Airbody structure and unmanned aerial vehicle

Abstract

The invention provides an airframe structure and an unmanned aerial vehicle. The aircraft body structure comprises an aircraft body, wings, a plurality of containing cavities and a plurality of electric devices, the aircraft body comprises an opening and a cavity, and the opening is formed in the top of the cavity and communicated with the cavity. The wings are arranged on the side portion of the fuselage, and the multiple containing cavities are formed in the fuselage and / or the wings and located on the peripheral sides of the cavities. And a mounting channel for a power supply device to pass through is arranged between the accommodating cavity and the cavity. The plurality of electric devices are correspondingly arranged in the plurality of accommodating cavities. The electric device enters the cavity from the opening and penetrates through the installation channel to be installed in the containing cavity. The body structure reasonably utilizes the cavity structure in the body, ensures the structural strength of the body, and improves the integrity of the body. Meanwhile, hidden installation and horizontal layout of electric parts are achieved, the space occupation of the electric parts in the height direction of the fuselage is reduced, then the installation space of a battery or an oil tank is enlarged, and the endurance and the voyage of the unmanned aerial vehicle are improved.

Description

Technical Field

[0001] The present invention relates to the technical field of installation and arrangement of unmanned aerial vehicle components, and in particular to a body structure and an unmanned aerial vehicle. Background Art

[0002] As an aircraft that can fly autonomously or remotely, drones are widely used in many fields such as aerial photography, surveying and mapping, logistics, agriculture, search and rescue, etc. Drones are small in size, and most of their main equipment is usually installed in the fuselage. The electrical equipment installed in drones, especially small and medium-sized drones, is small in size and large in number. The installation method of such electrical equipment in the fuselage is the traditional cover opening installation method. The traditional cover opening installation method is to open a large cover opening or multiple small cover openings on the fuselage corresponding to the centralized installation area or multiple dispersed installation areas of the electrical equipment, so as to meet the installation and maintenance of electrical components. The structural form of large cover opening or multiple small cover openings will not only destroy the structural strength of the fuselage, but also the electrical components will occupy more installation space and reserved maintenance operation space in the fuselage, reducing the space utilization rate in the fuselage. Summary of the invention

[0003] In view of the above problems existing in the prior art, the present invention provides a body structure and a UAV to improve the technical problem that the installation of electrical components of the existing UAV cannot take into account both the body structure strength and the space utilization.

[0004] To achieve the above-mentioned purpose and other related purposes, the first aspect of the present invention provides a fuselage structure, the fuselage structure includes a fuselage, wings, multiple accommodating cavities and multiple electrical components, the fuselage includes an opening and a cavity, the opening is arranged at the top of the cavity and is connected to the cavity. The wings are arranged on the side of the fuselage, and the multiple accommodating cavities are arranged in the fuselage and / or the wings and are located on the periphery of the cavity. Multiple electrical components are correspondingly arranged in the multiple accommodating cavities. Among them, there is an installation channel between the accommodating cavity and the cavity for the electrical components to pass through. The electrical component enters the cavity from the opening and is installed in the accommodating cavity through the installation channel.

[0005] In one embodiment of the fuselage structure of the present invention, the fuselage structure further comprises a mounting seat for fixedly mounting the electrical device, and the mounting seat is detachably fixedly connected to the fuselage or the wing.

[0006] In one embodiment of the body structure of the present invention, at least one of the accommodating cavities is arranged in the wing, and the mounting seat includes a first mounting seat, and the first mounting seat is detachably fixedly connected to the wing frame of the wing at one end close to the cavity, and the first mounting seat is pluggably connected to the wing frame at one end away from the cavity.

[0007] In one embodiment of the body structure of the present invention, the first mounting seat includes a support plate and a connecting plate, the support plate is located inside the wing, the connecting plate is arranged at one end of the support plate close to the cavity, the connecting plate is detachably fixedly connected to the wing frame, and a wiring port is opened on the connecting plate.

