Unmanned aerial vehicle

Abstract

The unmanned aerial vehicle comprises a vehicle body and at least one vehicle arm, at least one lens is arranged on the vehicle body, and the effective field angle of the lens is larger than 180 degrees; the at least one vehicle arm is arranged on the vehicle body, the vehicle arm can be switched between an unfolding position and a folding position, the vehicle arm is located outside the effective field angle at the unfolding position, and the vehicle arm is used for supporting the vehicle body at the folding position. When the vehicle arms are in the folding positions, the height of the lens of the unmanned aerial vehicle can be increased, so that the unmanned aerial vehicle can obtain a proper shooting height, the shooting effect of the unmanned aerial vehicle on the ground is effectively improved, and the use experience of a user is improved.

Description

TECHNICAL FIELD

[0001] The present disclosure relates to the field of aircraft, and in particular, to a UAV. BACKGROUND

[0002] An unmanned aircraft, commonly known as a drone, is an aircraft without a human pilot aboard. It is controlled either by a remote human operator or autonomously by onboard computers. With the rapid development of drone technology, drones are gradually applied to various fields, such as in the field of photography, users can use drones to achieve ultra-wide-angle photography or panoramic photography, etc.

[0003] When users use drones for shooting, they not only have the demand for flight shooting, but also have the demand for using drones as shooting equipment on the ground. However, the drones in the related art have poor shooting effect when used as shooting equipment on the ground, thereby affecting the user experience. UTILITY MODEL CONTENT

[0004] In order to overcome the problems in the related art, the present disclosure provides a UAV.

[0005] The present disclosure provides a UAV, which comprises: a body, at least one lens is arranged on the body, the effective field of view angle of the lens is greater than 180°; at least one arm is arranged on the body, the arm can be switched between an unfolded position and a folded position, in the unfolded position, the arm is located outside the effective field of view angle, in the folded position, the arm is used to support the body.

[0006] In some embodiments of the present disclosure, the at least one lens comprises a first lens and a second lens, the first lens is arranged on the top of the body, the second lens is arranged on the bottom of the body, the effective field of view angle of the first lens and the effective field of view angle of the second lens partially overlap, and the arm is rotatably connected with the side wall of the body.

[0007] In some embodiments of the present disclosure, the side wall of the body is provided with a mounting groove corresponding to each arm, the arm is rotatably connected with the mounting groove through a rotating shaft assembly, and at least part of the structure of the arm is located in the mounting groove in the folded position.

[0008] In some embodiments of the present disclosure, the arm includes opposite first and second ends, the first end of the arm is arranged in the mounting slot, and the first end of the arm is provided with a mounting hole, and the second end of the arm is provided with a rotor; the rotating shaft assembly includes a fixed shaft and a rotating member, the rotating member is sleeved outside the fixed shaft and is rotationally connected with the fixed shaft, the mounting slot includes opposite first and second slot side walls, the fixed shaft passes through the first slot side wall and the mounting hole in sequence from the outside of the first slot side wall and is fixedly connected with the second slot side wall, and the rotating member is fixedly arranged in the circumferential direction with the mounting hole.

[0009] In some embodiments of the present disclosure, one end of the rotating member in the axial direction is provided with a movable member and an elastic body, the movable member is located between the elastic body and the rotating member, the movable member is fixedly arranged in the circumferential direction with the fixed shaft, and the movable member and the elastic body can move in the axial direction of the fixed shaft; one of the movable member and the rotating member is provided with a first groove and a second groove, the other of the movable member and the rotating member is provided with a protrusion, in the folded position, the protrusion is matched with the first groove, in the unfolded position, the protrusion is matched with the second groove, and the elastic body is used to provide elastic force for the protrusion sliding into the first groove or the second groove.

[0010] In some embodiments of the present disclosure, the side wall of the fuselage body includes opposite first and second side walls, the first side wall is provided with a first circuit board module, and the second side wall is provided with a second circuit board module; wherein, the fuselage body is provided with a first air duct structure, the first air duct structure is used for heat dissipation of the first circuit board module; and / or, the fuselage body is provided with a second air duct structure, the second air duct structure is used for heat dissipation of the second circuit board module.

