Aircraft with battery fused airframe

Abstract

The invention relates to an aircraft with a battery fused airframe. The aircraft comprises at least one section of battery fusion aircraft body, and the battery fusion aircraft body is of an aircraft body and battery integrated structure; the machine body battery integrated structure comprises a machine body frame, an outer coating layer, an inner coating layer and an inner battery storage layer arranged in the machine body frame; the inner-layer battery storage layer comprises a plurality of battery cabins divided by the machine body frame and battery packs stored in the battery cabins; the outer coating covers the outer side of the machine body frame, and the inner coating covers the inner side of the machine body frame. According to the technical scheme, the airplane with the battery fusion airplane body has the following beneficial technical effects that the battery bearing capacity of the electric propulsion airplane body can be improved, and the carrying capacity of the electric propulsion airplane is not limited.

Description

Technical Field

[0001] The invention relates to an aircraft with a battery-fused body, and belongs to the field of overall aircraft design. Background Art

[0002] Using lithium batteries and other power batteries as the energy source of aircraft is one of the future directions of the development of civil aircraft products. As the energy density of power batteries increases year by year, the use of aviation fuel can be reduced every year by providing energy to aircraft through batteries to drive aircraft, reducing carbon emissions in the civil aviation industry, achieving the goal of high efficiency and energy saving, and making resources recycled and reused.

[0003] However, there are still many unresolved issues with electric-propulsion aircraft. Since the current energy density of lithium batteries is still a certain distance away from aircraft demand, the required layout space on the aircraft is also larger than that of traditional aircraft. The wing space originally used for fuel storage is relatively narrow, making it difficult to store large-scale lithium batteries, and daily disassembly and maintenance will also be affected. At present, most plans for electric-propulsion aircraft are to place lithium batteries directly in the cabin or cargo hold, but this will further limit the carrying capacity of electric-propulsion aircraft. Summary of the invention

[0004] An object of the present invention is to provide an aircraft with a battery-fused fuselage that can overcome at least some of the defects of the prior art, increase the battery capacity of the electric-propulsion aircraft fuselage, and not limit the carrying capacity of the electric-propulsion aircraft.

[0005] The above object of the present invention is achieved by an aircraft with a battery-fused airframe, the aircraft comprising at least one section of a battery-fused airframe, the battery-fused airframe being an airframe-battery integrated structure;

[0006] The body-battery integrated structure comprises a body frame, an outer covering layer, an inner covering layer and an inner battery storage layer arranged in the body frame;

[0007] The inner battery storage layer includes a plurality of battery compartments divided by the body frame, and battery packs stored in the battery compartments;

[0008] The outer cover covers the outer side of the body frame, and the inner cover covers the inner side of the body frame.

[0009] According to the above technical scheme, the aircraft with a battery-fused fuselage of the present invention can achieve the following beneficial technical effects: it can increase the battery capacity of the electric-propelled aircraft fuselage and does not limit the carrying capacity of the electric-propelled aircraft.

[0010] Preferably, the battery fusion body is distributed on the wings, tail wing and / or straight sections of the fuselage.

[0011] According to the above technical scheme, the aircraft with a battery-fused body of the present invention can achieve the following beneficial technical effects: by adopting a battery-fused body, the battery is integrated with the body structure such as the wing, tail and / or straight fuselage to increase the total battery capacity.

[0012] Preferably, positive electrode slide rails and negative electrode slide rails are respectively provided on opposite sides of the battery compartment, and the battery pack is provided with sliders at its four corners, namely two positive electrode sliders and two negative electrode sliders, the positive electrode slider is used to be mounted on the positive electrode slide rail, and the negative electrode slider is used to be mounted on the negative electrode slide rail.

[0013] According to the above technical solution, the aircraft with battery fusion body of the present invention can achieve the following beneficial technical effects: the batteries in a single battery compartment are connected in parallel, and the batteries in different battery compartments can be connected in series or in parallel as needed. The conductive slide rails with slide grooves installed at both ends of the battery compartment can not only help connect the batteries, but also play a role in fixing the batteries.

