Battery system and aircraft

Abstract

The utility model discloses a battery system and aircraft relates to battery technical field, wherein the battery system includes battery pack, pressure relief pipeline and pressure relief assembly, battery pack includes battery module, battery module includes the casing of containing cavity and is provided with the cell of containing cavity, the pressure relief pipeline is communicated with the containing cavity, and the pressure relief assembly is connected with the casing of containing cavity. The pressure relief assembly comprises a first pressure relief device and a fluid connector which are connected with a pressure relief pipeline, the pressure relief pipeline is used for releasing thermal runaway gas through the first pressure relief device, and the pressure relief pipeline is further used for conveying heat exchange fluid to the containing cavity and / or guiding the heat exchange fluid out of the containing cavity through the fluid connector. According to the technical scheme provided by the utility model, the weight of the battery system is reduced, so that the eVTOL can fly in a lightweight and efficient manner.

Description

Technical Field

[0001] The utility model relates to the technical field of batteries, and in particular to a battery system and an aircraft. Background Art

[0002] eVTOL (electric Vertical Take-off and Landing) is a type of aircraft. eVTOL includes a battery system, the battery system includes a battery pack, the battery pack includes a battery module, the battery module includes a shell with a receiving chamber, and a battery cell arranged in the receiving chamber. It can be understood that once the battery pack has thermal runaway, gas will be generated in the receiving chamber, causing the pressure in the receiving chamber to rise. For the convenience of explanation, this article refers to the gas as thermal runaway gas. In order to avoid the explosion of the battery pack due to excessive pressure in the receiving chamber, the battery system also includes a pressure relief pipeline connected to the receiving chamber and a pressure relief device arranged in the pressure relief pipeline. In this way, when the pressure in the receiving chamber reaches a threshold value, the receiving chamber can release the thermal runaway gas through the pressure relief device, thereby achieving the purpose of reducing the pressure in the receiving chamber.

[0003] However, this means that the battery system's pressure relief pipes and pressure relief devices will result in more pipes in the battery system, making the battery system heavy. The eVTOL is limited by its volume and weight, which is not conducive to the lightweight and efficient flight of the aircraft. Utility Model Content

[0004] The main purpose of the utility model is to propose a battery system and an aircraft, aiming to reduce the weight of the battery system so as to make the eVTOL lightweight and fly efficiently.

[0005] To achieve the above-mentioned purpose, the battery system proposed by the utility model includes:

[0006] A battery pack, comprising a battery module, wherein the battery module comprises a shell having a receiving cavity and a battery cell arranged in the receiving cavity;

[0007] a pressure relief pipeline, connected to the receiving chamber; and

[0008] The pressure relief assembly includes a first pressure relief device and a fluid joint respectively connected to the pressure relief pipeline, the pressure relief pipeline is used to release the thermal runaway gas through the first pressure relief device, and the pressure relief pipeline is also used to transport the heat exchange fluid to the receiving chamber and / or output it from the receiving chamber through the fluid joint.

[0009] In one embodiment, a plurality of pressure relief pipelines are provided, and a plurality of pressure relief assemblies are provided. One pressure relief assembly is correspondingly arranged for one pressure relief pipeline. The housing is provided with a first communication port and a second communication port both communicating with the accommodation cavity. The first communication port is connected to one pressure relief pipeline, and the second communication port is connected to another pressure relief pipeline. The heat exchange fluid is configured as a heat exchange liquid. The pressure relief pipeline is further configured to convey an incombustible gas to the accommodation cavity and / or discharge it from the accommodation cavity through the fluid connector. The first communication port is higher than the second communication port. The first communication port is used for the incombustible gas to flow into the accommodation cavity so that the accommodation cavity is filled with the incombustible gas. The second communication port is used for the heat exchange liquid to flow into the accommodation cavity so that the accommodation cavity is filled with the heat exchange liquid.

[0010] In one embodiment, the pressure relief pipeline is made of a fireproof material and configured as a metal pipe, a fiber pipe, an asbestos pipe, an aerogel pipe or a ceramic pipe.

[0011] In one embodiment, the inner surface of the pressure relief pipeline is provided with a fireproof layer, and the fireproof layer is configured as a fireproof coating layer or an aerogel layer;

[0012] And / or, the pressure relief pipeline is made of aluminum.

[0013] In one embodiment, the pressure relief assembly further includes a seat body. The seat body includes a seat main body provided with a first cavity, and a first interface portion, a second interface portion and a third interface portion all arranged on the seat main body and respectively communicating with the first cavity. The first interface portion is connected to the fluid connector, the second interface portion is connected to the first pressure relief device, and the third interface portion is connected to the pressure relief pipeline.

[0014] In one embodiment, the first interface and the second interface portion are different interface portions;

[0015] Or, the first interface portion and the second interface portion are the same interface portion, and the first pressure relief device and the fluid connector are selectively connected to the first interface portion.

[0016] The present utility model further provides an aircraft, which includes:

[0017] An aircraft main body: and

[0018] The aforementioned battery system, and the battery pack is arranged on the aircraft main body.

[0019] In one embodiment, the aircraft further includes a ground thermal management system. The fluid connector is communicatively arranged with the ground thermal management system so that when the aircraft is in a ground heat exchange state, the incombustible gas and / or the heat exchange fluid can be filled into the accommodation cavity through the pressure relief pipeline.

[0020] In one embodiment, the ground thermal management system includes a delivery pipe for connecting the fluid joint, and an inlet / outlet through which the delivery pipe enters and exits is provided on the outer surface of the aircraft body, so that the delivery pipe can be disassembled and assembled with the fluid joint.

[0021] In one embodiment, the inlet / outlet is provided on the lower surface of the aircraft body.

[0022] In one embodiment, the battery pack includes a plurality of the battery modules, at least one battery module corresponds to one pressure relief assembly, and a plurality of the fluid joints are arranged close to each other.

[0023] In one embodiment, in the thickness direction of the battery pack, the fluid joint is disposed opposite to the battery pack.

[0024] In one embodiment, the battery pack includes a plurality of the battery modules, the pressure relief pipeline includes a manifold pipe and a plurality of branch pipes connected to the manifold pipe, and one branch pipe corresponds to and communicates with the accommodation cavity of one battery module.

[0025] In one embodiment, the battery pack is disposed inside the aircraft body, a pressure relief port is provided on the outer surface of the aircraft body, and a first pressure relief device is connected to the pressure relief port.

