An eVTOL aircraft backup battery
By using external power supply heating control and a multi-cell battery design, combined with real-time monitoring and rapid switching functions, the problem of capacity loss and voltage incompatibility of eVTOL aircraft backup batteries in low-temperature environments has been solved, achieving efficient and stable power supply to the batteries and meeting the safety and stable operation requirements of eVTOL aircraft.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- HEFEI LANYI AVIATION TECHNOLOGY CO LTD
- Filing Date
- 2025-10-30
- Publication Date
- 2026-07-07
AI Technical Summary
Existing backup batteries for eVTOL aircraft suffer severe capacity loss in low-temperature environments, voltage incompatibility leads to voltage fluctuations, and lack real-time monitoring and rapid switching capabilities, thus failing to meet the safety and stability requirements of eVTOL aircraft.
The heating control logic employs an external power supply and a temperature relay, connecting the heating element in series with the external ground power supply to avoid power consumption; it uses a design of multiple ternary lithium batteries connected in series and parallel to match the low-voltage bus of the eVTOL aircraft; and it integrates current and temperature sensors to monitor battery status in real time and switch responses quickly.
Ensuring full battery capacity in low-temperature environments, avoiding voltage fluctuations, enabling rapid switching, improving power supply reliability and stability, and meeting the safety and stable operation requirements of eVTOL aircraft.
Smart Images
Figure CN224472531U_ABST
Abstract
Description
Technical Field
[0001] This utility model relates to the field of storage batteries, and more specifically, to a backup storage battery for eVTOL aircraft. Background Technology
[0002] As an emerging category in the field of low-altitude aircraft, eVTOL (electric vertical takeoff and landing) aircraft have shown broad application prospects in urban air traffic, emergency rescue, and short-distance commuting scenarios due to their core characteristics such as vertical takeoff and landing without the need for a dedicated runway and fully electric operation that is green and environmentally friendly. Their operation places extreme demands on the safety and reliability of the power supply system. As a key backup to the main power supply, the backup battery system is a core component that ensures the aircraft can safely maintain basic flight functions and achieve emergency landings when the main power supply fails or is abnormal. It is directly related to flight safety and equipment stability.
[0003] Existing backup battery systems suffer from two main problems. First, they exhibit significant capacity loss in low-temperature environments. In some traditional aircraft, the backup battery heating modules rely on their own power to start. In low-temperature environments (such as outdoor parking in winter or operations in high-altitude, low-temperature airspace), the internal backup power is continuously consumed to maintain the battery at a suitable operating temperature, leading to a substantial decrease in actual usable backup capacity. In extreme cases, if the main power supply fails suddenly, the backup battery may be unable to provide sufficient power due to prior heating losses, directly posing a safety hazard. Second, they have poor compatibility with the low-voltage buses of eVTOL aircraft. To ensure the stable operation of critical equipment such as avionics and control systems, eVTOL aircraft generally use 28V low-voltage buses. The existing backup battery system has a bus-based power supply architecture, but the voltage regulation mechanism of some backup batteries is complex and the voltage output range is not compatible with the 28V low-voltage bus. During the process of switching from the main power supply to the backup power supply, instantaneous voltage fluctuations or even surges are likely to occur, which may lead to problems such as avionics equipment failure and control signal interruption, affecting the stability of aircraft operation. On the other hand, traditional backup battery systems are mostly equipped with simple protection circuits and lack integrated status monitoring and intelligent management functions. They cannot collect key parameters such as battery voltage, current, and temperature in real time and accurately, making it difficult to judge the battery health status and remaining capacity. At the same time, the switching response mechanism when the main power supply is abnormal is lagging, and the switching time cannot meet the requirements of eVTOL aircraft for backup power.
[0004] Currently, the closest technical solution to the backup battery system of this eVTOL aircraft is the general low-voltage battery system. Its core components only include a basic battery pack, simple protection circuits and connectors. Although it can provide basic backup power, it does not have a low-temperature heating logic that does not consume its own power in terms of eVTOL adaptability, and cannot guarantee the integrity of the backup capacity. It also does not optimize the voltage range for the 28V low-voltage bus, resulting in poor switching compatibility. At the same time, the monitoring function is limited to overcharge and over-discharge protection, lacks real-time monitoring of the entire battery status, and the switching response speed is far lower than that required by eVTOL aircraft, making it difficult to meet its safe operation standards.
