Battery pack pressure relief system and aircraft

Abstract

The utility model discloses a battery pack pressure relief system and an aircraft, and relates to the technical field of battery pack pressure relief, the battery pack pressure relief system is applied to a battery pack, the battery pack comprises a plurality of battery modules, each battery module comprises a shell provided with a containing cavity and a battery cell arranged in the containing cavity, the battery pack pressure relief system comprises an integrated pipeline and a pressure relief assembly, the integrated pipeline comprises a collecting pipe and a plurality of branch pipes connected with the collecting pipe, one branch pipe is communicated with one containing cavity, the pressure relief assembly comprises a first pressure relief device arranged on the collecting pipe, and the integrated pipeline is used for releasing thermal runaway gas through the first pressure relief device. According to the technical scheme provided by the utility model, the weight of the battery pack pressure relief 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 battery pack pressure relief, and particularly relates to a battery pack pressure relief system and an aircraft. Background Art

[0002] eVTOL (electric Vertical Take-off and Landing, electric vertical take-off and landing aircraft) is a type of aircraft. An eVTOL includes a battery pack, the battery pack includes a plurality of battery modules, and each battery module includes a housing provided with a receiving cavity and an electric core disposed in the receiving cavity. It can be understood that once thermal runaway occurs in the battery pack, gas will be generated in the receiving cavity, causing the pressure in the receiving cavity to rise. For the convenience of description, this gas is referred to as thermal runaway gas in this article. To prevent the battery pack from exploding due to excessive pressure in the receiving cavity, the battery pack releases the thermal runaway gas through a battery pack pressure relief system.

[0003] Specifically, the current battery pack pressure relief system includes a pressure relief pipeline with a pressure relief device provided at one end. The other end of the pressure relief pipeline is connected to the housing of the battery module to communicate with the receiving cavity. There are multiple pressure relief pipelines, and one pressure relief pipeline is correspondingly arranged for one receiving cavity. This makes the weight of the battery pack pressure relief system relatively large, and since eVTOL is restricted by volume and weight, it is not conducive to the lightweight and efficient flight of eVTOL. Summary of the Utility Model

[0004] The main purpose of the utility model is to propose a battery pack pressure relief system and an aircraft, aiming to reduce the weight of the battery pack pressure relief system and enable the lightweight and efficient flight of eVTOL.

[0005] To achieve the above object, the battery pack pressure relief system proposed by the utility model is applied to a battery pack. The battery pack includes a plurality of battery modules, and each battery module includes a housing provided with a receiving cavity and an electric core disposed in the receiving cavity. The battery pack pressure relief system includes:

[0006] An integrated pipeline, including a manifold and a plurality of branch pipes connected to the manifold, with one branch pipe communicating with one receiving cavity; and

[0007] A pressure relief assembly, including a first pressure relief device provided on the manifold, and the integrated pipeline is used to release the thermal runaway gas through the first pressure relief device.

[0008] In one embodiment, the integrated pipeline is also used to allow a heat exchange fluid and / or a non-combustible gas to flow through.

[0009] In one embodiment, the pressure relief assembly further includes a fluid connector disposed on the integrated pipeline. The fluid connector is provided with a valve core so that the fluid connector has a first conducting state and a first closing state. The integrated pipeline is used to introduce heat exchange fluid and / or non-combustible gas into the receiving cavity through the fluid connector, and / or to discharge the heat exchange fluid and / or the non-combustible gas in the receiving cavity. In one embodiment, the fluid connector is disposed on the manifold. In the direction in which the manifold is used for the flow of the thermal runaway gas, the first pressure relief device is disposed downstream of the plurality of branch pipes.

[0010] 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 that are all disposed on the seat main body and are respectively communicated 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 integrated pipeline.

[0011] In one embodiment, the first interface and the second interface portion are different interface portions;

[0012] 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 alternatively connected to the first interface portion.

[0013] In one embodiment, at the connection of the branch pipe and the manifold, the direction in which the branch pipe is used for the flow of the thermal runaway gas is the first direction, and the direction in which the manifold is used for the flow of the thermal runaway gas is the second direction. The first direction and the second direction are arranged at an angle A, 0° < A < 90°. In the second direction, the plurality of branch pipes are arranged in sequence.

[0014] In one embodiment, 30° ≤ A ≤ 60°;

[0015] And / or, in the direction in which the manifold is used for the flow of the thermal runaway gas, the first pressure relief device is disposed downstream of the plurality of branch pipes;

[0016] And / or, in the direction in which the manifold is used for the flow of the thermal runaway gas, the inner diameter of the manifold gradually increases;

[0017] And / or, the branch pipe is arranged in an arc shape at the connection with the manifold.