[0014] Preferably, the shapes of the slideways in the positive electrode slide rail and the negative electrode slide rail are different, and correspondingly, the shapes of the positive electrode slider and the negative electrode slider are also different.

[0015] According to the above technical solution, the aircraft with a battery-fused body of the present invention can achieve the following beneficial technical effects: the above design is a fool-proof design to avoid reverse connection of the positive and negative poles when loading the battery pack.

[0016] Preferably, each slider includes a plurality of ball assemblies, each ball assembly is disposed in a corresponding groove of the slider, each ball assembly includes a ball, a ball bracket and a spring damper, the ball bracket is connected to the bottom of the corresponding groove of the slider through the spring damper, the ball is located on the ball bracket and at least partially extends out of the corresponding groove of the slider to maintain contact with the corresponding slide rail.

[0017] According to the above technical solution, the aircraft with a battery-fused body of the present invention can achieve the following beneficial technical effects: it can ensure that the slider maintains contact with the corresponding slide rail, thereby reducing friction during sliding.

[0018] Preferably, the positive electrode slide rail is provided with a positive electrode rail on its contact surface with the battery pack, and the battery pack is provided with a positive electrode conductive spring sheet at a corresponding position, and the positive electrode conductive spring sheet extends outward under its own elasticity to maintain contact with the positive electrode rail, and the positive electrodes of all batteries in the battery pack are uniformly connected to the positive electrode conductive spring sheet;

[0019] The negative electrode slide rail is provided with a negative electrode rail on its contact surface with the battery pack, and the battery pack is provided with a negative electrode conductive spring sheet at a corresponding position. The negative electrode conductive spring sheet extends outward under its own elastic action to maintain contact with the negative electrode rail, and the negative electrodes of all batteries in the battery pack are uniformly connected to the negative electrode conductive spring sheet.

[0020] According to the above technical solution, the aircraft with a battery-fused body of the present invention can achieve the following beneficial technical effects: it can ensure good electrical connection between the battery pack and the conductive rail.

[0021] Preferably, the inner cover is provided with an inspection port connected to the battery compartment for loading or removing the battery pack, and the size of the inspection port is slightly larger than the size of the battery pack.

[0022] According to the above technical scheme, the aircraft with a battery-fused body of the present invention can achieve the following beneficial technical effects: it can facilitate the loading and unloading of batteries and is also conducive to daily repair and maintenance work; it can meet the basic structural strength requirements of the battery compartment and facilitate the loading and unloading of batteries.

[0023] Preferably, at the inspection port, a group of mounting notches is provided on the slide rail, one group of mounting notches corresponds to the four sliders of the battery pack, and the size of the mounting notches is slightly larger than the size of the sliders.

[0024] According to the above technical solution, the aircraft with a battery-fused body of the present invention can achieve the following beneficial technical effects: it can facilitate the mounting and removal of battery packs.

[0025] Preferably, adjacent battery packs are kept connected in sequence via a hook assembly, which includes a limiting hook arranged at one end of the battery pack and a fixed hook arranged at the other end of the battery pack. When adjacent battery packs are connected, the limiting hook of one battery pack is inserted into the fixed hook of another adjacent battery pack.

[0026] According to the above technical solution, the aircraft with a battery-fused body of the present invention can achieve the following beneficial technical effects: it can facilitate keeping adjacent battery packs connected in sequence.

[0027] Preferably, each battery pack also includes a limit hook mounting seat and a limit hook spring, and the limit hook is installed on the limit hook mounting seat with the help of the limit hook spring; the battery pack is inserted into the inspection port, and when the limit hook of the battery pack is not connected to the fixed hook, the limit hook extends out of the surface of the battery pack and the inspection port by relying on the spring force provided by the limit hook spring.

[0028] According to the above technical solution, the aircraft with a battery-fused body of the present invention can achieve the following beneficial technical effects: the battery pack can be limited when necessary to prevent the battery pack from directly sliding into the depths of the battery compartment. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Figure 1 It is a partial cross-sectional view of an aircraft with a battery-fused body according to an embodiment of the present invention.