[0005] Therefore, those skilled in the art are dedicated to providing an eVTOL aircraft backup battery that can effectively solve the above-mentioned technical problems. Utility Model Content
[0006] To achieve the above objectives, this utility model provides an eVTOL aircraft backup battery, including a housing, a battery module, an electrical connector, a current detection sensor, a temperature relay, a BMS module, and a temperature sensor.
[0007] The housing is provided with a partition plate to form a first mounting cavity and a second mounting cavity;
[0008] The battery module is disposed in the first mounting cavity, and a heating band for heating the battery module is provided on the surface of the battery module.
[0009] The temperature relay is connected in series between the heating belt and the external ground power supply to control the heating on and off.
[0010] The BMS module and the current detection sensor are both disposed in the second mounting cavity, and the BMS module is electrically connected to the current detection sensor, the temperature sensor and the battery module respectively.
[0011] The current detection sensor is installed in the power supply circuit of the battery module and is used to detect the current of the battery module.
[0012] The temperature sensor is disposed on the surface or inside the battery module and is used to detect the temperature of the battery module.
[0013] The electrical connector includes a target interface for charging, discharging, and communication, which is connected to the BMS module and is located on the side of the housing.
[0014] Furthermore, the battery module is composed of multiple ternary lithium batteries connected in series and parallel.
[0015] Furthermore, the battery module is formed by 11 battery packs connected in parallel, and each battery pack is formed by 7 ternary lithium batteries connected in series;
[0016] Alternatively, the battery module may be formed by 13 battery packs connected in parallel, with each battery pack consisting of 6 ternary lithium-ion cells connected in series.
[0017] Furthermore, a cover is provided at the upper end of the housing, and the cover is detachably connected to the housing by a number of locking screws.
[0018] Furthermore, the upper end of the partition plate is provided with an opening that passes through the first mounting cavity and the second mounting cavity, and the temperature relay is located at the opening.
[0019] Furthermore, the shell has several legs on both sides, and each leg has a positioning hole.
[0020] Furthermore, the BMS module is provided with several lugs, and the BMS module is detachably mounted in the second mounting cavity via the lugs.
[0021] Furthermore, the target interface includes a positive charging / discharging interface, a negative charging / discharging interface, and a communication power supply interface;
[0022] The positive charging / discharging interface, the negative charging / discharging interface, and the communication power supply interface are all located on the same side of the housing. The positive charging / discharging interface and the negative charging / discharging interface are connected to the battery module, and the communication power supply interface is connected to the BMS module.
[0023] Furthermore, when the battery module is connected to the eVTOL aircraft, the battery module supplies power to the eVTOL aircraft through the positive charging / discharging interface and the negative charging / discharging interface;
[0024] When the battery module is connected to an external ground power source, the external ground power source supplies power to the battery module through the positive charging / discharging interface and the negative charging / discharging interface.
[0025] Furthermore, the current detection sensor is a Hall sensor or a current transformer.
[0026] This utility model has the following beneficial effects:
[0027] 1. This utility model adopts an independent heating control logic of external power supply and temperature relay, fundamentally solving the problem of traditional backup batteries consuming their own power when heating at low temperatures. By attaching the heating strip to the surface of the battery module and connecting the temperature relay in series between the heating strip and the external ground power supply, when the temperature of the battery module is lower than the set threshold, the temperature relay automatically connects the heating circuit and then uses the external ground power supply to power the heating strip to heat the battery module. When the temperature of the battery module is higher than or equal to the set threshold, the temperature relay automatically disconnects the heating circuit, thereby ensuring that the battery module does not consume its own power during the entire heating process, ensuring that the battery module's capacity can be fully retained, avoiding insufficient power when providing emergency power through the battery module in low-temperature environments, and significantly improving the reliability of power supply under extreme conditions.
[0028] 2. This utility model uses multiple ternary single cells connected in series and parallel to form a battery module, which can avoid fluctuations caused by voltage incompatibility when switching between the main power supply and the backup power supply, prevent key equipment such as avionics system and control system from malfunctioning due to unstable power supply, and ensure the operational stability of eVTOL aircraft.