[0018] In one embodiment, the material of the integrated pipeline is configured as a fireproof material, and the integrated pipeline is configured as a metal pipe, a fiber pipe, an asbestos pipe, an aerogel pipe, or a ceramic pipe.

[0019] In one embodiment, a fireproof layer is provided on the inner surface of the integrated pipeline, and the fireproof layer is configured as a fireproof coating layer or an aerogel layer;

[0020] And / or, the material of the integrated pipeline is configured as aluminum.

[0021] The present utility model further provides an aircraft, which includes:

[0022] An aircraft body; and

[0023] The aforementioned battery pack pressure relief system and the battery pack are provided on the aircraft body.

[0024] In one embodiment, the aircraft includes an on-board thermal management system, and the on-board thermal management system is connected to the integrated pipeline. Both ends of the integrated pipeline are connected to the receiving cavity to form a loop with the receiving cavity.

[0025] In one embodiment, the aircraft further includes a ground thermal management system, and the ground thermal management system is used to provide a heat exchange fluid and / or a non-combustible gas. The integrated pipeline can be connected to the ground thermal management system so that when the aircraft is in a ground heat exchange state, the heat exchange fluid and / or the non-combustible gas can be filled into the receiving cavity through the integrated pipeline.

[0026] In one embodiment, there are multiple integrated pipelines and multiple pressure relief assemblies. One pressure relief assembly is correspondingly arranged for one integrated pipeline. The housing is provided with a first communication port and a second communication port both communicating with the receiving cavity. One integrated pipeline is connected to the first communication port, and another integrated pipeline is connected to the second communication port. The heat exchange fluid is configured as a heat exchange liquid. 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 receiving cavity so that the receiving cavity is filled with the non-combustible gas, and the second communication port is used for the heat exchange liquid to flow into the receiving cavity so that the receiving cavity is filled with the heat exchange liquid.

[0027] In one embodiment, the pressure relief assembly further includes a fluid connector connecting the integrated pipeline. The fluid connector is provided with a valve core so that the fluid connector has a first conduction state and a first closing state. The ground thermal management system further includes a delivery pipe for connecting the fluid connector. An inlet and outlet for the delivery pipe to enter and exit are provided on the outer surface of the aircraft body so that the delivery pipe can be disassembled and assembled with the fluid connector.

[0028] In one embodiment, the battery pack is provided inside the aircraft body, and a pressure relief port is provided on the outer surface of the aircraft body. The first pressure relief device is provided at the pressure relief port.

[0029] 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;

[0030] and / or, the first pressure relief device is flexibly connected to the pressure relief port.

[0031] In one embodiment, 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.

[0032] 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.

[0033] 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 provided in the wings and / or the arms.

[0034] In the technical solution of the present invention, the battery pack pressure relief system enables the accommodation cavities of multiple battery modules to share the manifold. In other words, once thermal runaway gas is generated in the accommodation cavities of multiple battery modules, the thermal runaway gas will flow into the manifold, that is, the manifold is available for the thermal runaway gas generated in multiple accommodation cavities to flow through. Thus, the integration degree of the integrated pipeline is relatively high, which is beneficial to lighten the weight of the battery pack pressure relief system.

[0035] The pressure relief assembly includes a first pressure relief device provided on the manifold, and the integrated pipeline is used to release the thermal runaway gas through the first pressure relief device. Thus, it is beneficial to realize pressure relief of the accommodation cavities of multiple battery modules by one first pressure relief device, and it is beneficial to reduce the weight of the battery pack pressure relief system.

[0036] Without loss of generality, the battery pack pressure relief system is introduced herein as being applied to the battery pack of an aircraft. Thus, it is also beneficial to realize the light weight of the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0037] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required for use in the description of the embodiments or the prior art. Obviously, the following drawings 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.