[0008] In an embodiment of the airframe structure of the present invention, a first slot structure is provided between the first mounting seat and the wing frame at an end of the first mounting seat away from the cavity.

[0009] In one embodiment of the body structure of the present invention, the first slot structure includes a first latch tongue and a first slot hole, the first latch tongue is arranged on one of the first mounting seat and the wing frame, the first slot hole is correspondingly arranged on the other of the first mounting seat and the wing frame, and the first latch tongue is inserted into the first slot hole.

[0010] In one embodiment of the body structure of the present invention, at least one of the accommodating cavities is arranged in the fuselage, and the mounting seat includes a second mounting seat, and the second mounting seat is detachably fixedly connected to the fuselage frame of the fuselage at one end close to the cavity, and the second mounting seat is clamped to the fuselage frame at one end facing away from the cavity.

[0011] In one embodiment of the machine body structure of the present invention, the electrical component is detachably fixedly connected to the mounting base.

[0012] In one embodiment of the machine body structure of the present invention, a plurality of the electrical components are disposed in a single accommodating cavity.

[0013] A second aspect of the present invention further provides an unmanned aerial vehicle, comprising the body structure described in any one of the above items.

[0014] The present invention provides a body structure and an unmanned aerial vehicle. The body structure reasonably utilizes the cavity structure in the body, and a single opening on the body replaces a large opening or multiple openings, thereby ensuring the structural strength of the body and improving the integrity of the body. The cavity no longer serves as a storage cavity for electrical components, but as a transfer cavity for installing electrical components into the storage cavity in the body through an installation channel, thereby realizing the hidden installation of electrical components and the horizontal layout of electrical components without increasing the area or number of openings. At the same time, the horizontal layout reduces the space occupied by electrical components in the height direction of the fuselage, thereby increasing the installation space of batteries or fuel tanks, and improving the flight time and range of the unmanned aerial vehicle. Furthermore, small and unused space areas such as wings and fuselages are used as storage cavities for electrical components, further reducing the space occupied by the fuselage and other main parts for the installation of electrical components, thereby improving the overall space utilization rate of the unmanned aerial vehicle. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings in the following description are only some embodiments of the present invention. For ordinary technicians in this field, other embodiments can be obtained based on these drawings without paying creative work.

[0016] Figure 1 It is a top cross-sectional schematic diagram of the arrangement of electrical components in a machine body in an embodiment of the machine body structure of the present invention; Figure 2 It is a schematic diagram of the installation direction of the first mounting seat in an embodiment of the machine body structure of the present invention; Figure 3 An exploded view of the installation position of the first installation seat in an embodiment of the machine body structure of the present invention; Figure 4 This is a schematic diagram of a state after the first mounting seat is installed in an embodiment of the machine body structure of the present invention; Figure 5 It is an exploded view of the connection between the first mounting seat and the electrical device in an embodiment of the machine body structure of the present invention; Figure 6 It is a schematic diagram of the installation direction of the second mounting seat in an embodiment of the machine body structure of the present invention; Figure 7 This is a schematic diagram of a state after the second mounting seat is installed in an embodiment of the machine body structure of the present invention; Figure 8 This is a schematic diagram of the state after multiple electrical components are installed in the accommodating cavity in one embodiment of the body structure of the present invention.

[0017] Component number description: 100, fuselage; 110, opening; 120, fuselage frame; 101, cavity; 102, accommodating cavity; 1021, first accommodating cavity; 1022, second accommodating cavity; 200, wing; 210, wing frame; 211, first frame; 212, second frame; 213, through hole; 300, electrical component; 400, mounting seat; 410, first mounting seat; 411, support plate; 412, connecting plate; 413, wiring port; 420, second mounting seat; 500, fastener; 510, first fastener; 520, second fastener; 600, first slot structure; 610, first tongue; 620, first slot hole; 700, second slot structure; 710, second tongue. DETAILED DESCRIPTION

[0018] The following is an explanation of the embodiments of the present invention by specific examples, and those skilled in the art can easily understand other advantages and effects of the present invention from the contents disclosed in this specification. The present invention can also be implemented or applied through other different specific embodiments, and the details in this specification can also be modified or changed in various ways based on different viewpoints and applications without departing from the spirit of the present invention. It should be noted that the features in the following embodiments and the embodiments can be combined with each other without conflict. It should also be understood that the terms used in the embodiments of the present invention are intended to describe specific embodiments, rather than to limit the scope of protection of the present invention. The test methods for which specific conditions are not specified in the following examples are usually carried out under conventional conditions or according to the conditions recommended by the manufacturers.

