Unmanned aerial vehicle

Abstract

The unmanned aerial vehicle comprises a vehicle body and a vortex generator, the vehicle body is provided with a left side wall, a right side wall and a top side wall, the left side wall and the right side wall are oppositely arranged, the top side wall is connected with the top side of the left side wall and the top side of the right side wall, and the surface of the top side wall is arranged in a streamline mode. The vortex generators are arranged on the left side wall and the right side wall respectively. According to the technical scheme, differential pressure resistance formed by the top side wall of the fuselage and the bottom side wall of the fuselage can be reduced, and therefore the flight speed of the unmanned aerial vehicle is increased.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles, in particular to a unmanned aerial vehicle. Background Art

[0002] A drone is an unmanned aerial vehicle controlled by a radio remote control device or a self-contained program control device. Currently, drones are widely used in aerial photography, agriculture, plant protection, micro selfies, express delivery, disaster relief, wildlife observation, infectious disease monitoring, surveying and mapping, news reporting, power inspection, disaster relief, film and television shooting, creating romance and many other fields.

[0003] However, the drones currently on the market generally tilt forward when flying. At this time, the tail of the fuselage is higher than the head of the fuselage, the top surface of the fuselage is the windward side, and the bottom surface of the fuselage is on the leeward side. Then a strong pressure difference resistance will be formed between the top surface and the back surface, causing great forward resistance to the drone flight, thereby affecting the flight speed of the aircraft. Utility Model Content

[0004] The main purpose of the utility model is to provide a drone, aiming to reduce the pressure difference resistance between the top surface and the back surface of the drone.

[0005] To achieve the above-mentioned purpose, the drone proposed in the utility model comprises:

[0006] A fuselage, the fuselage having a left side wall and a right side wall arranged opposite to each other, and a top side wall connecting the top sides of the left side wall and the right side wall, wherein a surface of the top side wall is arranged in a streamlined shape; and

[0007] Vortex generators are respectively provided on the left side wall and the right side wall.

[0008] Optionally, the vortex generator comprises at least one vortex generating protrusion; and / or

[0009] The vortex generator includes at least one vortex generating groove.

[0010] Optionally, the vortex generating protrusion is arranged in a long strip shape, and the vortex generating protrusion gradually inclines toward the top of the fuselage in the direction close to the head of the fuselage.

[0011] Optionally, when the UAV is in the hovering state, the angle between the length extension direction of the vortex generating protrusion and the horizontal plane is in the range of 35° to 50°.

[0012] Optionally, the vortex generating protrusion is crescent-shaped.

[0013] Optionally, the vortex generating protrusion is detachably connected to the left side wall, and the vortex generating protrusion is detachably connected to the right side wall.

[0014] Optionally, the eddy current generating protrusion is magnetically connected to the left side wall, and the eddy current generating protrusion is magnetically connected to the right side wall.

[0015] Optionally, the vortex generating protrusion is rotationally connected to the left side wall, and the vortex generating protrusion is rotationally connected to the right side wall.

[0016] Optionally, the drone further comprises a negative pressure heat dissipation structure, wherein the negative pressure heat dissipation structure has an exhaust hole, and the exhaust hole is arranged on the end surface of the end of the vortex generating protrusion away from the head of the fuselage.

[0017] Optionally, the fuselage includes an installation cavity, which is used for installing a heat-generating component of the drone, and the negative pressure heat dissipation structure also includes a heat dissipation channel connected to the exhaust hole, and the heat dissipation channel is connected to the installation cavity.

[0018] Optionally, the fuselage includes a front side wall connected to the left side wall and the right side wall, the front side wall is provided with an air inlet connected to a heat dissipation channel, and the front side wall is used for the gimbal to be installed.

[0019] Optionally, the UAV further comprises a wing provided on the fuselage, and the length of the vortex generator is smaller than the length of the wing; or

[0020] The length of the vortex generator is equal to the length of the wing; or

[0021] The length of the vortex generator is greater than the length of the wing; and / or

[0022] The width of the vortex generator is less than the width of the wing; or

[0023] The width of the vortex generator is equal to the width of the wing; or

[0024] The width of the vortex generator is greater than the width of the wing.

