Battery pack suitable for flight equipment and flight equipment

Abstract

The utility model relates to the technical field of batteries, in particular to a battery pack suitable for flight equipment and the flight equipment, the battery pack comprises a battery box body and a battery, the battery is arranged in the battery box body, the battery box body is provided with a top plate and a bottom plate, and one of the top plate and the bottom plate faces the flight equipment. A through hole is formed in the other one of the top plate and the bottom plate, and the battery part is exposed out of the through hole; a protective plate is arranged on the side, back on to the battery, of the other one of the top plate and the bottom plate, an airflow channel is formed between the protective plate and the other one of the top plate and the bottom plate, the protective plate is provided with an opening, and the airflow channel is communicated with the opening and the through hole; and the battery pack is configured to allow external airflow to flow to the area, exposed out of the through hole, of the battery through the opening, the airflow channel and the through hole.

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] Flying equipment (such as flying cars, etc.) is required to be as light as possible under operating conditions. However, existing flying equipment uses a battery pack solution without thermal management, which only relies on the temperature rise of the battery to absorb the heat of the battery. However, due to the high battery discharge rate and high temperature rise during operation, there is a risk of overheating of the battery. 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 provide a battery pack suitable for flight equipment that meets the heat dissipation requirements.

[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 flying equipment is provided, wherein: it comprises a battery case and a battery, the battery being arranged in the battery case, the battery case having a top plate and a bottom plate, one of the top plate and the bottom plate facing the flying equipment, the other of the top plate and the bottom plate being provided with a through hole, and the battery being partially exposed in the through hole; a protective plate is provided on the side of the other of the top plate and the bottom plate facing away from the battery, an air flow channel is formed between the protective plate and the other of the top plate and the bottom plate, the protective plate being provided with an opening, and the air flow channel being connected to the opening and the through hole respectively; wherein the battery pack is configured to allow external air flow to flow through the opening, the air flow channel and the through hole to the area of ​​the battery exposed in the through hole.

[0006] In order to achieve the above purpose, the utility model adopts the following technical solutions:

[0007] According to another aspect of the utility model, a battery pack suitable for flight equipment is provided, which includes a battery box and a battery, wherein the battery box has a load-bearing wall and multiple side walls, wherein the load-bearing wall is a wall surface of the battery box away from the flight equipment, and one end of the multiple side walls is respectively connected to the other end of the load-bearing wall to jointly enclose a box opening of the battery box, wherein the box opening faces the flight equipment, and the flight equipment closes the box opening, wherein the battery is arranged in the battery box and fixed to the load-bearing wall, wherein the load-bearing wall is provided with a through hole, wherein the battery is partially exposed in the through hole, and wherein the through hole is used for allowing external airflow to flow to the area of ​​the battery exposed in the through hole; wherein a protective plate is provided on the side of the load-bearing wall facing away from the battery, wherein an airflow channel is formed between the protective plate and the load-bearing wall, wherein the protective plate is provided with an opening, and wherein the airflow channel is respectively connected to the opening and the through hole, wherein the battery pack is configured to allow external airflow to flow to the area of ​​the battery exposed in the through hole via the opening, the airflow channel and the through hole.

[0008] 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:

[0009] The battery box of the battery pack suitable for flight equipment proposed by the utility model includes a top plate and a bottom plate, one of which faces the flight equipment, and the other of which (or the bearing wall) is provided with a through hole, and the battery part is exposed in the through hole. A protective plate is provided on the side of the other of the top plate and the bottom plate facing away from the battery, and an air flow channel is formed between the protective plate and the other of the top plate and the bottom plate, and the protective plate is provided with an opening, and the air flow channel is connected to the opening and the through hole respectively, and the external air flow flows through the opening, the air flow channel and the through hole to the area of ​​the battery exposed in the through hole. Through the above-mentioned structural design, the utility model can use the protective plate to provide a protection function for the battery, and use the opening provided on the protective plate and the through hole provided on the battery box to realize the heat exchange between the external air flow and the battery, thereby realizing better structural protection function and heat dissipation function at the same time, and is particularly suitable for the application needs of flight equipment.