[0026] In one embodiment, the connection between the first pressure relief device and the pressure relief port is smoothly transitioned with the outer surface of the aircraft body, the first pressure relief device is flexibly connected to the pressure relief port, the first pressure relief device and the pressure relief port are connected through an elastic structure, and the elastic structure is configured as a rubber joint.

[0027] In one embodiment, a sealing structure is provided between the first pressure relief device and the pressure relief port, and the sealing structure is configured as a sealant structure, a fireproof glue structure, or a fireproof filler structure.

[0028] In one embodiment, the aircraft body includes a fuselage, wings provided on the fuselage, and arms provided on the wings, and the battery pack is disposed inside the wings and / or the arms.

[0029] In the technical solution of the present utility model, the pressure relief pipeline is not only used for the flow of heat runaway gas, but also reused for the flow of heat exchange fluid, which is beneficial to improving the integration degree of the pressure relief pipeline and is beneficial to reducing the weight of the battery system. Description of the Drawings

[0030] 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 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 be obtained based on the structures shown in these drawings.

[0031] Figure 1 Partial structural schematic diagram of the first embodiment of the aircraft provided by the present invention;

[0032] Figure 2 For Figure 1 Enlarged view of a partial structure of the aircraft in

[0033] Figure 3 For Figure 1 Structural schematic diagram of the battery pack and the pressure relief pipeline in

[0034] Figure 4 For Figure 3 Enlarged view of point B in

[0035] Figure 5 Partial structural schematic diagram of the second embodiment of the aircraft provided by the present invention;

[0036] Figure 6 For Figure 5 Enlarged view of a partial structure of the aircraft in

[0037] Figure 7 For Figure 6 Enlarged view of point C in

[0038] Figure 8 For Figure 5 Enlarged view of a partial structure of the aircraft in

[0039] Figure 9 For Figure 8 Enlarged view of point D in

[0040] Figure 10 For Figure 5 Structural schematic diagram of the battery system in

[0041] Figure 11 For Figure 10 Enlarged view of point E in

[0042] Figure 12 For Figure 10 Structural schematic diagram of the battery module, the pressure relief pipeline, and the pressure relief assembly in

[0043] Figure 13 For Figure 2 Structural schematic diagram of the pressure relief assembly in

[0044] Figure 14 is Figure 13 an explosion diagram of the pressure relief assembly in

[0045] Figure 15 a schematic structural diagram of the pressure relief assembly in the second embodiment of the battery system provided by the present utility model, wherein the pressure relief assembly is connected to a pressure relief pipeline and a delivery pipe;

[0046] Figure 16 is Figure 15 a schematic structural diagram of the first pressure relief device in

[0047] Figure 17 is Figure 15 a schematic structural diagram of the fluid connector in

[0048] Explanation of the reference numerals in the drawings:

[0049] 100, aircraft; 200, aircraft main body; 210, fuselage; 220, wing; 230, arm; 240, pressure relief port; 250, inlet and outlet; 300, ground thermal management system; 310, delivery pipe; 311, first delivery pipe; 312, second delivery pipe; 400, battery system; 410, battery pack; 411, battery module; 430, pressure relief pipeline; 440, manifold; 450, branch pipe; 500, pressure relief assembly; 600, seat body; 610, seat main body; 620, first interface part; 630, second interface part; 640, third interface part; 700, first pressure relief device; 710, first cover body; 711, first annular pressing part; 720, first pressure relief diaphragm; 721, first pressure relief groove; 730, pressure relief joint body; 740, fourth interface part; 750, fifth interface part; 800, fluid connector; 810, fluid connector body; 820, sixth interface part; 830, seventh interface part; 840, eighth interface part; 900, second pressure relief device; 910, second cover body; 911, second annular pressing part; 920, second pressure relief diaphragm; 921, second pressure relief groove.

[0050] The realization, functional features and advantages of the purpose of the present utility model will be further described with reference to the embodiments and the accompanying drawings. Detailed Embodiments

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

[0052] It should be noted that if there are directional indications (such as up, down, left, right, front, back...) involved in the embodiments of the present utility model, then such directional indications are only used to explain the relative positional relationship, movement conditions, etc. between components in a specific posture. If this specific posture changes, then the directional indications will also change accordingly.

[0053] In addition, if there are descriptions such as "first", "second", etc. involved in the embodiments of the present utility model, then such descriptions of "first", "second", etc. are only for descriptive purposes and cannot be understood as indicating or implying their relative importance or implicitly specifying the quantity of the indicated technical features. Thus, the features defined with "first", "second" may explicitly or implicitly include at least one such feature. In addition, if "and / or" or "and / or" appears throughout the text, its meaning includes three parallel solutions. Taking "A and / or B" as an example, it includes solution A, or solution B, or the solution where A and B are satisfied simultaneously. In addition, the technical solutions between various embodiments can be combined with each other, but it must be based on the fact that those skilled in the art can implement them. When the combination of technical solutions results in contradictions or cannot be implemented, it should be considered that such a combination of technical solutions does not exist and is not within the protection scope required by the present utility model.

[0054] Please refer to Figures 1 to 4 and also refer to Figure 13 and 14 The present utility model provides a battery system 400.

[0055] The battery system 400 can be applied to transportation means, such as ships, automobiles, aircraft 100, etc.

[0056] It should be pointed out that the battery system 400 can be used as a power source for transportation means to provide motive power for the transportation means; of course, the battery system 400 can also be used as a non-power source to provide power for systems such as lighting of the transportation means.

[0057] In the first embodiment of the present utility model, the battery system 400 includes a battery pack 410, a pressure relief pipeline 430, and a pressure relief assembly 500. Among them, the battery pack 410 includes battery modules 411, and the battery modules 411 include a housing provided with a receiving cavity and electric cores disposed in the receiving cavity. The pressure relief pipeline 430 is communicated with the receiving cavity. The pressure relief assembly 500 includes a first pressure relief device and a fluid connector 800 respectively connected to the pressure relief pipeline 430. The pressure relief pipeline 430 is used to release thermal runaway gas through the first pressure relief device, and the pressure relief pipeline 430 is also used to convey heat exchange fluid to and / or export heat exchange fluid from the receiving cavity through the fluid connector 800.

[0058] Thus, the pressure relief pipeline 430 is not only used for the flow of the heat runaway gas, but also reused for the flow of the heat exchange fluid, which is beneficial to improving the integration degree of the pressure relief pipeline 430 and reducing the weight of the battery system 400.

