Battery modules, wings and aircraft

Abstract

This invention provides a battery module, a wing, and an aircraft, relating to the field of air transportation technology. The battery module includes: a housing with an explosion-proof valve, configured to be installed within the wing body; a cell assembly and a support assembly installed within the housing, the cell assembly being connected to the support assembly, and the support assembly having first vent holes communicating with the explosion-proof valve at the positive and negative terminals corresponding to the cell assembly; and a state monitoring layer and a protective component installed within the housing, the state monitoring layer and the protective component being located on at least one side of the cell assembly. The state monitoring layer is configured to detect the operating state of the cell assembly, and the protective component is configured to suppress thermal runaway of the battery module. The battery module provided by this invention facilitates proactive control and suppression of the risk of thermal runaway of the cell assembly within the confined space of the wing body.

Description

Technical Field

[0001] This invention relates to the field of air transportation technology, and in particular to a battery module, wing, and aircraft. Background Technology

[0002] With the rise of urban air mobility concepts, electric vertical takeoff and landing (eVTOL) aircraft have become an important research and development direction in the aviation field. These aircraft are electrically powered, and their power systems rely entirely or partially on high-energy-density lithium battery packs to achieve efficient, environmentally friendly vertical takeoff and landing and flight capabilities.

[0003] In existing technologies, to optimize the structural design and weight distribution of aircraft, electric vertical takeoff and landing (EVTOL) aircraft employ a design scheme that integrates battery modules within the curved ducts of the wing. However, battery modules generate heat during charging and discharging, especially during high-power operation. This heat accumulation can lead to elevated battery temperatures and potentially trigger thermal runaway. Current technologies do not consider how to effectively suppress the propagation of thermal runaway within a wing-integrated environment. Summary of the Invention

[0004] The purpose of this invention is to provide a battery module that facilitates proactive control and suppression of the risk of thermal runaway of battery cells within the confined space of an airfoil. Additionally, it provides an airfoil including the aforementioned battery module, and an aircraft including either the aforementioned battery module or the aforementioned airfoil.

[0005] To achieve the above objectives, the present invention provides the following technical solution: In a first aspect, the present invention provides a battery module, comprising: The outer casing is equipped with an explosion-proof valve, and the outer casing is configured to be installed within the wing body; The battery cell assembly and the bracket assembly are installed inside the housing. The battery cell assembly is connected to the bracket assembly. The bracket assembly is provided with a first vent hole corresponding to the positive and negative terminals of the battery cell assembly, which is connected to the explosion-proof valve. A status monitoring layer and a protective component are installed within the housing, the status monitoring layer and the protective component being located on at least one side of the battery cell assembly, the status monitoring layer being configured to detect the operating status of the battery cell assembly, and the protective component being configured to suppress the propagation of thermal runaway of the battery module.

[0006] In an optional embodiment, the shape of the outer shell is adapted to the inner wall surface of a single arc-shaped duct of the wing body, and the condition monitoring layer and the protective components are both located on both sides of the battery cell assembly.

[0007] In an optional embodiment, the protective component includes a heat insulation layer and a fireproof layer, the heat insulation layer being located between the support assembly and the condition monitoring layer, and the fireproof layer being located between the condition monitoring layer and the outer shell; The heat insulation layer is provided with a second vent that is opposite to and communicates with the first vent, and the status monitoring layer is provided with a third vent that is opposite to and communicates with the second vent.

[0008] In an optional embodiment, the support assembly includes an upper support and a lower support, one end of the battery cell assembly is connected to the upper support, and the other end of the battery cell is connected to the lower support. Both the upper support and the lower support are provided with the first vent hole.

[0009] In an optional embodiment, the shape of the outer shell is adapted to the inner wall surface of the common area between two adjacent arcuate ducts of the wing body and the inner wall surface of one end of the two arcuate ducts adjacent to the common area to their own central axis, and the condition monitoring layer and the protective component are both located on one side of the battery cell assembly.

[0010] In an optional embodiment, the protective component includes a thermally conductive layer, a liquid cooling plate, and a substrate, wherein the thermally conductive layer is located between one side of the substrate and the liquid cooling plate, and the battery cell assembly is located on the other side of the substrate.

[0011] In an optional embodiment, the support assembly includes a single-sided support connected to the cell assembly, the single-sided support having the first vent hole.

[0012] In an optional embodiment, the housing includes an upper cover and a lower housing connected to the upper cover, the lower housing being provided with the explosion-proof valve.

