An airframe structure and an unmanned aerial vehicle

Abstract

The present invention provides a fuselage structure and an unmanned aerial vehicle. The fuselage structure includes a fuselage, wings, a plurality of accommodation cavities and a plurality of electrical components. The fuselage includes an opening and a cavity. The opening is provided at the top of the cavity and is in communication with the cavity. The wings are provided at the sides of the fuselage. The plurality of accommodation cavities are provided in the fuselage and / or the wings and are located on the periphery of the cavity. There is an installation passage for the electrical components to pass through between the accommodation cavity and the cavity. The plurality of electrical components are correspondingly arranged in the plurality of accommodation cavities. Among them, the electrical components enter the cavity from the opening and are installed in the accommodation cavity through the installation passage. This fuselage structure makes rational use of the cavity structure in the fuselage, ensures the structural strength of the fuselage, and improves the integrity of the fuselage. At the same time, it realizes the hidden installation of the electrical components and the horizontal layout of the electrical components, reduces the space occupied by the electrical components in the height direction of the fuselage, and further increases the installation space of the battery or fuel tank, thereby improving the flight time and flight range of the unmanned aerial vehicle.

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 an embodiment of the airframe 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, and the connecting plate is disposed at one end of the support plate close to the cavity. The connecting plate is detachably and fixedly connected to the wing skeleton, and a wiring opening is formed in the connecting plate.

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

[0009] In an embodiment of the airframe structure of the present invention, the first card slot structure includes a first tongue and a first slot. The first tongue is provided on one of the first mounting seat and the wing skeleton, and the first slot is correspondingly provided on the other of the first mounting seat and the wing skeleton. The first tongue is inserted into the first slot.

[0010] In an embodiment of the airframe structure of the present invention, at least one of the accommodation cavities is provided inside the fuselage. The mounting seat includes a second mounting seat. One end of the second mounting seat close to the cavity is detachably and fixedly connected to the fuselage skeleton of the fuselage, and the other end of the second mounting seat facing away from the cavity is snapped onto the fuselage skeleton.

[0011] In an embodiment of the airframe structure of the present invention, the electrical component is detachably and fixedly connected to the mounting seat.

[0012] In an embodiment of the airframe structure of the present invention, a plurality of the electrical components are provided in a single accommodation cavity.

[0013] In a second aspect of the present invention, a drone is further provided. The drone includes the airframe structure according to any one of the above.

[0014] The present invention provides an airframe structure and a drone. The airframe structure makes rational use of the cavity structure inside the airframe, replaces a large opening or multiple openings with a single opening on the fuselage, ensures the structural strength of the airframe, and improves the integrity of the airframe. The cavity is no longer used as an accommodation cavity for electrical components, but as a transfer cavity for electrical components to be installed into the accommodation cavity inside the airframe through an installation channel, realizing the hidden installation of electrical components and the horizontal layout of electrical components, and without increasing the opening area or the 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 for the battery or fuel tank, and improving the flight time and range of the drone. Further, narrow unused space areas such as the wing and the fuselage are used as accommodation cavities for electrical components, further reducing the space occupied by the installation of electrical components on the main parts such as the fuselage, and improving the overall space utilization rate of the drone. Description of the Drawings

[0015] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required for the description of the embodiments or the prior art. Obviously, the drawings in the following description are only some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other embodiments can be obtained based on these drawings.

[0016] Figure 1 It is a schematic top cross-sectional view of the arrangement state of electrical components in the body in an embodiment of the body structure of the present invention;

[0017] Figure 2 It is a schematic diagram of the installation direction of the first mounting seat in an embodiment of the body structure of the present invention;

[0018] Figure 3 It is an exploded view of the installation position of the first mounting seat in an embodiment of the body structure of the present invention;

[0019] Figure 4 It is a schematic diagram of the state after the first mounting seat is installed in an embodiment of the body structure of the present invention;

[0020] Figure 5 It is an exploded view of the connection between the first mounting seat and the electrical components in an embodiment of the body structure of the present invention;

[0021] Figure 6 It is a schematic diagram of the installation direction of the second mounting seat in an embodiment of the body structure of the present invention;

[0022] Figure 7 It is a schematic diagram of the state after the second mounting seat is installed in an embodiment of the body structure of the present invention;

[0023] Figure 8 It is a schematic diagram of the state after multiple electrical components are installed in the accommodation cavity in an embodiment of the body structure of the present invention.