[0059] In an exemplary usage scenario, the battery pack 410 system is applied to the aircraft 100. Thus, the relatively high integration degree of the pressure relief pipeline 430 is also beneficial to reducing the weight of the aircraft 100. The aircraft 100 further includes a thermal management system. The fluid connector 800 can be communicatively disposed with the thermal management system. The thermal management system can fill the accommodation cavity with a flowing heat exchange liquid through the fluid connector 800 to adjust the temperature of the battery cells.

[0060] There are various structural forms of the fluid connector 800. In the first embodiment, the fluid connector 800 is provided with a valve core so that the fluid connector 800 has a first conduction state and a first closed state. Thus, for the aircraft 100, its thermal management system for adjusting the temperature of the battery cells can be configured as the ground thermal management system 300. When the battery system 400 needs heat exchange, the fluid connector 800 can be made to enter the first conduction state to connect with the delivery pipe 310 of the ground thermal management system 300. When the battery system 400 does not need heat exchange, the fluid connector 800 can be made to enter the first closed state and separated from the delivery pipe 310 of the ground thermal management system 300. This enables the aircraft 100 to fly without carrying the ground thermal management system 300, which is beneficial to reducing the weight of the aircraft 100 during flight. In some other embodiments, the fluid connector 800 only has a conduction state and does not have a closed state. Thus, for the aircraft 100, its thermal management system for adjusting the temperature of the battery cells is always connected to the fluid connector 800, and this thermal management system flies with the aircraft 100.

[0061] In the first embodiment, there are multiple pressure relief pipelines 430 and multiple pressure relief assemblies 500. One pressure relief assembly 500 is correspondingly arranged for one pressure relief pipeline 430. The housing is provided with a first communication port and a second communication port both communicating with the accommodation cavity. The first communication port is connected to one pressure relief pipeline 430, and the second communication port is connected to another pressure relief pipeline 430. The heat exchange fluid is configured as a heat exchange liquid. The pressure relief pipeline 430 is also used to convey the non-combustible gas to and / or export it from the accommodation cavity through the fluid connector 800. The first communication port is higher than the second communication port. The first communication port is used for the non-combustible gas to flow into the accommodation cavity to fill the accommodation cavity with the non-combustible gas. The second communication port is used for the heat exchange liquid to flow into the accommodation cavity to fill the accommodation cavity with the heat exchange liquid.

[0062] Thus, once thermal runaway occurs in the battery module 411, the thermal runaway gas generated in the accommodation cavity can flow to a pressure relief pipeline 430 through the first communication port and also flow to another pressure relief pipeline 430 through the second communication port. In addition, pressure relief assemblies 500 are respectively provided on these two pressure relief pipelines 430, which is beneficial to improving the pressure relief redundancy of the battery pack 410.

[0063] In an exemplary usage scenario, the ground thermal management system 300 includes a heat exchange pipeline, a liquid storage tank provided on the heat exchange pipeline, a gas storage tank provided on the heat exchange pipeline, and two liquid delivery pipes connecting the heat exchange pipeline. The liquid storage tank is used to store the heat exchange liquid, and the gas storage tank is used to store the non-combustible gas. The heat exchange pipeline is provided with a control valve so that the ground thermal management system 300 has a first state in which the two delivery pipes 310 are in communication with the liquid storage tank and disconnected from the gas storage tank, and a second state in which the two delivery pipes 310 are in communication with the gas storage tank and the liquid storage tank is disconnected. It is worth mentioning that the structural design of the heat exchange pipeline can be but not limited to referring to the prior art and will not be elaborated here too much, as long as it can enable the ground thermal management system 300 to have the first state in which the two delivery pipes 310 are in communication with the liquid storage tank and disconnected from the gas storage tank, and the second state in which the two delivery pipes 310 are in communication with the gas storage tank and the liquid storage tank is disconnected.

[0064] For the convenience of description, the delivery pipe 310 that fills the accommodation cavity with non-combustible gas through the first communication port is called the first delivery pipe 311, and the delivery pipe 310 that fills the accommodation cavity with heat exchange liquid through the second communication port is called the second delivery pipe 312.

[0065] Thus, in the ground state of the aircraft 100, the first delivery pipe 311 and the second delivery pipe 312 can be respectively connected to the corresponding fluid connectors 800, and the ground thermal management system 300 enters the first state. The ground thermal management system 300 fills the accommodation cavity with the heat exchange liquid through the second delivery pipe 312. Since the height of the second communication port is lower than that of the first communication port, the liquid level of the heat exchange liquid gradually rises in the accommodation cavity. The liquid level of the heat exchange liquid squeezes the non-combustible gas in the accommodation cavity, so that the non-combustible gas is discharged from the first delivery pipe 311 outside the accommodation cavity. Then, when the liquid level of the heat exchange liquid rises to the first communication port, the heat exchange liquid can be discharged from the first delivery pipe 311. Thus, during the process of the ground thermal management system 300 introducing the heat exchange fluid into the accommodation cavity, it is convenient to discharge the non-combustible gas in the accommodation cavity outside the accommodation cavity, and the heat exchange liquid can continuously exchange heat with the battery cells in the accommodation cavity. When the battery cells reach the preset temperature, the ground thermal management system 300 can be made to enter the second state through the control valve. The ground thermal management system 300 delivers the non-combustible gas into the accommodation cavity through the first delivery pipe 311. Since the height of the first communication port is higher than that of the second communication port, the non-combustible gas entering the accommodation cavity will press against the liquid level of the heat exchange liquid, so as to promote the heat exchange liquid to be discharged from the second delivery pipe 312 outside the accommodation cavity, causing the liquid level of the heat exchange liquid to gradually decrease. When the heat exchange liquid level drops to the second communication port, the non-combustible gas can be discharged from the second delivery pipe 312. Thus, during the process of the ground thermal management system 300 introducing the non-combustible gas into the accommodation cavity, the accommodation cavity is filled with the non-combustible gas to isolate the battery cells from the air, reducing the probability of thermal runaway of the battery pack 410, and it is also convenient to discharge the heat exchange liquid in the accommodation cavity outside the accommodation cavity. In addition, after being heat-exchanged by the ground thermal management system 300, the aircraft 100 can be filled with the non-combustible gas in the accommodation cavity before flight. Thus, it not only meets the heat exchange requirements of the aircraft 100, but also the aircraft 100 does not need to carry the heavy heat exchange liquid for flight. In addition, the battery cells are protected by the non-combustible gas during flight.