[0013] In a second aspect, the present invention provides an air wing, including an air wing body and a plurality of battery modules as described in any of the foregoing embodiments; The wing body includes a skin and a wing spars connected within the skin. The wing spars have multiple interconnected arc-shaped ducts. The skin is provided with air inlets and outlets that communicate with each of the arc-shaped ducts. The air inlets and outlets are located between two adjacent arc-shaped ducts. Each of the arc-shaped ducts contains one battery module, or one battery module is provided between every two adjacent arc-shaped ducts.

[0014] Thirdly, the present invention provides an aircraft comprising a battery module as described in any of the foregoing embodiments, or comprising two wings as described in the foregoing embodiments.

[0015] The battery module, wing, and aircraft provided by this invention can produce the following beneficial effects: When the battery module provided by this invention is in use, the status monitoring layer can monitor parameters such as cell voltage and temperature in real time. When abnormal gas generation or temperature rise occurs in the cell assembly, the gas is quickly guided to the explosion-proof valve through the first exhaust port to be discharged in a directional manner, so as to avoid internal pressure accumulation and explosion. At the same time, the protective component suppresses the spread of thermal runaway of the battery module, thereby improving the safety of the battery module and the overall operational reliability of the aircraft.

[0016] Compared with the prior art, the battery module provided by the first aspect of the present invention integrates the shell, cell assembly, bracket assembly, status monitoring layer and protective assembly into a single design, and is specially configured with an explosion-proof valve connected to the first exhaust port on the bracket assembly corresponding to the positive and negative poles, which facilitates the active prevention and control of the risk of thermal runaway of the cell assembly and the suppression of its spread within the confined space of the wing body.

[0017] The wing provided by the second aspect of the present invention has the battery module provided by the first aspect of the present invention, thereby having all the beneficial effects of the battery module provided by the first aspect of the present invention.

[0018] The aircraft provided in the third aspect of the present invention has the battery module provided in the first aspect of the present invention or the wing provided in the second aspect of the present invention, thereby having all the beneficial effects of the battery module provided in the first aspect of the present invention or the wing provided in the second aspect of the present invention. Attached Figure Description

[0019] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0020] Figure 1 This is a rear view of the wing section structure provided in an embodiment of the present invention; Figure 2 This is a three-dimensional structural schematic diagram of the first type of battery module provided in an embodiment of the present invention; Figure 3 This is an exploded view of a first type of battery module provided in an embodiment of the present invention; Figure 4 This is a three-dimensional structural diagram of the second type of battery module provided in an embodiment of the present invention; Figure 5 This is an exploded view of a second type of battery module provided in an embodiment of the present invention; Figure 6 This is a front view of the wing section structure provided in an embodiment of the present invention; Figure 7 for Figure 1A magnified view of part A.

[0021] Icons: 1-Outer shell; 11-Upper cover; 12-Lower shell; 121-Explosion-proof valve; 2-Wing body; 21-Skin; 211-Air inlet / outlet; 212-Swing plate; 2121-Support frame; 213-Fixed shaft; 214-Torsion spring; 215-Limit block; 3-Battery cell assembly; 4-Bracket assembly; 41-First exhaust port; 42-Upper bracket; 43-Lower bracket; 44-Single-side bracket; 5-Status monitoring layer; 51-Third exhaust port; 6-Protective assembly; 61-Heat insulation layer; 611-Second exhaust port; 62-Fireproof layer; 63-Heat conductive layer; 64-Liquid cooling plate; 65-Base plate; 7-Sampling plate. Detailed Implementation

[0022] The technical solution of the present invention will now be clearly and completely described with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0023] In the description of this invention, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing the invention and for simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0024] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0025] The specific embodiments of the present invention will be described in detail below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are for illustration and explanation only and are not intended to limit the present invention.

[0026] A first aspect of the present invention provides a battery module, such as Figures 1 to 5 As shown, it includes: The outer shell 1 is equipped with an explosion-proof valve 121, and the outer shell 1 is configured to be installed inside the wing body 2; The battery cell assembly 3 and the bracket assembly 4 are installed inside the housing 1. The battery cell assembly 3 is connected to the bracket assembly 4. The bracket assembly 4 is provided with a first vent 41 that is connected to the explosion-proof valve 121 at the positive and negative terminals of the battery cell assembly 3. A state monitoring layer 5 and a protective component 6 are installed inside the housing 1. The state monitoring layer 5 and the protective component 6 are located on at least one side of the cell assembly 3. The state monitoring layer 5 is configured to detect the operating state of the cell assembly 3, and the protective component 6 is configured to suppress the spread of thermal runaway after the battery module has occurred.