[0010] 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.

[0011] In order to achieve the above purpose, the utility model adopts the following technical solutions:

[0012] 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.

[0013] 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:

[0014] The flying device proposed in the utility model can simultaneously achieve better structural protection function and heat dissipation function by adopting the battery pack suitable for the flying device proposed in the utility model, thereby ensuring the safety and reliability of the flying device. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] 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:

[0016] Figure 1 is a schematic diagram of a three-dimensional structure of a battery pack suitable for flight equipment according to an exemplary embodiment;

[0017] Figure 2 yes Figure 1 A perspective exploded schematic diagram of a battery pack suitable for flight equipment is shown;

[0018] Figure 3 yes Figure 1 A bottom view of a battery pack suitable for use in flight equipment is shown;

[0019] Figure 4 is along Figure 3 The cross-sectional view made by the straight line AA in;

[0020] Figure 5 yes Figure 4 An enlarged schematic diagram of part B in FIG.

[0021] Figure 6 is a schematic structural diagram of a flying device according to an exemplary embodiment.

[0022] The following are the descriptions of the reference numerals:

[0023] 100. Battery packs suitable for flight equipment;

[0024] 110. Battery box;

[0025] 111. Bottom plate;

[0026] 1111.Through hole;

[0027] 112. Guard plate;

[0028] 1121. Open your mouth;

[0029] 1122. bulge;

[0030] 1123. Groove;

[0031] 120.Battery;

[0032] 121. Explosion-proof valve;

[0033] 200. Car body;

[0034] H. Height;

[0035] P. Airflow channel;

[0036] X. First direction;

[0037] Y. Second direction;

[0038] Z. Third direction. DETAILED DESCRIPTION

[0039] 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.

[0040] 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.

[0041] 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.

[0042] like Figures 1 to 5 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 bottom view of a battery pack 100 suitable for use in flight equipment is representatively shown; Figure 4 The representative diagram shows the Figure 3 The cross-sectional view made by the straight line AA in; Figure 5 A representative example is shown in Figure 4 The enlarged schematic diagram of the B 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.

[0043] like Figures 1 to 5 As shown, in one embodiment of the present invention, the battery pack 100 for a flying device proposed by the present invention includes 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 and a 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 is provided with a through hole 1111, and the battery 120 is partially exposed in the through hole 1111. A protective plate 112 is provided on the side of the bottom plate 111 facing away from the battery 120, and an airflow channel P is formed between the protective plate 112 and the bottom plate 111. Among them, the protective plate 112 is provided with an opening 1121, and the airflow channel P is connected to the opening 1121 and the through hole 1111 respectively. Accordingly, the battery pack can allow external airflow to flow through the opening 1121, the airflow channel P and the through hole 1111 to the area of ​​the battery 120 exposed to the through hole 1111. Through the above structural design, the utility model can use the protective plate 112 to provide protection for the battery 120, and use the opening 1121 provided on the protective plate 112 and the through hole 1111 provided on the battery box 110 to achieve heat exchange between the external airflow and the battery 120, thereby achieving better structural protection function and heat dissipation function at the same time, and is particularly suitable for the application needs of flight equipment.

[0044] It should be noted that in some embodiments of the present invention, still taking the flying device as a flying car as an example, the battery box 110 can also be installed on the top of the flying car body 200 via its bottom plate 111. In this case, the through hole 1111 can be opened on the top plate of the battery box 110, and the protective plate 112 can be set on the side of the top plate facing away from the battery 120. In other words, in various possible embodiments consistent with the design concept of the present invention, the battery box 110 is installed on the flying device via one of the top plate and the bottom plate 111, the other of the top plate and the bottom plate 111 is provided with a through hole 1111, the battery 120 is partially exposed in the through hole 1111, the other of the top plate and the bottom plate 111 is provided with a protective plate 112 on the side facing away from the battery 120, and an airflow channel P is formed between the protective plate 112 and the other of the top plate and the bottom plate 111.