[0025] Optionally, the drone also includes a first front arm and a first rear arm spaced apart on the left side wall, and a second front arm and a second rear arm spaced apart on the right side wall, one vortex generator is disposed between the first front arm and the first rear arm, and the other vortex generator is disposed between the second front arm and the second rear arm.

[0026] The above-mentioned drone has at least the following beneficial effects:

[0027] The technical solution of the utility model is that the fuselage has two relatively arranged left and right walls; the left and right walls are respectively provided with vortex generators. Specifically, since the vortex generators are respectively provided on the relatively arranged left and right walls, when the air flows through the fuselage, the vortex generators can destroy the laminar air attached to the left and right walls of the fuselage, thereby causing the air flowing through the left and right walls of the fuselage to generate vortices. It can be seen that the vortices generated on the back of the fuselage in the present solution will occur in the left and right walls of the fuselage in advance, thereby generating negative pressure on the side of the fuselage, thereby reducing the pressure difference resistance formed by the top side wall and the bottom side wall of the fuselage, so as to increase the flight speed of the UAV. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] In order to more clearly illustrate the embodiments of the utility model 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 described below are only some embodiments of the utility model. For ordinary technicians in this field, other drawings can be obtained based on the structures shown in these drawings without paying creative work.

[0029] Figure 1 This is a schematic structural diagram of a first perspective of an embodiment of the utility model drone;

[0030] Figure 2 It is a partial structural schematic diagram of the utility model UAV;

[0031] Figure 3 for Figure 2 A partial enlarged view of the vortex generator at A in the middle;

[0032] Figure 4 This is a schematic diagram of the structure of the drone of the utility model from a second viewing angle;

[0033] Figure 5 The figure is a schematic diagram of the structure of the vortex generator of the UAV of the utility model.

[0034] Description of Figure Numbers:

[0035] Label name Label name 100 body 300 Exhaust Hole 110 Left wall 400 PTZ 120 Top side wall 500 First front arm 130 Front side wall 600 First rear arm 200 Vortex generator 700 Second front arm 210 Eddy current bulge 800 Second rear arm

[0036] The realization of the purpose, functional features and advantages of the utility model will be further explained in conjunction with embodiments and with reference to the accompanying drawings. DETAILED DESCRIPTION

[0037] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments of the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0038] It should be noted that all directional indications in the embodiments of the present invention (such as up, down, left, right, front, back...) are only used to explain the relative position relationship, movement status, etc. between the components under a certain specific posture (as shown in the accompanying drawings). If the specific posture changes, the directional indication will also change accordingly.

[0039] In the present invention, unless otherwise clearly specified and limited, the terms "connection", "fixation", etc. should be understood in a broad sense. For example, "fixation" can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0040] In addition, if there are descriptions involving "first", "second", etc. in the embodiments of the utility model, the descriptions of "first", "second", etc. are only used for descriptive purposes and cannot be understood as indicating or implying their relative importance or implicitly indicating the number of technical features indicated. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of the features. In addition, the meaning of "and / or" appearing in the full text includes three parallel schemes. Taking "A and / or B" as an example, it includes scheme A, or scheme B, or a scheme that satisfies both A and B. In addition, the technical solutions between the various embodiments can be combined with each other, but it must be based on the ability of ordinary technicians in this field to implement. When the combination of technical solutions is contradictory or cannot be implemented, it should be deemed that such a combination of technical solutions does not exist and is not within the scope of protection required by the utility model.

[0041] The utility model provides a drone.

[0042] Reference Figures 1 to 3 In one embodiment of the utility model, the drone includes a fuselage 100 and a vortex generator 200. The fuselage 100 has two left side walls 110 and a right side wall that are oppositely arranged; the left side wall 110 and the right side wall are respectively provided with a vortex generator 200.