[0030] Figure 2 It is a partial longitudinal sectional view of an aircraft with a battery-fused body according to an embodiment of the present invention.

[0031] Figure 3 It is a front view schematic diagram of a slide rail slider of an aircraft with a battery-fused body according to an embodiment of the present invention.

[0032] Figure 4 It is a top view schematic diagram of a slide rail slider of an aircraft with a battery-fused body according to an embodiment of the present invention.

[0033] Figure 5A It is a schematic diagram of a ball bearing assembly in a positive electrode slider of an aircraft with a battery integrated into a body according to an embodiment of the present invention.

[0034] Figure 5B It is a schematic diagram of a ball bearing assembly in a negative electrode slider of an aircraft with a battery integrated into a body according to an embodiment of the present invention.

[0035] Figure 6 It is an enlarged schematic diagram of a ball bearing assembly of an aircraft with a battery-fused body according to an embodiment of the present invention.

[0036] Figure 7 It is a schematic diagram of the positive electrical connection of an aircraft with a battery integrated into the body according to an embodiment of the present invention.

[0037] Figure 8 It is a schematic structural diagram of an inspection port of an aircraft with a battery-fused body according to an embodiment of the present invention.

[0038] Fig.9A It is a left side schematic diagram of an ear assembly of an aircraft with a battery integrated body according to an embodiment of the present invention.

[0039] Fig. 9B It is a front view schematic diagram of an aircraft ear assembly with a battery integrated body according to an embodiment of the present invention.

[0040] Fig. 10A It is a front view schematic diagram of adjacent battery packs mounted on an aircraft with a battery-fused body according to an embodiment of the present invention.

[0041] Fig. 10B It is a top view schematic diagram of adjacent battery packs mounted on an aircraft with a battery-fused body according to an embodiment of the present invention.

[0042] Reference numerals list

[0043] 1: outer covering;

[0044] 2: Inner battery storage layer;

[0045] 3: Inner covering;

[0046] 4: Body frame;

[0047] 5: Battery compartment;

[0048] 6: Battery pack;

[0049] 7: Inspection port;

[0050] 11: positive slide rail;

[0051] 12: Negative slide rail;

[0052] 13: Positive rail;

[0053] 14: positive electrode conductive spring;

[0054] 15: Mounting gap;

[0055] 21: positive electrode slider;

[0056] 22: negative electrode slider;

[0057] 23: ball assembly;

[0058] 24: groove;

[0059] 25: ball bearing;

[0060] 26: ball bracket;

[0061] 27: Spring damper;

[0062] 31: limit hanging ear;

[0063] 32: Fixed mounting ear;

[0064] 33: Limiting ear mounting seat;

[0065] 34: Limiting ear spring. DETAILED DESCRIPTION

[0066] The specific embodiments of the present invention will be described below. It should be noted that in the specific description of these embodiments, in order to be concise and clear, this specification cannot provide a detailed description of all the features of the actual embodiments. It should be understood that in the actual implementation of any embodiment, just as in the process of any engineering project or design project, in order to achieve the specific goals of the developer and to meet system-related or business-related restrictions, various specific decisions are often made, and this will also change from one embodiment to another. In addition, it can also be understood that although the efforts made in this development process may be complex and lengthy, for ordinary technicians in the field related to the content disclosed by the present invention, some changes in design, manufacturing or production based on the technical content disclosed in this disclosure are just conventional technical means, and should not be understood as insufficient content of this disclosure.

[0067] Unless otherwise defined, the technical or scientific terms used in the claims and the specification shall have the usual meaning understood by persons with ordinary skills in the technical field to which the invention belongs. The words "first", "second" and similar words used in the patent application specification and the claims of the present invention do not indicate any order, quantity or importance, but are only used to distinguish different components. "One" or "one" and other similar words do not indicate a quantitative limitation, but indicate the existence of at least one. "Include" or "comprises" and other similar words mean that the elements or objects appearing before "include" or "comprises" include the elements or objects listed after "include" or "comprises" and their equivalent elements, and do not exclude other elements or objects. "Connected" or "connected" and other similar words are not limited to physical or mechanical connections, nor are they limited to direct or indirect connections.