[0011] In some embodiments of the present disclosure, a plurality of installation slots are arranged along the circumference of the fuselage body, the plurality of installation slots include a first installation slot and a second installation slot arranged on both sides of the first side wall, the second slot side wall of the first installation slot and the first slot side wall of the second installation slot are opposite to each other, the first air outlet structure is arranged on the second slot side wall of the first installation slot and the first slot side wall of the second installation slot, the first air inlet is arranged on the top wall of the fuselage body corresponding to the position of the first circuit board module, the first air outlet is arranged on the first side wall, and the first air outlet structure, the first air inlet and the first air outlet jointly constitute the first air duct structure; and / or, a plurality of installation slots are arranged along the circumference of the fuselage body, the plurality of installation slots include a third installation slot and a fourth installation slot arranged on both sides of the second side wall, the second slot side wall of the third installation slot and the first slot side wall of the fourth installation slot are opposite to each other, the second air outlet structure is arranged on the second slot side wall of the third installation slot and the first slot side wall of the fourth installation slot, the second air inlet is arranged on the top wall of the fuselage body corresponding to the position of the second circuit board module, the second air outlet is arranged on the second side wall, and the second air outlet structure, the second air inlet and the second air outlet jointly constitute the second air duct structure.

[0012] In some embodiments of the present disclosure, the unmanned aerial vehicle further comprises: a landing gear arranged at the bottom of the fuselage body, the landing gear comprising an unfolded state and a closed state, in the unfolded state, the landing gear is used to support the fuselage body, and in the closed state, the landing gear is clamped on the fuselage body.

[0013] In some embodiments of the present disclosure, the inside of the fuselage body is provided with a containing cavity, and the unmanned aerial vehicle further comprises: a battery module arranged in the containing cavity, and the center of gravity of the battery module is located at the center of the containing cavity.

[0014] In some embodiments of the present disclosure, the top of the fuselage body comprises opposite first and second side edges, and the unmanned aerial vehicle further comprises: a positioning module arranged on the top of the fuselage body close to the first side edge; a control module arranged on the top of the fuselage body close to the second side edge; and an obstacle avoidance module arranged at the bottom of the fuselage body.

[0015] The technical scheme provided by the embodiments of the present disclosure can have the following beneficial effects:

[0016] The unmanned aerial vehicle provided by the present disclosure is provided with at least one lens on the body, and the effective field of view angle of the lens is greater than 180°, thereby helping the unmanned aerial vehicle to realize the ultra-wide-angle shooting or panoramic shooting function; at least one arm is arranged on the body, and each arm can be switched between an unfolded position and a folded position; when the arm is in the unfolded position, the arm is located outside the effective field of view angle, thereby effectively avoiding the arm from falling into the shooting range of the unmanned aerial vehicle in the unfolded state or the flight state, and improving the shooting effect of the unmanned aerial vehicle in the flight state; when the arm is in the folded position, the arm can support the body to raise the height of the lens of the unmanned aerial vehicle, so that the unmanned aerial vehicle can obtain a suitable shooting height, thereby effectively improving the shooting effect of the unmanned aerial vehicle on the ground and improving the use experience of the user.

[0017] It should be understood that the above general description and the following detailed description are only exemplary and explanatory, and cannot limit the present disclosure. BRIEF DESCRIPTION OF DRAWINGS

[0018] The accompanying drawings incorporated in the specification and forming a part of the specification illustrate embodiments consistent with the present disclosure and, together with the description, serve to explain the principles of the present disclosure.

[0019] Figure 1 is a structural schematic diagram of the unmanned aerial vehicle when the arm is in the unfolded position according to an exemplary embodiment;

[0020] Figure 2 is a structural schematic diagram of the unmanned aerial vehicle when the arm is in the folded position according to an exemplary embodiment;

[0021] Figure 3 is an exploded schematic diagram of the unmanned aerial vehicle according to an exemplary embodiment;

[0022] Figure 4 is a structural schematic diagram of the unmanned aerial vehicle according to an exemplary embodiment;

[0023] Figure 5 is a structural schematic diagram of the unmanned aerial vehicle after hiding part of the structure according to an exemplary embodiment;

[0024] Figure 6 is a structural schematic diagram of the unmanned aerial vehicle after hiding part of the structure according to another exemplary embodiment.