[0029] 3. This invention uses a current detection sensor to collect the current signal of the battery module during charging and discharging in real time and transmits it to the BMS module. The BMS module can then determine whether the battery module is operating normally. Simultaneously, a temperature sensor is installed on the surface or inside the battery module to provide real-time temperature data, allowing the BMS module to monitor the temperature distribution and prevent localized overheating or low-temperature damage. Furthermore, the BMS module can receive main power supply anomaly signals and trigger control commands to connect the battery module to the low-voltage bus. The switching response time is less than 0.5 seconds, far superior to traditional backup batteries, ensuring that the battery module can be promptly activated as a backup power source in the event of a main power supply failure, meeting the rapid backup power requirements of eVTOL aircraft.
[0030] 4. Compared to traditional aircraft backup batteries, the dimensions of the housing of this utility model are 260mm×230mm×95mm (excluding electrical connectors, mounting lugs, and screws), with a total weight of only 5.18kg (including 3.85kg for a single battery, 0.5kg for the housing, and 0.32kg for the BMS module, etc.). This design can significantly reduce volume and weight, saving limited installation space on the aircraft and avoiding additional load on the aircraft. It meets the equipment selection requirements for lightweight and miniaturized eVTOL aircraft. At the same time, the positioning holes on both sides of the housing allow for quick disassembly and stable fixation. It also has the advantages of simple structure, low damage resistance, and low manufacturing cost. Attached Figure Description
[0031] Figure 1This is a structural schematic diagram of a specific embodiment of the present invention.
[0032] Figure 2 This is a schematic diagram of the structure of this utility model without a shell cover.
[0033] Figure 3 This is a schematic diagram of the shell structure in this utility model.
[0034] Figure 4 This is a schematic diagram of the battery module in this utility model.
[0035] Figure 5 This is a schematic diagram of the structure of 77 18650 type ternary single cells in this utility model.
[0036] Figure 6 This is a schematic diagram of the Hall sensor and BMS module in this utility model.
[0037] Figure 7 This is a schematic diagram of the heating control logic flow in this utility model.
[0038] The attached diagram lists the components represented by each number as follows:
[0039] 1. Housing; 2. Battery module; 4. Electrical connector; 5. Current sensor; 6. Temperature relay; 7. BMS module; 11. Housing cover; 12. Positive charge / discharge interface; 13. Negative charge / discharge interface; 15. Communication power supply interface; 17. Support foot; 17a. Positioning hole; 20. Divider plate; 21. First mounting cavity; 22. Second mounting cavity; 23. Opening; 26. Individual battery cell; 30. Locking screw; 33. Support lug. Detailed Implementation
[0040] The present invention will be further described below with reference to the accompanying drawings and embodiments:
[0041] In the description of this utility model, it should be noted that the terms "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this utility model. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.
[0042] In the description of this utility model, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "setting," and "connection" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model based on the specific circumstances.
[0043] like Figures 1 to 7 As shown, a backup battery for an eVTOL (electric vertical takeoff and landing) aircraft includes a housing 1, a battery module 2, an electrical connector 4, a current detection sensor 5, a temperature relay 6, a BMS (Battery Management System) module 7, and a temperature sensor.
[0044] A first mounting cavity 21 and a second mounting cavity 22 are formed inside the housing 1 by means of a partition plate 20;
[0045] The battery module 2 is disposed inside the first mounting cavity 21, and a heating band for heating the battery module 2 is provided on the surface of the battery module 2.
[0046] Temperature relay 6 is connected in series between the heating belt and the external ground power supply to control the heating on and off;
[0047] Both the BMS module 7 and the current detection sensor 5 are located in the second mounting cavity 22. The BMS module 7 is electrically connected to the current detection sensor 5, the temperature sensor, and the battery module 2, respectively.
[0048] The current detection sensor 5 is installed in the power supply circuit of the battery module 2 and is used to detect the current of the battery module 2.
[0049] A temperature sensor is disposed on the surface or inside the battery module 2 for detecting the temperature of the battery module 2;
[0050] The electrical connector 4 includes a target interface for charging, discharging, and communication, which is connected to the BMS module 7 and the battery module 2. The target interface is located on the side of the housing 1.
[0051] In some embodiments, by providing the battery module 2 in the first mounting cavity 21 and the BMS module 7 and current detection sensor 5 in the second mounting cavity 22, physical isolation between the battery module 2 and the monitoring components can be achieved, avoiding interference from battery heat generation on the monitoring components and improving the overall structural stability. The partition plate 20 and the housing 1 are integrally formed.