[0038] Figure 1 It is a partial structural schematic diagram of the first embodiment of the aircraft provided by the present invention;

[0039] Figure 2 is Figure 1 an enlarged view of a partial structure of the aircraft in

[0040] Figure 3 is Figure 1 a schematic structural view of the battery pack and the integrated pipeline in

[0041] Figure 4 is Figure 3 an enlarged view of part B in

[0042] Figure 5 is Figure 2 a schematic structural view of the pressure relief assembly in

[0043] Figure 6 is Figure 5 an exploded view of the pressure relief assembly in

[0044] Figure 7 is a schematic structural view of the pressure relief assembly in the second embodiment of the battery pack pressure relief system provided by the present utility model, wherein the pressure relief assembly is connected to the integrated pipeline and the delivery pipe;

[0045] Figure 8 is Figure 7 a schematic structural view of the first pressure relief device in

[0046] Figure 9 is Figure 7 a schematic structural view of the fluid connector in

[0047] Explanation of the reference numerals in the drawings:

[0048] 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; 410, battery pack; 411, battery module; 420, battery pack pressure relief system; 430, integrated 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; 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; 911, second annular pressing part; 920, second pressure relief diaphragm; 921, second pressure relief groove.

[0049] The realization, functional features and advantages of the object of the present utility model will be further described with reference to the embodiments and the accompanying drawings. Detailed implementation manners

[0050] The following will clearly and completely describe the technical solutions in the embodiments of the present utility model 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 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.

[0051] 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, the directional indications are only used to explain the relative position relationship and movement conditions between components in a specific posture. If the specific posture changes, the directional indications will also change accordingly.

[0052] In addition, if there are descriptions involving "first", "second", etc. in the embodiments of the present utility model, the descriptions of "first", "second", etc. are only for descriptive purposes and cannot be understood as indicating or implying their relative importance or implicitly indicating the quantity of the indicated technical features. Thus, the features defined with "first" and "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, solution B, or a solution where A and B are satisfied simultaneously. In addition, the technical solutions between the various embodiments can be combined with each other, but it must be based on the fact that those of ordinary skill in the art can implement it. When the combination of technical solutions is contradictory 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.

[0053] Please refer to Figures 1 to 6 , the present utility model provides a battery pack pressure relief system 420.

[0054] In the first embodiment of the present utility model, the battery pack pressure relief system 420 can be applied to an electric vehicle. The electric vehicle includes a battery pack 410. The battery pack 410 includes a plurality of battery modules 411. The battery module 411 includes a housing provided with a receiving cavity and an electric core disposed in the receiving cavity.

[0055] The battery pack pressure relief system 420 includes an integrated pipeline 430 and a pressure relief assembly 500.

[0056] Among them, the integrated pipeline 430 includes a manifold pipe 440 and a plurality of branch pipes 450 connected to the manifold pipe 440. One branch pipe 450 communicates with one receiving cavity. In this way, the battery pack pressure relief system 420 enables the receiving cavities of multiple battery modules 411 to share the manifold pipe 440. In other words, once thermal runaway gas is generated in the receiving cavities of multiple battery modules 411, the thermal runaway gas will flow into the manifold pipe 440. That is to say, the manifold pipe 440 can be flowed through by the thermal runaway gas generated in multiple receiving cavities. In this way, the integration degree of the integrated pipeline 430 is relatively high, which is beneficial to lightening the weight of the battery pack pressure relief system 420.

[0057] The pressure relief assembly 500 includes a first pressure relief device provided on the manifold pipe 440. The integrated pipeline 430 is used to release thermal runaway gas through the first pressure relief device. In this way, it is beneficial to realize pressure relief of the receiving cavities of multiple battery modules 411 by one first pressure relief device, and it is beneficial to reduce the weight of the battery pack pressure relief system 420.

[0058] Without loss of generality, this article introduces the application of the battery pack pressure relief system 420 to the battery pack 410 of the aircraft 100. In this way, it is also beneficial to realize the light weight of the aircraft 100.

[0059] In the first embodiment, at the connection between the branch pipe 450 and the manifold pipe 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 pipe 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, a plurality of branch pipes 450 are arranged in sequence. In this way, the situation where the thermal runaway gas enters the manifold pipe 440 from the upstream branch pipe 450 and then enters the downstream branch pipe 450 from the manifold pipe 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 pipe 440 from the branch pipe 450.

[0060] 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 pipe 440 from the upstream branch pipe 450 and then enters the downstream branch pipe 450 from the manifold pipe 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 aircraft 100 body structure, convenient installation and efficient confluence occur simultaneously. In addition, this angle design scheme also reduces the manufacturing difficulty of the integrated pipeline 430.

[0061] In the first embodiment, in the direction in which the manifold 440 is used to supply heat for the flow of out-of-control gas, the first pressure relief device is disposed downstream of the plurality of branch pipes 450. In this way, a plurality of first pressure relief devices can be saved, and one first pressure relief device can be used to relieve the pressure of the accommodation cavities of a plurality of battery modules 411, which is beneficial to reducing the weight of the battery pack pressure relief system 420 and realizing the light weight of the aircraft 100. In some other embodiments, a first pressure relief device is provided in one branch pipe 450. In this way, blocked by the first pressure relief device, the situation where the out-of-control 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.