[0025] In the drawings:

[0026] 1 - unmanned aerial vehicle; 101 - first circuit board module; 102 - second circuit board module; 103 - positioning module; 104 - control module; 105 - obstacle avoidance module; 106 - interface assembly; 11 - body; 111 - first side wall; 1111 - first air outlet; 112 - top wall; 1121 - first air inlet; 113 - bottom; 114 - top; 115 - cavity; 116 - first side edge; 117 - second side edge; 12 - first lens; 13 - second lens; 14 - mounting groove; 141 - first mounting groove; 142 - first groove side wall; 143 - first air outlet structure; 15 - rotating shaft assembly; 151 - screw; 16 - arm; 161 - rotor; 17 - landing gear. DETAILED DESCRIPTION

[0027] The exemplary embodiments will be described in detail herein with reference to the attached drawings. In the following description, unless otherwise indicated, like numbers in the attached drawings refer to the same or similar elements. The following detailed description includes specific details for the purpose of providing a thorough understanding of the exemplary embodiments. However, it will be apparent to those skilled in the art that the exemplary embodiments can be practiced without these specific details. In some instances, well-known structures and components are not described in detail in order to avoid obscuring the understanding of the exemplary embodiments.

[0028] An unmanned aerial vehicle, referred to as a "drone", is a pilotless aircraft that is controlled by radio control equipment and self-provided program control devices, or is completely or intermittently operated by a vehicle-mounted computer. With the rapid development of drone technology, drones are gradually applied in various fields, such as in the field of shooting, users can use drones to achieve ultra-wide angle shooting or panoramic shooting, etc.

[0029] When a user uses a drone to shoot, not only is there a demand for flight shooting, but there is also a demand for using the drone as a shooting device on the ground. The drone in the related art has poor shooting effect when used as a shooting device on the ground, thereby affecting the user's experience. For example, the drone in the related art has a low position height of the lens on the drone when placed on the ground, which cannot meet the user's requirement for shooting height, thereby resulting in poor shooting effect.

[0030] To solve the above technical problems, the present disclosure provides a kind of unmanned plane, at least one lens is provided on the body body, the effective field of view angle of lens is greater than 180 °, to help unmanned plane realize ultra-wide angle shooting or panoramic shooting function;At least one arm is provided on the body body, each arm can be switched between unfolded position and folded position, when arm is in unfolded position, arm is located outside effective field of view angle, effectively avoid arm in unfolded state or flight state to fall into the shooting range of unmanned plane, to improve the shooting effect of unmanned plane in flight state;When arm is in folded position, it can support body body to raise the height of unmanned plane lens, so that unmanned plane can obtain suitable shooting height, to effectively improve the shooting effect of unmanned plane when shooting on ground, improve the use experience of user.

[0031] An exemplary embodiment of the present disclosure provides a kind of unmanned plane, in combination Figure 1 And Figure 2 Unmanned plane 1 includes body body 11 and at least one arm 16. At least one lens is provided on the body body 11, for example, only one lens can be provided on the body body 11, or multiple lenses can be provided on the body body 11. The effective field of view angle of each lens is greater than 180 °, so that the unmanned plane 1 realizes ultra-wide angle shooting or panoramic shooting function, to meet the different use requirements of user. For example, when only one lens is provided on the body body 11, the effective field of view angle of the lens is greater than 180 °, so that the unmanned plane 1 realizes ultra-wide angle shooting. When multiple lenses are provided on the body body 11, the effective field of view angle of each lens is greater than 180 °, and the effective field of view angle between each two lenses partially overlaps, so that the unmanned plane 1 can realize panoramic shooting.

[0032] At least one arm 16 is provided on the body body 11, for example, only one arm 16 can be provided on the body body 11, such as being provided on the top 114 of the body body 11, to ensure the stability of unmanned plane 1 when only one arm 16 is provided, or the arm 16 is provided on the side of the body body 11, which is not limited herein;Multiple arms 16 can also be provided on the body body 11, for example, multiple arms 16 are dispersedly provided on the side of the body body 11, so that more power can be provided for the flight of unmanned plane 1, to improve the take-off speed of unmanned plane 1 and the stability of unmanned plane 1 in flight.

[0033] Each arm 16 can be switched between unfolded position and folded position, in unfolded position, unmanned plane 1 can be driven to flight state. When arm 16 is in unfolded state or unmanned plane 1 is in flight state, each arm 16 is located outside effective field of view angle, to effectively avoid arm 16 falling into the shooting range of unmanned plane 1, to improve the shooting effect of unmanned plane 1 in flight state or arm 16 in unfolded state.

[0034] When the unmanned aerial vehicle 1 is used as a shooting device on the ground, the arm 16 can be adjusted to a folded position, and the arm 16 in the folded position can support the body 11 to raise the height of the lens of the unmanned aerial vehicle 1, so that the unmanned aerial vehicle 1 can obtain a suitable shooting height, thereby effectively improving the shooting effect of the unmanned aerial vehicle 1 when shooting on the ground and improving the user experience.