[0043] In the prior art, the left and right sides of a drone are generally smooth surfaces. When the drone is flying, the head of the drone is low and the tail is high, and the air is tightly attached to the left and right sides of the fuselage in a laminar flow. When the air flows over the left and right sides of the fuselage and flows to the back of the fuselage, vortices are generated on the back due to the lack of attached sides, thereby generating negative pressure on the back of the fuselage, and the air on the front of the fuselage is compressed, so that the front and rear pressure difference of the drone increases, thereby hindering the flight of the drone. In the present solution, since there are vortex generators 200 on the relatively arranged left and right walls, when air flows through the fuselage 100, the vortex generators 200 can destroy the laminar air attached to the left and right walls of the fuselage 100, thereby causing vortices to be generated in the air flowing through the left and right walls of the fuselage 100. It can be seen that the present solution causes the vortices generated on the back of the fuselage 100 to occur on the left and right walls of the fuselage 100 in advance, thereby generating negative pressure on the sides of the fuselage, thereby reducing the pressure difference resistance formed by the top side wall and the bottom side wall of the fuselage 100 (similar to the principle of the convex and concave surface of a golf ball), thereby increasing the flight speed of the drone.

[0044] Moreover, the present solution has vortex generators 200 on the left side wall 110 and the right side wall, which can balance the weight of the UAV body and balance the airflow on the left and right sides of the fuselage during flight, thereby ensuring a smooth flight of the UAV and increasing safety.

[0045] It should be noted that the fuselage 100 also has a top side wall 120 connecting the left side wall 110 and the top side of the right side wall. The surface of the top side wall 120 is streamlined. The top side wall 120 can better guide the air flow when the drone is flying, thereby reducing the resistance of the fuselage 100 and increasing the flight speed of the drone.

[0046] The left side wall 110 and the right side wall are the sides of the fuselage 100 , and the top side wall 120 is the top surface, that is, the windward surface, of the fuselage 100 . The bottom side wall of the fuselage 100 is arranged opposite to the top side wall 120 of the fuselage 100 .

[0047] Furthermore, in one embodiment, the vortex generator 200 includes at least one vortex generating protrusion 210. The vortex generating protrusion 210 has a simple structure and is easy to process and manufacture. The vortex generating protrusion 210 can destroy the air flow attached to the left side wall 110 and the right side wall of the fuselage 100, so that the air flow is not easy to tightly adhere to the left side wall 110 and the right side wall of the fuselage 100, thereby causing the air flowing through the left side wall 110 and the right side wall of the fuselage 100 to generate vortices, thereby reducing the pressure difference resistance between the windward side of the drone fuselage 100 and the back side of the fuselage 100, which is beneficial to increasing the flight speed of the drone.

[0048] In this solution, each vortex generator 200 includes two vortex generating protrusions 210 arranged at intervals on the left side wall 110 or the right side wall, and the two vortex generating protrusions 210 can ensure the vortex size of the vortex, thereby facilitating the pressure difference resistance between the windward side of the drone fuselage 100 and the back side of the fuselage 100. Of course, in other embodiments, each vortex generator 200 may also include only one vortex generating protrusion 210 arranged on the left side wall 110 or the right side wall.

[0049] Specifically, the vortex generating protrusion 210 is arranged in a long strip shape, and the vortex generating protrusion 210 gradually tilts toward the top of the fuselage 100 in the direction close to the head of the fuselage 100; it can be understood that when the UAV flies forward, it is generally in a state of head low and tail high. The vortex generating protrusion 210 is tilted. When the UAV flies forward, the vortex generating protrusion 210 can tend to be perpendicular to the flight direction, that is, the vortex generating protrusion 210 can tend to be parallel to the horizontal plane, which can reduce the vortex generating protrusion 210. 0, thereby reducing the resistance of the UAV flight; and the air is tightly attached to and flows along the left and right sides of the fuselage in a laminar flow. When the laminar air encounters the vortex generating protrusion 210, the vortex generating protrusion 210 will destroy the laminar air, so that the air flowing through the left side wall 110 and the right side wall of the fuselage 100 will generate vortices, so as to generate negative pressure on the side of the fuselage 100, thereby reducing the pressure difference resistance formed by the top side wall of the fuselage 100 and the bottom side wall of the fuselage 100, so as to increase the flight speed of the UAV.