[0052] In some embodiments, the upper end of the partition plate 20 is provided with an opening 23 that passes through the first mounting cavity 21 and the second mounting cavity 22, and the temperature relay 6 is located at the opening 23. In addition, a plurality of lugs 33 may be provided on the BMS module 7, and the BMS module 7 is detachably mounted in the second mounting cavity 22 through the plurality of lugs 33.
[0053] In some embodiments, the target interface may include a positive charge / discharge interface 12, a negative charge / discharge interface 13, and a communication power supply interface 15. These interfaces are all located on the same side of the housing 1. The positive and negative interfaces 12 and 13 are connected to the battery module 2, and the communication power supply interface 15 is connected to the BMS module 7. When the battery module 2 is connected to the eVTOL aircraft, i.e., when it is used as a backup battery, the battery module 2 supplies power to the eVTOL aircraft through the positive and negative interfaces 12 and 13. When the battery module 2 is connected to an external ground power source, i.e., when it is being charged by the external ground power source, the external ground power source supplies power to the battery module 2 through the positive and negative interfaces 12 and 13. The BMS module can monitor the battery's charge / discharge status and temperature status in real time by receiving current signals detected by Hall sensors and temperature signals detected by temperature sensors. In some examples, the specific process or principle of the BMS module monitoring the charge / discharge status and temperature status of the battery in real time can be found in existing related technologies, and will not be elaborated here.
[0054] In some embodiments, battery module 2 can be composed of multiple ternary lithium-ion cells 26 connected in series and parallel. For example, battery module 2 can be formed by 11 battery packs connected in parallel, with each battery pack consisting of 7 ternary lithium-ion cells 26 connected in series. Specifically, if the rated capacity of each ternary lithium-ion cell 26 is 3Ah and the operating voltage range is 2.5V to 4.2V, then the total voltage range of each battery pack can be 17.5V to 29.4V, which can match the 28V low-voltage bus commonly used in eVTOL aircraft, avoiding fluctuations caused by voltage incompatibility during main and backup power switching. Combined with the 10.8Wh capacity of each cell, the total capacity of the battery module formed by 11 battery packs connected in parallel can be 0.83kWh, which can meet the emergency backup power supply requirements in case of aircraft main power failure. Alternatively, battery module 2 can also be formed by 13 battery packs connected in parallel, with each battery pack consisting of 6 ternary lithium-ion cells 26 connected in series. In this case, the total voltage range and total capacity of the battery module can be determined as described above, and will not be repeated here.
[0055] In some embodiments, the cover 11 can be detachably connected to the housing 1 by a number of locking screws 30, thereby facilitating the inspection and maintenance of internal components later. In addition, a number of support legs 17 can be provided on both sides of the housing 1, each support leg 17 having a positioning hole 17a, so as to fix the entire spare battery on the aircraft, which not only facilitates disassembly but also further improves the stability of the overall structure.
[0056] In some embodiments, the dimensions of the housing 1 can be 260mm × 230mm × 95mm, excluding electrical connectors, mounting lugs, and screws, with a total weight of 5.18kg. This meets the lightweight and miniaturization requirements of eVTOL aircraft, saving onboard space without increasing the aircraft's additional load. Specifically, the total weight of 5.18kg includes 3.85kg for the individual battery, 0.5kg for the housing, 0.32kg for the BMS module, 0.065kg for the nickel strip, 0.01kg for the heating strip, 0.1kg for the electrical connector, 0.08kg for the Hall sensor, 0.02kg for the temperature relay, 0.005kg for the temperature sensor, 0.03kg for standard parts, 0.05kg for insulating tape, and 0.15kg for the wires. See Table 1 for the weight composition of the low-voltage battery.
[0057] Table 1. Battery Weight Composition Table
[0058]
[0059] In some embodiments, the current sensing sensor 5 may be a Hall sensor, or any other sensor in the prior art that can achieve the same monitoring accuracy and response speed, such as a current transformer.
