Battery pack suitable for flight equipment and flight equipment
By designing the exposed areas between the battery box and the battery case in the flight equipment battery pack, the problem of difficulty in meeting the battery heat dissipation and connection strength in the prior art is solved, and significant improvement in heat dissipation performance and fixed sealing effect are achieved.
Patent Information
- Application Number
- CN202421063856.9
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-05-15
- Publication Date
- 2025-02-21
- Estimated Expiration
- 2034-05-15
AI Technical Summary
In the design of existing flight equipment battery packs, it is difficult to meet the requirements of battery heat dissipation and battery connection strength at the same time.
A battery pack is designed, wherein the battery box is installed on the flight equipment through one of the top plate and the bottom plate, and the other part is provided with a through hole. The top and bottom walls of the battery case are exposed to the through holes, and the area of the exposed area accounts for 10% to 85% of the total area.
Through this design, the fixation and sealing between the battery and the battery box is ensured, and the heat dissipation performance of the battery is improved.
Smart Images
Figure CN222514984U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of batteries, and in particular to a battery pack suitable for flight equipment and the flight equipment. Background Art
[0002] In the existing design of battery packs for flying equipment (such as flying cars, etc.), through holes are provided on the bottom plate of the battery box to achieve heat dissipation of the battery. However, the size of the through hole will affect the heat exchange effect it can provide and the connection strength between the battery and the battery box. The design of the through hole area in the existing solution is difficult to meet the above two requirements at the same time. Utility Model Content
[0003] A main purpose of the present invention is to overcome at least one defect of the above-mentioned prior art and to provide a battery pack suitable for flight equipment that takes into account both the heat exchange effect and the connection strength between the battery and the battery box.
[0004] In order to achieve the above purpose, the utility model adopts the following technical solutions:
[0005] According to one aspect of the utility model, a battery pack suitable for flight equipment is provided, wherein: it includes a battery box and a battery, the battery is arranged in the battery box, the battery box has a top plate, a bottom plate and a plurality of side plates connected between the bottom plate and the bottom plate, the battery box is installed on the flight equipment via one of the top plate and the bottom plate, and the other of the top plate and the bottom plate is provided with a through hole; the shell of the battery has a top wall, a bottom wall and a side wall connected between the top wall and the bottom wall, the top wall and the bottom wall face the top plate and the bottom plate respectively, and one of the top wall and the bottom wall is partially exposed in the through hole; wherein one of the top wall and the bottom wall has an exposed area, the exposed area is an area having a positive projection of the through hole, and for one battery, the area of the exposed area accounts for 10% to 85% of the area of one of the top wall and the bottom wall.
[0006] Another main purpose of the present invention is to overcome at least one defect of the above-mentioned prior art and to provide a battery pack and flight equipment suitable for flight equipment that have better heat exchange performance and meet insulation requirements.
[0007] In order to achieve the above purpose, the utility model adopts the following technical solutions:
[0008] According to another aspect of the utility model, a battery pack suitable for flight equipment is provided, wherein: it comprises a battery box and a battery, the battery is arranged in the battery box, the battery box has a load-bearing plate and a plurality of side plates, the load-bearing plate is a wall surface of the battery box away from the flight equipment, the load-bearing plate is provided with a through hole, one end of a plurality of side plates are respectively connected to the load-bearing plate, and the other ends are jointly enclosed to form a box opening of the battery box, the battery box is connected to the flight equipment via the box opening, and the flight equipment closes the box opening; the shell of the battery has two end walls and a side wall connected between the two end walls, the two end walls are respectively facing the load-bearing wall and the box opening, and one of the end walls is partially exposed in the through hole; wherein the end wall exposed in the through hole has an exposed area, the exposed area is an area having a positive projection of the through hole, and for one battery, the area of the exposed area accounts for 10% to 85% of the area of the end wall exposed in the through hole.
[0009] It can be seen from the above technical solutions that the advantages and positive effects of the battery pack suitable for flight equipment proposed by the utility model are:
[0010] The battery box of the battery pack suitable for flight equipment proposed by the utility model is installed on the flight equipment via one of the top plate and the bottom plate, and the other one is provided with a through hole. One of the top wall and the bottom wall of the battery housing is partially exposed in the through hole, and the area of the one with the positive projection of the through hole is the exposed area. For a battery, the exposed area accounts for 10% to 85% of the area of the one. Through the above-mentioned structural design, the utility model can avoid the area of the exposed area being too large, thereby ensuring that there is enough connection space between the battery and the battery box, ensuring the fixation and sealing between the battery and the battery box, and at the same time, it can avoid the area of the exposed area being too small, thereby ensuring that there is enough outside air to contact and exchange heat with the exposed area of the battery through the through hole, ensuring a significant improvement in the heat exchange performance of the battery.
