the electric aircraft. At the same time, if a busbar in a closed circuit fails, other busbars can also normally distribute power. The system has sufficient safety design margin and reliability, thereby ensuring the safe flight of the electric aircraft.

[0057] In addition, the high-voltage charging and power distribution system not only has high-voltage power distribution function, but also can contain high-voltage charging function. The high-voltage power distribution system can realize the setting of 800V DC voltage platform in the electric aircraft. Compared with 400V or 600V voltage platform, the current of high-voltage loop equipment can be reduced. Since the smaller the current is, the cross-sectional area of the electric wire in the electric aircraft can be smaller, thereby the weight of the high-voltage equipment can be greatly reduced. Taking the high-voltage wire harness as an example, compared with the 400V platform, the weight of the high-voltage wire harness can be reduced by nearly 40% under the 800V DC. In addition, the application of 800V DC high-voltage charging and power distribution system in the electric vertical take-off and landing aircraft fills the gap of EVTOL, which is conducive to the rapid development of EVTOL.

[0058] Optionally, each busbar in each closed circuit is connected with at least one pair of symmetric first electric drives. In this way, in the case that any busbar in the closed circuit cannot supply power due to abnormality, the first electric drives connected with the busbar are symmetrically distributed. At this time, the electric aircraft can still maintain balance, thereby ensuring the safe flight of the electric aircraft.

[0059] Optionally, each power supply circuit of each electric drive is uniformly distributed on the corresponding closed circuit, thereby ensuring the load balance between different busbars.

[0060] For example, refer to Figure 4 Taking the first electric drive as the lift electric drive and the lift electric drive as 8, M1-M8 as an example. The busbar 1 in the closed circuit in the high-voltage charging and power distribution box 1 supplies power to the A power supply circuit of a pair of symmetrically arranged lift electric drives M2 and M4 through the high-voltage line. The busbar 2 supplies power to the A power supply circuit of a pair of symmetrically arranged lift electric drives M1 and M3 through the high-voltage line. The busbar 3 supplies power to the A power supply circuit of a pair of symmetrically arranged lift electric drives M6 and M8 through the high-voltage line. The busbar 4 supplies power to the A power supply circuit of a pair of symmetrically arranged lift electric drives M5 and M7 through the high-voltage line.

[0061] Similarly, the busbar 5 in the closed circuit in the high-voltage charging and distribution box 2 supplies power to the B power supply circuit of a pair of symmetrically arranged lift electric drives M2 and M4 through the high-voltage line, the busbar 6 supplies power to the B power supply circuit of a pair of symmetrically arranged lift electric drives M1 and M3 through the high-voltage line, the busbar 7 supplies power to the B power supply circuit of a pair of symmetrically arranged lift electric drives M6 and M8 through the high-voltage line, and the busbar 8 supplies power to the B power supply circuit of a pair of symmetrically arranged lift electric drives M5 and M7 through the high-voltage line.

[0062] Figure 4 The symmetrically arranged lift electric drives connected by each busbar shown are only illustrative, and in other implementations, the numbers of the symmetrically arranged lift electric drives connected by each busbar can also be other manners, for example, the pair of lift electric drives connected by the busbar 1 are M1 and M3, and which pair of lift electric drives is connected by each busbar can be set based on the shortest line principle, and the present embodiment does not limit the symmetrically arranged lift electric drives connected by each busbar.

[0063] Optionally, the symmetrically arranged second electric drives connected to the same closed circuit are distributed in different busbars in the closed circuit.

[0064] For example, the second electric drives are thrust electric drives, and the number of the thrust electric drives is 2 (i.e., a pair). Since each power supply circuit of the 2 thrust electric drives is distributed in different busbars in the corresponding closed circuit (i.e., the power supply circuits of different thrust electric drives are connected to different busbars), it can be ensured that even if the line in which one busbar is located cannot supply power, the other thrust electric drive can still work, thereby ensuring the flight safety of the electric aircraft. For example, referring to Figure 4 The A power supply circuit of the pair of thrust electric drives M9 and M10 is connected to the closed circuit in the high-voltage charging and distribution box 1 through the high-voltage line, wherein the A power supply circuit of the thrust electric drive M9 is connected to the busbar 1 in the closed circuit, the A power supply circuit of the thrust electric drive M10 is connected to the busbar 3 in the closed circuit, and the thrust electric drives M9 and M10 are distributed in different busbars.