[0060] In some embodiments, such as Figure 7As shown, after connecting to an external power source, a temperature relay detects whether the temperature is below a set threshold. If it is below, the temperature relay connects the heating element to the external ground power source to heat the battery module; if it is not below, the temperature relay disconnects the heating element and stops heating the battery module. Specifically, the heating element is attached to the surface of the battery module 2, and the temperature relay 6 is connected in series between the heating element and the external ground power source. The temperature relay 6 has a fixed temperature threshold. When the temperature sensor (attached to the surface of the individual battery cell 26) detects that the temperature of the battery module 2 is below the threshold, the temperature relay 6 automatically connects the heating circuit, and the external ground power source heats the battery module 2 through the heating element. When the temperature rises above the threshold, the temperature relay 6 disconnects the heating circuit and stops heating. The entire heating process relies on the external ground power source and does not consume the battery module 2's own power, ensuring sufficient backup capacity and avoiding the safety hazard of backup power loss in low-temperature environments. Therefore, by connecting the temperature relay in series between the heating belt and the external ground power supply, when the temperature of the battery module is lower than the set threshold, the temperature relay automatically turns on the heating circuit and then uses the external ground power supply to power the heating belt so that the battery module can be heated through the heating belt; when the temperature of the battery module is higher than or equal to the set threshold, the temperature relay automatically turns off the heating circuit, thereby ensuring that the entire heating process does not consume the battery module's own power.
[0061] In some embodiments, the BMS module 7 can also be used to receive abnormal signals transmitted by the main power supply through the communication interface 15, and control the battery module 2 to supply power to the evtol aircraft after the battery module 2 is connected and turned on with the 28V low-voltage bus of the evtol aircraft. The specific control process of the BMS module 7 controlling the battery module 2 to supply power can be found in existing related technologies, and will not be described in detail here.
[0062] In some embodiments, the BMS module 7 can also be used to directly control the on / off state of the heating belt. For specific control procedures, please refer to existing related technologies, which will not be elaborated here.
[0063] In summary, this utility model provides a backup battery for an eVTOL aircraft. By connecting a temperature relay in series between the heating element and the external ground power source, when the battery module temperature is below a set threshold, the temperature relay automatically activates the heating circuit, using the external ground power source to supply power to the heating element to heat the battery module. When the battery module temperature is above or equal to the set threshold, the temperature relay automatically disconnects the heating circuit, ensuring that the entire heating process does not consume the battery module's own power. Furthermore, the battery module 2 can be composed of 77 18650 ternary lithium batteries 26 connected in series and parallel. The series design, based on the individual battery 26's operating voltage of 2.5V-4.2V, allows the total voltage range of the battery module 2 to reach 17.5V-29.4V, highly compatible with the eVTOL aircraft's 28V low-voltage bus, avoiding fluctuations due to voltage incompatibility during main / backup power switching. Parallel design: Combining the 263Ah rated capacity and 10.8Wh of individual battery cells, the total capacity of battery module 2 reaches 0.83kWh, meeting the emergency backup power supply needs in case of aircraft main power failure. Furthermore, when battery module 2 is connected to the eVTOL aircraft, i.e., when battery module 2 is activated as a backup battery, it supplies power to the eVTOL aircraft through positive charge / discharge interface 12 and negative charge / discharge interface 13. When battery module 2 is connected to an external ground power source, i.e., when the external ground power source is used to charge battery module 2, it supplies power to battery module 2 through positive charge / discharge interface 12 and negative charge / discharge interface 13. The communication power supply interface 15 is connected to BMS module 7, providing operating power to BMS module 7 and enabling communication between BMS module 7 and the aircraft control system.
[0064] Meanwhile, the BMS module 7 is placed inside the second mounting cavity 22 and is detachably fixed by the lug 33, and electrically connected to the Hall sensor 5 and the temperature sensor respectively. The Hall sensor 5 is connected in series in the power supply circuit of the battery module 2 to detect the charging and discharging current of the battery module 2 in real time and transmit the current signal to the BMS module 7. The BMS module 7 determines whether the battery charging and discharging status is normal based on this. The temperature sensor is attached to the surface of the individual battery 26 to collect the temperature of the individual battery 26 in real time and transmit the temperature signal to the BMS module 7. The BMS module 7 monitors the temperature distribution of the battery module 2 in real time to avoid local overheating or low temperature damage.
