Aircraft and power battery system thereof

Abstract

The invention discloses a power battery system of an aircraft, the power battery system comprises a plurality of power pack modules and a high-voltage control box, each power pack module comprises a shell, a battery cell, a BMS slave plate and a cooling plate; the high-voltage control box comprises a high-voltage control assembly and a BMS main control board, the BMS main control board is electrically connected with the high-voltage control assembly, and the BMS slave boards of the power pack modules which are sequentially connected in series are electrically connected with the BMS main control board and used for conducting high-voltage distribution on direct current supplied by the power pack modules which are sequentially connected in series; the cooling plates of the power pack modules which are sequentially connected in series are communicated with the cooling liquid, and the cooling liquid is used for cooling the power pack modules. The invention further discloses an aircraft. According to the aircraft and the power battery system thereof, the battery system can be arranged in multiple fragmentary spaces of the aircraft fuselage, and the space utilization rate of the aircraft is increased; the structure is simplified, and the heat dissipation performance and the safety of the power battery are enhanced.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft batteries, and particularly to an aircraft and its power battery system. Background Art

[0002] Electric aircraft have a wide range of applications in usage scenarios such as aerial photography, air logistics transportation, air passenger flight, and space traffic networks.

[0003] Existing electric aircraft usually adopt an integrated power supply system design. This structural solution has the following technical problems: 1. The integrated power supply system itself is relatively large in size, occupying most of the space in the aircraft cabin, making it difficult to streamline the aircraft in terms of volume design, resulting in low space utilization of the aircraft. 2. The heat generated by the battery cells in the integrated power supply system design is more likely to accumulate and is not easy to dissipate. At the same time, once a single battery cell in the pack touches off a thermal runaway, it is easy to trigger hazards at the whole pack level, posing certain safety hazards. Summary of the Invention

[0004] The technical problem to be solved by the present invention is to provide an aircraft and its power battery system that can arrange the battery system in multiple fragmented spaces on the aircraft fuselage, improve the space utilization rate of the aircraft; have a streamlined structure, and enhance the heat dissipation performance and safety of the power battery.

[0005] To solve the above technical problem, the present invention provides a power battery system for an aircraft, including: a plurality of power supply group modules and a high-voltage control box. The plurality of power supply group modules are connected in series in sequence to form a high-voltage circuit, and the high-voltage control box is connected to the high-voltage circuit. The power supply group module includes: a housing, battery cells installed in the housing, a BMS slave board, and a cooling plate for heat conduction of the power supply group module. The high-voltage control box at least includes: a high-voltage control component, and a BMS main board for monitoring the various states of the power supply group module by obtaining the working electrical signals of the BMS slave boards of each power supply group module. The BMS main board is electrically connected to the high-voltage control component, wherein: the BMS slave boards of the plurality of power supply group modules connected in series in sequence are respectively electrically connected to the BMS main board for high-voltage distribution of the direct current supplied by the plurality of power supply group modules connected in series in sequence; the cooling plates of the plurality of power supply group modules connected in series in sequence are in liquid communication with each other through a coolant for dissipating heat from the power supply group module.

[0006] Wherein, the power supply group module further includes: a temperature and voltage acquisition board installed on the battery cells for acquiring the temperature and voltage signals of the battery cells. The temperature and voltage acquisition board is electrically connected to the BMS slave board, and the BMS slave board is electrically connected to the battery cells.

[0007] Wherein, heat insulation foam is installed between the periphery of the battery cell and the housing; the housing includes a bottom housing and a top housing surrounding the bottom housing, and heat conduction structures are respectively arranged between the battery cell and the bottom housing and between the battery cell and the top housing.

[0008] Wherein, the heat conduction structure includes an L-shaped aluminum plate attached to one side of the battery cell and an aerogel layer bonded between the L-shaped aluminum plate and the battery cell; and / or a foamed polyurethane layer attached to the other side of the battery cell and a heat conduction structural adhesive bonded between the foamed polyurethane layer and the battery cell.