[0011] Another main purpose of the present invention is to overcome at least one defect of the above-mentioned prior art and provide a flying device using the above-mentioned battery pack suitable for flying devices.
[0012] In order to achieve the above purpose, the utility model adopts the following technical solutions:
[0013] According to another aspect of the present invention, a flying device is provided, which includes the battery pack suitable for the flying device proposed in the present invention.
[0014] It can be seen from the above technical solutions that the advantages and positive effects of the flying device proposed by the utility model are:
[0015] The flying device proposed in the utility model can ensure the fixation and sealing between the battery and the battery box, and at the same time can ensure a significant improvement in the heat exchange performance of the battery, by adopting the battery pack suitable for the flying device proposed in the utility model. BRIEF DESCRIPTION OF THE DRAWINGS
[0016] The various objects, features and advantages of the present invention will become more apparent by considering the following detailed description of the preferred embodiments of the present invention in conjunction with the accompanying drawings. The accompanying drawings are only exemplary illustrations of the present invention and are not necessarily drawn to scale. In the accompanying drawings, the same reference numerals always represent the same or similar parts. Among them:
[0017] Figure 1 is a schematic diagram of a three-dimensional structure of a battery pack according to an exemplary embodiment;
[0018] Figure 2 yes Figure 1 A three-dimensional exploded schematic diagram of a battery pack is shown;
[0019] Figure 3 yes Figure 1 A three-dimensional exploded schematic diagram of a partial structure of a battery pack is shown;
[0020] Figure 4 yes Figure 1 A bottom view of the battery pack is shown;
[0021] Figure 5 is along Figure 4 The cross-sectional view made by the straight line BB in;
[0022] Figure 6 yes Figure 5 An enlarged schematic diagram of part D in FIG.
[0023] Figure 7 It is a schematic structural diagram of a flying device according to an exemplary embodiment.
[0024] The following are the descriptions of the reference numerals:
[0025] 100. Battery packs suitable for flight equipment;
[0026] 110. Battery box;
[0027] 111. Bottom plate;
[0028] 1111.Through hole;
[0029] 120.Battery;
[0030] 121. Bottom wall;
[0031] 1211. Revealed area;
[0032] 122. Explosion-proof valve;
[0033] 200. Car body. DETAILED DESCRIPTION
[0034] Typical embodiments that embody the features and advantages of the present invention will be described in detail in the following description. It should be understood that the present invention can have various changes in different embodiments without departing from the scope of the present invention, and the descriptions and drawings therein are essentially for illustrative purposes rather than for limiting the present invention.
[0035] In the following description of different exemplary embodiments of the utility model, reference is made to the accompanying drawings, which form a part of the utility model and in which different exemplary structures, systems and steps that can implement multiple aspects of the utility model are shown by way of example. It should be understood that other specific schemes of components, structures, exemplary devices, systems and steps can be used, and structural and functional modifications can be made without departing from the scope of the utility model. Moreover, although the terms "above", "between", "within", etc. can be used in this specification to describe different exemplary features and elements of the utility model, these terms are used herein only for convenience, such as according to the direction of the examples described in the accompanying drawings. Nothing in this specification should be construed as requiring a specific three-dimensional orientation of the structure to fall within the scope of the utility model.
[0036] The battery pack 100 for flying equipment proposed in the present invention is described by taking the application in a flying car as an example. It is easy for those skilled in the art to understand that in order to apply the relevant design of the present invention to other types of flying equipment, various modifications, additions, substitutions, deletions or other changes are made to the following specific embodiments, and these changes are still within the scope of the principle of the battery pack 100 for flying equipment proposed in the present invention.