[0019] When numerical ranges are given in the embodiments, it should be understood that unless otherwise specified in the present invention, both endpoints of each numerical range and any value between the two endpoints can be selected. Unless otherwise defined, all technical and scientific terms used in the present invention are familiar to those skilled in the art and the description of the present invention, and any method, device and material of the prior art similar or equivalent to the method, device and material in the embodiments of the present invention can also be used to implement the present invention.

[0020] It should be noted that the terms such as "upper", "lower", "left", "right", "middle" and "one" etc. used in this specification are only for the convenience of description and are not intended to limit the scope of implementation of the present invention. Changes or adjustments to their relative relationships, without substantially changing the technical content, should also be regarded as the scope of implementation of the present invention.

[0021] In order to improve the technical problem that the installation of electrical components of existing drones cannot take into account both the structural strength and space utilization of the body, the present invention provides a body structure and a drone. The body structure can reduce the area or number of the cover openings, ensure the structural strength of the drone body, and improve the integrity of the body. At the same time, it can reduce the space occupied by electrical components in the fuselage, thereby increasing the installation space of batteries or fuel tanks, improving the flight time and range of the drone, and the internal space utilization of the drone.

[0022] See also Figures 1 to 8In a first aspect, the present invention provides a body structure, which is suitable for the installation and arrangement of multiple electrical devices 300 in a drone or other aircraft to improve the space utilization rate in the body. The body structure includes a fuselage 100, wings 200, multiple accommodating cavities 102 and multiple electrical devices 300, wherein the fuselage 100 is the main part of the drone body, and the fuselage 100 has an installation cavity for installing the drone body frame, battery or fuel tank, control module and other conventional drone equipment and functional modules. An opening 110 is provided at the top of the cavity 101, and the opening 110 connects the outside of the fuselage 100 with the inside of the cavity 101. When the electrical device 300 is installed, the electrical device 300 can enter the body through the opening 110. The shape of the opening 110 is not limited, and can be any shape that can enable the electrical device 300 to enter the body. While ensuring that the electrical device 300 can smoothly enter the body, the area of ​​the opening 110 is reduced as much as possible to ensure the structural strength of the fuselage 100. The cavity 101 is a part of the internal cavity of the fuselage 100. The cavity 101 in this embodiment is a cavity space inside the fuselage 100 corresponding to the position of the opening 110 along the height direction of the fuselage 100, and the cavity 101 is connected to the outside of the fuselage 100 through the opening 110. When the internal assembly of the drone is completed, a cover (not shown in the figure) is also installed on the fuselage 100 at the opening 110, and the cover is detachably connected to the fuselage 100, and the cover covers the opening 110.

[0023] As one of the structural components of the fuselage, the wing 200 is installed on the side of the fuselage 100. Specifically, in this embodiment, taking the fixed-wing UAV as an example, the wings 200 are symmetrically arranged on both sides of the fuselage 100. The interior of the wing 200 is a cavity structure, and a wing frame 210 supporting the outer shell of the wing 200 is usually arranged inside the wing 200.