[0024] Element number description:

[0025] 100, fuselage; 110, opening; 120, fuselage frame; 101, cavity; 102, accommodation cavity; 1021, first accommodation cavity; 1022, second accommodation 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 card slot structure; 610, first tongue; 620, first slot; 700, second card slot structure; 710, second tongue. Detailed implementation manners

[0026] The following describes the embodiments of the present invention through specific examples. Those skilled in the art can easily understand other advantages and effects of the present invention from the content disclosed in this specification. The present invention can also be implemented or applied through other different specific embodiments. Various details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of the present invention. It should be noted that, without conflict, the following embodiments and the features in the embodiments can be combined with each other. It should also be understood that the terms used in the embodiments of the present invention are for the purpose of describing specific embodiments and are not intended to limit the protection scope of the present invention. The test methods without specific conditions noted in the following embodiments are generally carried out according to conventional conditions or according to the conditions recommended by each manufacturer.

[0027] When the embodiments give a numerical range, it should be understood that unless otherwise specified in the present invention, any value between the two endpoints of each numerical range and either of the two endpoints can be selected. Unless otherwise defined, all technical and scientific terms used in the present invention, based on the understanding of those skilled in the art of the prior art and the description of the present invention, any method, device, and material similar or equivalent to the prior art in the methods, devices, and materials in the embodiments of the present invention can also be used to implement the present invention.

[0028] It should be noted that the terms such as "upper", "lower", "left", "right", "middle", and "one" cited in this specification are only for the convenience of clear description and are not intended to limit the scope of implementation of the present invention. The change or adjustment of their relative relationships, without substantial change in the technical content, should also be regarded as the scope within which the present invention can be implemented.

[0029] In order to improve the technical problem that the installation of existing unmanned aerial vehicle (UAV) electrical components cannot take into account both the structural strength of the airframe and the space utilization rate, the present invention provides an airframe structure and a UAV. This airframe structure can reduce the area or number of hatch openings, ensure the structural strength of the UAV airframe, and improve the airframe integrity. At the same time, it can reduce the space occupied by electrical components inside the fuselage, thereby increasing the installation space for the battery or fuel tank, enhancing the flight time and range of the UAV, as well as the internal space utilization rate of the UAV.

[0030] Please refer to Figures 1 to 8, the first aspect of the present invention provides a body structure, which is applicable to the installation and arrangement of multiple electrical components 300 in an unmanned aerial vehicle or other aircraft, so as to improve the space utilization rate inside the body. The body structure includes a fuselage 100, wings 200, multiple accommodation cavities 102 and multiple electrical components 300. The fuselage 100 is the main part of the unmanned aerial vehicle body, and the inside of the fuselage 100 has installation chambers for installing conventional equipment and functional modules of the unmanned aerial vehicle such as the body frame, battery or fuel tank, and control module of the unmanned aerial vehicle. An opening 110 is provided at the top of the cavity 101, and the opening 110 communicates with the outside of the fuselage 100 and the inside of the cavity 101. When installing the electrical component 300, the electrical component 300 can enter the body through the opening 110. The shape of the opening 110 is not limited, and any shape that can enable the electrical component 300 to enter the body can be used. While ensuring that the electrical component 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. In this embodiment, the cavity 101 is the 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 communicates with the outside of the fuselage 100 through the opening 110. After the internal assembly of the unmanned aerial vehicle is completed, a cover (not shown in the figure) is also installed on the fuselage 100 at the opening 110. The cover is detachably connected to the fuselage 100, and the cover seals the opening 110.

[0031] As one of the structural components of the body, the wing 200 is installed on the side of the fuselage 100. Specifically, in this embodiment, taking a fixed-wing unmanned aerial vehicle as an example, the wings 200 are symmetrically arranged on both sides of the fuselage 100. The inside of the wing 200 is a cavity structure, and a wing frame 210 for supporting the outer shell of the wing 200 is usually provided inside the wing 200.