[0035] In combination with Figure 1 and Figure 2 , in an embodiment, the at least one lens includes a first lens 12 and a second lens 13, the first lens 12 is arranged at the top 114 of the body 11, the second lens 13 is arranged at the bottom 113 of the body 11, and the arm 16 is rotationally connected with the side wall of the body 11. With such a setting form, the arm 16 interferes with the first lens 12 and the second lens 13, avoiding the arm 16 from blocking the first lens 12 and the second lens 13, thereby effectively improving the shooting effect of the unmanned aerial vehicle 1. The effective field of view angle of the first lens 12 and the effective field of view angle of the second lens 13 partially overlap, so that the unmanned aerial vehicle 1 can realize panoramic shooting and improve the user experience.

[0036] In combination with Figure 1 , Figure 2 and Figure 3 , in an embodiment, the side wall of the body 11 is provided with a mounting groove 14 corresponding to each arm 16, and the arm 16 is rotationally connected with the mounting groove 14 through a rotating shaft assembly 15. Such a design not only makes the structure of the unmanned aerial vehicle 1 simple and easy to process, but also makes the structure of the unmanned aerial vehicle 1 more compact, thereby facilitating the miniaturization design of the unmanned aerial vehicle 1. When the arm 16 is in the folded position, at least part of the structure of the arm 16 is located in the mounting groove 14. Exemplarily, only part of the structure of the arm 16 can be located in the mounting groove 14, or all the structure of the arm 16 can be located in the mounting groove 14. With such a setting form, the hidden design of at least part of the structure of the arm 16 can be realized, thereby not only reducing the volume of the unmanned aerial vehicle 1 when the arm 16 is in the folded position, but also facilitating the holding of the unmanned aerial vehicle 1 and improving the convenience of the user when using the unmanned aerial vehicle 1.

[0037] In combination with Figure 3 , in an embodiment, the arm 16 includes opposite first and second ends, the first end of the arm 16 is arranged in the mounting groove 14, and the first end of the arm 16 is provided with a mounting hole, and the rotating shaft assembly 15 rotationally connects the first end of the arm 16 in the mounting groove 14 through the mounting hole. The second end of the arm 16 is provided with a rotor 161, and exemplarily, the arm 16 is provided with a motor driving the rotation of the rotor 161, and the motor drives the rotation of the rotor 161 to provide power for the flight of the unmanned aerial vehicle 1.

[0038] The rotating shaft assembly 15 comprises a fixed shaft and a rotating member. The rotating member is sleeved outside the fixed shaft and is rotationally connected with the fixed shaft. The mounting groove 14 comprises opposite first and second groove side walls, and the fixed shaft passes through the first groove side wall 142 and the mounting hole in sequence from the outside of the first groove side wall 142 and is fixedly connected with the second groove side wall, for example, the fixed shaft is fixed on the body 11 by screws 151, so that the first end of the arm 16 is positioned in the mounting groove 14. The rotating member is fixedly connected with the mounting hole in the circumferential direction. For example, the shape of the mounting hole can be an oval hole, a square hole, a rectangular hole, etc., and the outer surface of the rotating member is matched with the shape of the mounting hole, so that the rotating member is fixedly connected with the mounting hole in the circumferential direction. In this way, the first end of the arm 16 can rotate around the fixed shaft, so that the arm 16 can be switched between the unfolded position and the folded position. With such a structure, the structure of the unmanned aerial vehicle 1 is simple, which is convenient for processing and can effectively improve the efficiency of assembling the unmanned aerial vehicle 1.

[0039] In an embodiment, the rotating member is provided with a movable member and an elastic body at one axial end, and the movable member is located between the elastic body and the rotating member. The elastic body can be a spring or an elastic material member, such as a silica gel material. The movable member is fixedly connected with the fixed shaft in the circumferential direction, and the movable member and the elastic body can move along the axial direction of the fixed shaft. One of the movable member and the rotating member is provided with a first groove and a second groove, and the other of the movable member and the rotating member is provided with a protrusion. For example, the first groove and the second groove can be provided on the movable member, and the protrusion can be provided on the rotating member; or the protrusion can be provided on the movable member, and the first groove and the second groove can be provided on the rotating member.