[0045] It should be noted that, taking the bottom plate 111 provided with the through hole 1111 as an example, at this time, the top plate of the battery box 110 may not have a direct connection relationship with the body 200 of the flying car, for example, it may be connected to the bottom of the body 200 through the side wall of the battery box 110 through other connection structures. In some embodiments, when the through hole is provided on the top plate, the bottom plate 111 of the battery box 110 may not have a direct connection relationship with the body 200 of the flying car, for example, it may be connected to the top of the body 200 through the side wall of the battery box 110 through other connection structures (such as a hoisting structure, etc.). In other words, in various possible embodiments consistent with the design concept of the utility model, one of the top plate and the bottom plate 111 faces the flying device, and the other of the top plate and the bottom plate 111 (i.e., the one facing away from the flying device) is provided with a through hole. On this basis, the battery box 110 is installed on the flying device, but it is not limited to the position of the battery box 110 itself and the type of connection structure through which the battery box 110 is installed with the flying device.

[0046] like Figures 1 to 3 As shown, in one embodiment of the utility model, the openings 1121 can be arranged in pairs on the guard plate 112. Among them, at least one pair of openings 1121 can be respectively located at the two ends of the guard plate 112 corresponding to the front and rear directions of the flight equipment. In other words, the two ends of the guard plate 112 corresponding to the front and rear directions of the flight equipment can be respectively provided with two openings 1121 in the same pair. Through the above-mentioned structural design, the utility model can form convection of the external airflow entering and exiting the airflow channel P through the openings 1121. At the same time, since the air intake resistance of the flight equipment along the front and rear directions is smaller during flight, the wind speed of the external airflow entering the airflow channel P through the openings 1121 can be accelerated, thereby further improving the heat exchange effect. In some embodiments, at least one pair of openings 1121 may be located at the two ends of the guard plate 112 corresponding to the left and right directions of the flight equipment. Furthermore, the guard plate 112 may be provided with at least two pairs of openings 1121, and at least one pair of openings 1121 is located at the two ends of the guard plate 112 corresponding to the front and rear directions of the flight equipment, and at least another pair of openings 1121 is located at the two ends of the guard plate 112 corresponding to the left and right directions of the flight equipment. This embodiment is not limited thereto. Figures 1 to 3As shown, based on the structural design of the openings 1121 arranged in pairs, in one embodiment of the present invention, for at least one pair of openings 1121, for example, a pair of openings 1121 respectively located at the two ends of the guard plate 112 corresponding to the front and rear directions of the flight equipment as shown in the accompanying drawings, the relative arrangement direction of the two openings 1121 included in the pair is a first direction X (for example, the front and rear direction of the flight equipment), and at least another pair of openings 1121 may be arranged at intervals in a second direction Y (for example, the left and right direction of the flight equipment) perpendicular to the first direction X and parallel to the guard plate 112. Through the above structural design, the present invention can increase the air volume of the external airflow entering and exiting the airflow channel P through the openings 1121, and can make the heat exchange effect of the external airflow on the batteries 120 at different positions more uniform.

[0047] like Figure 5 As shown, in one embodiment of the present invention, the guard plate 112 has a protrusion 1122 protruding away from the battery 120 (i.e., away from the bottom plate 111), and a groove 1123 is formed at a position corresponding to the protrusion 1122 on one side surface of the guard plate 112 facing the battery 120 (i.e., on one side surface facing the bottom plate 111). On this basis, the opening 1121 of the guard plate 112 can be arranged at the groove wall of the groove 1123. Through the above structural design, the present invention can form the above-mentioned airflow channel P by using the groove 1123 and the bottom plate 111, and at the same time, arranging the opening 1121 at the groove wall of the groove 1123 can facilitate the inflow and outflow of external airflow. In addition, the present invention can enhance the structural strength of the guard plate 112 by using the design of the protrusion 1122 and the groove 1123, and at the same time, facilitate the formation of the wall surface (i.e., the groove wall of the groove 1123) on which the opening 1121 is arranged.