[0066] It is worth mentioning that when the battery pack 410 is used in the flight state of the aircraft 100, the non-combustible gas in the accommodation cavity reduces the content of the combustible gas in the accommodation cavity, thereby reducing the probability of thermal runaway of the battery pack 410. Combining with the design of the pressure relief pipeline 430 and the first pressure relief device, the probability of the occurrence of thermal runaway of the battery pack 410 can be significantly reduced.

[0067] In the first embodiment, the battery pack 410 includes a plurality of battery modules 411. The pressure relief pipeline 430 includes a manifold 440 and a plurality of branch pipes 450 connected to the manifold 440. One branch pipe 450 is correspondingly communicated with the cavity of one receiving battery module 411. In this way, the cavities of the plurality of battery modules 411 share the manifold 440. For example, once thermal runaway gas is generated in the cavities of the plurality of battery modules 411, the thermal runaway gas will flow into the manifold 440, that is, the manifold 440 can supply the thermal runaway gas generated in the plurality of cavities to flow through. In this way, the integration degree of the pressure relief pipeline 430 is relatively high, which is beneficial to the lightweight of the battery system 400.

[0068] In the first embodiment, at the connection between the branch pipe 450 and the manifold 440, the direction for the thermal runaway gas to flow in the branch pipe 450 is the first direction, and the direction for the thermal runaway gas to flow in the manifold 440 is the second direction. The first direction and the second direction are arranged at an angle A, where 0° < A < 90°. In the second direction, the plurality of branch pipes 450 are arranged in sequence. In this way, the situation where the thermal runaway gas enters the manifold 440 from the upstream branch pipe 450 and then enters the downstream branch pipe 450 from the manifold 440 is reduced, avoiding thermal runaway of the battery module 411 corresponding to the downstream branch pipe 450, so as to improve the safety of the battery pack 410. In addition, since the first direction has a component in the second direction, this also makes it easier for the thermal runaway gas to enter the manifold 440 from the branch pipe 450.

[0069] In the first embodiment, 30° ≤ A ≤ 60°. This setting of the angle A, on the one hand, is beneficial to reducing the situation where the thermal runaway gas enters the manifold 440 from the upstream branch pipe 450 and then enters the downstream branch pipe 450 from the manifold 440, avoiding thermal runaway of the battery module 411 corresponding to the downstream branch pipe 450, so as to improve the safety of the battery pack 410. On the other hand, under the limited installation space of the airframe structure of the aircraft 100, convenient installation and efficient confluence occur simultaneously. In addition, this angle design scheme also reduces the manufacturing difficulty of the pressure relief pipeline 430.

[0070] In the first embodiment, in the direction in which the manifold 440 is used to supply heat runaway gas to flow, the first pressure relief device is provided downstream of the plurality of branch pipes 450. In this way, a plurality of first pressure relief devices can be saved, and it is possible to realize pressure relief of the accommodation cavities of a plurality of battery modules 411 by one first pressure relief device, which is beneficial to reducing the weight of the battery system 400 and realizing the light weight of the aircraft 100. In some other embodiments, a first pressure relief device is provided on one branch pipe 450. In this way, under the blockage of the first pressure relief device, it is possible to reduce the situation where the heat runaway gas enters the manifold 440 from the upstream branch pipe 450 and then flows into the accommodation cavity corresponding to the downstream branch pipe 450 from the downstream branch pipe 450, thereby improving the safety of the battery pack 410.

[0071] In the first embodiment, in the direction in which the manifold 440 is used to supply heat runaway gas to flow, the inner diameter of the manifold 440 gradually increases. When a plurality of battery modules 411 undergo thermal runaway, the heat runaway gas generated in the corresponding plurality of accommodation cavities flows into the manifold 440 through their respective corresponding branch pipes 450. It can be understood that in the direction in which the manifold 440 is used to supply heat runaway gas to flow, the closer to the downstream, the more heat runaway gas is converged. In this way, in the direction in which the manifold 440 is used to supply heat runaway gas to flow, the inner diameter of the manifold 440 gradually increases, which can relieve the pressure of the heat runaway gas released from each branch pipe 450 and is beneficial to the smooth release of the heat runaway gas in each accommodation cavity.

[0072] It is worth mentioning that the inner diameter of the manifold 440 described in this embodiment is not intended to limit the cross-section of the inner wall of the manifold 440 to be circular. The inner diameter herein should be understood in a broad sense and should be understood as an equivalent inner diameter. It can be understood that the cross-section of the inner wall of the manifold 440 can be circular, polygonal, or even irregular, as long as the space available for the heat runaway gas to flow downstream in the manifold 440 is larger than the space available for the heat runaway gas to flow upstream in the direction in which the manifold 440 is used to supply heat runaway gas to flow.

[0073] In some other embodiments, in the direction in which the manifold 440 is used to supply heat runaway gas to flow, the inner diameter of each part of the manifold 440 is the same.

[0074] In the first embodiment, the branch pipe 450 is arranged in an arc shape at the connection with the manifold 440. In this way, further reducing the situation where the heat runaway gas enters the manifold 440 from the upstream branch pipe 450 and then enters the accommodation cavity through the downstream branch pipe 450, so as to improve the safety of the battery pack 410. In some other embodiments, the branch pipe 450 extends in the first direction, that is, the branch pipe 450 is a straight pipe.

[0075] In the first embodiment, the first pressure relief device is disposed on the manifold 440. In this way, it is beneficial to realize pressure relief of the accommodation cavities of multiple battery modules 411 by one first pressure relief device, which is beneficial to reducing the weight of the battery system 400 and also beneficial to realizing the light weight of the aircraft 100. In some other embodiments, there are multiple first pressure relief devices, and each branch pipe 450 is provided with a first pressure relief device. In this way, blocked by the first pressure relief device, the situation where the thermal runaway gas enters the manifold 440 from the upstream branch pipe 450 and then flows into the accommodation cavity corresponding to the downstream branch pipe 450 from the downstream branch pipe 450 can be reduced, thereby improving the safety of the battery pack 410.