[0050] It should be noted that when the UAV is in high-speed flight, that is, the flight speed is greater than 75 km / h, the UAV tilts forward. At this time, the tail of the fuselage is higher than the head of the fuselage, and the vortex generating protrusion 210 is parallel to the horizontal plane. This can better destroy the air flow attached to the left side wall 110 and the right side wall of the fuselage 100, so that the air flow is not easy to tightly adhere to the left side wall 110 and the right side wall of the fuselage 100, thereby causing the air flowing through the left side wall 110 and the right side wall of the fuselage 100 to generate vortices, thereby reducing the pressure difference resistance between the windward side of the UAV fuselage 100 and the back side of the fuselage 100.

[0051] Among them, in this solution, the vortex generating protrusion 210 is parallel to the horizontal plane, which means that the vortex generating protrusion 210 is slightly inclined relative to the horizontal plane (the angle between them is not greater than 5°) or the vortex generating protrusion 210 is parallel to the horizontal plane.

[0052] Optionally, when the UAV is in a hovering state, the angle between the length extension direction of the vortex generating protrusion 210 and the horizontal plane is in the range of 35° to 50°. This can better enable the airflow passing through the left wall 110 and the right wall to generate vortices, and can reasonably reduce the pressure difference resistance between the windward side of the fuselage 100 and the back side of the fuselage 100, avoiding the generation of vortices that are too large or too small.

[0053] Furthermore, the vortex generating protrusion 210 is crescent-shaped; when the drone is in flight, the airflow generates a vortex when passing through the crescent-shaped vortex generating protrusion 210 from the top side wall 120 of the fuselage 100. At this time, the upper and lower surfaces of the vortex generating protrusion 210 will form different flow velocities. When the airflow passes through the upper surface of the vortex generating protrusion 210, the flow velocity is large and the pressure is small. When the airflow passes through the lower surface of the vortex generating protrusion 210, the flow velocity is small and the pressure is large. Therefore, the drone will have an upward force, that is, lift, which is equivalent to adding fixed small wings to the left side wall 110 and the right side wall of the fuselage 100 to the drone, thereby generating lift and extending the endurance. Secondly, the crescent-shaped vortex generating protrusion 210 can guide the airflow, thereby reducing the resistance of the fuselage 100.

[0054] Optionally, in one embodiment, the vortex generating protrusion 210 is detachably connected to the left side wall 110, and the vortex generating protrusion 210 is detachably connected to the right side wall; in this way, when storing the drone, the vortex generating protrusion 210 can be removed and then stored, which is conducive to reducing the size of the drone and convenient for users to store; and if the vortex generating protrusion 210 is accidentally damaged, the vortex generating protrusion 210 can also be replaced in a detachable manner, which can reduce costs. Furthermore, the detachable vortex generating protrusion 210 can be installed on the left side wall 110 when the user needs to increase the flight speed of the drone. When the user does not need to increase the flight speed of the drone, for example but not limited to when only low-speed flight is required throughout the entire process, the vortex generating protrusion 210 can be not installed, thereby adapting to different users or different scene requirements for drone flight.

[0055] Furthermore, in the first embodiment, the eddy current generating protrusion 210 is magnetically connected to the left side wall 110, and the eddy current generating protrusion 210 is magnetically connected to the right side wall. This is because the magnetic connection is convenient and fast, and does not require precise alignment. It only relies on the automatic attraction of the magnet, thereby saving time and speeding up the installation. In addition, the connection is reliable and stable, with a long service life, and the installation method is flexible, and can be directly inserted, vertically inserted, side-sliding, and in any direction. It can be seen that the use of magnetic connection can improve the assembly and disassembly efficiency of the drone. Of course, the utility model is not limited to this. In other embodiments, the eddy current generating protrusion 210 and the left side wall 110 can also be snap-connected, and the eddy current generating protrusion 210 and the right side wall can be snap-connected.

[0056] Optionally, in a second embodiment, the vortex generating protrusion 210 is rotatably connected to the left side wall 110, and the vortex generating protrusion 210 is rotatably connected to the right side wall. In this way, the user can adjust the inclination angle of the vortex generating protrusion 210 to adapt to different users or different scene requirements for drone flight. Secondly, the vortex generating protrusion 210 is rotatably arranged on the left side wall 110, and the vortex generating protrusion 210 is rotatably arranged on the right side wall. When the drone is stored, the vortex generating protrusion 210 can be rotated to a state of being in contact with the left side wall 110 or the right side wall, thereby reducing the storage volume of the drone.