[0062] In the first embodiment, in the direction in which the manifold 440 is used to supply heat for the flow of out-of-control gas, the inner diameter of the manifold 440 gradually increases. When a plurality of battery modules 411 are out of control, the out-of-control 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 for the flow of out-of-control gas, the closer to the downstream, the more out-of-control gas is converged. In this way, in the direction in which the manifold 440 is used to supply heat for the flow of out-of-control gas, the inner diameter of the manifold 440 gradually increases, which can relieve the pressure of the out-of-control gas released from each branch pipe 450 and is beneficial to the smooth release of the out-of-control gas in each accommodation cavity.

[0063] 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 out-of-control gas to flow downstream in the manifold 440 is larger than the space available for the out-of-control gas to flow upstream in the direction in which the manifold 440 is used to supply heat for the flow of out-of-control gas.

[0064] In some other embodiments, in the direction in which the manifold 440 is used to supply heat for the flow of out-of-control gas, the inner diameters of all parts of the manifold 440 are the same.

[0065] In the first embodiment, the branch pipe 450 is arranged in an arc shape at the connection with the manifold 440. In this way, the situation where the out-of-control gas enters the manifold 440 from the upstream branch pipe 450 and then enters the accommodation cavity through the downstream branch pipe 450 is further reduced, so as to improve the safety of the battery pack 410. In some other embodiments, the branch pipe 450 extends along the first direction, that is, the branch pipe 450 is a straight pipe.

[0066] In the first embodiment, the material of the integrated pipeline 430 is configured as a fireproof material. It can be understood that when the battery pack 410 undergoes thermal runaway, the temperature of the thermal runaway gas generated is relatively high. Configuring the material of the integrated pipeline 430 as a fireproof material can reduce the probability of the integrated pipeline 430 being burned out, enabling the integrated pipeline 430 to maintain its guiding function for 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 a large amount of thermal runaway gas. Further, in the first embodiment, the integrated pipeline 430 is configured as a metal pipe, a fiber pipe, an asbestos pipe, an aerogel pipe or a ceramic pipe. This gives the integrated pipeline 430 good fireproof performance.

[0067] In some other embodiments, a fireproof layer is provided on the inner surface of the integrated pipeline 430. It can be understood that when the battery pack 410 undergoes thermal runaway, the temperature of the thermal runaway gas generated is relatively high, and the inner surface of the integrated pipeline 430 is in contact with the thermal runaway gas. Setting a fireproof layer on the inner surface of the integrated pipeline 430 can reduce the probability of the integrated pipeline 430 being burned out, enabling the integrated pipeline 430 to maintain its guiding function for 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 a large amount of thermal runaway gas. Further, in some other embodiments, the fireproof layer is configured as a fireproof coating layer or an aerogel layer, which gives the integrated pipeline 430 good fireproof performance; and / or, the material of the integrated pipeline 430 is configured as aluminum.

[0068] In the first embodiment, the integrated pipeline 430 is also used for heat exchange fluid and / or non-combustible gas to flow through. In this way, the integrated pipeline 430 is not only used for the thermal runaway gas to flow through, but also reused for heat exchange fluid and / or non-combustible gas to flow through, which is beneficial to improving the integration degree of the integrated pipeline 430.

[0069] In the first embodiment, the pressure relief assembly 500 further includes a fluid connector 800 connected to the integrated pipeline 430. The fluid connector 800 is provided with a valve core, so that the fluid connector 800 has a first conducting state and a first closing state. The integrated pipeline 430 is used to introduce heat exchange fluid and / or non-combustible gas into the receiving cavity through the fluid connector 800, and / or to discharge the heat exchange fluid and / or non-combustible gas in the receiving cavity. In this way, the integrated pipeline 430 is not only used for the thermal runaway gas to flow through, but also reused for heat exchange fluid and / or non-combustible gas to flow through, which is beneficial to improving the integration degree of the integrated pipeline 430.

[0070] Without loss of generality, taking the electric vehicle as the aircraft 100 as an example below, the aircraft 100 further includes a ground thermal management system 300 as an example to introduce the battery pack pressure relief system 420. The ground thermal management system 300 includes a delivery pipe 310 for connecting the fluid connector 800, and the heat exchange fluid is configured as a heat exchange liquid. The ground thermal management system 300 transports the heat exchange liquid and / or non-combustible gas through the delivery pipe 310.