[0032] In this embodiment, the accommodation cavity 102 refers to a narrow space area located inside the aircraft body and capable of accommodating one or more electrical components 300. The number of accommodation cavities 102 is usually multiple. For example, the accommodation cavity 102 can be a narrow space area within the wing 200 that is not occupied by other UAV assembly components, or a narrow space area at the head or tail of the fuselage 100 that is not occupied by other UAV assembly components, or an area inside the fuselage 100 that does not meet the requirements for opening an access panel. Specifically, in this embodiment, at least one accommodation cavity 102 is located within the wing 200, and at least one accommodation cavity 102 is located within the fuselage 100. The multiple accommodation cavities 102 are all located on the periphery of the cavity 101 to facilitate the installation of the electrical components 300 into the accommodation cavities 102. Multiple electrical components 300 are arranged in the multiple accommodation cavities 102. The chamber space of a single accommodation cavity 102 can at least accommodate and install one electrical component 300. Among them, there is an installation channel for the electrical component 300 to pass through between the cavity 101 and the accommodation cavity 102. The electrical component 300 enters the cavity 101 from the opening 110 and is installed in the accommodation cavity 102 through the installation channel. The type of the electrical component 300 is not limited. It can be equipment in the existing data link system, flight control system, and electrical system of the UAV. For example, it can be existing conventional electrical equipment such as a signal transceiver, gyroscope, accelerometer, GPS module, magnetometer, electronic speed controller, barometer, etc., but not limited thereto.

[0033] This aircraft body structure makes rational use of the cavity structure inside the aircraft body, opens an opening 110 on the fuselage 100 only for the passage of the electrical component 300, and maximally controls the area of the opening 110. There is no need to set multiple access panel opening structures on the aircraft body structure corresponding to the installation areas of multiple electrical components 300, which ensures the structural strength of the aircraft body and improves the integrity of the aircraft body. The cavity 101 is no longer used as the installation chamber for multiple electrical components 300, but as a transfer chamber for a single electrical component 300 to be installed into the accommodation cavity 102 inside the aircraft body through the installation channel, realizing the hidden installation of multiple electrical components 300 inside the aircraft body. At the same time, the multiple electrical components 300 are arranged in a horizontal layout structure inside the aircraft body, compressing the space occupied by the electrical components 300 in the height direction of the fuselage, thereby increasing the installation space for the battery, fuel tank, or other components inside the fuselage 100, and improving the flight time and range of the UAV. Further, narrow unused space areas such as the wing 200 and the fuselage 100 are used as accommodation cavities for the electrical components 300, further reducing the space occupied by the installation of the electrical components 300 on the main part of the fuselage 100 and improving the overall space utilization rate of the UAV body.

[0034] Please refer to Figure 2, in an embodiment of the body structure of the present invention, the cavity 101 is located in the area of the fuselage 100 between the two wings 200 and close to the end of the fuselage 100. Thus, it is convenient to reasonably utilize the end area of the special-shaped structure of the fuselage 100 and the space inside the wings 200 on both sides of the fuselage 100, improve the space utilization rate, meet the installation requirements of multiple electrical components 300, and reduce the influence of difficult opening caused by the body structure design.

[0035] Please refer to Figures 2 to 7 , in an embodiment of the body structure of the present invention, the body structure further includes a mounting seat 400 for fixedly installing the electrical component 300. The installation method of the electrical component 300 on the mounting seat 400 is not limited. For example, it can be screw connection, clamp connection, bonding, welding, etc., but not limited thereto. At the same time, the mounting seat 400 is also a connecting seat for detachably fixedly connecting the body. The electrical component 300 is pre-fixed and installed on the mounting seat 400, and then the mounting seat 400 and the electrical component 300 are jointly installed in the body. For the convenience of description, the accommodation cavity 102 located in the fuselage 100 is denoted as the second accommodation cavity 1022, and the accommodation cavity 102 located in the wing 200 is denoted as the first accommodation cavity 1021. Specifically, when a certain electrical component 300 can be installed in the second accommodation cavity 1022, the electrical component 300 together with the mounting seat 400 is placed into the cavity 101 through the opening 110, and then enters the second accommodation cavity 1022 through the installation channel between the cavity 101 and the second accommodation cavity 1022, and the mounting seat 400 is detachably fixedly connected to the fuselage 100 or the installation structure on the periphery of the second accommodation cavity 1022. Similarly, when a certain electrical component 300 can be installed in the first accommodation cavity 1021, the electrical component 300 together with the mounting seat 400 is placed into the cavity 101 through the opening 110, and then enters the first accommodation cavity 1021 through the installation channel between the cavity 101 and the first accommodation cavity 1021, and the mounting seat 400 is detachably fixedly connected to the wing 200 installation structure or the fuselage 100 on the periphery of the first accommodation cavity 1021.

[0036] One electrical component 300 can be correspondingly installed on a single mounting seat 400. When the space of the accommodation cavity 102 can meet the installation of multiple electrical components 300, multiple electrical components 300 can be installed on a single mounting seat 400. Specifically, in this embodiment, one electrical component 300 is correspondingly arranged on a single mounting seat 400, so as to facilitate the independent disassembly and assembly of the corresponding electrical component 300 and improve the working efficiency of maintenance or repair. The structure of the mounting seat 400 is not limited. The structural designs of multiple mounting seats 400 can be the same or different, as long as they can meet the installation requirements at different positions in the body. The application of the mounting seat 400 can solve the difficulty of fixing different externally purchased electrical components 300 in the body, better match the installation connection with the structure in the body, and reduce the design difficulty and design cost.