[0027] In actual assembly and use, the battery module is first embedded into the internal duct of the wing body 2 of the electric vertical take-off and landing aircraft through the structural adaptability of the outer shell 1; the cell assembly 3 is fixed on the bracket assembly 4, which provides mechanical support. The first exhaust port 41 at the corresponding positive and negative terminals of each cell forms a directional pressure relief channel with the explosion-proof valve 121 preset on the outer shell 1; when the cell assembly 3 experiences thermal runaway under high-rate charging and discharging or abnormal operating conditions, the internal gas pressure rises rapidly. The gas flows through the first exhaust port 41 to the explosion-proof valve 121 and is directionally discharged outside the shell to avoid disorderly pressure release that could cause the outer shell 1 to rupture; at the same time, the status monitoring layer 5 collects the working status information of each area of ​​the cell assembly 3 in real time, and the protection component 6 can suppress the spread of thermal runaway of the battery module.

[0028] The above-mentioned battery module has the following advantages: 1. The battery modules are installed inside the wing body 2, which can make full use of the idle space of the wing duct, improve battery capacity and space utilization, and avoid the battery modules being concentrated in the fuselage of the aircraft, which would cause the center of the aircraft to be concentrated, which is conducive to flight stability and operability adjustment. The distributed battery module configuration also facilitates the heat dissipation of the battery modules, reduces the risk of thermal runaway propagation, and after the aircraft crashes, the thermal runaway of the battery will not directly affect the cabin, which has a high degree of safety. 2. Through the structured exhaust path formed by the bracket assembly 4 and the explosion-proof valve 121, when the battery cell assembly 3 experiences abnormal gas generation or temperature rise, the gas is quickly guided to the explosion-proof valve 121 through the first exhaust port 41 for directional discharge, avoiding internal pressure accumulation that could lead to an explosion, and ensuring the directional discharge efficiency and pressure relief response speed of the thermal runaway gas. 3. A status monitoring layer 5 and a protection component 6 are provided. The status monitoring layer 5 can monitor the working status of the battery cell assembly 3, which is conducive to the active prevention and control of the risk of thermal runaway of the battery cell assembly 3. The protection component 6 suppresses the spread of thermal runaway of the battery module and improves the safety of the battery module and the overall operational reliability of the aircraft.

[0029] Among them, the battery cell assembly 3 can be formed by first connecting 7 ternary lithium battery cells in parallel to form a high-capacity / high-rate battery cell unit, and then connecting 80 battery cell units in series.

[0030] Of course, the above-mentioned cell assembly 3 is only one example. Each cell unit may also include other numbers of ternary lithium cells, and the number of cell units can be adjusted according to actual needs.

[0031] In alternative implementations, such as Figure 1 and Figure 2 As shown, the outer shell 1 has an arc-shaped shell structure, and its outer contour shape matches the inner wall shape of a single arc-shaped duct inside the wing body 2, so that the outer shell 1 can make full use of the space inside the duct; there can be a heat dissipation gap between the outer shell 1 and the wing body 2. During flight, the airflow enters the heat dissipation gap through the air inlet and outlet 211 on the wing body 2, takes away the heat of the outer shell 1, and then exits through the air inlet and outlet 211 to achieve heat dissipation of the outer shell 1.

[0032] Furthermore, the condition monitoring layer 5 and the protective component 6 are respectively arranged on both sides of the axial direction of the cell assembly 3. This bilateral symmetrical arrangement allows the condition monitoring layer 5 and the protective component 6 to fully detect the operating status of each cell assembly 3 and to suppress the spread of thermal runaway of the battery module to both sides of the axial direction.

[0033] In alternative implementations, such as Figure 3 As shown, the protective component 6 adopts a multi-layer composite structure design, specifically including a heat insulation layer 61 and a fireproof layer 62, which together form a graded barrier against the thermal runaway propagation path.

[0034] The heat insulation layer 61 is disposed between the support assembly 4 and the status monitoring layer 5. Its material is preferably mica sheet with high insulation, high temperature resistance, low thermal conductivity and good mechanical stability. The mica sheet is provided with second exhaust holes 611 that correspond one-to-one with the first exhaust holes 41 on the support assembly 4. The axis of each second exhaust hole 611 is collinear with the axis of the corresponding first exhaust hole 41, ensuring that the airflow channel remains continuous and without deflection within the heat insulation layer 61.