[0065] Similarly, the B power supply circuit of the pair of thrust electric drives M9 and M10 is connected to the closed circuit in the high-voltage charging and distribution box 2 through the high-voltage line, wherein the B power supply circuit of the thrust electric drive M9 is connected to the busbar 5 in the closed circuit, the B power supply circuit of the thrust electric drive M10 is connected to the busbar 7 in the closed circuit, and the thrust electric drives M9 and M10 are distributed in different busbars.

[0066] According to Figure 4 It can be known that at this time, each closed circuit includes 4 busbars, the 4 busbars are connected to 4 pairs of first electric drives respectively, and 1 pair of second electric drives is distributed in different busbars in the closed circuit.

[0067] Figure 4 The symmetrical thrust electric drives connected by each busbar shown are only illustrative, in other implementations, symmetrical lift electric drives can also be distributed to other busbars, such as: M9 in the thrust electric drive connected by busbar 2, M10 in the thrust electric drive connected by busbar 4, which thrust electric drive each busbar is specifically connected to can be set based on the shortest line principle, and the present embodiment does not limit the thrust electric drive connected by each busbar.

[0068] Optionally, the load 210 further includes at least two environmental control devices and at least two DC-DC converters; the at least two environmental control devices are connected to different busbars, and the at least two DC-DC converters are connected to different busbars.

[0069] Optionally, in the case where the number of environmental control devices and DC-DC converters is less than or equal to the number of busbars, the environmental control devices and DC-DC converters are also arranged on different busbars.

[0070] For example, the environmental control devices include 3, which are: high-voltage electric air conditioning equipment, high-voltage electric heating equipment, and high-voltage battery thermal management equipment. Figure 4 As shown, the environmental control device 1 is connected to the busbar 4, the environmental control device 2 is connected to the busbar 2, and the environmental control device 3 is connected to the busbar 8. Figure 4 As shown, the DCDC 1 is connected to the busbar 1, and the DCDC 2 is connected to the busbar 6.

[0071] Optionally, the load 210 on each closed line is connected to the closed line based on the shortest line principle, at this time, it can be ensured that the lines in the electric aircraft are as short as possible, thereby reducing the weight of the electric wire, which is conducive to the lightweight design of the electric aircraft.

[0072] Optionally, in the case where the electric aircraft includes a charging structure, when the charging structure is connected to an external power source, the connected battery pack is charged through the first closed line; the first closed line is electrically connected to the second closed line to charge the battery pack connected by the second closed line through the first closed circuit; wherein the second closed line is other closed lines in addition to the first closed line among the m closed lines. Illustratively, the electrical connection between the first closed line and the second closed line can be achieved through a high-voltage wire harness.

[0073] For example, refer to Figure 4, the closed circuit in the high-voltage charging and distribution box 2 is a first closed circuit, and the closed circuit in the high-voltage charging and distribution box 1 is a second closed circuit. At this time, the charging structure is connected to the busbar 8 in the first closed circuit through the relay S1, so that the battery packs B5-B8 connected to the busbars 5-8 in the first closed circuit can be charged in direct current. Since the first closed circuit is electrically connected to the second closed circuit, the battery packs B1-B4 connected to the second closed circuit can be charged through the first closed circuit.

[0074] At this time, when the electric aircraft is charged in direct current, the fast charging relay S1 in the high-voltage charging and distribution box 2 is closed, and the high-voltage power of the external power supply enters the fast charging loop of the high-voltage charging and distribution box 2 through the fast charging high-voltage line, while charging the eight battery packs.