[0037] like Figures 1 to 6 As shown, Figure 1 A three-dimensional structural schematic diagram of a battery pack 100 suitable for flight equipment proposed by the present invention is representatively shown in FIG. Figure 2 A three-dimensional exploded schematic diagram of a battery pack 100 suitable for flight equipment is representatively shown in FIG. Figure 3 , a three-dimensional exploded schematic diagram of a partial structure of a battery pack 100 suitable for flight equipment is representatively shown, wherein the three-dimensional exploded structure of the battery 120 and the bottom plate 111 is specifically shown; Figure 4 A bottom view of a battery pack 100 suitable for use in flight equipment is representatively shown; Figure 5 The representative diagram shows the Figure 4 The cross-sectional view made by the straight line BB in;
[0038] Figure 6 A representative example is shown in Figure 5 The enlarged schematic diagram of the D part in FIG. The following will be combined with the above drawings to describe in detail the structure, connection method and functional relationship of the main components of the battery pack 100 suitable for flight equipment proposed by the present invention.
[0039] like Figures 1 to 3 As shown, in one embodiment of the present invention, the battery pack 100 for a flying device proposed by the present invention comprises a battery box 110 and a battery 120. The battery 120 is arranged in the battery box 110, and the battery box 110 has a top plate, a bottom plate 111, and a plurality of side plates connected between the bottom plate 111 and the bottom plate 111. The battery box 110 is installed on the flying device via the top plate. For example, when the flying device is a flying car, the battery box 110 is installed on the bottom of the body 200 of the flying car via the top plate. Among them, the bottom plate 111 of the battery box 110 is provided with a through hole 1111. The shell of the battery 120 has a top wall, a bottom wall 121, and a side wall connected between the top wall and the bottom wall 121. The top wall and the bottom wall 121 of the shell of the battery 120 face the top plate and the bottom plate 111 of the battery box 110 respectively, and the bottom wall 121 is partially exposed in the through hole 1111. On this basis, the bottom wall 121 has an exposed area 1211, which is an area on the bottom wall 121 with a positive projection of the through hole 1111. For a battery 120, the area of the exposed area 1211 accounts for 10% to 85% of the area of the bottom wall 121, such as 10%, 15%, 25%, 50%, 70%, 85%, etc. Through the above structural design, the utility model can avoid the area of the exposed area 1211 being too large, thereby ensuring that there is enough connection space between the battery 120 and the battery box 110, ensuring the fixation and sealing between the battery 120 and the battery box 110, and at the same time, it can avoid the area of the exposed area 1211 being too small, thereby ensuring that there is enough outside air to contact and exchange heat with the exposed area 1211 of the battery 120 through the through hole 1111, ensuring a significant improvement in the heat exchange performance of the battery 120.
[0040] like Figure 3 As shown, in one embodiment of the present invention, the battery 120 may be a cylindrical battery 120, that is, the top wall and the bottom wall 121 of the battery 120 shell are circular. On this basis, the capacity of a battery 120 is defined as C1, and the unit of the capacity is Ah. At the same time, the area of the bottom wall 121 of the battery 120 shell is defined as S1, and the unit of the area is mm. 2, accordingly, the ratio of the capacity of the battery 120 to the area of the bottom wall 121 can satisfy the following numerical range: 0.01≤C1 / S1≤12.5, such as 0.01, 0.05, 1, 2.5, 8, 12.5, etc., and the capacity of the battery 120 and the area of the bottom wall 121 can satisfy the following numerical range: 18Ah≤C1≤50Ah, such as 18Ah, 20Ah, 25Ah, 30Ah, 40Ah, 50Ah, etc., 4mm 2 ≤S1≤1400mm 2 , for example 4mm 2 , 20mm 2 , 100mm 2 , 200mm 2 , 500mm 2 , 800mm 2 , 1000mm 2 , 1200mm 2 、1400mm 2 Etc. Since the larger the capacity of the battery 120, the more heat it generates, and the higher the demand for heat exchange performance, the area of the through hole 1111 can be designed to be larger accordingly. On the contrary, the smaller the capacity of the battery 120, the less heat it generates, and the lower the demand for heat exchange performance, the area of the through hole 1111 can be designed to be smaller accordingly. Accordingly, the utility model can adapt to the capacity range of the existing commonly used cylindrical batteries 120, and on this basis, reasonably design the area ratio of the exposed area 1211 to meet the requirements of heat exchange performance, while avoiding the through hole 1111 from being too large, and ensuring the fixation and sealing of the battery 120 and the battery box 110.
[0041] Based on the structural design of the battery 120 being a cylindrical battery 120, in one embodiment of the present invention, when 18Ah≤C1≤50Ah, and 4mm 2 ≤S1≤1400mm 2 When the ratio of the capacity of the battery 120 to the area of the bottom wall 121 can further satisfy the following numerical range, 0.1≤C1 / S1≤0.8, for example, 0.1, 0.2, 0.3, 0.5, 0.7, 0.8, etc.