[0024] In this embodiment, the accommodating cavity 102 refers to a narrow space area located in the fuselage and capable of installing one or more electrical devices 300. The number of accommodating cavities 102 is usually multiple. For example, the accommodating cavity 102 can be a narrow space area located in the wing 200 that is not occupied by other drone assembly components, or a narrow space area at the head or tail of the fuselage 100 that is not occupied by other drone assembly components or an area inside the fuselage 100 that does not meet the requirements for opening a cover. Specifically, in this embodiment, at least one accommodating cavity 102 is located in the wing 200, and at least one accommodating cavity 102 is located in the fuselage 100. Multiple accommodating cavities 102 are all located on the periphery of the cavity 101, so that the electrical device 300 can be installed in the accommodating cavity 102. Multiple electrical devices 300 are arranged in multiple accommodating cavities 102. The chamber space of a single accommodating cavity 102 can at least meet the accommodation and installation of one electrical device 300. Among them, there is an installation channel between the cavity 101 and the accommodating cavity 102 for the power supply device 300 to pass through. The electrical device 300 enters the cavity 101 from the opening 110, and is installed in the accommodating cavity 102 through the installation channel. The type of the electrical device 300 is not limited, and can be equipment in the data link system, flight control system, and electrical system of an existing drone, such as a signal transceiver, a gyroscope, an accelerometer, a GPS module, a magnetometer, an electronic speed regulator, a barometer, and other existing conventional electrical equipment, but is not limited thereto.

[0025] The body structure rationally utilizes the cavity structure in the body, and opens an opening 110 on the body 100 only for the passage of the electrical device 300, controls the area of ​​the opening 110 to the maximum extent, and does not need to set multiple cover opening structures on the body structure corresponding to the installation area of ​​multiple electrical devices 300, thereby ensuring the structural strength of the body and improving the integrity of the body. The cavity 101 is no longer used as an installation chamber for multiple electrical devices 300, but as a transfer chamber for a single electrical device 300 to be installed in the accommodating chamber 102 in the body through an installation channel, thereby realizing the hidden installation of multiple electrical devices 300 in the body. At the same time, multiple electrical devices 300 are arranged horizontally in the body, compressing the space occupied by the electrical devices 300 in the height direction of the body, thereby increasing the installation space of batteries, fuel tanks or other components in the body 100, and improving the flight time and range of the drone. Furthermore, the narrow and unused space areas such as the wing 200 and the fuselage 100 are used as accommodating cavities for the electrical components 300, further reducing the space occupied by the main part of the fuselage 100 when installing the electrical components 300, thereby improving the overall space utilization of the drone body.

[0026] See also Figure 2In an embodiment of the fuselage structure of the present invention, the cavity 101 is located in the fuselage 100 region between the wings 200 on both sides, and is close to the end of the fuselage 100. Thus, the end region of the special-shaped structure of the fuselage 100 and the space inside the wings 200 on both sides of the fuselage 100 can be conveniently and reasonably utilized, thereby improving space utilization and meeting the installation requirements of multiple electrical devices 300. And the impact of the difficulty of opening caused by the fuselage structure design can be reduced.

[0027] See also Figures 2 to 7 In one embodiment of the fuselage structure of the present invention, the fuselage structure further includes a mounting seat 400 for fixing and mounting the electrical device 300. The electrical device 300 may be mounted on the mounting seat 400 in any manner, such as by screw connection, clamp connection, bonding, welding, etc., but is not limited thereto. At the same time, the mounting seat 400 is also a connection seat for detachably fixing and connecting the fuselage. The electrical device 300 is pre-fixedly mounted on the mounting seat 400, and then the mounting seat 400 and the electrical device 300 are installed together in the fuselage. For the convenience of description, the accommodating cavity 102 located in the fuselage 100 is referred to as the second accommodating cavity 1022, and the accommodating cavity 102 located in the wing 200 is referred to as the first accommodating cavity 1021. Specifically, when an electrical device 300 can be installed in the second accommodating cavity 1022, the electrical device 300 and the mounting seat 400 are placed in the cavity 101 through the opening 110, and then enter the second accommodating cavity 1022 through the mounting channel between the cavity 101 and the second accommodating cavity 1022, and the mounting seat 400 is detachably fixedly connected to the fuselage 100 or the mounting structure on the side of the second accommodating cavity 1022. Similarly, when an electrical device 300 can be installed in the first accommodating cavity 1021, the electrical device 300 and the mounting seat 400 are placed in the cavity 101 through the opening 110, and then enter the first accommodating cavity 1021 through the mounting channel between the cavity 101 and the first accommodating cavity 1021, and the mounting seat 400 is detachably fixedly connected to the wing 200 mounting structure or the fuselage 100 on the side of the first accommodating cavity 1021.