[0035] The status monitoring layer 5 is a flexible circuit board structure that integrates a temperature sensor array, voltage sampling points, and signal transmission lines. A third vent 51, precisely corresponding to the position of the second vent 611, is located on the side facing the heat insulation layer 61. The third vent 51 penetrates the substrate of the status monitoring layer 5. The third vent 51 and the second vent 611 are coaxially aligned, together forming part of a complete pressure relief airflow channel from the positive and negative electrode areas of the battery cell to the explosion-proof valve 121.

[0036] The fireproof layer 62 is located on the side of the condition monitoring layer 5 away from the cell assembly 3, that is, between the condition monitoring layer 5 and the inner wall of the outer shell 1. A gap is reserved between the fireproof layer 62 and the condition monitoring layer 5. The fireproof layer 62 is preferably a fireproof blanket, which has excellent flame penetration blocking ability.

[0037] When the battery cell assembly 3 experiences localized thermal runaway and generates high-temperature, high-pressure gas, the gas first escapes through the positive / negative electrode areas of the battery cell, then sequentially passes through the first vent 41, the second vent 611, the third vent 51, and the explosion-proof valve 121 on the outer casing 1, forming a pressure relief path. This path not only ensures the rapid and controllable discharge of thermal runaway gas, preventing pressure buildup that could lead to casing rupture, but also effectively delays heat conduction to the condition monitoring layer 5 through the heat insulation layer 61, preventing sensor failure; and blocks direct flame attack on the outer casing 1 and the wing body 2 structural components through the fireproof layer 62.

[0038] In alternative implementations, such as Figure 3 As shown, the bracket assembly 4 adopts a split double-layer structure, including an upper bracket 42 and a lower bracket 43 arranged opposite to each other along the axial direction of the battery cell assembly 3; the first end of the battery cell assembly 3 is fixed to the bearing surface of the upper bracket 42 by mechanical fasteners or elastic clamping structure, and the second end is fixed to the bearing surface of the lower bracket 43, thereby realizing rigid constraint and three-dimensional positioning of the two ends of the battery cell assembly 3.

[0039] Both the upper bracket 42 and the lower bracket 43 are equipped with a first vent hole 41 that extends through their thickness direction, and the position of each first vent hole 41 corresponds one-to-one with the positive electrode cover plate area and the negative electrode base area of ​​the corresponding cell in the cell assembly 3; when any cell experiences thermal runaway and generates high temperature and high pressure gas, the gas can be discharged through the first vent hole 41 of the upper bracket 42 and the lower bracket 43 respectively, forming a bidirectional cooperative pressure relief path.

[0040] In alternative implementations, such as Figure 4 As shown, the outer shell 1 adopts a dual-duct conformal envelope structure. Its overall shape is not adapted to the inner wall of a single curved duct, but precisely matches the contour of the shared structural area between two adjacent curved ducts, and further extends to cover the fan-shaped annular inner wall area enclosed by the geometric central axis of the two adjacent curved ducts from one end of each adjacent curved duct near the shared area. In other words, the outer shell 1 is a "Y"-shaped three-dimensional shell, with both ends extending to the geometric central axis of the two adjacent curved ducts, achieving high-density filling of the complex space inside the wing.

[0041] In this structure, the condition monitoring layer 5 and the protection component 6 are no longer symmetrically arranged on both sides of the cell assembly 3, but are integrated together on one side of the cell assembly 3 along the axial direction.

[0042] In alternative implementations, such as Figure 5As shown, the protective component 6 includes a thermally conductive layer 63, a liquid cooling plate 64, and a substrate 65; wherein: The thermally conductive layer 63 may include thermally conductive adhesive, one side of which is tightly attached to the opposite side of the substrate 65 facing the cell assembly 3, and the other side is tightly attached to the liquid cooling plate 64; the liquid cooling plate 64 is a plate with embedded microchannels, and its internal channels are connected to the airborne thermal management system of the aircraft, configured to circulate and transport cooling medium to achieve continuous temperature control. Furthermore, the battery cell assembly 3 is disposed on the side of the substrate 65 away from the heat-conducting layer 63. The positive and negative electrodes of each battery cell in the battery cell assembly 3 are arranged on the side close to the substrate 65. The substrate 65 is provided to provide a mounting base for the liquid cooling plate 64, and at the same time, the heat of the battery cell assembly 3 is transferred to the liquid cooling plate 64 through the heat-conducting layer 63 to achieve heat dissipation of the battery cell assembly 3.