[0068] In the following description, in order to clearly show the structure and working mode of the present invention, many directional words will be used for description, but the words "front", "back", "left", "right", "outside", "inside", "outward", "inward", "up", "down", etc. should be understood as convenient terms and should not be understood as restrictive terms.

[0069] Figure 1 It is a partial cross-sectional view of an aircraft with a battery-fused body according to an embodiment of the present invention. Figure 2 FIG. 1 is a partial longitudinal section of an aircraft with a battery-fused body according to an embodiment of the present invention. Figure 1 - Figure 2 As shown, an aircraft with a battery-fused airframe according to an embodiment of the present invention comprises at least one section of a battery-fused airframe, and the battery-fused airframe is an airframe-battery integrated structure;

[0070] The body battery integrated structure includes a body frame 4, an outer cover layer 1, an inner cover layer 3 and an inner battery storage layer 2 arranged in the body frame 4;

[0071] The inner battery storage layer 2 includes a plurality of battery compartments 5 divided by the body frame 4 (for example, the body frame 4 is circumferentially divided into X equal battery compartments according to actual conditions), and battery packs 6 stored in the battery compartments 5;

[0072] The outer cover 1 covers the outer side of the body frame 4 , and the inner cover 3 covers the inner side of the body frame 4 .

[0073] According to the above technical scheme, the aircraft with a battery-fused fuselage of the present invention can achieve the following beneficial technical effects: it can increase the battery capacity of the electric-propelled aircraft fuselage and does not limit the carrying capacity of the electric-propelled aircraft.

[0074] Specifically, the battery is integrated into the fuselage to integrate the battery with the fuselage, wing, tail and other fuselage structures to increase the total battery capacity. Taking the straight section fusion fuselage as an example, the straight section of the aircraft fuselage is relatively long and the cabin section is relatively large; a battery layout space is set on the inside of the straight section fuselage, and the upper and lower arc-shaped fuselage frames are divided into X-equal battery compartments along the circumferential direction according to actual conditions, so that it has space for arranging multiple battery packs and increasing the power battery capacity.

[0075] In some embodiments, the battery fusion body is distributed on the wing, tail and / or straight fuselage. The outer covering 1 can be similar to the traditional fuselage structure, for example, it can be the outer covering at the straight fuselage, or it can be the outer covering at the wing part, or the outer covering at the tail part. Therefore, the battery fusion body is adopted to integrate the battery with the body structure such as the wing, tail and / or straight fuselage, so as to increase the total battery capacity.

[0076] Figure 3 It is a front view schematic diagram of a slide rail slider of an aircraft with a battery-fused body according to an embodiment of the present invention. Figure 4 FIG. 1 is a schematic top view of a slide rail of an aircraft with a battery-integrated body according to an embodiment of the present invention. Figure 3 - Figure 4 As shown, a positive electrode slide rail 11 and a negative electrode slide rail 12 are respectively provided on opposite sides of the battery compartment 5. The extension direction of the slide rail is the length direction of the fuselage. The battery pack 6 is provided with sliders at its four corners, namely two positive electrode sliders 21 and two negative electrode sliders 22. The positive electrode slider 21 is used to be mounted on the positive electrode slide rail 11, and the negative electrode slider 22 is used to be mounted on the negative electrode slide rail 12.

[0077] In some embodiments, Figure 3 - Figure 4As shown, the shapes of the slideways in the positive slide rail 11 and the negative slide rail 12 are different, and accordingly the shapes of the positive slider 21 and the negative slider 22 are also different. The above design is a foolproof design to avoid reverse connection of the positive and negative electrodes when loading the battery pack.