[0040] When the arm 16 rotates from the unfolded position to the folded position, the protrusion first gradually moves away from the second groove until the contact point between the movable member and the rotating member reaches the highest point of the protrusion. In this process, the protrusion presses the movable member to move away from the rotating member along the axial direction of the fixed shaft, and the elastic body is compressed. The arm 16 continues to rotate towards the folded position, and the contact point between the rotating member and the movable member avoids the highest point of the protrusion until the arm 16 rotates to the folded position. At this time, the protrusion cooperates with the first groove, and in this process, the elastic body is released, thereby providing elastic force for the protrusion to slide into the first groove, so that the arm 16 automatically rotates to the folded position, thereby effectively improving the operation convenience of the user. In addition, when the arm 16 is in the folded position, the cooperation between the protrusion and the first groove can also limit the arm 16 in the folded position, so as to avoid damage to the arm 16 caused by self-rotation of the arm 16, thereby effectively improving the reliability of the unmanned aerial vehicle 1.

[0041] When the arm 16 rotates from the folded position to the unfolded position, the protrusion gradually moves away from the first groove until the contact point between the movable element and the rotating element reaches the highest point of the protrusion, in this process, the protrusion presses the movable element to move away from the rotating element in the axial direction of the fixed shaft, and the elastic body is compressed. The arm 16 continues to rotate to the unfolded position, and the contact point between the rotating element and the movable element avoids the highest point of the protrusion, until the arm 16 rotates to the unfolded position, at this time, the protrusion is matched with the second groove, in this process, the elastic body is released, so as to provide elastic force for the protrusion to slide into the second groove, so that the arm 16 is automatically rotated to the unfolded position, thereby effectively improving the operation convenience of the user. In addition, when the arm 16 is in the unfolded position, the protrusion matched with the second groove can also realize the limiting of the arm 16 in the unfolded position, avoiding the rotation of the arm 16 affecting the normal flight of the unmanned aerial vehicle 1, thereby effectively improving the stability of the flight of the unmanned aerial vehicle 1.

[0042] In combination Figure 5 and Figure 6 In an embodiment, the side wall of the fuselage body 11 includes a first side wall 111 and a second side wall facing away from each other, the first side wall 111 is provided with a first circuit board module 101, for example, the first circuit board module 101 can be a mainboard module of the unmanned aerial vehicle 1. It can be understood that the mainboard module refers to the control board of the unmanned aerial vehicle 1, which is the control center of the unmanned aerial vehicle 1 and is composed of central processing units, memories, input / output interfaces and other electronic devices. The second side wall is provided with a second circuit board module 102, for example, the second circuit board module 102 can be a video transmission board module. It can be understood that the video transmission board module is a circuit board for image transmission and video monitoring of the unmanned aerial vehicle 1.

[0043] The fuselage body 11 is provided with a first air duct structure, which is used for heat dissipation of the first circuit board module 101, thereby effectively improving the reliability of the first circuit board module 101, and further improving the reliability of the operation of the unmanned aerial vehicle 1.

[0044] In another embodiment, the fuselage body 11 is provided with a second air duct structure, which is used for heat dissipation of the second circuit board module 102, thereby effectively improving the reliability of the first circuit board module 101, and further improving the reliability of the operation of the unmanned aerial vehicle 1.

[0045] In still another embodiment, the fuselage body 11 is provided with a first air duct structure, which is used for heat dissipation of the first circuit board module 101, and the fuselage body 11 is provided with a second air duct structure, which is used for heat dissipation of the second circuit board module 102. By adopting such a setting form, the reliability of the operation of the unmanned aerial vehicle 1 can be further improved.

[0046] In an embodiment, a plurality of mounting grooves 14 are arranged along the circumference of the fuselage body 11, and each mounting groove 14 is arranged with a machine arm 16 and rotationally connected therewith. In this way, the take-off speed of the unmanned aerial vehicle 1 and the stability of the unmanned aerial vehicle 1 in flight are effectively improved.

[0047] In combination Figure 4 , the plurality of mounting grooves 14 include a first mounting groove 141 and a second mounting groove arranged on both sides of the first side wall 111. The second groove side wall of the first mounting groove 141 and the first groove side wall 142 of the second mounting groove are opposite, and the first air outlet structure 143 is arranged on the second groove side wall of the first mounting groove 141 and the first groove side wall 142 of the second mounting groove. The top wall 112 of the fuselage body 11 is provided with a first air inlet 1121 corresponding to the position of the first circuit board module 101, and the first side wall 111 is provided with a first air outlet 1111. The first air outlet structure 143, the first air inlet 1121 and the first air outlet 1111 jointly constitute a first air duct structure.