[0057] Reference Figures 3 to 5 Optionally, the drone also includes a negative pressure heat dissipation structure, and the exhaust hole 300 of the negative pressure heat dissipation structure is arranged on the end face of the end of the vortex generating protrusion 210 away from the head of the fuselage 100, and is arranged close to the corresponding left wall 110 or right wall; during the flight of the drone, since the exhaust hole 300 is located on the back side of the vortex generating protrusion 210, the vortex generating protrusion 210 can block its airflow from directly flowing to the exhaust hole 300, and vortices will be generated at the left wall 110 and the right wall near the end of the vortex generating protrusion 210. Under the action of the gas vortex, negative pressure will be formed at the exhaust hole 300. Since the atmospheric pressure in the fuselage is greater than the atmospheric pressure of the exhaust hole 300, a strong suction force is generated, so that the air inside the fuselage 100 is sucked out from the exhaust hole 300 on the side of the fuselage 100, thereby playing a role in cooling the drone. Such a negative pressure heat dissipation structure can reduce structures such as cooling fans, which is beneficial to reducing the weight of the drone, thereby reducing the energy consumption of the drone, and thus improving the endurance of the drone.

[0058] It should be noted that the exhaust hole 300 is set corresponding to the left side wall 110 or the right side wall, which means that the exhaust hole 300 on the vortex generating protrusion 210 is set close to the side wall on which the vortex generating protrusion 210 is installed, that is, the exhaust hole 300 on the vortex generating protrusion 210 on the left side wall 110 is set close to the left side wall 110, and the exhaust hole 300 on the vortex generating protrusion 210 on the right side wall is set close to the right side wall.

[0059] Optionally, the fuselage 100 includes an installation cavity, which is used for installing the heating components of the drone. The negative pressure heat dissipation structure also includes a heat dissipation channel connected to the exhaust hole 300, and the heat dissipation channel is connected to the installation cavity; since the exhaust hole 300 is arranged on the end surface of the vortex generating protrusion 210 away from the end of the head of the fuselage 100, during the flight of the drone, the vortex generating protrusion 210 can block its airflow from directly flowing to the exhaust hole 300. During the flight of the drone, vortices will be generated at the vortex generating protrusion 210. Under the action of the gas vortex, negative pressure will be formed at the exhaust hole 300, causing the atmospheric pressure of the installation cavity and the heat dissipation channel inside the fuselage 100 to be greater than the atmospheric pressure of the exhaust hole 300, thereby generating a strong suction force at the exhaust hole 300, thereby accelerating the efficiency of hot air discharge from the installation cavity and the heat dissipation channel. Secondly, since heating devices such as circuit boards and / or batteries are installed in the installation cavity, the flowing air can be closer to the heat source, thereby accelerating the heat dissipation efficiency of the circuit boards and / or batteries. Of course, the present invention is not limited thereto, and in other embodiments, the heat dissipation channel may not be connected to the installation cavity.

[0060] Among them, the installation cavity is arranged inside the fuselage, and the heat-generating components include circuit boards, batteries, etc.

[0061] Furthermore, the fuselage 100 includes a front side wall 130 connected to the left side wall 110 and the right side wall, and the front side wall 130 is provided with an air inlet connected to the heat dissipation channel, and the front side wall 130 is used for the installation of the gimbal 400; that is, in this solution, the air inlet of the heat dissipation channel is arranged at the front end of the drone, and the airflow directly blows into the drone fuselage 100 from the front end during the flight of the drone, which can increase the efficiency of the normal temperature airflow entering the fuselage 100, thereby improving the heat dissipation efficiency of the drone. Of course, the utility model is not limited to this, and in other embodiments, the air inlet of the heat dissipation channel can also be arranged on the top side wall 120, the bottom side wall, the left side wall 110 or the right side wall.

[0062] Optionally, the vortex generator 200 includes at least one vortex generating groove; it can be understood that the vortex generating groove can destroy its boundary layer to generate vortex flow, thereby reducing the pressure difference resistance between the windward side of the UAV fuselage 100 and the back side of the fuselage 100.