[0048] Based on the structural design that the guard plate 112 has the protrusion 1122 and the groove 1123 and the opening 1121 is disposed on the groove wall of the groove 1123, in one embodiment of the utility model, the protrusion 1122 and the groove 1123 can be formed by integrally stamping the guard plate 112. In some embodiments, the guard plate 112 can also be formed with the protrusion 1122 and the groove 1123 by other processes, which are not limited to this embodiment.

[0049] Based on the structural design of the groove wall of the guard plate 112 having the protrusion 1122 and the groove 1123 and the opening 1121 being arranged in the groove 1123, in one embodiment of the present utility model, for the convenience of distinction and description, the groove wall provided with the opening 1121 is referred to as the target groove wall below, and for any target groove wall, the sum of the areas of the openings 1121 arranged thereon may account for 10% to 80% of the area of ​​the target groove wall, such as 10%, 12%, 15%, 65%, 70%, 80%, etc. It should be noted that the sum of the areas of the above-mentioned openings 1121 refers to the sum of the areas of all the openings 1121 opened on a target groove wall, and of course does not limit the specific number of the openings 1121 opened by the target groove wall, that is, it may be one, or two or more. Since the size of the opening 1121 is related to the volume of the external airflow entering the airflow channel P through the opening 1121, through the above structural design, the utility model can avoid the opening 1121 being too small and causing insufficient air intake, thereby ensuring that the heat exchange needs are met, and at the same time, it can avoid the opening 1121 being too large and reducing the structural strength of the guard plate 112. In some embodiments, for any target slot wall, the sum of the areas of the openings 1121 set thereon may account for less than 10% of the area of ​​the target slot wall, or may be greater than 80%, such as 9.9%, 80.1%, etc., and is not limited to this embodiment.

[0050] Based on the structural design that the sum of the areas of the openings 1121 accounts for 10% to 80% of the area of ​​the target groove wall, in one embodiment of the utility model, for any target groove wall, the sum of the areas of the openings 1121 arranged thereon may further account for 20% to 60% of the area of ​​the target groove wall, for example, 20%, 25%, 30%, 40%, 50%, 60%, etc.

[0051] like Figure 5 As shown, in one embodiment of the present invention, the relative arrangement direction of the top plate and the bottom plate 111 is defined as the third direction Z. In the third direction Z, the height H of the airflow channel P is 3 mm to 30 mm, such as 3 mm, 5 mm, 10 mm, 15 mm, 20 mm, 25 mm, 30 mm, etc. Since the larger the airflow channel P (for example, the size of the cross-sectional area determined by the height H), it is related to the amount of air entering the airflow channel P through the opening 1121. Through the above structural design, the present invention can avoid the excessive space occupation caused by the excessive height H of the airflow channel P, and avoid the temperature of the battery 120 facing the guard plate 112 being too low, resulting in a large temperature difference of the battery 120. In some embodiments, the height H of the airflow channel P can also be less than 3 mm, or can be greater than 30 mm, such as 2.9 mm, 30.5 mm, etc., and is not limited to this embodiment.

[0052] In one embodiment of the utility model, the battery pack 100 suitable for flight equipment proposed by the utility model may also include a shielding member, which is movably arranged at the opening 1121, and the shielding member can adjustably shield the opening 1121. Among them, the battery pack can control the opening and closing and the size of the opening of the shielding member according to at least one of the temperature and wind speed (such as the speed or the relative wind speed of the outside world, etc.). Through the above-mentioned structural design, the utility model can adaptively adjust the heat exchange function according to the temperature of the battery 120 and the flight state of the flight equipment, so that the function of introducing external airflow for heat exchange using the opening 1121 and the through hole 1111 is more flexible.