[0078] Figure 5A It is a schematic diagram of a ball bearing assembly in a positive electrode slider of an aircraft with a battery integrated into a body according to an embodiment of the present invention. Figure 5B It is a schematic diagram of a ball bearing assembly in a negative electrode slider of an aircraft with a battery integrated into a body according to an embodiment of the present invention. Figure 6 FIG. 1 is an enlarged schematic diagram of a ball bearing assembly of an aircraft having a battery-fused body according to an embodiment of the present invention. Figure 5A - Figure 6 As shown, each slider includes a plurality of ball assemblies 23, each ball assembly 23 is arranged in a corresponding groove 24 of the slider, each ball assembly 23 includes a ball 25, a ball bracket 26 and a spring damper 27, the ball bracket 26 (for example, a movable bracket) is connected to the bottom of the corresponding groove 24 of the slider through the spring damper 27, the ball 25 is located on the ball bracket 26 and at least partially extends out of the corresponding groove 24 of the slider (that is, extends out of the slider) to maintain contact with the corresponding slide rail to reduce friction during sliding.

[0079] Preferably, at least four contact surfaces in different directions of each slider are provided with ball assemblies 23 , so that the slider cooperates with the slide rail only through the ball assemblies 23 .

[0080] Figure 7 FIG. 1 is a schematic diagram of the electrical connection of the positive electrode of an aircraft with a battery-fused body according to an embodiment of the present invention. Figure 7 As shown, the positive electrode slide rail 11 is provided with a positive electrode rail 13 (at least partially exposed) on its contact surface with the battery pack 6, and the battery pack 6 is provided with a positive electrode conductive spring 14 at a corresponding position. The positive electrode conductive spring 14 extends outward under its own elastic action to maintain contact with the positive electrode rail 13, and the positive electrodes of all batteries in the battery pack 6 are uniformly connected to the positive electrode conductive spring 14.

[0081] Similarly, the negative electrode slide rail 12 is provided with a negative electrode rail on its contact surface with the battery pack 6, and the battery pack 6 is provided with a negative electrode conductive spring clip at the corresponding position. The negative electrode conductive spring clip extends outward under its own elastic action to maintain contact with the negative electrode rail, and the negative electrodes of all batteries in the battery pack 6 are uniformly connected to the negative electrode conductive spring clip.

[0082] Preferably, the positive rail 13 is a continuous conductive metal strip extending from the starting end to the end of the positive slide rail 11; the positive conductive springs 14 of all battery packs mounted on the positive slide rail 11 are electrically connected to the positive rail 13, and the positive rail 13 is led out at the starting end or the end as the total positive pole of the battery compartment.

[0083] Figure 8 FIG. 1 is a schematic diagram of the structure of the inspection port of an aircraft with a battery-integrated body according to an embodiment of the present invention. Figure 8 As shown, the inner cover 3 is provided with an inspection port 7 connected to the battery compartment 5 for loading or removing the battery pack 6. Preferably, as Figure 8 As shown, the size of the inspection port 7 is slightly larger than the size of the battery pack 6. It should be noted that "the size of the inspection port 7 is slightly larger than the size of the battery pack 6" means that the size of the inspection port 7 is 100-110% of the size of the battery pack 6. Since the internal space of the battery compartment 5 is relatively narrow, and based on the basic structural strength requirements, the opening of the inner covering should not be too large. Therefore, an inspection port 7 with an appropriate area can facilitate the loading and unloading of the battery and is also conducive to daily repair and maintenance work. Preferably, Figure 8 As shown, each battery compartment 5 has only one inspection opening 7 .

[0084] Specifically, multiple battery packs 6 can be mounted in a battery compartment 5, but due to actual technical limitations, only a few inspection ports 7 (the locations for loading and removing batteries) can generally be set (preferably only one), and after the battery pack 6 is loaded through the inspection port 7, it needs to be pushed along the slide rail to the deep end of the battery compartment; when a battery pack 6 fails, the nearest battery pack 6 must also be taken out from the inspection port 7 in turn, and then the battery pack 6 at the deep end must be moved closer to the inspection port 7 until the faulty battery pack 6 is taken out.