[0076] In the first embodiment, the material of the pressure relief pipeline 430 is configured as a fireproof material. It can be understood that the temperature of the thermal runaway gas generated when the battery pack 410 has a thermal runaway is relatively high. Configuring the material of the pressure relief pipeline 430 as a fireproof material can reduce the probability of the pressure relief pipeline 430 being burned, enabling the pressure relief pipeline 430 to maintain the function of guiding the thermal runaway gas, so as to ensure that the thermal runaway gas can flow out from the first pressure relief device, thereby preventing the occupants in the aircraft 100 from inhaling more thermal runaway gas. Further, in the first embodiment, the pressure relief pipeline 430 is configured as a metal pipe, a fiber pipe, an asbestos pipe, an aerogel pipe or a ceramic pipe. This makes the pressure relief pipeline 430 have good fireproof performance.

[0077] In some other embodiments, a fireproof layer is provided on the inner surface of the pressure relief pipeline 430. It can be understood that the temperature of the thermal runaway gas generated when the battery pack 410 has a thermal runaway is relatively high, and the inner surface of the pressure relief pipeline 430 is in contact with the thermal runaway gas. Providing a fireproof layer on the inner surface of the pressure relief pipeline 430 can reduce the probability of the pressure relief pipeline 430 being burned, enabling the pressure relief pipeline 430 to maintain the function of guiding the thermal runaway gas, so as to ensure that the thermal runaway gas can flow out from the pressure relief device, thereby preventing the occupants in the aircraft 100 from inhaling more thermal runaway gas. Further, in some other embodiments, the fireproof layer is configured as a fireproof coating layer or an aerogel layer, which makes the pressure relief pipeline 430 have good fireproof performance; and / or, the material of the pressure relief pipeline 430 is configured as aluminum.

[0078] Without loss of generality, the battery system 400 will be introduced below by taking the aircraft 100 further including a ground thermal management system 300 as an exemplary usage scenario. The ground thermal management system 300 includes a delivery pipe 310 for connecting a fluid joint 800, and the ground thermal management system 300 transports a heat exchange liquid and / or a non-combustible gas through the delivery pipe 310.

[0079] In the first embodiment, the pressure relief assembly 500 further includes a seat body 600. The seat body 600 includes a seat main body 610 provided with a first cavity, and a first interface portion 620, a second interface portion 630, and a third interface portion 640 that are all provided on the seat main body 610 and communicate with the first cavity respectively. The first interface portion 620 is connected to the fluid connector 800, the second interface portion 630 is connected to the first pressure relief device, and the third interface portion 640 is connected to the pressure relief pipeline 430. In this way, both the fluid connector 800 and the first pressure relief device are connected to the pressure relief pipeline 430 through the third interface portion 640 of the seat body 600. On the one hand, this is beneficial to reducing the interfaces opened on the pressure relief pipeline 430 for installing the fluid connector 800 and the first pressure relief device, facilitating the manufacture of the pressure relief pipeline 430. On the other hand, if the first interface portion 620 and the second interface portion 630 are damaged, only the seat body 600 needs to be replaced, without replacing the entire pressure relief pipeline 430, which is beneficial to saving the maintenance cost of the battery system 400. In some other embodiments, the pressure relief pipeline 430 is provided with a first interface portion 620 for connecting the fluid connector 800 and a second interface portion 630 for connecting the first pressure relief device, thus saving the seat body 600.

[0080] In the first embodiment, the first interface and the second interface portion 630 are different interface portions. In this way, the pressure relief assembly 500 has a state where the fluid connector 800 and the first pressure relief device are both connected to the seat body 600. When the aircraft 100 is in the ground heat exchange state, the conveying pipe 310 can be directly connected to the corresponding fluid connector 800, which is very convenient.

[0081] In the first embodiment, the fluid connector 800 has a tendency to maintain in the first closed state. In this way, when the fluid connector 800 is disconnected from the corresponding conveying pipe 310, the fluid connector 800 can change from the first conducting state to the first closed state. In this way, the self-sealing function of the fluid connector 800 is realized. This makes the pressure relief assembly 500 convenient for users to use. It should be noted that the fluid connector 800 having a tendency to maintain in the first closed state can be achieved but not limited to the following methods. For example, in the first conducting state, the valve core has a first gravitational potential energy, and in the first closed state, the valve core has a second gravitational potential energy. The first gravitational potential energy is greater than the second gravitational potential energy, and the valve core relies on its own weight to make the fluid connector 800 have a tendency to maintain in the first closed state; or, the fluid connector 800 has an elastic reset member connected to the valve core, and through the elastic reset member, the fluid connector 800 has a tendency to maintain in the first closed state. In some other embodiments, the fluid connector 800 does not have a tendency to maintain in the first closed state, and the user manually switches the first conducting state and the first closed state of the fluid connector 800.

[0082] In the first embodiment, the first pressure relief device is configured as a pressure relief valve, an explosion-proof valve, an explosion-proof membrane, or a pressure relief breathing valve.

[0083] In the first embodiment, the second interface portion 630 is provided on the outer side of the seat body 610. The first pressure relief device includes a first cover body 700 threadedly connected to the outer peripheral edge of the second interface portion 630, and a first pressure relief diaphragm 720 covering the second interface portion 630. The first cover body 700 is provided with a first annular pressing portion 711 opposite to the first pressure relief diaphragm 720, and the first annular pressing portion 711 is used to press the first pressure relief diaphragm 720 against the second interface portion 630. In this way, when the battery pack 410 undergoes thermal runaway, when the pressure received by the first pressure relief diaphragm 720 under the extrusion of the thermal runaway gas meets the preset pressure, the first pressure relief diaphragm 720 will rupture to relieve the pressure of the pressure relief pipeline 430.

[0084] In the first embodiment, a first pressure relief groove 721 is formed on the surface of the first pressure relief diaphragm 720. In this way, the pressure increment required for the first pressure relief diaphragm 720 to deform from the beginning to complete rupture is reduced, which helps to prevent excessive pressure accumulation in the pressure relief pipeline 430, thereby protecting the safety of the pressure relief pipeline 430.

[0085] There are many structural forms of the seat body 600. In the first embodiment, the first interface portion 620 and the second interface portion 630 are provided on the same side of the seat body 610 in parallel, and the first interface portion 620 and the second interface portion 630 face the same direction. In some other embodiments, the structural form of the seat body 600 may also be other, which is not limited herein.

[0086] In the first embodiment, the third interface portion 640 is provided with a threaded connection structure. In this way, the third interface portion 640 can be more firmly connected to the pressure relief pipeline 430. In some other embodiments, the third interface portion 640 is provided with a clamping structure. In this way, the third interface portion 640 can be more conveniently connected to the pressure relief pipeline 430.