[0009] Wherein, an L-shaped aluminum plate is installed between the housing and the battery cell, and a plurality of through holes are formed in the L-shaped aluminum plate.

[0010] Wherein, a coolant inlet and outlet are arranged on one side of the cooling plate, and a plurality of coolant flow channels are arranged between the coolant inlet and outlet, and the coolant inlets and outlets between the cooling plates of multiple power supply module groups are connected in series in sequence; cooling fin channels are arranged on the other side of the cooling plate opposite to each other.

[0011] Wherein, the high-voltage control box further includes a box body, the BMS main control board is installed in the box body, and an assembly port for assembling the BMS main control board is reserved in the box body.

[0012] Wherein, the high-voltage control component further includes an input high-voltage socket, an output high-voltage socket, a low-voltage electrical interface for the whole machine communication respectively installed on the box body, and a plurality of relays installed in the box body for opening and closing electrical components in the high-voltage circuit and performing circuit protection; the BMS main control board is electrically connected to the plurality of relays respectively.

[0013] Wherein, the plurality of relays include a pre-charge relay, a main positive relay and a main negative relay.

[0014] To solve the above technical problems, the present invention also discloses an aircraft having the above power battery system.

[0015] Implementing an aircraft and its power battery system of the present invention has the following beneficial effects:

[0016] First, the power battery system of the aircraft includes: multiple power supply module groups and a high-voltage control box. The multiple power supply module groups are connected in series in sequence to form a high-voltage circuit, and the high-voltage control box is connected to this high-voltage circuit. The power supply module group includes: a housing, battery cells installed in the housing, and a BMS slave board installed on the battery cells for collecting the working electrical signals of the battery cells. The high-voltage control box includes: a high-voltage control component and a BMS master board for monitoring the various states of the power supply module group by obtaining the working electrical signals of the BMS slave board of each power supply module group. The BMS master board is electrically connected to the high-voltage control component, where: the BMS slave boards of multiple power supply module groups connected in series in sequence are respectively electrically connected to the BMS master board, used for high-voltage distribution of the direct current supplied by multiple power supply module groups connected in series in sequence, dividing the power battery system into several small power supply module groups, which can be integrated in multiple fragmented space positions on the aircraft fuselage, improving the space utilization rate and integration degree of the aircraft.

[0017] Second, the power supply module group is provided with a cooling plate, and the cooling liquids between the cooling plates of multiple power supply module groups connected in series in sequence are in liquid communication, capable of dissipating heat from the power supply module group, enhancing the heat dissipation performance and safety of the power battery.

[0018] Third, it has a compact structure, which is convenient for installation and replacement. Description of the Drawings

[0019] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required for use in the description of the embodiments or the prior art. Obviously, the drawings in the following description are only some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on these drawings.

[0020] Figure 1 It is a structural block diagram of the power battery system of the aircraft in the embodiment of the present invention.

[0021] Figure 2 It is a schematic explosion structure diagram of the power supply module group in the embodiment of the present invention.

[0022] Figure 3 It is a schematic structural diagram of the assembly of the battery cells of the power supply module group and the L-shaped aluminum plate in the embodiment of the present invention.

[0023] Figure 4 It is a schematic top view structure diagram of the L-shaped aluminum plate in the embodiment of the present invention.

[0024] Figure 5 It is a schematic structural diagram of the cooling plate of the power supply module group in the embodiment of the present invention.

[0025] Figure 6This is a schematic diagram of a partial structure of the cooling plate of the power supply module of the power source in the embodiment of the present invention from a side view angle.

[0026] Figure 7 This is a schematic diagram of the external structure of the high-voltage control box in the embodiment of the present invention.

[0027] Figure 8 This is a schematic diagram of the internal structure of the high-voltage control box in the embodiment of the present invention. Detailed implementation manners

[0028] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0029] As Figures 1-8 shown, this is the first embodiment of the power battery system of the aircraft of the present invention.