[0071] Thus, the fluid connector 800 can be communicatively disposed with the ground thermal management system 300 so that when the aircraft 100 is in the ground heat exchange state, the flowing non-combustible gas and / or heat exchange liquid can be filled into the receiving cavity through the fluid connector 800.

[0072] In some other embodiments, the aircraft 100 includes an on-board thermal management system which is communicatively disposed with the integrated pipeline 430. Both ends of the integrated pipeline 430 are connected to the receiving cavity to form a loop with the receiving cavity. Thus, the fluid connector 800 can be omitted.

[0073] In the first embodiment, the pressure relief assembly 500 further includes a seat body 600 which includes a seat main body 610 having a first cavity, and a first interface portion 620, a second interface portion 630 and a third interface portion 640 which are all disposed on the seat main body 610 and are respectively communicated with the first cavity. 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 integrated pipeline 430. Thus, both the fluid connector 800 and the first pressure relief device are connected to the integrated pipeline 430 through the third interface portion 640 of the seat body 600. On the one hand, this is conducive to reducing the interfaces opened on the integrated pipeline 430 for installing the fluid connector 800 and the first pressure relief device, facilitating the manufacture of the integrated 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 integrated pipeline 430, which is conducive to saving the maintenance cost of the battery pack pressure relief system 420. In some other embodiments, the integrated 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, thereby omitting the seat body 600.

[0074] In the first embodiment, the first interface and the second interface portion 630 are different interface portions. Thus, the pressure relief assembly 500 has a state in which the fluid connector 800 and the first pressure relief device are simultaneously connected to the seat body 600. When the aircraft 100 is in the ground heat exchange state, the delivery pipe 310 can be directly connected to the corresponding fluid connector 800, which is very convenient.

[0075] In the first embodiment, the fluid connector 800 has a tendency to maintain in the first closed state. Thus, when the fluid connector 800 is disconnected from the corresponding delivery 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. It should be noted that the fluid connector 800 having a tendency to maintain in the first closed state can be achieved but is 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; alternatively, the fluid connector 800 has an elastic reset member connected to the valve core, and the elastic reset member makes the fluid connector 800 have 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.

[0076] In the first 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.

[0077] 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. Thus, when a thermal runaway occurs in the battery pack 410, when the pressure received by the first pressure relief diaphragm 720 under the extrusion of the thermal runaway gas meets a preset pressure, the first pressure relief diaphragm 720 will rupture to relieve the pressure of the integrated pipeline 430.

[0078] 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 integrated pipeline 430, thereby protecting the safety of the integrated pipeline 430.

[0079] 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 arranged in parallel on the same side of the seat body 610, and the orientations of the first interface portion 620 and the second interface portion 630 are the same. In some other embodiments, the structural form of the seat body 600 can also be other, which is not limited here.

[0080] 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 integrated pipeline 430. In some other embodiments, the third interface portion 640 is provided with a snap connection structure. In this way, the third interface portion 640 can be more conveniently connected to the integrated pipeline 430.

[0081] 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.

[0082] 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.

[0083] Referring together to Figures 7 to 9 , the present utility model also provides a second embodiment of the battery pack pressure relief system 420. The same parts of the second embodiment and the first embodiment can be referred to the first embodiment, and will not be elaborated here.

[0084] 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 it is necessary to use the heat exchange liquid to heat exchange 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 it is not necessary to use the heat exchange liquid to heat exchange 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 avoid the 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.

[0085] 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 with 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. Thus, 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 integrated pipeline 430.

[0086] In the second embodiment, a first pressure relief groove 721 is formed on the surface of the first pressure relief diaphragm 720. Thus, 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 integrated pipeline 430, thereby protecting the safety of the integrated pipeline 430.

[0087] 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 orientations of the fourth interface portion 740 and the fifth interface portion 750 are opposite. In some other embodiments, the structural form of the first pressure relief device may also be other, which is not limited herein.

[0088] 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 to exchange heat for 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.

[0089] In the second embodiment, the fluid connector 800 includes a fluid connector body 810 provided with a third cavity, and a sixth interface portion 820, a seventh interface portion 830 and an eighth interface portion 840 respectively provided on the fluid connector body 810 and communicating with the third cavity. The sixth interface portion 820 is used to connect with the first interface portion 620, and the second pressure relief device 900 is arranged at the eighth interface portion 840. 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 to exchange heat for 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.

[0090] 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 breather valve.

[0091] 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, and 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, 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 integrated pipeline 430.