[0028] One electrical component 300 can be mounted on a single mounting seat 400. When the space of the accommodating cavity 102 can accommodate the installation of multiple electrical components 300, multiple electrical components 300 can be mounted on a single mounting seat 400. Specifically, in the present embodiment, one electrical component 300 is arranged on a single mounting seat 400, so that the corresponding electrical component 300 can be easily disassembled and assembled independently, thereby improving the efficiency of maintenance or overhaul. There is no restriction on the structure of the mounting seat 400. The structural designs of multiple mounting seats 400 can be the same or different, as long as they can meet the requirements of installation at different positions in the machine body. The application of the mounting seat 400 can solve the difficulty of fixing different purchased electrical components 300 in the machine body, better match the installation connection with the structure in the machine body, and reduce the design difficulty and design cost.

[0029] See also Figures 2 to 5 In one embodiment of the airframe structure of the present invention, at least one accommodating cavity 102 is disposed in the wing 200. The wing 200 includes a wing frame 210, and the mounting seat 400 includes a first mounting seat 410. The first mounting seat 410 is a mounting seat 400 structure for connecting to the wing frame 210 of the wing 200. Among them, the end of the first mounting seat 410 close to the cavity 101 is detachably fixedly connected to the wing frame 210 by a fastener 500, and the manner of detachable fixed connection is not limited, for example, it can be a bolt connection, a screw connection or a clamp connection, etc., but it is not limited thereto, as long as it can satisfy the fixation of the first mounting seat 410 and the airframe and ensure the installation stability of the electrical device 300. The end of the first mounting seat 410 away from the cavity 101 is plugged and connected to the wing frame 210. One end of the first mounting seat 410 is connected by plug-in connection and the other end is connected by detachable connection, making full use of the structure of the wing frame 210, so that the electrical device 300 together with the first mounting seat 410 can still ensure the stable installation of the first mounting seat 410 even in the case of hidden installation, avoiding the unstable installation of the electrical device 300 and causing the device to shake. At the same time, the fastener 500 is located at one end close to the cavity 101, which reduces the difficulty of locking the first mounting seat 410 and facilitates operation.

[0030] In one embodiment of the airframe structure of the present invention, the first mounting seat 410 includes a support plate 411 and a connecting plate 412. The support plate 411 is located in the wing 200, and the connecting plate 412 is arranged at one end of the support plate 411 close to the cavity 101. The connecting plate 412 is connected to the wing frame 210 through a fastener 500, and a wiring port 413 is provided on the connecting plate 412. Specifically, for the convenience of description, the fastener 500 used for fixing and connecting the first mounting seat 410 and the wing frame 210 is referred to as the first fastener 510, and the first fastener 510 is a screw. The wing frame 210 includes a first frame 211 and a second frame 212 arranged at intervals along the extension direction of the wing 200, and the outer contours of the first frame 211 and the second frame 212 match the inner contour of the shell of the wing 200. The first frame 211, the second frame 212 and the shell of the wing 200 enclose a first accommodating cavity 1021. The first frame 211 is provided with a through hole 213, and the size of the through hole 213 is sufficient for the support plate 411 and the electrical device 300 installed on the support plate 411 to pass through. After the first mounting seat 410 is installed and fixed, the end of the support plate 411 away from the cavity 101 is clamped with the second frame 212, the connecting plate 412 is attached to the first frame 211 outside the through hole 213, and the line of the electrical device 300 passes through the first accommodating cavity 1021 through the wiring port 413. The first fastener 510 is tightened and fixed to the connecting plate 412 and the first frame 211 along the installation direction of the first mounting seat 410.