[0085] In some embodiments, Figure 8 As shown, at the inspection port 7, a group of mounting notches 15 are provided on the slide rail, and a group of mounting notches 15 correspond to the four sliders of the battery pack 6, and the size of the mounting notches 15 is slightly larger than the size of the slider. It should be noted that "the size of the mounting notch 15 is slightly larger than the size of the slider" here means that the size of the mounting notch 15 is 100-110% of the size of the slider. Therefore, after the battery pack 6 is inserted from the mounting notch 15, it can be pushed along the slide rail into the depth of the battery compartment 5. Similarly, when disassembling the battery pack 6, pull the battery pack 6 to the mounting notch 15 and then take it out.

[0086] Fig.9A It is a left side schematic diagram of an ear assembly of an aircraft with a battery integrated body according to an embodiment of the present invention. Fig. 9B It is a front view schematic diagram of an aircraft ear assembly with a battery integrated body according to an embodiment of the present invention. Fig. 10A It is a front view schematic diagram of adjacent battery packs mounted on an aircraft with a battery-fused body according to an embodiment of the present invention. Fig. 10B FIG. 1 is a top view schematic diagram of adjacent battery packs mounted on an aircraft with a battery-fused body according to an embodiment of the present invention. Fig.9A - Fig. 10BAs shown, adjacent battery packs 6 are connected in sequence through a hook assembly, and the hook assembly includes a limiting hook 31 arranged at one end of the battery pack 6 and a fixed hook 32 arranged at the other end of the battery pack 6. When adjacent battery packs 6 are connected, the limiting hook 31 of one battery pack 6 is inserted into the fixed hook 32 of another adjacent battery pack 6.

[0087] In some embodiments, Fig.9A - Fig. 10B As shown, each battery pack 6 further includes a limiting lug mounting seat 33 and a limiting lug spring 34, and the limiting lug 31 is mounted on the limiting lug mounting seat 33 by means of the limiting lug spring 34; when the battery pack 6 is loaded into the inspection port 7, the limiting lug 31 of the battery pack 6, when not connected to the fixed lug 32, extends out of the surface of the battery pack 6 and the inspection port 7 by means of the spring force provided by the limiting lug spring 33. Therefore, the limiting lug 31 will abut against the edge of the inner cover 3 at the inspection port 7, and the battery pack 6 can be prevented from directly sliding into the deep of the battery compartment 5. When the limiting lug 31 overcomes the force of the limiting lug spring 34 and is pressed down, the loaded battery pack 6 can move to the deep of the battery compartment 5.

[0088] It should be noted that the battery compartment 5 should be kept away from necessary structures such as aircraft doors and windows.

[0089] The innovative features of the aircraft with battery fusion body of the present invention are mainly as follows:

[0090] (1) The power battery used in the present invention is a structural fusion battery, which integrates the battery with the fuselage, wing, tail and other body structures to increase the total battery capacity. Taking the straight section fusion fuselage as an example, the straight section of the aircraft fuselage is relatively long and the cabin section is relatively large; a battery layout space is set on the inner side of the straight section fuselage, and the upper and lower arc-shaped fuselage frames are divided into X equal parts of battery compartments along the circumferential direction according to actual conditions, so that it has space to arrange multiple battery packs, thereby increasing the power battery capacity. Therefore, more battery packs can be arranged, the battery layout space is increased, and the total battery capacity is increased.

[0091] (2) The batteries in a single battery compartment are connected in parallel, and the batteries in different battery compartments can be connected in series or in parallel as needed. The conductive rails with slide grooves installed at both ends of the battery compartment can not only help connect the batteries, but also play a role in fixing the batteries.

[0092] (3) As the internal space of the battery compartment is relatively narrow and based on the basic structural strength requirements, the inner cover opening should not be too large. Therefore, an inspection port with an appropriate area can not only facilitate the loading and unloading of the battery, but also facilitate daily repair and maintenance work.

[0093] (4) The specially designed battery pack mounting structure of the present invention can facilitate mounting and removing the battery pack, and can facilitate keeping adjacent battery packs connected in sequence, and can also limit the battery pack when necessary to prevent the battery pack from sliding directly into the depth of the battery compartment.