[0092] In the second embodiment, a second pressure relief groove 921 is formed on the surface of the second pressure relief diaphragm 920. Thus, the pressure increment required for the second pressure relief diaphragm 920 to deform from the start to complete rupture is reduced, which helps to prevent excessive pressure accumulation in the integrated pipeline 430, thereby protecting the safety of the integrated pipeline 430.

[0093] 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 that 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.

[0094] 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. Thus, 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. Thus, it is convenient for users to use.

[0095] 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 breather valve.

[0096] The present utility model also provides an aircraft 100, which includes an aircraft body 200, the aforementioned battery pack pressure relief system 420, and a battery pack 410. The specific structure of the battery pack pressure relief system 420 refers to the above embodiments. Since this aircraft 100 adopts all the technical solutions of the above embodiments, it at least has all the beneficial effects brought by the technical solutions of the above embodiments, which will not be elaborated herein one by one. Among them, the battery pack pressure relief system 420 and the battery pack 410 are arranged in the aircraft body 200. It should be noted that the aircraft 100 can be but is not limited to being configured as an eVTOL.

[0097] In the first embodiment, the aircraft 100 further includes a ground thermal management system 300. The ground thermal management system 300 is used to provide a heat exchange fluid and / or a non-combustible gas. The integrated pipeline 430 can be communicatively arranged with the ground thermal management system 300, so that when the aircraft 100 is in the ground heat exchange state, the heat exchange fluid and / or the non-combustible gas can be filled into the accommodation cavity through the integrated 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.

[0098] In addition, when the aircraft 100 is in the ground heat exchange state, the ground thermal management system 300 can fill the accommodation cavity with a heat exchange liquid through the integrated 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 a non-combustible gas through the integrated 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 a heavy heat exchange liquid for flight, which is beneficial to the lightweight of the aircraft 100.

[0099] In the first embodiment, there are multiple integrated pipelines 430 and multiple pressure relief assemblies 500. One pressure relief assembly 500 is arranged corresponding to one integrated 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 an integrated pipeline 430, and the second communication port is connected to another integrated pipeline 430. The heat exchange fluid is configured as a heat exchange liquid. 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, and 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.

[0100] Thus, once thermal runaway occurs in the battery module 411, the thermal runaway gas generated in the accommodation cavity can flow to an integrated pipeline 430 through the first communication port and also to another integrated pipeline 430 through the second communication port. In addition, pressure relief assemblies 500 are respectively provided on these two integrated pipelines 430, which is beneficial to improving the pressure relief redundancy of the battery pack 410.

[0101] When the aircraft 100 is in the ground heat exchange state, the ground heat management system 300 can transport heat exchange liquid to the accommodation cavity through the second communication port. 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 communication port 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 communication port. Thus, in the process of the ground heat exchange system introducing the heat exchange fluid into the accommodation cavity, it is both convenient to guide the non-combustible gas in the accommodation cavity outside the accommodation cavity and enables the heat exchange liquid to continuously exchange heat with the battery cells in the accommodation cavity. When the battery cells reach the preset temperature, the ground heat management system 300 can communicate with the first communication port to transport non-combustible gas to the accommodation cavity. 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 prompt the heat exchange liquid to be discharged from the second communication port outside the accommodation cavity, making the liquid level of the heat exchange liquid gradually decrease. When the heat exchange liquid level drops to the second communication port, the non-combustible gas can be discharged from the second communication port. Thus, in the process of the ground heat exchange system introducing non-combustible gas into the accommodation cavity, it not only fills the accommodation cavity with non-combustible gas to isolate the battery cells and air, reducing the probability of thermal runaway of the battery pack 410, but also facilitates guiding the heat exchange liquid in the accommodation cavity outside the accommodation cavity.

[0102] There are many structural forms of the ground heat exchange system. Without loss of generality, the ground heat 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 heat exchange liquid, and the gas storage tank is used to store non-combustible gas. The heat exchange pipeline is provided with a control valve, so that the ground heat management system 300 has a first state in which the two delivery pipes 310 are communicated with the liquid storage tank and disconnected from the gas storage tank, and a second state in which the two delivery pipes 310 are communicated with the gas storage tank and the liquid storage tank is disconnected. It should be noted 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 heat management system 300 to have a first state in which the two delivery pipes 310 are communicated with the liquid storage tank and disconnected from the gas storage tank, and a second state in which the two delivery pipes 310 are communicated with the gas storage tank and the liquid storage tank is disconnected.