[0087] In the first embodiment, the fluid connector 800 is threadedly connected to the first interface portion 620. In this way, the fluid connector 800 and the first interface portion 620 are more firmly connected. In some other embodiments, the fluid connector 800 is inserted into the first interface portion 620.

[0088] In the first embodiment, the fluid connector 800 is provided with an insertion conduction structure. In this way, the fluid connector 800 can be plugged by the delivery pipe 310, and enters the first conduction state when plugged with the delivery pipe 310. In this way, it is convenient for users to use.

[0089] Refer to together Figures 15 to 17 , the present utility model also provides a second embodiment of the battery system 400. The same parts of the second embodiment and the first embodiment can be referred to the first embodiment, and will not be elaborated herein too much.

[0090] In the second embodiment, the first interface portion 620 and the second interface portion 630 are the same interface portion, and the first pressure relief device and the fluid connector 800 are selectively connected to the first interface portion 620. In this way, the structure of the seat body 600 is relatively simplified. When heat exchange liquid is required to exchange heat with the battery pack 410, the user can install the fluid connector 800 on the first interface portion 620 and remove the first pressure relief device from the first interface portion 620. When heat exchange liquid is not required to exchange heat with the battery pack 410, the user can remove the fluid connector 800 from the first interface portion 620 and install the first pressure relief device on the first interface portion 620. It is worth mentioning that before the aircraft 100 takes off, the fluid connector 800 can be left on the ground and the first pressure relief device can be installed on the first interface portion 620. In this way, it is beneficial to the lightweight of the aircraft 100. In addition, it can be understood that when the first pressure relief device is connected to the first interface portion 620, if the pressure received by the first pressure relief device does not exceed its preset value, the first pressure relief device will block the integrated pipe and the external environment to prevent non-combustible gas from flowing out of the pressure relief assembly 500 to the external environment. In this way, it is beneficial to reduce the probability of thermal runaway of the battery pack 410.

[0091] In the second embodiment, the first pressure relief device includes a pressure relief joint body 730 provided with a second cavity, a fourth interface portion 740 and a fifth interface portion 750 respectively provided on the pressure relief joint body 730 and communicating with the second cavity. The fourth interface portion 740 is used to connect to the second interface portion 630. The first pressure relief device further includes a first cover body 700 threadedly connected to the fifth interface portion 750 and a first pressure relief diaphragm 720 covering the fifth interface portion 750. The first cover body 700 is provided with a first annular pressing portion 711 opposite to the first pressure relief diaphragm 720, and the first annular pressing portion 711 is used to press the first pressure relief diaphragm 720 against the fifth interface portion 750. In this way, when the battery pack 410 undergoes thermal runaway and the pressure received by the first pressure relief diaphragm 720 under the extrusion of the thermal runaway gas meets the preset pressure, the first pressure relief diaphragm 720 will rupture to relieve pressure on the pressure relief pipeline 430.

[0092] In the second embodiment, a first pressure relief groove 721 is formed on the surface of the first pressure relief diaphragm 720. In this way, the pressure increment required for the first pressure relief diaphragm 720 to deform from the beginning to complete rupture is reduced, which helps to prevent excessive pressure accumulation in the pressure relief pipeline 430, thereby protecting the safety of the pressure relief pipeline 430.

[0093] There are many structural forms of the first pressure relief device. In the second embodiment, the fourth interface portion 740 and the fifth interface portion 750 are respectively provided at both ends of the pressure relief joint body 730, and the fourth interface portion 740 and the fifth interface portion 750 face in opposite directions. In some other embodiments, the structural form of the first pressure relief device can also be other, which is not limited here.

[0094] In the second embodiment, the fluid connector 800 is configured with a second pressure relief device 900. Thus, the fluid connector 800 not only allows the heat exchange liquid to flow through for heat exchange of the battery cells, but also protects the battery pack 410 through the second pressure relief device 900 during the heat exchange process to prevent the battery pack 410 from exploding due to thermal runaway.

[0095] In the second embodiment, the fluid connector 800 includes a fluid connector body 810 having a third cavity, and a sixth interface portion 820, a seventh interface portion 830, and an eighth interface portion 840 that are respectively provided on the fluid connector body 810 and communicate with the third cavity. The sixth interface portion 820 is used to connect to the first interface portion 620. The second pressure relief device 900 is provided at the eighth interface portion 840. The seventh interface portion 830 is used to connect to the thermal management system. Thus, the delivery pipe 310 can be connected to the delivery pipe 310 through the seventh interface portion 830. In addition, the fluid connector 800 not only allows the heat exchange liquid to flow through for heat exchange of the battery cells, but also protects the battery pack 410 through the second pressure relief device 900 during the heat exchange process to prevent the battery pack 410 from exploding due to thermal runaway.

[0096] In the second embodiment, the second pressure relief device 900 is configured as a pressure relief valve, an explosion-proof valve, an explosion-proof film, or a pressure relief breathing valve.

[0097] In the second embodiment, the second pressure relief device 900 includes a second cover body 910 threadedly connected to the outer peripheral edge of the eighth interface portion 840, and a second pressure relief diaphragm 920 covering the eighth interface portion 840. The second cover body 910 is provided with a second annular pressing portion 911 opposite to the second pressure relief diaphragm 920. The second annular pressing portion 911 is used to press the second pressure relief diaphragm 920 against the eighth interface portion 840. Thus, when the battery pack 410 undergoes thermal runaway and the pressure received by the first pressure relief diaphragm 720 under the extrusion of the thermal runaway gas meets the preset pressure, the first pressure relief diaphragm 720 will rupture to relieve pressure on the pressure relief pipeline 430.

[0098] In the second embodiment, the surface of the second pressure relief diaphragm 920 is provided with a second pressure relief groove 921. Thus, the pressure increment required for the second pressure relief diaphragm 920 to deform from the start to complete rupture is reduced, which helps prevent excessive pressure accumulation in the pressure relief pipeline 430, thereby protecting the safety of the pressure relief pipeline 430.

[0099] There are many structural forms of the fluid connector 800. In the second embodiment, the sixth interface portion 820 and the seventh interface portion 830 are respectively provided at both ends of the fluid connector body 810, and the orientations of the sixth interface portion 820 and the seventh interface portion 830 are opposite. The eighth interface portion 840 is provided on the outer peripheral surface of the fluid connector body 810, and the orientation of the eighth interface portion 840 is different from those of the sixth interface portion 820 and the seventh interface portion 830 respectively. In some other embodiments, the structural form of the fluid connector 800 may also be other, which is not limited herein.