[0030] In this embodiment, the power battery system of the aircraft includes: a plurality of power supply modules 1 and a high-voltage control box 2. The plurality of power supply modules 1 are connected in series in sequence to form a high-voltage circuit A, and the high-voltage control box 2 is connected to the high-voltage circuit A. During implementation, the high-voltage circuit A formed by the series connection of the plurality of power supply modules 1 has a total positive electrode and a total negative electrode led out, and the positive and negative electrodes of the high-voltage control box are correspondingly connected to the total positive electrode and the total negative electrode of the high-voltage circuit A to achieve access control.

[0031] The power supply module 1 includes: a housing, a battery cell 12 installed in the housing, a BMS slave board 13 installed on the battery cell 12 for collecting the working electrical signals of the battery cell, and a cooling plate 14 installed at the bottom of the housing for heat conduction of the power supply module 1.

[0032] The high-voltage control box 2 at least includes: a high-voltage control component 21, and a BMS main board 22 for monitoring the various states of the power supply module 1 by obtaining the working electrical signals of the BMS slave board 13 of each power supply module 1. The BMS main board 22 is electrically connected to the high-voltage control component 21. Among them: the BMS slave boards 13 of the plurality of power supply modules 1 connected in series in sequence are respectively electrically connected to the BMS main board 22 to achieve high-voltage distribution of the direct current supplied by the plurality of power supply modules 1 connected in series in sequence.

[0033] The cooling plates 14 of the plurality of power supply modules 1 connected in series in sequence are in liquid communication with each other through a coolant to form a cooling circuit B, and the cooling circuit B is used for dissipating heat from the power supply module 1.

[0034] In specific implementation, by controlling the weight and volume of a single power supply module 1, multiple power supply modules 1 can be respectively integrated into the fragmented spaces of parts such as the fuselage, cabin, and wing of the aircraft, so as to improve the space utilization rate and integration degree of the aircraft. In this embodiment, it is set as four power supply modules 1, and it can also be configured as other numbers of power supply modules 1 according to the quantity, position, and volume of the specific fragmented spaces of the aircraft.

[0035] It can be understood that by independently setting multiple power supply modules 1, the installation and replacement of the power battery system are also more convenient. The internal of the power supply module 1 realizes high integration in the limited space of the aircraft through the CTP integration method. Connecting multiple power supply modules 1 in series replaces the traditional integrated power PACK, which is more convenient for the overall machine layout and improves the power density of the power supply system.

[0036] Furthermore, each power supply module 1 includes: a housing, battery cells 12, a BMS slave board 13, and a cooling plate 14.

[0037] Among them: the housing includes: a bottom housing 111 and a top housing 112 surrounding the bottom housing 111, and the battery cells 12 are installed in the housing. In this embodiment, heat insulation foam is installed between the periphery of the battery cells 12 and the housing (bottom housing 111 and top housing 112). The function of the heat insulation foam is: it can absorb the expansion of the battery cells 12 caused by the change of the external temperature.

[0038] Preferably, heat conduction structures are respectively provided between the battery cells 12 and the bottom housing 111, and between the battery cells 12 and the top housing 112.

[0039] In implementation, the heat conduction structure between the battery cells 12 and the top housing 112 is: an L-shaped aluminum plate 113 attached to one side of the battery cell and an aerogel layer 114 bonded between the L-shaped aluminum plate 113 and the battery cells 12. The heat conduction structure between the battery cells 12 and the bottom housing 111 is: a foamed polyurethane layer attached to the other side of the battery cells 12 and a heat conduction structural adhesive bonded between the foamed polyurethane layer and the battery cells. The battery cells 12 and the bottom housing 111 form a CTP integrated structure through this heat conduction structure.