[0075] Optionally, the first closed circuit and the second closed circuit are electrically connected through a third protection device, which is used to cut off the connection between the first closed circuit and the second closed circuit when an abnormality occurs in the first closed circuit or the second closed circuit connected thereto, so that the abnormality is isolated, and the flight safety of the electric aircraft is ensured.

[0076] Exemplarily, referring to Figure 4 , the electrical connection between the first closed circuit and the second closed circuit includes the electrical connection between the busbar 4 and the busbar 8, and the electrical connection between the busbar 2 and the busbar 6. In other implementations, the electrical connection between the first closed circuit and the second closed circuit can also connect other busbars in different closed circuits, such as the busbar 4 and the busbar 7, or the busbar 1 and the busbar 5, etc. The present embodiment does not limit the electrical connection mode between the first closed circuit and the second closed circuit.

[0077] Optionally, the different busbars in each closed circuit are connected in a head-to-tail manner through a first protection device; the first protection device connected to each busbar is used to cut off the connection between the busbar and other busbars in the case of an abnormality in the circuit where the busbar is located. For example, the first protection device is used for overload protection between different busbars.

[0078] The n busbars and the electric drives are connected through a second protection device; the second protection device connected to each electric drive is used to cut off the connection between the electric drive and the busbar in the case of an abnormality in the circuit where the electric drive is located. For example, the second protection device can be Figure 5 the fuses F1-F25 in the high-voltage charging and distribution box 2, which respectively provide short-circuit and overcurrent protection for the power supply circuits of the electric drives.

[0079] The system architecture can distribute high-voltage electricity of the battery pack to the electric drive, the environmental control, and other high-voltage loads 210 through the busbar during normal operation of the electric airplane, and can balance the voltage among different battery packs. In the case of an abnormality in one of the m closed circuits or one of the n battery packs, the redundancy of the system enables the normal battery pack to supply power to the load 210 on the normal closed circuit, thereby ensuring the flight safety and reliability of the electric airplane.

[0080] The abnormality in one of the m closed circuits or one of the n battery packs includes, but is not limited to, at least one of the following:

[0081] 1. A short-circuit abnormality occurs in the circuit in which any one of the busbars is connected. At this time, the first protection device can detect the short-circuit abnormality of the circuit in which the busbar is connected, and thereby be disconnected based on the overload protection function. At this time, the battery pack connected to the busbar that does not have the short-circuit abnormality can supply power to the load 210 connected thereto, thereby ensuring the normal operation of the load 210.

[0082] The disconnection of the first protection device includes: controlling all the first protection devices to be disconnected; or controlling all the first protection devices to be disconnected, and after a preset time period, restoring the connection of the first protection device connected to the busbar that does not have the short-circuit abnormality.

[0083] During the operation of the electric airplane, a short-circuit abnormality can occur in any busbar or external high-voltage circuit of the high-voltage charging and distribution box 230. For example, referring to Figure 5 , it is assumed that the short-circuit point is at the red dot of the high-voltage circuit between the busbar 3 or the front end of the electric drive fuse F2 or the battery pack B3 and the high-voltage charging and distribution box 230. At this time, under the action of the short-circuit current, all the first protection devices are disconnected, as shown in Figure 6 , all the third protection devices can also be disconnected, and the short-circuit fault is isolated on the circuit of the busbar 3 or the battery pack 3. At this time, the battery pack B3 stops outputting, and the electric drives M6, M8, and M10 lose the A-path high-voltage power supply. However, the other battery packs except the battery pack B3 can work normally and supply power to the loads 210 of the busbars where they are located, and the different battery packs cannot continue to share electric energy, but the airplane can still land safely.

[0084] If the first protection device connected to the busbar that does not have the short-circuit abnormality is restored to be connected after a preset time period, the different battery packs can also continue to share electric energy, and the airplane can still land safely, which can ensure the flight safety and reliability of the electric airplane. In the case of disconnection of the third protection device and no short-circuit abnormality in the busbar connected to the third protection device, the third protection device can also be restored to be connected.

[0085] 2. One of the busbars in any one closed circuit has an open circuit fault. At this time, the battery packs and the load 210 connected to the busbars that do not have an open circuit fault are operating normally.