[0053] like Figure 5 As shown, in one embodiment of the present invention, the explosion-proof valve 121 of the battery 120 can be located on the side surface of the battery 120 facing the guard plate 112 (i.e., facing the bottom plate 111), and the explosion-proof valve 121 is arranged to overlap at least partially with 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 121 through the through hole 1111 when the battery 120 has thermal runaway, reduce or avoid blocking the high-temperature material, improve the spraying effect of the explosion-proof valve 121, and ensure safety.

[0054] In one embodiment of the present invention, a surface of the battery 120 facing the protective plate 112 (i.e., facing the bottom plate 111) may be provided with an anti-corrosion layer. Since the battery 120 is directly connected to the outside world via the through hole 1111, the airflow channel P, and the opening 1121, the present invention can prevent water vapor in the air from entering the battery box 110 through the above structural design. In particular, when the battery 120 is a cylindrical battery 120 with an exposed steel shell, the present invention can avoid the problem that the shell of the battery 120 is easily corroded when it is exposed for a long time, thereby extending the service life of the battery 120.

[0055] Based on the structural design that the surface of the battery 120 facing the protective plate 112 is provided with an anti-corrosion layer, in one embodiment of the present utility model, the thermal conductivity of the material of the anti-corrosion layer can be 0.5W / (m·K) to 3.0W / (m·K), such as 0.5W / (m·K), 0.7W / (m·K), 1.0W / (m·K), 1.5W / (m·K), 2.0W / (m·K), 3.0W / (m·K), etc. Through the above structural design, the present utility model can ensure that the anti-corrosion layer has a certain heat conduction effect, avoid the anti-corrosion layer blocking heat exchange, and further improve the heat exchange effect between the battery 120 and the external airflow.

[0056] Based on the structural design that an anti-corrosion layer is provided on the surface of the battery 120 facing the protective plate 112, in one embodiment of the utility model, the anti-corrosion layer can be made of a material with better insulation performance, so that the anti-corrosion layer has an insulation function.

[0057] Based on the structural design that the battery 120 is provided with an anti-corrosion layer on one side of the protective plate 112, in one embodiment of the present invention, the anti-corrosion layer may be a coating formed by spraying an anti-corrosion material on the surface of the battery 120. For example, the anti-corrosion material may be an epoxy spray material or the like.

[0058] like Figure 2 As shown, in one embodiment of the utility model, the battery 120 can be a cylindrical battery, and the cylindrical battery includes two circular end faces and a side surface connected between the two end faces, and the two end faces are respectively facing the top plate and the bottom plate 111. Among them, since the flight equipment requires a longer endurance, the energy density of the battery pack is required to be higher. In the existing batteries using a ternary system, the nickel content of the battery is required to be higher (for example, the nickel content is greater than 60%), that is, more than 6 series, and even needs to reach 9 series, in order to meet the energy density requirements of the flight equipment. Of course, an increase in energy density also means an increase in the risk of thermal runaway. In this regard, cylindrical batteries have the characteristics of small size and the capacity of a single battery 120 is lower than that of other types of batteries (such as square shell batteries). Therefore, by using cylindrical batteries, the utility model can further reduce the risk of thermal runaway.

[0059] It should be noted that Figures 1 to 5In 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 wall 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 slot-shaped structure. Specifically, the battery box 110 has a bearing wall and a plurality of side walls. The bearing wall is the wall surface of the battery box 110 away from the flight equipment. One end of the plurality of side walls is respectively connected to the bearing wall, and the other end together encloses the box opening of the battery box 110 (i.e., the slot of the slot-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 equipment, the fuselage (or vehicle body 200, etc.) of the flight equipment 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 equipment, the fuselage (or vehicle body 200, etc.) of the flight equipment is connected to the box opening at the bottom of the battery box 110 and serves as the bottom plate of the battery box 110. On this basis, an airflow channel P is formed between the guard plate 112 and the bearing wall, and the guard plate 112 is provided with an opening 1121, and the airflow channel P is connected to the opening 1121 and the through hole 1111 respectively. The battery pack can allow external airflow to flow through the opening 1121, the airflow channel P and the through hole 1111 to the area of ​​the battery 120 exposed to the through hole 1111.