[0040] Through the above heat conduction structure, the heat conduction between the battery cells 12 and the housing can be further enhanced, and the heat dissipation performance of the power supply module 1 can be improved. In addition, the above heat conduction structure can also be adjusted in position according to actual needs. For example: assembling the structure side containing the L-shaped aluminum plate 113 at the position between the battery cells 12 and the bottom housing 111.

[0041] Preferably, a plurality of through holes 1131 are opened on the L-shaped aluminum plate 113. The plurality of through holes 1131 in this embodiment are arranged equidistantly and uniformly. Its function is: to reduce the weight of the L-shaped aluminum plate 113 and make the power supply module 1 lightweight.

[0042] Further, each power supply module 1 is equipped with a BMS slave board 13, and the BMS slave board 13 is connected to the battery cells 12. In this embodiment, the BMS slave board 13 is fixed to the inner side of the housing by bolts.

[0043] The function of the BMS slave board 13 is to collect the working electrical signals of the battery cells 12 and perform power management on a single power supply module 1. For example, it equalizes the energy of the battery cells 12 of a single power supply module 1, collects the current and voltage data of the battery cells 12, performs charge and discharge control, and monitors the status of each power supply module 1.

[0044] Further, the cooling plate 14 in this embodiment is fixed to the housing by friction stir welding. The function of arranging the cooling plate 14 at the bottom of each power supply module 1 is to conduct heat for each power supply module 1, ensure that each battery cell 12 is at an appropriate temperature during operation, and enhance the heat dissipation performance and safety of the power battery.

[0045] During specific implementation, coolant inlets and outlets 141, 142 are arranged on one side of each cooling plate 14, and multiple coolant flow channels 143 are provided between the coolant inlets and outlets 141, 142. For example, in this embodiment, there are three coolant flow channels. Between the adjacent cooling plates 14 of multiple power supply modules 1, series connection is implemented through their respective coolant inlets and outlets 141, 142. During implementation, when the assembly positions between individual power supply modules 1 are slightly far apart, connection can be achieved by setting cooling software between adjacent cooling plates 14.

[0046] Preferably, cooling fin channels 144 are provided on the opposite side of the cooling plate 14.

[0047] The function of setting the cooling fin channels 144 is that since the cooling plate 14 of each power supply module 1 is arranged at the bottom of the housing, when the power supply module 1 is assembled at the bottom of the aircraft, the cooling fin channels 144 of the cooling plate 14 are in contact with the external air, and heat dissipation of the entire power system is accelerated through the contact between the cooling fin channels 144 and the air flow in flight.

[0048] Further, the power supply module 1 further includes a temperature and voltage acquisition board 15 installed on the battery cells 12. The temperature and voltage acquisition board 15 is electrically connected to the BMS slave board 13, for example, through a low-voltage wire harness. The temperature and voltage acquisition board 15 acquires the temperature and voltage signals of each battery cell 12, and the BMS slave board 13 uses the above data as the basis for battery cell charging control, power health monitoring, and SOX estimation.

[0049] Further, the high-voltage control box 2 includes: a box body 20, a high-voltage control component 21 installed in the box body 20, and a BMS main control board 22 electrically connected to the high-voltage control component 21. The BMS main control board 22 is installed in the box body 20, and the box body 20 is provided with an assembly port for assembling the BMS main control board 22. In this way, each component of the high-voltage control component 21 can be connected through a collection line to achieve quick plugging and unplugging.

[0050] During implementation, the high-voltage control component 21 is a BDU and a CMU module in this embodiment; the BMS slave boards 13 of multiple sequentially connected power supply group modules 1 are electrically connected to the BMS main control board 22 respectively. For example, they are connected through a CAN line.