[0065] In addition, BMS module 7 can receive abnormal signals from the aircraft's main power supply. When a main power supply failure is detected, it immediately triggers the control command for battery module 2 to connect to the low-voltage bus. Since the voltage of battery module 2 is compatible with the low-voltage bus, the entire switching response time is less than 0.5s, ensuring that the power supply to critical aircraft equipment (such as avionics system and control system) is uninterrupted, and meeting the requirements of eVTOL aircraft for rapid backup power supply.
[0066] The preferred embodiments of this utility model have been described in detail above. It should be understood that those skilled in the art can make numerous modifications and variations based on the concept of this utility model without creative effort. Therefore, all technical solutions that can be obtained by those skilled in the art based on the concept of this utility model through logical analysis, reasoning, or limited experimentation on the basis of existing technology should be within the scope of protection defined by the claims.
Claims
1. A backup battery for an eVTOL aircraft, characterized in that: Includes housing (1), battery module (2), electrical connector (4), current detection sensor (5), temperature relay (6), BMS module (7) and temperature sensor; The housing (1) is provided with a partition plate (20) to form a first mounting cavity (21) and a second mounting cavity (22); The battery module (2) is disposed in the first mounting cavity (21), and the surface of the battery module (2) is provided with a heating band for heating the battery module (2); The temperature relay (6) is connected in series between the heating belt and the external ground power supply to control the heating on and off; The BMS module (7) and the current detection sensor (5) are both disposed in the second mounting cavity (22), and the BMS module (7) is electrically connected to the current detection sensor (5), the temperature sensor, and the battery module (2) respectively. The current detection sensor (5) is installed in the power supply circuit of the battery module (2) and is used to detect the current of the battery module (2). The temperature sensor is disposed on the surface or inside the battery module (2) for detecting the temperature of the battery module (2); The electrical connector (4) includes a target interface for charging, discharging and communication, which is connected to the BMS module (7) and the battery module (2). The target interface is located on the side of the housing (1).
2. The eVTOL aircraft backup battery as described in claim 1, characterized in that: The battery module (2) is composed of multiple ternary single cells (26) connected in series and in parallel.
3. The eVTOL aircraft backup battery as described in claim 2, characterized in that: The battery module (2) is formed by 11 battery packs connected in parallel, and each battery pack is formed by 7 ternary single cells (26) connected in series; Alternatively, the battery module (2) is formed by 13 battery packs connected in parallel, and each battery pack is formed by 6 ternary single cells (26) connected in series.
4. The eVTOL aircraft backup battery as described in claim 1, characterized in that: The upper end of the housing (1) is provided with a cover (11), and the cover (11) is detachably connected to the housing (1) by a number of locking screws (30).
5. The eVTOL aircraft backup battery as described in claim 1, characterized in that: The upper end of the partition plate (20) is provided with an opening (23) that passes through the first mounting cavity (21) and the second mounting cavity (22), and the temperature relay (6) is located at the opening (23).
6. The eVTOL aircraft backup battery as described in claim 1, characterized in that: The housing (1) has several legs (17) on both sides, and each leg (17) has a positioning hole (17a).
7. The eVTOL aircraft backup battery as described in claim 1, characterized in that: The BMS module (7) is provided with a plurality of lugs (33), and the BMS module (7) is detachably disposed in the second mounting cavity (22) through the lugs (33).
8. The eVTOL aircraft backup battery as described in claim 1, characterized in that: The target interface includes a positive charging / discharging interface (12), a negative charging / discharging interface (13), and a communication power supply interface (15); The positive charging / discharging interface (12), the negative charging / discharging interface (13), and the communication power supply interface (15) are all located on the same side of the housing (1). The positive charging / discharging interface (12) and the negative charging / discharging interface (13) are connected to the battery module (2), and the communication power supply interface (15) is connected to the BMS module (7).
9. The eVTOL aircraft backup battery as described in claim 1 or 8, characterized in that: When the battery module (2) is connected to the eVTOL aircraft, the battery module (2) supplies power to the eVTOL aircraft through the positive charging and discharging interface (12) and the negative charging and discharging interface (13); When the battery module (2) is connected to an external ground power source, the external ground power source supplies power to the battery module (2) through the positive charging / discharging interface (12) and the negative charging / discharging interface (13).
10. The eVTOL aircraft backup battery as described in claim 1, characterized in that: The current detection sensor (5) is a Hall sensor or a current transformer.