[0043] In addition, the condition monitoring layer 5 can be installed on the side of the liquid cooling plate 64 away from the heat conduction layer 63, so that the liquid cooling plate 64 can not only cool the battery cell assembly 3, but also cool the components in the condition monitoring layer 5.

[0044] The above-described embodiment forms a multi-level thermal management structure from bottom to top, consisting of a battery cell assembly 3, a substrate 65, a thermally conductive layer 63, a liquid cooling plate 64, and a condition monitoring layer 5, which can effectively ensure that the components in the battery cell assembly 3 and the condition monitoring layer 5 operate in a suitable temperature environment.

[0045] In alternative implementations, such as Figure 5 As shown, the support assembly 4 includes a single-sided support 44 connected to the cell assembly 3. The single-sided support 44 is provided with a first vent 41, and the position of the first vent 41 corresponds to the positive or negative terminal of each cell unit in the cell assembly 3.

[0046] The side surface of the single-sided bracket 44 facing the cell assembly 3 is fixedly connected to one end or side wall of the cell assembly 3 by mechanical fasteners or adhesive structures.

[0047] The aforementioned single-sided bracket design simplifies the internal structural hierarchy of the module and provides more space in the thickness direction, facilitating the installation of the liquid cooling plate 64 and thereby accelerating the heat dissipation of the cell assembly 3 and the status monitoring layer 5.

[0048] Based on the above-described embodiments, such as Figure 3 and Figure 5 As shown, the outer casing 1 includes an upper cover 11 and a lower casing 12 connected to the upper cover 11, and an explosion-proof valve 121 is disposed in the lower casing 12.

[0049] The upper cover 11 is a rigid cover plate with an arc-shaped curved surface profile, and the bottom surface of the lower housing 12 is provided with a mounting bracket. The bracket has countersunk bolt holes for rigidly connecting the entire battery module to the wing spars of the wing body 2 by bolts.

[0050] The outer shell 1 is made of flame-retardant ABS (Acrylonitrile Butadiene Styrene) + glass fiber, with a thickness of 2-3mm.

[0051] A second aspect of the present invention provides a wing, such as Figure 1 and Figure 6 As shown, the wing provided in the second aspect of the present invention includes a wing body 2 and the aforementioned battery module; the wing body 2 includes a skin 21 and a wing spars (not shown in the figure) connected to the skin 21. The wing spars have multiple interconnected arc-shaped ducts. The skin 21 is provided with air inlets and outlets 211 that communicate with each arc-shaped duct. The air inlets and outlets 211 are located between two adjacent arc-shaped ducts. Each arc-shaped duct contains a battery module, or a battery module is provided between every two adjacent arc-shaped ducts.

[0052] The above-described implementation utilizes the unused space of the curved duct to deploy the energy system, upgrading the wing from a purely aerodynamic component into an energy carrier. Furthermore, the air inlets and outlets 211 on the skin 21 are connected to the curved duct, forming not only a pressure relief channel but also enabling the cooling of the battery modules using airflow. This not only improves the space utilization of the wing body 2 and the safety of the battery modules but also enhances the overall stability and operational performance of the aircraft. Specifically, multiple battery modules within each wing body 2 are connected in series with other modules and BDU (Battery Distribution Unit) located inside the fuselage via high-voltage connectors and high-voltage wiring harnesses or via busbars (outerly wrapped with insulating sleeves) to form a battery pack; a sampling board 7 (slave controller) is placed between every two battery modules to collect voltage and temperature information of the two modules, and is connected to the main controller via low-voltage wiring harnesses. The main controller module is located inside the fuselage.

[0053] After multiple battery modules are combined into a module, high voltage is output to the outside through BDU, and low voltage wiring harness is used to interact with the battery management system.

[0054] like Figure 7 As shown, a swing plate 212 is provided at the air inlet / outlet 211 of the skin 21, and there is a certain gap between the outer periphery of the swing plate 212 and the skin 21; a fixed shaft 213 is provided on the inner side of the skin 21, and a support frame 2121 that rotates with the fixed shaft 213 is provided on the inner side of the swing plate 212; a torsion spring 214 is sleeved on the fixed shaft 213, one leg of the torsion spring 214 abuts against the inner surface of the skin 21, and the other leg abuts against the inner surface of the swing plate 212, so that the top of the swing plate 212 abuts against the limiting block 215 of the skin 21 under the action of the torsion spring.