[0051] The function of the BMS main control board 22 is: to be able to perform high-voltage distribution on the direct current power supplied by multiple sequentially connected power supply group modules 1. In addition, the BMS main control board 22 can also monitor the various states of the power supply group module 1 by obtaining the working electrical signals of the BMS slave boards 13 of each power supply group module 1 to ensure the safe use of the power supply during the charging and discharging process; at the same time, the BMS main control board 22 is further connected to the positive and negative high-voltage buses and has the function of collecting electrical signals on the high-voltage buses.

[0052] Preferably, to implement the above functions of the BMS main control board 22, the following components adapted to the BMS main control board 22 need to be assembled for implementation. For example, an input high-voltage socket 211, an output high-voltage socket 212, a low-voltage electrical interface 213 for the whole machine communication, which are respectively installed on the box body, and multiple relays installed in the box body for opening, closing and circuit protection of the electrical components in the high-voltage circuit. The BMS main control board is electrically connected to the multiple relays respectively.

[0053] The relays in this embodiment include: a pre-charge relay 214, a main positive relay 215 and a main negative relay 216. In addition, the high-voltage control component 21 also includes components such as a current sensor and a fuse installed in the box body 20 to cooperate with the above multiple relays to achieve the opening, closing and circuit protection functions of the system.

[0054] In addition, the BMS slave boards 13 of multiple sequentially connected power supply group modules 1 are connected to the BMS main control board 22 of the high-voltage control box 2 through a CAN line. On the basis of canceling the BDU unit, the thermal management ability of the power supply module is increased, and the unexpected effect of reducing the complexity of the power supply system is achieved.

[0055] In the specific implementation of the power battery system of the aircraft in this embodiment, the power supply group module 1 supplies output direct current to the high-voltage control box 2 during discharge, and the BMS main control board 22 performs a high-voltage power distribution function to distribute the output direct current to high-voltage working parts such as the motor of the aircraft; the BMS of the power supply group module 1 collects the temperature and cell voltage signals of each battery cell 12 from the board 13, monitors the single cell voltage, single cell temperature and other information of each battery cell 12 in real time, and then transmits the collected signals to the BMS main control board 22 to achieve the purpose of power balance.

[0056] After the operating temperature of the power supply module 1 exceeds a certain temperature threshold, the cooling assembly of the power battery system of the aircraft starts to work, taking away the heat through the flow of the coolant, and contacting with the air through the cooling wing channel 144 of the cooling plate 14 to achieve heat conduction and heat transfer;

[0057] The BMS main control board 22 collects electrical signals from various components of the high-voltage control component 21 and receives signals from the BMS slave board 13, communicates with the entire machine through the low-voltage electrical interface 213, and controls the related actions of the pre-charge relay 214, the main positive relay 215 and the main negative relay 216 of the high-voltage control component 21, thereby achieving the purpose of monitoring the power supply status.

[0058] The present invention further discloses an aircraft, the power battery system contained in the aircraft is the power battery system of the aircraft in the above-mentioned embodiment of the present invention, and the specific implementation manner is not repeated here.

[0059] The aircraft and the power battery system thereof implementing the present invention have the following beneficial effects:

[0060] First, the power battery system of the aircraft includes: a plurality of power supply group modules and a high-voltage control box, wherein the plurality of power supply group modules are sequentially connected in series to form a high-voltage circuit, and the high-voltage control box is connected to the high-voltage circuit; the power supply group module includes: a shell, a battery cell installed in the shell, and a BMS slave board installed on the battery cell for collecting the working electrical signals of the battery cell; the high-voltage control box includes: a high-voltage control component and a BMS main control board for monitoring various states of the power supply group module by acquiring the working electrical signals of the BMS slave board of each power supply group module; the BMS main control board is electrically connected to the high-voltage control component, wherein: the BMS slave boards of the plurality of power supply group modules sequentially connected in series are respectively electrically connected to the BMS main control board, for high-voltage distribution of the direct current supplied by the plurality of power supply group modules sequentially connected in series, and the power battery system is divided into a plurality of small power supply group modules, which can be integrated in a plurality of fragmented space positions of the aircraft fuselage, thereby improving the space utilization and integration of the aircraft.