[0031] See also Figures 1 to 3In one embodiment of the body structure of the present invention, a first slot structure 600 is provided between the first mounting seat 410 and the wing frame 210 at one end of the first mounting seat 410 away from the cavity 101. Specifically, the first slot structure 600 is located between the support plate 411 and the second frame 212, and the first slot structure 600 cooperates with the first fastener 510 to achieve hidden installation and fixation of the first mounting seat 410.

[0032] See also Figure 3 In an embodiment of the body structure of the present invention, the first slot structure 600 includes a first tongue 610 and a first slot 620. The first tongue 610 is arranged on one of the first mounting seat 410 and the wing frame 210. The first slot 620 is correspondingly arranged on the other of the first mounting seat 410 and the wing frame 210. The first tongue 610 is inserted into the first slot 620. Specifically, in this embodiment, the first tongue 610 is located at one end of the support plate 411 away from the cavity 101. The support plate 411 and the first tongue 610 are an integral structure. The second frame 212 is provided with a first slot 620 adapted to the first tongue 610, so as to achieve the support and limit of the first mounting seat 410 in the wing 200.

[0033] See also Figure 6 and Figure 7In one embodiment of the fuselage structure of the present invention, the mounting seat 400 includes a second mounting seat 420, and the second mounting seat 420 is a mounting seat 400 structure used to be connected to the fuselage frame 120 of the fuselage 100. The second mounting seat 420 is installed in a similar manner to the first mounting seat 410. The end of the second mounting seat 420 close to the cavity 101 is detachably fixedly connected to the fuselage frame 120 by a fastener 500, and the end of the second mounting seat 420 away from the cavity 101 is clamped to the fuselage frame 120. Specifically, the fastener 500 used to connect the fuselage frame 120 and the second mounting seat 420 is a second fastener 520, and the second fastener 520 is a screw. The second mounting seat 420 is a plate-like structure, and the corresponding electrical device 300 is fixed on the second mounting seat 420. The end of the second mounting seat 420 away from the cavity 101 is clamped to the fuselage frame 120 through the second clamping groove structure 700. The second clamping groove structure 700 has the same structure as the first clamping groove structure 600. The second clamping groove structure 700 includes a second clamping tongue 710 and a second slot (not shown in the figure). The second clamping tongue 710 and the second mounting seat 420 are an integral structure. The second slot is provided on the fuselage frame 120 in the second accommodating cavity 1022. The second clamping groove structure 700 realizes the support and limit of one end of the second mounting seat 420 and the fuselage frame 120. Along the height direction of the fuselage 100, that is, the through direction of the opening 110 to the cavity 101, the second fastener 520 locks and fixes the second mounting seat 420 and the fuselage frame 120. And the second fastener 520 is located near the contour edge of the cavity 101 to facilitate the tightening operation of the second fastener 520.

[0034] See also Figure 5 In one embodiment of the body structure of the present invention, the electrical component 300 is detachably fixedly connected to the mounting base 400 by a fastener 500. In this embodiment, the fastener 500 is a screw, and the electrical component 300 is fixedly mounted on the mounting base 400 by the screw. When the electrical component 300 needs to be repaired or replaced, there is no need to replace the mounting base 400, and only the electrical component 300 located on the mounting base 400 needs to be replaced.

[0035] See also Figure 8 In an embodiment of the body structure of the present invention, when the space of the accommodating cavity 102 is large, a plurality of electrical devices 300 are arranged in a single accommodating cavity 102. The arrangement of the plurality of electrical devices 300 in a single accommodating cavity 102 may be arranged horizontally in parallel, or may be arranged in a stacked manner along the height direction of the body 100, so as to further improve the space utilization. Specifically, in this embodiment, the plurality of electrical devices 300 are installed in a stacked manner in the second accommodating cavity 1022 along the height direction of the body 100.

[0036] The second aspect of the present invention further provides a drone, which includes the body structure described in any of the above embodiments. It should be noted that the drone of the present invention also includes conventional structures and conventional functional modules of existing drones such as a tail, a gimbal, a communication module, a control module, and a power module, which will not be described one by one here.