[0086] For example, referring to ​ , suppose that the battery pack B3 cannot output power due to a body failure, and the battery pack B8 cannot output power to the load 210 due to an open circuit between the battery pack B8 and the high-voltage charging distribution box 230. Since the system architecture is a closed architecture, the eight battery packs can share power, and therefore, the electric drives M6, M8, and M10 on the busbar 3 and the busbar 7 can still be provided by the remaining six battery packs. Although this may affect the flight range to some extent, it does not affect the safe landing of the aircraft, and can ensure the flight safety and reliability of the electric aircraft.

[0087] The above has described various embodiments of the present disclosure, and the above description is exemplary, is not exhaustive, and is not limited to the disclosed embodiments. Many modifications and changes are obvious to those skilled in the art without departing from the scope and spirit of the described embodiments. The choice of terms used herein is intended to best explain the principles of the embodiments, practical applications, or improvements to the technology in the market, or to enable other ordinary skilled persons in the art to understand the embodiments disclosed herein.

Claims

1. A closed-loop high-voltage charging and distribution system for an electric aircraft, characterized in that, The system includes: The load includes an electric drive, each electric drive including m power supply circuits; wherein m is an integer greater than 1; n battery packs connected in parallel are used to provide electrical energy to the load through a high-voltage charging and distribution box; where n is an integer greater than 1; The n busbars located in the high-voltage charging and distribution box are respectively connected to the n battery packs; the n busbars form m closed circuits; the i-th closed circuit is connected to the i-th power supply circuit of the electric drive to supply power to the i-th power supply circuit; where i is a positive integer less than or equal to m, and m is an integer less than n.

2. The system according to claim 1, characterized in that, Different busbars in each enclosed line are connected end to end by a first protection device; the first protection device connected to each busbar is used to disconnect the connection between the busbar and other busbars in the event of an abnormality in the line where the busbar is located.

3. The system according to claim 1, characterized in that, The electric drive includes a first electric drive, which is used to provide lift for the electric aircraft and is symmetrically distributed on the arms of the electric aircraft. Each busbar in each enclosed circuit is connected to at least one pair of symmetrical first electric drives.

4. The system according to claim 1, characterized in that, The electric drive includes a second electric drive; the second electric drive is used to provide thrust to the electric aircraft and is symmetrically distributed on the tail of the electric aircraft. A symmetrical second electric drive connected to the same enclosed circuit is distributed in different busbars within the enclosed circuit.

5. The system according to claim 1, characterized in that, The first closed circuit among the m closed circuits is connected to a charging structure. When the charging structure is connected to an external power source, it charges the connected battery pack through the first closed circuit. The first closed circuit is electrically connected to the second closed circuit so as to charge the battery pack connected to the second closed circuit through the first closed circuit; The second closed circuit is any of the m closed circuits other than the first closed circuit.

6. The system according to claim 1, characterized in that, The n busbars are connected to the electric drive via a second protection device. The second protection device connected to each electric drive is used to disconnect the connection between the electric drive and the busbar in the event of an abnormality in the line where the electric drive is located.

7. The system according to claim 1, characterized in that, The load also includes at least two environmental control devices and at least two DC converters; the at least two environmental control devices are connected to different busbars, and the at least two DC converters are connected to different busbars.

8. The system according to claim 1, characterized in that, The load on each closed line is connected to the closed line based on the shortest path principle.

9. The system according to any one of claims 1 to 8, characterized in that, The n battery packs connected in parallel provide a high-voltage platform for the high-voltage charging and distribution box, with a working DC voltage range of 500V to 900V and a rated voltage of 800V.

10. The system according to claim 9, characterized in that, The electric drive includes four pairs of first electric drives and one pair of second electric drives arranged symmetrically; the value of m is 2; the high-voltage charging and distribution box includes two boxes; each high-voltage charging and distribution box includes a closed circuit; each closed circuit includes four busbars; the four busbars are respectively connected to the four pairs of first electric drives; and the one pair of second electric drives is distributed in different busbars in the closed circuit.

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