[0063] It should be noted that, in the present embodiment, each vortex generator 200 includes two vortex generating grooves spaced apart on the left side wall 110, and the two vortex generating grooves can ensure the vortex size of the vortex, thereby facilitating the reduction of the pressure difference resistance between the windward side of the drone fuselage 100 and the back side of the fuselage 100. Of course, in other embodiments, each vortex generator 200 may also include only one vortex generating groove disposed on the left side wall 110.

[0064] Specifically, the vortex generating groove is arranged in the form of a long strip, and the length direction of the vortex generating groove gradually tilts toward the top of the fuselage 100 in the direction close to the head of the fuselage 100; it can be understood that the vortex generating groove is arranged in an inclined manner, which can better destroy the air flow attached to the left side wall 110 and the right side wall of the fuselage 100, so that the air flow is not easy to tightly adhere to the left side wall 110 and the right side wall of the fuselage 100, and then the air flowing through the left side wall 110 and the right side wall of the fuselage 100 generates vortices, which is conducive to reducing the pressure difference resistance of the windward surface of the fuselage 100 of the drone and the back of the fuselage 100. Of course, the utility model is not limited to this. In other embodiments, the vortex generating groove is arranged in the form of a long strip, and the length direction of the vortex generating groove extends in the horizontal direction.

[0065] It should be noted that when the UAV is in high-speed flight, that is, the flight speed is greater than 75km / h, the UAV tilts forward. At this time, the tail of the fuselage is higher than the head of the fuselage, and the vortex generating groove is parallel to the horizontal plane. This can better destroy the air flow attached to the left side wall 110 and the right side wall of the fuselage 100, so that the air flow is not easy to tightly adhere to the left side wall 110 and the right side wall of the fuselage 100, thereby causing the air flowing through the left side wall 110 and the right side wall of the fuselage 100 to generate vortices, thereby reducing the pressure difference resistance between the windward side of the UAV fuselage 100 and the back side of the fuselage 100.

[0066] Optionally, when the UAV is in a hovering state, the angle between the length extension direction of the vortex generating groove and the horizontal plane is in the range of 35° to 50°, so that the airflow flowing through the left wall 110 and the right wall can better reduce the pressure difference resistance between the windward side of the fuselage 100 and the back side of the fuselage 100.

[0067] The UAV also includes a wing provided on the fuselage 100. In one embodiment, the length of the vortex generator 200 is less than the length of the wing. It can be understood that the vortex generating protrusion 210 gradually tilts toward the top of the fuselage 100 in the direction close to the head of the fuselage 100. The longer the length of the vortex generator 200, the larger the windward surface of the vortex generator 200 during flight, and the greater the resistance of the UAV. Limiting the length of the vortex generator 200 to be less than the length of the wing can reduce the windward surface of the vortex generator 200 during flight while generating vortices in the airflow passing through the left side wall 110 and the right side wall, thereby reducing the resistance of the UAV and helping to increase the flight speed of the UAV.

[0068] In the second embodiment, the length of the vortex generator 200 may also be equal to the length of the wing, so that vortices can be generated on the side of the drone. In the third embodiment, the length of the vortex generator 200 may also be greater than the length of the wing, so that vortices can be generated on the side of the drone; no specific restrictions are made on the length of the vortex generator 200.

[0069] Furthermore, in one embodiment, the width of the vortex generator 200 is smaller than the width of the wing; it can be understood that when the UAV is flying, the vortex generator will face or be slightly inclined relative to the flight direction of the UAV, that is, the width of the vortex generator 200 corresponds to the width of the windward surface of the vortex generator. In this solution, the width of the vortex generator 200 is smaller than the width of the wing, which can generate vortices in the airflow passing through the left wall 110 and the right wall, while reducing the windward surface of the vortex generator 200 during flight, thereby reducing the resistance of the UAV, which is beneficial to increasing the flight speed of the UAV.

[0070] In the second embodiment, the width of the vortex generator 200 may also be equal to the width of the wing, so that vortices can be generated on the side of the drone. In the third embodiment, the width of the vortex generator 200 may also be greater than the width of the wing, so that vortices can be generated on the side of the drone; no specific limitation is made to the width of the vortex generator 200.