[0100] In the second embodiment, the first interface portion 620 is provided with a plug-in conduction structure, and either the fluid connector 800 or the first pressure relief device is plugged into the plug-in conduction structure. In this way, both the fluid connector 800 and the first pressure relief device can be plugged into the first interface portion 620, and after plugging, they are in conduction with the first cavity. In this way, it is convenient for users to use.

[0101] In the second embodiment, the first pressure relief device is configured as a pressure relief valve, an explosion-proof valve, an explosion-proof film or a pressure relief breathing valve.

[0102] With reference to Figures 5 to 12 , the present utility model also provides a third embodiment of the battery system 400. The same parts of the third embodiment and the first embodiment can be referred to the first embodiment, and will not be elaborated herein too much.

[0103] In the third embodiment, the battery pack 410 includes a plurality of battery modules 411, there are multiple pressure relief pipelines 430, and there are multiple pressure relief assemblies 500. At least one pressure relief pipeline 430 is correspondingly connected to one battery module 411, and one pressure relief pipeline 430 is correspondingly connected to one pressure relief assembly 500. In this way, when multiple battery modules 411 have thermal runaway, they can be pressure-relieved separately without affecting each other.

[0104] The present utility model also proposes an aircraft 100, which includes an aircraft body 200 and the aforementioned battery system 400. The specific structure of the battery system 400 refers to the above embodiments. Since the aircraft 100 adopts all the technical solutions of the above embodiments, it has at least all the beneficial effects brought by the technical solutions of the above embodiments, which will not be elaborated herein one by one. Among them, the battery pack 410 is arranged on the aircraft body 200. It should be noted that the aircraft 100 can be but is not limited to being configured as an eVTOL.

[0105] In the first embodiment, the aircraft 100 further includes a ground thermal management system 300. The fluid connector 800 is communicatively disposed with the ground thermal management system 300 so that when the aircraft 100 is in a ground heat exchange state, non-combustible gas and / or heat exchange fluid can be filled into the accommodation cavity through the pressure relief pipeline 430. It can be understood that when the aircraft 100 is flying, the aircraft 100 is separated from the ground thermal management system 300, and the ground thermal management system 300 remains on the ground. That is, when the aircraft 100 is flying, the aircraft 100 does not carry the ground thermal management system 300, which is beneficial to the lightweight of the aircraft 100.

[0106] In addition, when the aircraft 100 is in a ground heat exchange state, the ground thermal management system 300 can fill the accommodation cavity with heat exchange liquid through the pressure relief pipeline 430 so that the temperature of the battery pack 410 meets the preset temperature. When the battery pack 410 meets the preset temperature, the ground thermal management system 300 can fill the accommodation cavity with non-combustible gas through the pressure relief pipeline 430. The non-combustible gas is filled in the accommodation cavity. On the one hand, it is beneficial to isolate the battery cells from the air to reduce the probability of thermal runaway of the battery pack 410. On the other hand, it enables the aircraft 100 not to carry heavy heat exchange liquid for flight, which is beneficial to the lightweight of the aircraft 100.

[0107] In the first embodiment, the ground thermal management system 300 includes a delivery pipe 310 for connecting to the fluid connector 800. An inlet / outlet 250 for the delivery pipe 310 to pass through is provided on the outer surface of the aircraft body 200 so that the delivery pipe 310 can be disassembled and assembled with the fluid connector 800. In this way, the staff can make the delivery pipe 310 enter and exit the inlet / outlet 250 to realize the disassembly and assembly of the delivery pipe 310 and the fluid connector 800 without entering the interior of the aircraft 100, and this process is relatively convenient. Further, in the first embodiment, the inlet / outlet 250 is provided on the lower surface of the aircraft body 200, which makes the height of the inlet / outlet 250 relatively low, facilitating the disassembly and assembly of the delivery pipe 310 with the fluid connector 800.

[0108] In the first embodiment, the battery pack 410 is disposed inside the aircraft body 200, and a pressure relief port 240 is provided on the outer surface of the aircraft body 200. The first pressure relief device is connected to the pressure relief port 240. In this way, once the battery pack 410 has a thermal runaway, the thermal runaway gas can be discharged out of the aircraft body 200 through the first pressure relief device from the pressure relief port 240, preventing the pilot or passenger from inhaling too much thermal runaway gas. In some other embodiments, the aircraft body 200 may not be provided with the pressure relief port 240 as long as the aircraft 100 is provided with a container to collect the thermal runaway gas released by the pressure relief device.

[0109] In the first embodiment, the connection between the first pressure relief device and the pressure relief port 240 is smoothly transitioned with the outer surface of the aircraft body 200. Thus, the influence of the first pressure relief device on the aerodynamics of the aircraft 100 can be reduced, enabling the aircraft 100 to fly efficiently.

[0110] In the first embodiment, the first pressure relief device is flexibly connected to the pressure relief port 240. Thus, the pose of the first pressure relief device relative to the pressure relief port 240 is adjustable, making the installation position of the battery system 400 on the aircraft 100 relatively flexible. In addition, it is also beneficial to achieve a smooth transition between the connection of the first pressure relief device and the pressure relief port 240 and the outer surface of the aircraft body 200. In some other embodiments, the pressure relief pipeline 430 is flexible.

[0111] In the first embodiment, the first pressure relief device is connected to the pressure relief port 240 through an elastic structure. In some other embodiments, the pressure relief device can also be flexibly connected to the pressure relief port 240 through other structures, which are not limited herein.

[0112] In one embodiment, the elastic structure is configured as a rubber joint. In some other embodiments, the elastic structure can also be other, which is not limited herein as long as the elastic structure has elasticity.

[0113] In the first embodiment, a sealing structure is provided between the first pressure relief device and the pressure relief port 240. Thus, the hot runaway gas released outside the aircraft body 200 can be reduced from flowing back into the aircraft body 200 through the gap between the first pressure relief device and the pressure relief port 240.

[0114] In the first embodiment, the sealing structure is configured as a sealant structure, a fireproof glue structure, or a fireproof filler structure. It is worth mentioning that the fireproof glue and the fireproof filler can prevent the hot runaway gas at a relatively high temperature from burning the sealing structure, enabling the sealing structure to better maintain its sealing performance.