[0055] During use, once the flight reaches a certain speed, the external airflow can overcome the elastic force of the torsion spring 214, causing the lower end of the swing plate 212 to flip inward toward the skin 21 and the upper end of the swing plate 212 to flip outward toward the skin 21, thereby opening the air inlet / outlet 211. External airflow can enter the skin 21 through the air inlet / outlet 211 on the lower side of the swing plate 212, and airflow inside the skin 21 can exit the skin 21 through the air inlet / outlet 211 on the upper side of the swing plate 212.

[0056] A third aspect of the present invention provides an aircraft comprising the aforementioned battery module or comprising two of the aforementioned wings.

[0057] The aircraft provided by the third aspect of the present invention has the battery module provided by the first aspect of the present invention or the wing provided by the second aspect of the present invention, thereby having all the beneficial effects of the battery module provided by the first aspect of the present invention or the wing provided by the second aspect of the present invention.

[0058] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. A battery module, characterized by, include: The outer shell (1) is equipped with an explosion-proof valve (121), and the outer shell (1) is configured to be installed inside the wing body (2); The battery cell assembly (3) and the bracket assembly (4) are installed inside the housing (1). The battery cell assembly (3) is connected to the bracket assembly (4). The bracket assembly (4) is provided with a first vent (41) at the positive and negative terminals of the battery cell assembly (3) and is connected to the explosion-proof valve (121). A status monitoring layer (5) and a protective component (6) are installed inside the housing (1), the status monitoring layer (5) and the protective component (6) are located on at least one side of the cell assembly (3), the status monitoring layer (5) is configured to detect the operating status of the cell assembly (3), and the protective component (6) is configured to suppress the spread of thermal runaway of the battery module.

2. The battery module of claim 1, wherein, The shape of the outer shell (1) is adapted to the inner wall of the single arc-shaped duct of the wing body (2), and the status monitoring layer (5) and the protective component (6) are located on both sides of the battery cell assembly (3).

3. The battery module of claim 2, wherein, The protective component (6) includes a heat insulation layer (61) and a fireproof layer (62). The heat insulation layer (61) is located between the support assembly (4) and the status monitoring layer (5), and the fireproof layer (62) is located between the status monitoring layer (5) and the outer shell (1). The heat insulation layer (61) is provided with a second exhaust hole (611) that is opposite to and communicates with the first exhaust hole (41), and the status monitoring layer (5) is provided with a third exhaust hole (51) that is opposite to and communicates with the second exhaust hole (611).

4. The battery module of claim 2, wherein, The bracket assembly (4) includes an upper bracket (42) and a lower bracket (43). One end of the battery cell assembly (3) is connected to the upper bracket (42), and the other end of the battery cell is connected to the lower bracket (43). Both the upper bracket (42) and the lower bracket (43) are provided with the first exhaust hole (41).

5. The battery module of claim 1, wherein, The shape of the outer shell (1) is adapted to the inner wall surface of the common area between two adjacent arc-shaped ducts of the wing body (2) and the inner wall surface of one end of the two arc-shaped ducts adjacent to the common area to their own central axis. The status monitoring layer (5) and the protective component (6) are both located on one side of the battery cell assembly (3).

6. The battery module according to claim 5, characterized in that, The protective component (6) includes a thermally conductive layer (63), a liquid cooling plate (64), and a substrate (65). The thermally conductive layer (63) is located between one side of the substrate (65) and the liquid cooling plate (64), and the battery cell assembly (3) is located on the other side of the substrate (65).

7. The battery module according to claim 5, characterized in that, The bracket assembly (4) includes a single-sided bracket (44) connected to the cell assembly (3), and the single-sided bracket (44) is provided with the first vent hole (41).

8. The battery module according to any one of claims 1-7, characterized in that, The outer casing (1) includes an upper cover (11) and a lower casing (12) connected to the upper cover (11), and the lower casing (12) is provided with the explosion-proof valve (121).

9. A wing, characterized in that, Includes the wing body (2) and multiple battery modules as described in any one of claims 1-8; The wing body (2) includes a skin (21) and a wing spars connected within the skin (21). The wing spars have multiple interconnected arc-shaped ducts. The skin (21) is provided with air inlets and outlets (211) that communicate with each of the arc-shaped ducts. The air inlets and outlets (211) are located between two adjacent arc-shaped ducts. Each of the arc-shaped ducts contains one battery module, or one battery module is provided between every two adjacent arc-shaped ducts.

10. An aircraft, characterized in that, It includes the battery module as described in any one of claims 1-8, or includes two wings as described in claim 9.

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