[0048] When the unmanned aerial vehicle 1 is in a flight state, the airflow enters from the first air outlet structure 143 on the second groove side wall of the first mounting groove 141 and flows out from the first air outlet structure 143 on the first groove side wall 142 of the second mounting groove; or the airflow enters from the first air outlet structure 143 on the first groove side wall 142 of the second mounting groove and flows out from the first air outlet structure 143 on the second groove side wall of the first mounting groove 141. In this way, the heat on the first circuit board module 101 can be taken away. When the unmanned aerial vehicle 1 is in a hovering state and a flight state, under the rotation of the rotor 161 on the machine arm 16, negative pressure will be generated at the first side wall 111, so that the airflow enters from the first air inlet 1121 and flows out from the first air outlet 1111. In this way, the heat on the first circuit board module 101 can also be taken away, thereby improving the reliability of the first circuit board module 101. With such a setting form, the structure of the first air duct structure is simple and easy to process.

[0049] In another embodiment, a plurality of mounting grooves 14 are arranged along the circumference of the fuselage body 11, and each mounting groove 14 is arranged with a machine arm 16 and rotationally connected therewith. In this way, the take-off speed of the unmanned aerial vehicle 1 and the stability of the unmanned aerial vehicle 1 in flight are effectively improved.

[0050] The plurality of mounting grooves 14 include a third mounting groove and a fourth mounting groove arranged on both sides of the second side wall. The second groove side wall of the third mounting groove and the first groove side wall 142 of the fourth mounting groove are opposite, and the second air outlet structure is arranged on the second groove side wall of the third mounting groove and the first groove side wall 142 of the fourth mounting groove. The top wall 112 of the fuselage body 11 is provided with a second air inlet corresponding to the position of the second circuit board module 102, and the second side wall is provided with a second air outlet. The second air outlet structure, the second air inlet and the second air outlet jointly constitute a second air duct structure.

[0051] When the unmanned aerial vehicle 1 is in the flying state, the airflow enters from the second air outlet structure on the second slot side wall of the third installation slot and flows out from the second air outlet structure on the first slot side wall 142 of the fourth installation slot; or the airflow enters from the second air outlet structure on the first slot side wall 142 of the fourth installation slot and flows out from the second air outlet structure on the second slot side wall of the third installation slot. In this way, the heat on the second circuit board module 102 can be taken away. When the unmanned aerial vehicle 1 is in the hovering state and the flying state, under the rotation of the rotor 161 on the arm 16, negative pressure will be generated at the second side wall, so that the airflow enters from the second air inlet and flows out from the second air outlet, so that the heat on the second circuit board module 102 can also be taken away, thereby improving the reliability of the second circuit board module 102. With such a setting form, the structure of the second air duct structure is simple and easy to process.

[0052] In combination Figure 4 In still another embodiment, a plurality of installation slots 14 are arranged along the circumference of the fuselage body 11, the plurality of installation slots 14 including first installation slots 141 and second installation slots located on both sides of the first side wall 111, and third installation slots and fourth installation slots located on both sides of the second side wall. The second slot side wall of the first installation slot 141 and the first slot side wall 142 of the second installation slot are opposite to each other, and the second slot side wall of the first installation slot 141 and the first slot side wall 142 of the second installation slot are provided with first air outlet structures 143. The top wall 112 of the fuselage body 11 is provided with a first air inlet 1121 corresponding to the position of the first circuit board module 101, and the first side wall 111 is provided with a first air outlet 1111. The first air outlet structure 143, the first air inlet 1121 and the first air outlet 1111 jointly constitute a first air duct structure. The second slot side wall of the third installation slot and the first slot side wall 142 of the fourth installation slot are opposite to each other, and the second slot side wall of the third installation slot and the first slot side wall 142 of the fourth installation slot are provided with second air outlet structures. The top wall 112 of the fuselage body 11 is provided with a second air inlet corresponding to the position of the second circuit board module 102, and the second side wall is provided with a second air outlet. The second air outlet structure, the second air inlet and the second air outlet jointly constitute a second air duct structure.

[0053] With such a setting form, the reliability of the first circuit board module 101 and the second circuit board module 102 can be improved, and the structure of the first air duct structure and the second air duct structure is simple and easy to process.