[0094] The above describes the specific embodiments of the present invention, but those skilled in the art will understand that the above specific embodiments do not constitute a limitation of the present invention. Those skilled in the art can make various modifications based on the above disclosure without exceeding the scope of the present invention.

Claims

1. An aircraft with a battery-fused body, characterized in that: The aircraft comprises at least one section of battery-fused airframe, wherein the battery-fused airframe is an airframe-battery integrated structure; The body-battery integrated structure comprises a body frame, an outer covering layer, an inner covering layer and an inner battery storage layer arranged in the body frame; The inner battery storage layer includes a plurality of battery compartments divided by the body frame, and battery packs stored in the battery compartments; The outer cover covers the outer side of the body frame, and the inner cover covers the inner side of the body frame.

2. The aircraft with a battery-fused body according to claim 1, characterized in that: The battery fusion body is distributed on the wings, tail wing and / or straight section of the fuselage.

3. The aircraft with battery fusion body according to claim 1, characterized in that: Positive electrode slide rails and negative electrode slide rails are respectively arranged on opposite sides of the battery compartment, and sliders are respectively arranged at the four corners of the battery pack, which are two positive electrode slide rails and two negative electrode slide rails. The positive electrode slide rails are used to be mounted on the positive electrode slide rails, and the negative electrode slide rails are used to be mounted on the negative electrode slide rails.

4. The aircraft with a battery-fused body as claimed in claim 3, characterized in that: The shapes of the slideways in the positive electrode slide rail and the negative electrode slide rail are different, and accordingly, the shapes of the positive electrode slider and the negative electrode slider are also different.

5. The aircraft with battery fusion body according to claim 3, characterized in that: Each slider includes a plurality of ball assemblies, each of which is disposed in a corresponding groove of the slider, and each of which includes a ball, a ball bracket and a spring damper. The ball bracket is connected to the bottom of the corresponding groove of the slider through the spring damper, and the ball is located on the ball bracket and at least partially extends out of the corresponding groove of the slider to maintain contact with the corresponding slide rail.

6. The aircraft with a battery-fused body as claimed in claim 3, characterized in that: The positive electrode slide rail is provided with a positive electrode rail on the contact surface between the positive electrode slide rail and the battery pack, and the battery pack is provided with a positive electrode conductive spring at a corresponding position. The positive electrode conductive spring extends outward under its own elasticity to maintain contact with the positive electrode rail, and the positive electrodes of all batteries in the battery pack are uniformly connected to the positive electrode conductive spring; The negative electrode slide rail is provided with a negative electrode rail on its contact surface with the battery pack, and the battery pack is provided with a negative electrode conductive spring sheet at a corresponding position. The negative electrode conductive spring sheet extends outward under its own elastic action to maintain contact with the negative electrode rail, and the negative electrodes of all batteries in the battery pack are uniformly connected to the negative electrode conductive spring sheet.

7. The aircraft with battery fusion body according to claim 3, characterized in that: The inner cover is provided with an inspection port connected to the battery compartment for loading or removing the battery pack, and the size of the inspection port is slightly larger than the size of the battery pack.

8. The aircraft with battery fusion body according to claim 7, characterized in that: At the inspection port, a group of mounting notches is arranged on the slide rail, and the group of mounting notches corresponds to the four sliders of the battery pack, and the size of the mounting notches is slightly larger than the size of the sliders.

9. The aircraft with a battery-fused body as claimed in claim 8, characterized in that: Adjacent battery packs are kept connected in sequence through a hook assembly, which includes a limiting hook arranged at one end of the battery pack and a fixed hook arranged at the other end of the battery pack. When the adjacent battery packs are connected, the limiting hook of one battery pack is inserted into the fixed hook of another adjacent battery pack.

10. The aircraft with battery fusion body according to claim 9, characterized in that: Each battery pack also includes a limit hook mounting seat and a limit hook spring, and the limit hook is installed on the limit hook mounting seat with the help of the limit hook spring; the battery pack is inserted into the inspection port, and when the limit hook of the battery pack is not connected to the fixed hook, the limit hook extends out of the surface of the battery pack and the inspection port by relying on the spring force provided by the limit hook spring.

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