[0060] It should be noted that, taking the case where the battery box 110 is a trough-shaped structure and the bottom plate 111 is provided with a through hole 1111 as an example, at this time, the top of the battery box 110 may not have a direct connection relationship with the body 200 of the flying car, for example, it may be connected to the bottom of the body 200 through the side wall of the battery box 110 through other connection structures (such as a hoisting structure, etc.), and thereby ensure that the flying car closes the box opening at the bottom. In some embodiments, when the battery box 110 is a trough-shaped structure and the through hole is provided on the top plate, the bottom of the battery box 110 may not have a direct connection relationship with the body 200 of the flying car, for example, it may be connected to the top of the body 200 through the side wall of the battery box 110 through other connection structures, and thereby ensure that the flying car closes the box opening at the top. In other words, in various possible embodiments that conform to the design concept of the utility model, the box opening of the battery box 110 faces the flying device, and a through hole is opened on the side facing away from the flying device. On this basis, the battery box 110 is installed on the aircraft, but it is not limited to the position of the battery box 110 and the connection structure through which it is installed on the aircraft.

[0061] It should be noted that the battery packs for flight equipment shown in the drawings and described in this specification are only a few examples of the 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 packs for flight equipment shown in the drawings or described in this specification.

[0062] In summary, the battery box 110 of the battery pack 100 suitable for the flight equipment proposed in the utility model includes a top plate and a bottom plate 111, one of which faces the flight equipment, and the other of which (or the bearing wall) is provided with a through hole 1111, and the battery 120 is partially exposed in the through hole 1111. A protective plate 112 is provided on the side of the other of which faces away from the battery 120, and an airflow channel P is formed between the protective plate 112 and the other of which, the protective plate 112 is provided with an opening 1121, and the airflow channel P is respectively connected with the opening 1121 and the through hole 1111, and the external airflow flows through the opening 1121, the airflow channel P and the through hole 1111 to the area of ​​the battery 120 exposed in the through hole 1111. Through the above-mentioned structural design, the utility model can utilize the protective plate 112 to provide a protection function for the battery 120, and utilize the opening 1121 set in the protective plate 112 and the through hole 1111 set in the battery box 110 to realize heat exchange between the external airflow and the battery 120, thereby realizing better structural protection function and heat dissipation function at the same time, and is particularly suitable for the application needs of flight equipment.

[0063] 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.

[0064] See also Figure 6 , Figure 6 The 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 a protective plate 112 is provided on the side of the bottom plate 111 facing away from the battery 120. In some embodiments, the battery pack 100 suitable for the flying device may also be arranged on the top of the vehicle body 200, then the through hole 1111 is provided on the top plate of the battery box 110, and a protective plate 112 is provided on the side of the top plate facing away from the battery 120.

[0065] 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.

[0066] 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 simultaneously achieve better structural protection function and heat dissipation function, thereby ensuring the safety and reliability of the flight equipment.

[0067] 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.

[0068] 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 and a bottom plate, one of the top plate and the bottom plate faces the flight device, and the other of the top plate and the bottom plate is provided with a through hole, and the battery is partially exposed in the through hole; A guard plate is provided on the side of the other of the top plate and the bottom plate facing away from the battery, an air flow channel is formed between the guard plate and the other of the top plate and the bottom plate, the guard plate is provided with an opening, and the air flow channel is respectively connected with the opening and the through hole; The battery pack is configured to allow external airflow to flow through the opening, the airflow channel and the through hole to the area of ​​the battery exposed to the through hole.