[0103] For the sake of convenience of description, the delivery pipe 310 for filling the non-combustible gas into the accommodation cavity through the first communication port is referred to as the first delivery pipe 311, and the delivery pipe 310 for filling the heat exchange liquid into the accommodation cavity through the second communication port is referred to as the second delivery pipe 312.

[0104] In this way, when the aircraft 100 is in the ground state, 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 out of 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. In this way, 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 out of the accommodation cavity, and at the same time, 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 transports 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 out of the accommodation cavity, and the liquid level of the heat exchange liquid gradually decreases. 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. In this way, 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 at the same time, it is convenient to discharge the heat exchange liquid in the accommodation cavity out of the accommodation cavity. In addition, after the aircraft 100 is heat-exchanged by the ground thermal management system 300, the accommodation cavity can be filled with the non-combustible gas before flight. In this way, both the heat exchange requirement of the aircraft 100 is satisfied, and the aircraft 100 does not need to carry the heavy heat exchange liquid for flight. In addition, during the flight process, the battery cells are protected by the non-combustible gas.

[0105] 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. Combined with the design of the integrated 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.

[0106] In the first embodiment, the pressure relief assembly 500 further includes a fluid connector 800 connected to the integrated pipeline 430. 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. The ground thermal management system 300 further includes a delivery pipe 310 for connecting the fluid connector 800. An inlet / outlet 250 for the delivery pipe 310 to enter and exit 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, so as to facilitate the disassembly and assembly of the delivery pipe 310 with the fluid connector 800.

[0107] In the first embodiment, the battery pack 410 is arranged 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 arranged at the pressure relief port 240. In this way, once the battery pack 410 undergoes a thermal runaway, the thermal runaway gas can be discharged from the pressure relief port 240 to the outside of the aircraft body 200 through the first pressure relief device, 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.

[0108] 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. In this way, 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.

[0109] In the first embodiment, the first pressure relief device is flexibly connected to the pressure relief port 240. In this way, the position and pose of the first pressure relief device relative to the pressure relief port 240 can be adjusted, making the installation position of the battery pack pressure relief system 420 on the aircraft 100 relatively flexible. In addition, it is also beneficial to achieve a smooth transition between the connection between 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 integrated pipeline 430 is flexible.

[0110] 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 here.

[0111] In one embodiment, the elastic structure is configured as a rubber joint. In some other embodiments, the elastic structure can also be other, which are not limited here, as long as the elastic structure has elasticity.

[0112] In the first embodiment, a sealing structure is provided between the first pressure relief device and the pressure relief port 240. In this way, 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.

[0113] 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, so that the sealing structure can better maintain its sealing performance.

[0114] 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 in the wings 220 and / or the arms 230. In this way, the space of the wings 220 and / or the arms 230 is fully utilized. In some other embodiments, the battery pack 410 is disposed in the fuselage 210.

[0115] The above are only exemplary embodiments of the present utility model, and do not limit the patent scope of the present utility model accordingly. Any equivalent structural transformation made under the technical concept of the present utility model by using the content of the specification and drawings of the present utility model, or any direct / indirect application in other related technical fields is included in the patent protection scope of the present utility model.

[0116] The above are only exemplary embodiments of the present utility model, and do not limit the patent scope of the present utility model accordingly. Any equivalent structural transformation made under the technical concept of the present utility model by using the content of the specification and drawings of the present utility model, or any direct / indirect application in other related technical fields is included in the patent protection scope of the present utility model.

Claims

1. A battery pack pressure relief system, characterized in that, Applied to a battery pack, the battery pack includes a plurality of battery modules, each battery module includes a housing having a receiving cavity and an electric core disposed in the receiving cavity, and the battery pack pressure relief system includes: An integrated pipeline, including a manifold and a plurality of branch pipes connected to the manifold, one of the branch pipes communicating with one of the receiving cavities; and A pressure relief assembly, including a first pressure relief device disposed on the manifold, and the integrated pipeline is used to release thermal runaway gas through the first pressure relief device.

2. The battery pack pressure relief system according to claim 1, wherein The pressure relief assembly further includes a fluid connector disposed on the integrated pipeline, the fluid connector is provided with a valve core so that the fluid connector has a first conduction state and a first closed state, and the integrated pipeline is used to introduce a heat exchange fluid and / or a non-combustible gas into the receiving cavity through the fluid connector, and / or to discharge the heat exchange fluid and / or the non-combustible gas in the receiving cavity.

3. The battery pack pressure relief system according to claim 2, characterized in that, The fluid connector is disposed on the manifold, and in the direction in which the manifold is used for the thermal runaway gas to flow, the first pressure relief device is disposed downstream of the plurality of branch pipes.