[0054] In combination Figure 4In an embodiment, the unmanned aerial vehicle 1 further comprises a landing gear 17 arranged at the bottom 113 of the body 11. The landing gear 17 comprises an unfolded state and a closed state. For example, when the unmanned aerial vehicle 1 lands, the landing gear 17 is controlled to be in the unfolded state, and when the unmanned aerial vehicle 1 takes off, the landing gear 17 is controlled to be in the closed state. When the landing gear 17 is in the unfolded state, the body 11 can be supported, so that the second camera 13 at the bottom 113 of the body 11 is effectively prevented from being damaged when the bottom 113 of the body 11 contacts a landing surface, and the reliability and the shooting effect of the unmanned aerial vehicle 1 are further improved. When the landing gear 17 is in the closed state, the landing gear 17 is clamped on the body 11, so that the resistance of the landing gear 17 during flight is effectively reduced, and the flexibility of the unmanned aerial vehicle 1 during flight is improved.

[0055] In combination Figure 5 and Figure 6 In an embodiment, the body 11 comprises an internal cavity 115, and the unmanned aerial vehicle 1 further comprises a battery module. The battery module can provide power for the unmanned aerial vehicle 1 to ensure normal flight of the unmanned aerial vehicle 1. The battery module is arranged in the cavity 115, and the center of gravity of the battery module is located at the center of the cavity 115. In this way, the stability of the battery module during fixation is effectively improved, and the stability of the unmanned aerial vehicle 1 during flight is further improved.

[0056] In combination Figure 5 In an embodiment, the top 114 of the body 11 comprises opposite first and second side edges 116 and 117, and the unmanned aerial vehicle 1 further comprises a positioning module 103, a control module 104, and an obstacle avoidance module 105. The positioning module 103 can comprise, for example, a global positioning system (GPS), an inertial measurement unit (IMU), and a magnetometer. The control module 104 can comprise, for example, an electronic speed controller (ESC), which is an electronic element for adjusting the speed of a motor of the unmanned aerial vehicle 1. The obstacle avoidance module 105 can comprise, for example, a time of flight (TOF) module and a binocular vision inertial module. The TOF module is a technology for measuring the distance between an object and a device. When the binocular vision inertial module is installed, the baseline of the binocular vision inertial module is greater than 35 mm to improve the accuracy of the binocular vision inertial module.

[0057] The positioning module 103 is arranged on the top 114 of the fuselage body 11 close to the first side edge 116, so as to avoid the positioning module 103 from being blocked and thus interfering with the positioning, thereby facilitating the improvement of the positioning performance of the unmanned aerial vehicle 1. The control module 104 is arranged on the top 114 of the fuselage body 11 close to the second side edge 117, so as to be arranged away from the positioning module 103 on the top 114 of the fuselage body 11, thereby avoiding the interference with the positioning module 103 and further improving the positioning performance of the unmanned aerial vehicle 1. The obstacle avoidance module 105 is arranged on the bottom 113 of the fuselage body 11, so as to facilitate the measurement and avoidance of the obstacle avoidance module 105 to the obstacles, thereby effectively improving the obstacle avoidance performance.

[0058] The unmanned aerial vehicle 1 in the embodiment can improve the production convenience and the maintainability through the modular design, and the functional modules can be reused.

[0059] In combination Figure 6 In an embodiment, the unmanned aerial vehicle 1 further comprises an interface assembly 106 and a storage member. The interface assembly 106, for example, comprises a USB interface and a circuit board electrically connected with the USB interface. The interface assembly 106 and the storage member are both arranged on the bottom 113 of the fuselage body 11, so as to facilitate the data transmission between the unmanned aerial vehicle 1 and external devices.

[0060] Other embodiments of the present disclosure will be apparent to those skilled in the art from consideration of the specification and practice of the application disclosed herein. This application is intended to cover any variations, uses or adaptations of the present disclosure following, in general, the principles of the present disclosure and including such departures from the present disclosure that come within known

[0061] It should be understood that the present disclosure is not limited to the precise structures herein described and illustrated in the drawings, and that various modifications and changes can be made without departing from the scope thereof. The scope of the present disclosure is limited only by the claims that follow.

Claims

1. A drone, characterized in that, The unmanned aerial vehicle comprises: a fuselage body, at least one lens being arranged on the fuselage body, the effective field of view angle of the lens being greater than 180°; at least one arm being arranged on the fuselage body, the arm being capable of switching between an unfolded position and a folded position, in the unfolded position, the arm is located outside the effective field of view angle, in the folded position, the arm is used for supporting the fuselage body.