2. The battery pack suitable for flight equipment according to claim 1, characterized in that: The openings are arranged in pairs; wherein: At least one pair of the openings are respectively located at two ends of the guard plate in the front and rear directions of the flight equipment; and / or At least one pair of the openings is located at two ends of the guard plate in the left and right directions corresponding to the flying equipment.

3. The battery pack suitable for flight equipment according to claim 2, characterized in that: For at least one pair of the openings, the relative arrangement direction of the two openings is taken as a first direction, and at least another pair of the openings are arranged at intervals in a second direction perpendicular to the first direction and parallel to the guard plate.

4. The battery pack suitable for flight equipment according to claim 1, characterized in that: The guard plate has a protrusion protruding away from the battery, and a groove is formed on a surface of one side of the guard plate facing the battery corresponding to the position of the protrusion; wherein the opening is arranged on a groove wall of the groove.

5. The battery pack suitable for flight equipment according to claim 4, characterized in that: The groove wall provided with the openings is a target groove wall. For any target groove wall, the sum of the areas of the openings provided thereon accounts for 10% to 80% of the area of ​​the target groove wall.

6. The battery pack suitable for flight equipment according to claim 5, characterized in that: For any one of the target groove walls, the sum of the areas of the openings arranged thereon accounts for 20% to 60% of the area of ​​the target groove wall.

7. The battery pack suitable for flight equipment according to claim 1, characterized in that: The relative arrangement direction of the top plate and the bottom plate is defined as a third direction. In the third direction, the height of the airflow channel is 3 mm to 30 mm.

8. The battery pack suitable for flight equipment according to claim 1, characterized in that: It also includes a shielding member, which is movably disposed on the opening to adjustably shield the opening.

9. The battery pack suitable for flight equipment according to claim 1, characterized in that: The explosion-proof valve of the battery is located on a side surface of the battery facing the guard plate, and the explosion-proof valve is arranged to at least partially overlap with the through hole.

10. The battery pack suitable for flight equipment according to claim 1, characterized in that: An anti-corrosion layer is arranged on a surface of one side of the battery facing the guard plate.

11. The battery pack suitable for flight equipment according to claim 10, characterized in that: The thermal conductivity of the material of the anti-corrosion layer is 0.5W / (m·K) to 3.0W / (m·K).

12. The battery pack suitable for flight equipment according to claim 10, characterized in that: The anti-corrosion layer is a coating formed by spraying an anti-corrosion material on the surface of the battery.

13. The battery pack suitable for flight equipment according to claim 1, characterized in that: The battery is a cylindrical battery, which includes two circular end faces and a side face connected between the two end faces, and the two end faces face the top plate and the bottom plate respectively.

14. A battery pack suitable for flight equipment, characterized in that: The invention comprises a battery box and a battery, wherein the battery box has a bearing wall and a plurality of side walls, wherein the bearing wall is a wall surface of the battery box away from the flight device, wherein one end of the plurality of side walls is respectively connected to the bearing wall, and the other ends of the plurality of side walls are jointly enclosed to form a box opening of the battery box, wherein the box opening faces the flight device, and the flight device closes the box opening, wherein the battery is arranged in the battery box and fixed to the bearing wall, wherein the bearing wall is provided with a through hole, wherein a portion of the battery is exposed in the through hole, and wherein the through hole is used for allowing external airflow to flow to a region of the battery exposed in the through hole; A guard plate is provided on the side of the bearing wall facing away from the battery, an air flow channel is formed between the guard plate and the bearing wall, the guard plate is provided with an opening, and the air flow channel is respectively connected with the opening and the through hole; The battery pack is configured to allow external airflow to flow through the opening, the airflow channel and the through hole to the area of ​​the battery exposed to the through hole.

15. A flying device, characterized in that: A battery pack suitable for flight equipment comprising any one of claims 1 to 14.

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