[0042] In some other embodiments of the present invention, the battery 120 may also be a square shell battery 120, that is, the top wall and the bottom wall of the battery 120 shell are respectively rectangular. On this basis, the capacity of a battery 120 is defined as C2, and the unit of capacity is Ah, and the area of the bottom wall 121 of the battery 120 shell is defined as S2, and the unit of area is mm 2, accordingly, the ratio of the capacity of the battery 120 to the area of the bottom wall 121 can satisfy the following numerical range: 0.01≤C2 / S2≤4, such as 0.01, 0.05, 0.12, 1, 2, 4, etc., and the capacity of the battery 120 and the area of the bottom wall 121 can satisfy the following numerical range: 100Ah≤C2≤400Ah, such as 100Ah, 150Ah, 200Ah, 250Ah, 300Ah, 400Ah, etc., 100mm 2 ≤S2≤20000mm 2 , for example 100mm 2 , 200mm 2 , 500mm 2 , 1000mm 2 , 2000mm 2 , 5000mm 2 , 10000mm 2 、15000mm 2 , 20000mm 2 Etc. Accordingly, the utility model can adapt to the capacity range of the existing commonly used square shell battery 120, and on this basis reasonably design the area ratio of the exposed area 1211 to meet the requirements of heat exchange performance, while avoiding the through hole 1111 being too large, ensuring the fixation and sealing of the battery 120 and the battery box 110.
[0043] Based on the structural design of the battery 120 as a square shell battery 120, in one embodiment of the present utility model, when 100Ah≤C2≤400Ah, and 100mm 2 ≤S2≤20000mm 2 When the ratio of the capacity of the battery 120 to the area of the bottom wall 121 can further satisfy the following numerical range, 0.2≤C2 / S2≤0.8, for example, 0.2, 0.3, 0.4, 0.5, 0.7, 0.8, etc.
[0044] like Figure 6 As shown, in one embodiment of the present invention, the bottom wall 121 of the battery 120 housing is provided with an explosion-proof valve 122, and the explosion-proof valve 122 is at least partially exposed in the through hole 1111. Through the above structural design, the present invention can facilitate the high-temperature material sprayed out of the explosion-proof valve 122 to be sprayed out through the through hole 1111 when the battery 120 has thermal runaway, thereby reducing or avoiding the blocking of the high-temperature material, improving the spraying effect of the explosion-proof valve 122, and ensuring safety.
[0045] Based on the structural design that the explosion-proof valve 122 of the battery 120 is at least partially exposed in the through hole 1111, in one embodiment of the utility model, the explosion-proof valve 122 can be completely located within the range of the exposed area 1211. Through the above structural design, the utility model can completely avoid the bottom plate 111 from blocking the explosion-proof valve 122 when the valve is opened, further ensuring the safety of the battery pack.
[0046] like Figure 3 As shown, in one embodiment of the present invention, the battery 120 may be a cylindrical battery 120, that is, the top wall and the bottom wall of the battery 120 housing are respectively circular. On this basis, for a battery 120, the area of the exposed area 1211 may account for greater than or equal to 20% of the area of the bottom wall 121, such as 20%, 25%, 30%, 45%, 65%, 85%, etc.
[0047] It should be noted that Figures 1 to 6 In the illustrated embodiment, the battery box 110 of the battery pack is roughly a closed box-shaped structure as an example for explanation, that is, the battery box 110 has a top plate and a bottom plate 111, and of course also includes a side plate connected between the top plate and the bottom plate 111. At this time, the battery box 110 is connected to the flight equipment via one of its top plate and bottom plate 111. In some embodiments of the present invention, different from the above-mentioned structural design, the battery box 110 of the battery pack 100 suitable for the flight equipment proposed by the present invention can also be a trough-shaped structure. Specifically, the battery box 110 has a bearing plate and a plurality of side plates. The bearing plate is the wall surface of the battery box 110 away from the flight equipment. One end of the plurality of side plates is respectively connected to the bearing plate, and the other end together encloses the box opening of the battery box 110 (i.e., the notch of the trough-shaped structure). Accordingly, the battery box 110 is connected to the top or bottom of the flight equipment via the box opening, and the flight equipment closes the box opening of the battery box 110. In other words, when the battery pack is arranged at the bottom of the flight device, the fuselage (or vehicle body 200, etc.) of the flight device is connected to the box opening at the top of the battery box 110 and serves as the top plate of the battery box 110, or, when the battery pack is arranged at the top of the flight device, the fuselage (or vehicle body 200, etc.) of the flight device is connected to the box opening at the bottom of the battery box 110 and serves as the bottom plate 111 of the battery box 110. On this basis, the exposed area 1211 refers to the area of the top wall and the bottom wall 121 of the battery 120 housing that faces the through hole 1111 (that is, the one facing away from the fuselage of the flight device) and has the orthographic projection of the through hole 1111, and the area of the exposed area 1211 accounts for 10% to 80% of the area of the one.