[0037] Please refer to Figures 2 to 5 In an embodiment of the body structure of the present invention, at least one accommodation cavity 102 is provided in the wing 200. The wing 200 includes a wing skeleton 210, and the mounting seat 400 includes a first mounting seat 410. The first mounting seat 410 is a structure of the mounting seat 400 for connecting with the wing skeleton 210 of the wing 200. Among them, one end of the first mounting seat 410 close to the cavity 101 is detachably fixedly connected to the wing skeleton 210 by a fastener 500. The way of detachable fixed connection is not limited. For example, it can be bolt connection, screw connection or clamp connection, etc., but not limited thereto. As long as the fixation of the first mounting seat 410 with the body can be satisfied and the installation stability of the electrical component 300 can be ensured. One end of the first mounting seat 410 away from the cavity 101 is plugged and unplugged with the wing skeleton 210. One end of the first mounting seat 410 adopts the plug-and-unplug connection, and the other end adopts the detachable connection method, making full use of the structure of the wing skeleton 210, so that even in the case of hidden installation, the electrical component 300 together with the first mounting seat 410 can still ensure the stable installation of the first mounting seat 410 and avoid the equipment shaking caused by the unstable installation of the electrical component 300. At the same time, the fastener 500 is located at one end close to the cavity 101, reducing the locking connection difficulty of the first mounting seat 410 and facilitating operation.

[0038] In an embodiment of the body 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 inside 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 skeleton 210 by a fastener 500, and a wiring opening 413 is provided on the connecting plate 412. Specifically, for the convenience of description, the fastener 500 used to fixedly connect the first mounting seat 410 and the wing skeleton 210 is denoted as the first fastener 510, and the first fastener 510 adopts a screw. The wing skeleton 210 includes a first skeleton 211 and a second skeleton 212 arranged at intervals along the extending direction of the wing 200. The outer contours of the first skeleton 211 and the second skeleton 212 match the inner contour of the shell of the wing 200. The first skeleton 211, the second skeleton 212 and the shell of the wing 200 enclose a first accommodation cavity 1021. A through hole 213 is provided on the first skeleton 211, and the size of the through hole 213 can satisfy the passage of the support plate 411 and the electrical component 300 mounted on the support plate 411. After the first mounting seat 410 is installed and fixed, one end of the support plate 411 away from the cavity 101 is clamped with the second skeleton 212, the connecting plate 412 fits the first skeleton 211 outside the through hole 213, and the line of the electrical component 300 passes out of the first accommodation cavity 1021 through the wiring opening 413. The first fastener 510 is tightened along the installation direction of the first mounting seat 410 to fix the connecting plate 412 and the first skeleton 211.

[0039] Please refer to Figures 1 to 3, in an embodiment of the airframe structure of the present invention, at one end of the first mounting seat 410 away from the cavity 101, a first slot structure 600 is provided between the first mounting seat 410 and the wing skeleton 210. Specifically, the first slot structure 600 is located between the support plate 411 and the second skeleton 212, and the first slot structure 600 cooperates with the first fastener 510 to achieve the concealed installation and fixation of the first mounting seat 410.

[0040] Please refer to Figure 3 , in an embodiment of the airframe structure of the present invention, the first slot structure 600 includes a first tongue 610 and a first slot hole 620. The first tongue 610 is provided on one of the first mounting seat 410 and the wing skeleton 210, and the first slot hole 620 is correspondingly provided on the other of the first mounting seat 410 and the wing skeleton 210. The first tongue 610 is inserted into the first slot hole 620. Specifically, in this embodiment, the first tongue 610 is located at one end of the support plate 411 away from the cavity 101, and the support plate 411 and the first tongue 610 are an integral structure. The first slot hole 620 adapted to the first tongue 610 is opened on the second skeleton 212, so as to realize the support and limit of the first mounting seat 410 in the wing 200.