[0037] The body structure of the present invention rationally utilizes the cavity structure in the body, and a single opening on the body replaces a large opening or multiple openings to ensure the structural strength of the body and improve the integrity of the body. The cavity is no longer used as a accommodating cavity for electrical devices, but as a transition cavity for the electrical devices to be installed in the accommodating cavity in the body through the installation channel, so as to realize the hidden installation of electrical devices and the horizontal layout of electrical devices, without increasing the area or number of openings. At the same time, the horizontal layout reduces the space occupied by electrical devices in the height direction of the fuselage, thereby increasing the installation space of batteries or fuel tanks and improving the flight time and range of the drone. Furthermore, the narrow and unused space areas such as wings and fuselages are used as accommodating cavities for electrical devices, further reducing the space occupied by the main parts such as the fuselage for the installation of electrical devices, and improving the overall space utilization of the drone. This improves the technical problem that the installation of electrical devices for existing drones cannot take into account both the structural strength of the body and the space utilization. Therefore, the present invention effectively overcomes some practical problems in the prior art and has high utilization value and use significance.

[0038] The above embodiments are merely illustrative of the principles and effects of the present invention, and are not intended to limit the present invention. Anyone familiar with the art may modify or alter the above embodiments without departing from the spirit and scope of the present invention. Therefore, all equivalent modifications or alterations made by a person of ordinary skill in the art without departing from the spirit and technical concept disclosed by the present invention shall still be covered by the claims of the present invention.

Claims

1. A machine body structure, characterized in that: include: A fuselage, the fuselage comprising an opening and a cavity, the opening being arranged at the top of the cavity and communicating with the cavity; Wings, arranged on the sides of the fuselage; A plurality of accommodating cavities are arranged in the fuselage and / or the wing and are located around the cavities; A plurality of electrical components are correspondingly arranged in the plurality of accommodating cavities; There is an installation passage between the accommodating cavity and the cavity body for the electrical device to pass through; the electrical device enters the cavity body from the opening and passes through the installation passage to be installed in the accommodating cavity.

2. The machine body structure according to claim 1, characterized in that: The fuselage structure also includes a mounting seat for fixedly mounting the electrical device, and the mounting seat is detachably fixedly connected to the fuselage or the wing.

3. The machine body structure according to claim 2, characterized in that: At least one of the accommodating cavities is arranged in the wing, and the mounting seat includes a first mounting seat, and the first mounting seat is detachably fixedly connected to the wing frame of the wing at one end close to the cavity, and the first mounting seat is pluggably connected to the wing frame at one end away from the cavity.

4. The machine body structure according to claim 3, characterized in that: The first mounting seat includes a support plate and a connecting plate, the support plate is located in the wing, the connecting plate is arranged at one end of the support plate close to the cavity, the connecting plate is detachably fixedly connected to the wing frame, and a wiring port is opened on the connecting plate.

5. The machine body structure according to claim 3, characterized in that: At one end of the first mounting seat away from the cavity, a first slot structure is arranged between the first mounting seat and the wing frame.

6. The machine body structure according to claim 5, characterized in that: The first slot structure includes a first latch tongue and a first slot hole, the first latch tongue is arranged on one of the first mounting seat and the wing frame, the first slot hole is correspondingly arranged on the other of the first mounting seat and the wing frame, and the first latch tongue is inserted into the first slot hole.

7. The machine body structure according to claim 2, characterized in that: At least one of the accommodating cavities is disposed in the fuselage, and the mounting seat includes a second mounting seat, an end of the second mounting seat close to the cavity is detachably fixedly connected to the fuselage frame of the fuselage, and an end of the second mounting seat away from the cavity is clamped to the fuselage frame.

8. The machine body structure according to claim 2, characterized in that: The electrical component is detachably fixedly connected to the mounting seat.

9. The machine body structure according to claim 1, characterized in that: A plurality of the electrical components are arranged in a single accommodating cavity.

10. A drone, characterized in that: A machine body structure comprising any one of claims 1 to 9.

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