4. The battery pack pressure relief system according to claim 2, wherein, The pressure relief assembly further includes a seat body, the seat body includes a seat main body having a first cavity, and a first interface portion, a second interface portion and a third interface portion that are all disposed on the seat main body and communicate with the first cavity respectively, 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 integrated pipeline.

5. The battery pack pressure relief system according to claim 4, characterized in that, The first interface and the second interface portion are different interface portions; 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.

6. The battery pack pressure relief system according to any one of claims 1 to 5, characterized in that, At the connection between the branch pipe and the manifold, the direction in which the branch pipe is used for the thermal runaway gas to flow is the first direction, the direction in which the manifold is used for the thermal runaway gas to flow is the second direction, the first direction and the second direction are arranged at an angle A, 0° < A < 90°, and in the second direction, the plurality of branch pipes are arranged in sequence.

7. The battery pack pressure relief system according to claim 6, wherein, 30°≤A≤60°； And / or, in the direction in which the manifold is used for the thermal runaway gas to flow, the first pressure relief device is disposed downstream of the plurality of branch pipes; And / or, in the direction in which the manifold is used for the thermal runaway gas to flow, the inner diameter of the manifold gradually increases; And / or, the branch pipe is arranged in an arc shape at the connection with the manifold.

8. The battery pack pressure relief system according to claim 1, characterized in that, The material of the integrated pipeline is configured as a fireproof material, and the integrated pipeline is configured as a metal pipe, a fiber pipe, an asbestos pipe, an aerogel pipe or a ceramic pipe.

9. The battery pack pressure relief system according to claim 1, wherein The inner surface of the integrated 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 material of the integrated pipeline is configured as aluminum.

10. An aircraft, characterized in that, Including: An aircraft body: and The battery pack pressure relief system and the battery pack according to any one of claims 1 to 9, disposed on the aircraft body.

11. The aircraft according to claim 10, wherein The aircraft includes an on-board thermal management system, the on-board thermal management system is connected to the integrated pipeline, and both ends of the integrated pipeline are connected to the receiving cavity to form a loop with the receiving cavity.

12. The aircraft according to claim 10, characterized in that, The aircraft further includes a ground thermal management system for providing a heat exchange fluid and / or a non-combustible gas. The integrated pipeline can be communicatively arranged with the ground thermal management system so that, in the ground heat exchange state, the aircraft can fill the accommodation cavity with the heat exchange fluid and / or the non-combustible gas through the integrated pipeline.

13. The aircraft according to claim 12, characterized in that, A plurality of the integrated pipelines are provided, and a plurality of the pressure relief assemblies are provided. One pressure relief assembly is correspondingly arranged for one integrated pipeline. The housing is provided with a first communication port and a second communication port both communicating with the accommodation cavity. One integrated pipeline is connected to the first communication port, and another integrated pipeline is connected to the second communication port. The heat exchange fluid is configured as a heat exchange liquid. The first communication port is higher than the second communication port. The first communication port is used for allowing the non-combustible gas to flow into the accommodation cavity so that the accommodation cavity is filled with the non-combustible gas, and the second communication port is used for allowing the heat exchange liquid to flow into the accommodation cavity so that the accommodation cavity is filled with the heat exchange liquid.

14. The aircraft according to claim 12, wherein, The pressure relief assembly further includes a fluid connector connecting the integrated pipeline. The fluid connector is provided with a valve core so that the fluid connector has a first conduction state and a first closed state. The ground thermal management system further includes a delivery pipe for connecting the fluid connector. An inlet and outlet for the delivery pipe to pass through are provided on the outer surface of the aircraft body so that the delivery pipe can be disassembled and assembled with the fluid connector.

15. The aircraft according to any one of claims 10 to 14, characterized in that The battery pack is arranged in the aircraft body, and a pressure relief port is provided on the outer surface of the aircraft body. The first pressure relief device is arranged at the pressure relief port.

16. The aircraft according to claim 15, wherein, The connection between the first pressure relief device and the pressure relief port is smoothly transitioned with the outer surface of the aircraft body; and / or, the first pressure relief device is flexibly connected to the pressure relief port.

17. The aircraft according to claim 15, characterized in that, 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.

18. The aircraft according to claim 16, 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 adhesive structure, or a fireproof filler structure.

19. The aircraft according to claim 10, characterized in that, The aircraft body includes a fuselage, wings arranged on the fuselage, and arms arranged on the wings. The battery pack is arranged in the wings and / or the arms.

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