[0048] It should be noted that the battery pack 100 for flight equipment shown in the drawings and described in this specification is only a few examples of many types of battery packs that can adopt the principles of the present invention. It should be clearly understood that the principles of the present invention are by no means limited to any details or any components of the battery pack 100 for flight equipment shown in the drawings or described in this specification.
[0049] In summary, the battery box 110 of the battery pack 100 for flight equipment proposed in the utility model is installed on the flight equipment via one of the top plate and the bottom plate 111, and the other of the top plate and the bottom plate 111 is provided with a through hole 1111. One of the top wall and the bottom wall 121 of the battery 120 housing is partially exposed in the through hole 1111, and the area of the one of the top and the bottom wall 121 having the orthographic projection of the through hole 1111 is the exposed area 1211. For one battery 120, the exposed area 1211 accounts for 10% to 85% of the area of the one of the top and the bottom wall 121. Through the above-mentioned structural design, the utility model can avoid the area of the exposed area 1211 being too large, thereby ensuring that there is sufficient connection space between the battery 120 and the battery case 110, ensuring the fixation and sealing between the battery 120 and the battery case 110, and at the same time can avoid the area of the exposed area 1211 being too small, thereby ensuring that there is enough outside air to contact and exchange heat with the exposed area 1211 of the battery 120 through the through hole 1111, thereby ensuring a significant improvement in the heat exchange performance of the battery 120.
[0050] Based on the above detailed description of several exemplary embodiments of the battery pack 100 applicable to the flight equipment proposed by the present invention, an exemplary embodiment of the flight equipment proposed by the present invention will be described below.
[0051] See also Figure 7 , Figure 7The structural schematic diagram of the flying device proposed in the present invention is representatively shown in FIG. In one embodiment of the present invention, the flying device proposed in the present invention may be, for example, a flying car, which includes a battery pack 100 suitable for the flying device proposed in the present invention and described in detail in the above embodiment. For example, the flying car includes a vehicle body 200, and the battery pack 100 suitable for the flying device is arranged at the bottom of the vehicle body 200, that is, the bottom plate 111 of the battery box 110 is provided with a through hole 1111, and the bottom wall 121 of the battery 120 shell faces the through hole 1111, and the area on the bottom wall 121 having the positive projection of the through hole 1111 is the exposed area 1211, and the area of the exposed area 1211 accounts for 10% to 80% of the area of the bottom wall 121. In some embodiments, the battery pack 100 suitable for flight equipment can also be set on the top of the vehicle body 200, and the through hole 1111 is set on the top plate of the battery box 110, and the top wall of the battery 120 shell faces the through hole 1111, and the area on the top wall with the positive projection of the through hole 1111 is the exposed area 1211, and the area of the exposed area 1211 accounts for 10% to 80% of the area of the top wall.
[0052] It should be noted that the flying devices shown in the drawings and described in this specification are only a few examples of the many flying devices that can adopt the principles of the present invention. It should be clearly understood that the principles of the present invention are by no means limited to any details or any components of the flying devices shown in the drawings or described in this specification.
[0053] In summary, the flight equipment proposed in the present invention, by adopting the battery pack 100 suitable for the flight equipment proposed in the present invention, can ensure the fixation and sealing between the battery 120 and the battery box 110, and at the same time can ensure a significant improvement in the heat exchange performance of the battery 120.