[0115] In the first embodiment, the aircraft body 200 includes a fuselage 210, wings 220 provided on the fuselage 210, and arms 230 provided on the wings 220. The battery pack 410 is disposed within the wings 220 and / or the arms 230. Thus, the space of the wings 220 and / or the arms 230 is fully utilized. In some other embodiments, the battery pack 410 is disposed within the fuselage 210.

[0116] The present utility model also provides a second embodiment of the aircraft 100. The similarities between the second embodiment and the first embodiment can be referred to the first embodiment, and will not be elaborated herein too much.

[0117] If the aircraft 100 adopts the third embodiment of the battery system 400, in the second embodiment, the battery pack 410 includes a plurality of battery modules 411, at least one battery module 411 is provided corresponding to at least one pressure relief assembly 500, and a plurality of fluid connectors 800 are arranged close to each other. In this way, the total time for the plurality of fluid connectors 800 to connect the delivery pipe 310 can be reduced. Further, in the second embodiment, in the thickness direction of the battery pack 410, the fluid connectors 800 are arranged opposite to the battery pack 410. In this way, it is beneficial to make the total length of the plurality of pressure relief pipelines 430 shorter to save costs.

[0118] The above are only exemplary embodiments of the present invention, and do not limit the patent scope of the present invention accordingly. Any equivalent structural transformation made under the technical concept of the present invention by using the content of the specification and drawings of the present invention, or any direct / indirect application in other related technical fields is included in the patent protection scope of the present invention.

Claims

1. A battery system, characterized in that: include: A battery pack, comprising a battery module, wherein the battery module comprises a shell having a receiving cavity and a battery cell arranged in the receiving cavity; A pressure relief pipeline, connected to the receiving chamber; as well as The pressure relief assembly includes a first pressure relief device and a fluid joint respectively connected to the pressure relief pipeline, the pressure relief pipeline is used to release the thermal runaway gas through the first pressure relief device, and the pressure relief pipeline is also used to transport the heat exchange fluid to the receiving chamber and / or output it from the receiving chamber through the fluid joint.

2. The battery system according to claim 1, characterized in that: The pressure relief pipelines are provided in plurality, and the pressure relief assemblies are provided in plurality. One pressure relief assembly is provided corresponding to one pressure relief pipeline. The shell is provided with a first connecting port and a second connecting port, both of which are connected to the receiving chamber. The first connecting port is connected to one pressure relief pipeline, and the second connecting port is connected to another pressure relief pipeline. The heat exchange fluid is configured as a heat exchange liquid. The pressure relief pipeline is also used to transport the non-combustible gas to the receiving chamber and / or to discharge it from the receiving chamber through the fluid joint. The first connecting port is higher than the second connecting port. The first connecting port is used for the non-combustible gas to flow into the receiving chamber so that the receiving chamber is filled with the non-combustible gas. The second connecting port is used for the heat exchange liquid to flow into the receiving chamber so that the receiving chamber is filled with the heat exchange liquid.

3. The battery system according to claim 1, characterized in that: The material of the pressure relief pipeline is a fireproof material, and the pressure relief pipeline is a metal tube, a fiber tube, an asbestos tube, an aerogel tube or a ceramic tube.

4. The battery system according to claim 1, characterized in that: The inner surface of the pressure relief pipeline is provided with a fireproof layer, and the fireproof layer is configured as a fireproof coating layer or an aerogel layer; And / or, the pressure relief pipeline is made of aluminum.

5. The battery system according to any one of claims 1 to 4, characterized in that: The pressure relief assembly also includes a seat body, which includes a seat body provided with a first cavity, and a first interface portion, a second interface portion and a third interface portion, which are all provided on the seat body and are respectively connected to the first cavity, the first interface portion is connected to the fluid connector, the second interface portion is connected to the first pressure relief device, and the third interface portion is connected to the pressure relief pipeline.

6. The battery system according to claim 5, characterized in that: The first interface and the second interface portion are different interface portions; Alternatively, the first interface portion and the second interface portion are the same interface portion, and either the first pressure relief device or the fluid connector is selectively connected to the first interface portion.

7. An aircraft, characterized in that: include: Aircraft body: and The battery system according to any one of claims 1 to 6, wherein the battery pack is disposed on the aircraft body.

8. The aircraft according to claim 7, characterized in that The aircraft also includes a ground thermal management system, and the fluid connector can be arranged in communication with the ground thermal management system so that when the aircraft is in a ground heat exchange state, non-flammable gas and / or the heat exchange fluid can be filled into the receiving cavity through the pressure relief pipeline.

9. The aircraft according to claim 8, characterized in that The ground thermal management system includes a delivery pipe for connecting the fluid joint, and an inlet and outlet for the delivery pipe are arranged on the outer surface of the aircraft body, so that the delivery pipe can be detached from the fluid joint.

10. The aircraft according to claim 9, characterized in that The inlet and outlet are arranged on the lower surface of the aircraft body.

11. The aircraft according to claim 9, characterized in that The battery pack includes a plurality of the battery modules, one battery module is arranged corresponding to at least one pressure relief assembly, and a plurality of the fluid connectors are arranged close to each other.

12. The aircraft according to claim 11, characterized in that The fluid connector is disposed opposite to the battery pack in a thickness direction of the battery pack.

13. The aircraft according to claim 7, characterized in that The battery pack includes a plurality of battery modules, the pressure relief pipeline includes a manifold and a plurality of branch pipes connected to the manifold, and one branch pipe is correspondingly connected to a receiving cavity of the battery module.

14. An aircraft according to any one of claims 7 to 13, characterized in that The battery pack is arranged in the aircraft body, a pressure relief port is arranged on the outer surface of the aircraft body, and a first pressure relief device is connected to the pressure relief port.

15. The aircraft according to claim 14, characterized in that The connection between the first pressure relief device and the pressure relief port smoothly transitions to the outer surface of the aircraft body, the first pressure relief device is flexibly connected to the pressure relief port, the first pressure relief device is connected to the pressure relief port through an elastic structure, and the elastic structure is configured as a rubber joint.

16. The aircraft according to claim 15, characterized in that A sealing structure is provided between the first pressure relief device and the pressure relief port, and the sealing structure is configured as a sealant structure, a fireproof glue structure, and a fireproof filler structure.

17. The aircraft according to claim 7, characterized in that The aircraft body includes a fuselage, wings arranged on the fuselage, and arms arranged on the wings, and the battery pack is arranged in the wings and / or the arms.

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