[0041] Please refer to Figure 6 and Figure 7, in an embodiment of the body structure of the present invention, the mounting base 400 includes a second mounting base 420, and the second mounting base 420 is a structure of the mounting base 400 for connecting with the fuselage frame 120 of the fuselage 100. The mounting method of the second mounting base 420 is similar to that of the first mounting base 410. One end of the second mounting base 420 close to the cavity 101 is detachably and fixedly connected to the fuselage frame 120 through a fastener 500, and one end of the second mounting base 420 facing away from the cavity 101 is snap-connected to the fuselage frame 120. Specifically, the fastener 500 for connecting the fuselage frame 120 and the second mounting base 420 is denoted as the second fastener 520. The second fastener 520 uses a screw. The second mounting base 420 is a plate-like structure, and the corresponding electrical component 300 is fixed on the second mounting base 420. One end of the second mounting base 420 facing away from the cavity 101 is snap-connected to the fuselage frame 120 through a second slot structure 700. The second slot structure 700 has the same structure as the first slot structure 600. The second slot structure 700 includes a second tongue 710 and a second slot hole (not shown in the figure). The second tongue 710 and the second mounting base 420 are an integral structure. The second slot hole is opened on the fuselage frame 120 in the second accommodation cavity 1022. The second slot structure 700 realizes the support and limit of one end of the second mounting base 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 base 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.

[0042] Please refer to Figure 5 , in an embodiment of the body structure of the present invention, the electrical component 300 is detachably and fixedly connected to the mounting base 400 through a fastener 500. In this embodiment, the fastener 500 is a screw, and the electrical component 300 is fixedly installed on the mounting base 400 through a screw. When the electrical component 300 needs to be repaired or replaced, it is not necessary to replace the mounting base 400, and only the electrical component 300 located on the mounting base 400 needs to be replaced.

[0043] Please refer to Figure 8 , in an embodiment of the body structure of the present invention, when the space of the accommodation cavity 102 is large, multiple electrical components 300 are arranged in a single accommodation cavity 102. The arrangement method of the multiple electrical components 300 in a single accommodation cavity 102 can be arranged horizontally side by side, or can be arranged stacked along the height direction of the fuselage 100 to further improve the space utilization rate. Specifically, in this embodiment, the multiple electrical components 300 are stacked and installed in the second accommodation cavity 1022 along the height direction of the fuselage 100.

[0044] In a second aspect of the present invention, a drone is further provided, which includes the fuselage structure described in any one of the above embodiments. It should be noted that the drone of the present invention further includes conventional structures and functional modules of existing drones such as a tail fin, a gimbal, a communication module, a control module, and a power module, which will not be elaborated here one by one.

[0045] In the fuselage structure of the present invention, the cavity structure inside the fuselage is reasonably utilized, and a single opening on the fuselage replaces a large opening or multiple openings, ensuring the structural strength of the fuselage and improving the integrity of the fuselage. The cavity is no longer used as a cavity for accommodating electrical components, but as a transition cavity for installing electrical components into the accommodation cavity inside the fuselage through an installation channel, realizing the hidden installation of electrical components and the horizontal layout of electrical components, without the need to increase the opening area or the 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 for the battery or fuel tank, and improving the flight time and range of the drone. Further, narrow unused space areas such as the wings and the fuselage are used as accommodation cavities for electrical components, further reducing the space occupied by the installation of electrical components in the main parts such as the fuselage, and improving the overall space utilization rate of the drone. To improve the technical problem that the installation of electrical components in existing drones cannot take into account both the structural strength of the fuselage and the space utilization rate. Therefore, the present invention effectively overcomes some practical problems in the prior art and thus has high utilization value and practical significance.

[0046] The above embodiments are only illustrative of the principles and effects of the present invention, and are not used to limit the present invention. Any person familiar with this technology can modify or change the above embodiments without departing from the spirit and scope of the present invention. Therefore, all equivalent modifications or changes made by those with ordinary knowledge in the technical field without departing from the spirit and technical idea disclosed by the present invention should 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; The fuselage structure also includes a mounting seat for fixedly mounting the electrical device, wherein the mounting seat is detachably fixedly connected to the fuselage or the wing; At least one of the accommodating cavities is disposed in the wing, and the mounting seat comprises a first mounting seat, wherein one end of the first mounting seat close to the cavity is detachably fixedly connected to the wing frame of the wing, and one end of the first mounting seat away from the cavity is pluggably connected to the wing frame; At one end of the first mounting seat away from the cavity, a first slot structure is provided between the first mounting seat and the wing frame; 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.

2. The machine body structure according to claim 1, 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.

3. The machine body structure according to claim 1, 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.

4. The machine body structure according to claim 1, characterized in that: The electrical component is detachably fixedly connected to the mounting seat.

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

6. A drone, characterized in that: The machine body structure comprises any one of claims 1 to 5.

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