[0054] The above describes and / or illustrates in detail the exemplary embodiments of the battery pack and flight equipment proposed by the utility model. However, the embodiments of the utility model are not limited to the specific embodiments described here. On the contrary, the components and / or steps of each embodiment can be used independently and separately from other components and / or steps described here. Each component and / or each step of an embodiment can also be used in combination with other components and / or steps of other embodiments. When introducing the elements / components / etc. described and / or illustrated here, the terms "one", "one" and "above" are used to indicate the presence of one or more elements / components / etc. The terms "comprising", "including" and "having" are used to indicate the meaning of open inclusion and mean that in addition to the listed elements / components / etc., there may be other elements / components / etc. In addition, the terms "first" and "second" in the claims and the specification are used only as marks and are not numerical restrictions on their objects.
[0055] Although the battery pack and the flight equipment proposed by the present invention are described according to different specific embodiments, those skilled in the art will recognize that the implementation of the present invention can be modified within the spirit and scope of the claims.
Claims
1. A battery pack suitable for flight equipment, characterized in that: The invention comprises a battery box and a battery, wherein the battery is arranged in the battery box, the battery box has a top plate, a bottom plate and a plurality of side plates connected between the bottom plate and the bottom plate, the battery box is installed on the flight equipment via one of the top plate and the bottom plate, and the other of the top plate and the bottom plate is provided with a through hole; The battery housing has a top wall, a bottom wall, and a side wall connected between the top wall and the bottom wall, the top wall and the bottom wall face the top plate and the bottom plate respectively, and one of the top wall and the bottom wall is partially exposed in the through hole; One of the top wall and the bottom wall has an exposed area, which is an area having a positive projection of the through hole. For one battery, the area of the exposed area accounts for 10% to 85% of the area of one of the top wall and the bottom wall.
2. The battery pack suitable for flight equipment according to claim 1, characterized in that: The battery is a cylindrical battery, and the top wall and the bottom wall are circular respectively; wherein the capacity of the battery is defined as C1, and the unit of the capacity is Ah, and the area of one of the top wall and the bottom wall of the battery exposed in the through hole is defined as S1, and the unit of the area is mm 2 , then: 0.01≤C1 / S1≤12.5, and 18Ah≤C1≤50Ah, 4mm 2 ≤S1≤1400mm 2 .
3. The battery pack suitable for flight equipment according to claim 2, characterized in that: 0.1≤C1 / S1≤0.
8.
4. The battery pack suitable for flight equipment according to claim 1, characterized in that: The battery is a square shell battery, and the top wall and the bottom wall are respectively rectangular; wherein the capacity of the battery is defined as C2, and the unit of the capacity is Ah, and the area of one of the top wall and the bottom wall of the battery exposed in the through hole is defined as S2, and the unit of the area is mm 2 , then: 0.01≤C2 / S2≤4, and 100Ah≤C2≤400Ah, 100mm 2 ≤S2≤20000mm 2 .
5. The battery pack suitable for flight equipment according to claim 4, characterized in that: 0.2≤C2 / S2≤0.
8.
6. The battery pack suitable for flight equipment according to claim 1, characterized in that: One of the top wall and the bottom wall of the battery exposed in the through hole is provided with an explosion-proof valve, and the explosion-proof valve is at least partially exposed in the through hole.
7. The battery pack suitable for flight equipment according to claim 6, characterized in that: The explosion-proof valves are all located within the range of the exposed area.
8. The battery pack suitable for flight equipment according to claim 1, characterized in that: The battery is a cylindrical battery, and the top wall and the bottom wall are circular respectively; wherein, for one of the batteries, the exposed area accounts for greater than or equal to 20% of the area of one of the top wall and the bottom wall.
9. A battery pack suitable for flight equipment, characterized in that: The invention comprises a battery box and a battery, wherein the battery is arranged in the battery box, and the battery box has a bearing plate and a plurality of side plates, wherein the bearing plate is a wall surface of the battery box away from the flight device, the bearing plate is provided with a through hole, one end of the plurality of side plates is respectively connected to the bearing plate, and the other ends thereof are jointly enclosed to form a box opening of the battery box, the battery box is connected to the flight device via the box opening, and the flight device closes the box opening; The battery housing has two end walls and a side wall connected between the two end walls, the two end walls face the bearing wall and the box opening respectively, and one of the end walls is partially exposed in the through hole; The end wall exposed in the through hole has an exposed area, which is an area having a positive projection of the through hole. For one battery, the area of the exposed area accounts for 10% to 85% of the area of the end wall exposed in the through hole.
10. A flying device, characterized in that: A battery pack suitable for flight equipment comprising the battery pack according to any one of claims 1 to 9.