[0071] It should be noted that the wing refers to the entire combination of the arm, blades and power assembly.

[0072] Optionally, the drone further includes a first front arm 500 and a first rear arm 600 spaced apart on the left side wall 110, and a second front arm 700 and a second rear arm 800 spaced apart on the right side wall, a vortex generator 200 is disposed between the first front arm 500 and the first rear arm 600, and another vortex generator is disposed between the second front arm 700 and the second rear arm 800. Since the left side wall 110 between the first front arm 500 and the first rear arm 600 is relatively smooth, and the right side wall between the second front arm 700 and the second rear arm 800 is relatively smooth, the vortex generator 200 is disposed between the first front arm 500 and the first rear arm 600, and the vortex generator is disposed between the second front arm 700 and the second rear arm 800, so that the airflow flowing through the left side wall 110 and the right side wall can be better vortexed, thereby being able to reasonably reduce the pressure difference resistance between the windward side of the fuselage 100 and the back side of the fuselage 100.

[0073] The above description is only an optional embodiment of the utility model, and does not limit the patent scope of the utility model. All equivalent structural changes made by using the contents of the utility model specification and drawings under the utility model concept, or directly / indirectly used in other related technical fields are included in the patent protection scope of the utility model.

Claims

1. A drone, characterized in that: include: A fuselage, the fuselage having a left side wall and a right side wall arranged opposite to each other, and a top side wall connecting the left side wall and the right side wall, wherein a surface of the top side wall is arranged in a streamlined shape; and Vortex generators are respectively provided on the left side wall and the right side wall.

2. The drone according to claim 1, characterized in that: The vortex generator comprises at least one vortex generating protrusion; and / or The vortex generator includes at least one vortex generating groove.

3. The drone according to claim 2, characterized in that: The vortex generating protrusion is arranged in a long strip shape, and the vortex generating protrusion is gradually inclined toward the top of the fuselage in the direction close to the head of the fuselage.

4. The drone according to claim 3, characterized in that: When the UAV is in a hovering state, the angle between the length extension direction of the vortex generating protrusion and the horizontal plane is in the range of 35° to 50°.

5. The drone according to claim 3, characterized in that: The eddy current generating protrusion is crescent-shaped.

6. The drone according to claim 2, wherein: The vortex generating protrusion is detachably connected to the left side wall, and the vortex generating protrusion is detachably connected to the right side wall.

7. The drone according to claim 6, characterized in that: The eddy current generating protrusion is magnetically connected to the left side wall, and the eddy current generating protrusion is magnetically connected to the right side wall.

8. The drone according to claim 2, wherein: The vortex generating protrusion is rotationally connected to the left side wall, and the vortex generating protrusion is rotationally connected to the right side wall.

9. The drone according to claim 2, characterized in that: The drone also includes a negative pressure heat dissipation structure, which has an exhaust hole, and the exhaust hole is arranged at the end of the vortex generating protrusion in a direction away from the head of the fuselage.

10. The drone according to claim 9, characterized in that: The fuselage includes an installation cavity, which is used for installing a heat-generating component of the drone. The negative pressure heat dissipation structure also includes a heat dissipation channel connected to the exhaust hole, and the heat dissipation channel is connected to the installation cavity.

11. The drone according to claim 9, characterized in that: The fuselage includes a front side wall connected to the left side wall and the right side wall, the front side wall is provided with an air inlet connected to the heat dissipation channel, and the front side wall is used for the gimbal to be installed.

12. The drone according to claim 1, wherein: The UAV further comprises a wing provided on the fuselage, and the length of the vortex generator is smaller than the length of the wing; or The length of the vortex generator is equal to the length of the wing; or The length of the vortex generator is greater than the length of the wing; and / or The width of the vortex generator is less than the width of the wing; or The width of the vortex generator is equal to the width of the wing; or The width of the vortex generator is greater than the width of the wing.

13. The drone according to any one of claims 1 to 12, characterized in that: The drone also includes a first front arm and a first rear arm spaced apart on the left side wall, and a second front arm and a second rear arm spaced apart on the right side wall, one vortex generator is disposed between the first front arm and the first rear arm, and the other vortex generator is disposed between the second front arm and the second rear arm.

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