2. The drone of claim 1, wherein, The at least one lens comprises a first lens and a second lens, the first lens is arranged on the top of the fuselage body, the second lens is arranged on the bottom of the fuselage body, the effective field of view angle of the first lens and the effective field of view angle of the second lens partially overlap, the arm is rotationally connected with the side wall of the fuselage body.

3. The drone of claim 2, wherein, The side wall of the fuselage body is provided with a mounting groove corresponding to each arm, the arm is rotationally connected with the mounting groove through a rotating shaft assembly, in the folded position, at least part of the structure of the arm is located in the mounting groove.

4. The drone of claim 3, wherein, The arm comprises opposite first and second ends, the first end of the arm is arranged in the mounting groove, and the first end of the arm is provided with a mounting hole, the second end of the arm is provided with a rotor; The rotating shaft assembly comprises a fixed shaft and a rotating part, the rotating part is sleeved outside the fixed shaft and is rotationally connected with the fixed shaft, the mounting groove comprises opposite first and second groove side walls, the fixed shaft passes through the first groove side wall and the mounting hole in sequence from the outside of the first groove side wall and is fixedly connected with the second groove side wall, and the rotating part is fixedly connected with the mounting hole in the circumferential direction.

5. The drone of claim 4, wherein, An active part and an elastic body are arranged at one axial end of the rotating part, the active part is located between the elastic body and the rotating part, the active part is fixedly connected with the fixed shaft in the circumferential direction, and the active part and the elastic body are capable of moving in the axial direction of the fixed shaft; One of the active part and the rotating part is provided with a first groove and a second groove, the other of the active part and the rotating part is provided with a protrusion, in the folded position, the protrusion is matched with the first groove, in the unfolded position, the protrusion is matched with the second groove, and the elastic body is used for providing elastic force to the protrusion sliding into the first groove or the second groove.

6. The drone of claim 4, wherein, The side wall of the fuselage body comprises opposite first and second side walls, the first circuit board module is arranged on the first side wall, and the second circuit board module is arranged on the second side wall; The fuselage body is provided with a first air duct structure for dissipating heat of the first circuit board module, and / or the fuselage body is provided with a second air duct structure for dissipating heat of the second circuit board module.

7. The drone of claim 6, wherein, A plurality of installation slots are arranged along the circumference of the fuselage body, the plurality of installation slots include a first installation slot and a second installation slot located on both sides of the first side wall, the second slot side wall of the first installation slot and the first slot side wall of the second installation slot are opposite, the first slot side wall of the second slot side wall of the first installation slot and the second installation slot are provided with a first air port structure, the top wall of the fuselage body is provided with a first air inlet corresponding to the position of the first circuit board module, the first side wall is provided with a first air outlet, and the first air port structure, the first air inlet and the first air outlet jointly constitute the first air duct structure; and / or, A plurality of installation slots are arranged along the circumference of the fuselage body, the plurality of installation slots include a third installation slot and a fourth installation slot located on both sides of the second side wall, the second slot side wall of the third installation slot and the first slot side wall of the fourth installation slot are opposite, the second slot side wall of the third installation slot and the first slot side wall of the fourth installation slot are provided with a second air port structure, the top wall of the fuselage body is provided with a second air inlet corresponding to the position of the second circuit board module, the second side wall is provided with a second air outlet, and the second air port structure, the second air inlet and the second air outlet jointly constitute the second air duct structure.

8. The drone according to any one of claims 1 to 7, characterized in that, The unmanned aerial vehicle further comprises: A landing gear arranged at the bottom of the fuselage body, the landing gear comprising an expanded state and a closed state, in the expanded state, the landing gear is used to support the fuselage body, and in the closed state, the landing gear is clamped on the fuselage body.

9. The drone according to any one of claims 1 to 7, wherein, The inside of the fuselage body is provided with a cavity, and the unmanned aerial vehicle further comprises: A battery module arranged in the cavity, and the center of gravity of the battery module is located at the center of the cavity.

10. The drone of any one of claims 1 to 7, wherein, The top of the fuselage body comprises opposite first and second side edges, and the unmanned aerial vehicle further comprises: A positioning module arranged on the top of the fuselage body near the first side edge; A control module arranged on the top of the fuselage body near the second side edge; An obstacle avoidance module arranged at the bottom of the fuselage body.

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