[0061] Second, the power supply module group is provided with a cooling plate, and the cooling liquids between the cooling plates of multiple power supply module groups connected in series are in liquid communication with each other, which can dissipate heat from the power supply module group and enhance the heat dissipation performance and safety of the power battery.

[0062] Third, it has a compact structure, which is convenient for installation and replacement.

Claims

1. A power battery system for an aircraft, characterized in that, it includes: a plurality of power supply module groups and a high-voltage control box, the plurality of power supply module groups are connected in series in sequence to form a high-voltage circuit, and the high-voltage control box is connected to this high-voltage circuit; The power supply module group includes: a housing, battery cells installed in the housing, a BMS slave board, and a cooling plate for conducting heat of the power supply module; The high-voltage control box at least includes: a high-voltage control component, and a BMS main control board for monitoring the various states of the power supply module group by obtaining the working electrical signals of the BMS slave boards of each power supply module group, the BMS main control board is electrically connected to the high-voltage control component, wherein: The BMS slave boards of the plurality of power supply module groups connected in series in sequence are respectively electrically connected to the BMS main control board for performing high-voltage distribution on the direct current power supplied by the plurality of power supply module groups connected in series in sequence; The cooling plates between the plurality of power supply module groups connected in series in sequence are in liquid communication with each other by a coolant for dissipating heat of the power supply module group.

2. The power battery system for an aircraft according to claim 1, characterized in that, The power supply module group further includes: a temperature and voltage acquisition board installed on the battery cell for acquiring the battery cell temperature and battery cell voltage signals, the temperature and voltage acquisition board is electrically connected to the BMS slave board, and the BMS slave board is electrically connected to the battery cell.

3. The power battery system for an aircraft according to claim 1 or 2, characterized in that, Heat insulation foam is installed between the periphery of the battery cell and the housing; The housing includes: a bottom housing and a top housing surrounded on the bottom housing, and heat conduction structures are respectively provided between the battery cell and the bottom housing, and between the battery cell and the top housing.

4. The power battery system for an aircraft according to claim 3, characterized in that, The heat conduction structure includes: an L-shaped aluminum plate attached to one side surface of the battery cell and an aerogel layer bonded between the L-shaped aluminum plate and the battery cell; and / or A foamed polyurethane layer attached to the other side surface of the battery cell and a heat conductive structural adhesive bonded between the foamed polyurethane layer and the battery cell.

5. The power battery system for an aircraft according to claim 3, characterized in that, An L-shaped aluminum plate is installed between the housing and the battery cell, and a plurality of through holes are opened on the L-shaped aluminum plate.

6. The power battery system for an aircraft according to claim 1, characterized in that, Coolant inlets and outlets are arranged on one side of the cooling plate, and a plurality of coolant flow channels are provided between the coolant inlets and outlets, and the coolant inlets and outlets between the cooling plates of the plurality of power supply module groups are connected in series in sequence; Cooling fin channels are provided on the other opposite side of the cooling plate.

7. The power battery system for an aircraft according to claim 1, characterized in that, The high-voltage control box further includes: a box body, the BMS main control board is installed in the box body, and an assembly port for assembling the BMS main control board is reserved on the box body.

8. The power battery system for an aircraft according to claim 7, characterized in that, The high-voltage control component further includes: an input high-voltage socket, an output high-voltage socket interface, a low-voltage electrical interface for the communication of the whole machine, which are respectively installed on the box body, and a plurality of relays installed in the box body for opening and closing the electrical components in the high-voltage circuit and for circuit protection; The BMS main control board is electrically connected to the plurality of relays respectively.

9. The aircraft and its power battery system according to claim 8, characterized in that, The plurality of relays include: a pre-charge relay, a main positive relay and a main negative relay.

10. An aircraft, characterized in that, including the power battery system according to any one of claims 1-9.

Images