Unmanned aerial vehicle

Abstract

An unmanned aerial vehicle (100). The unmanned aerial vehicle (100) comprises a vehicle body (10) and two vehicle arm assemblies (20), the two vehicle arm assemblies (20) are symmetrically arranged on the two opposite sides of the vehicle body (10), each vehicle arm assembly (20) comprises a vehicle arm (21) and a power component (22) arranged on the vehicle arm (21), and each vehicle arm (21) comprises a first end (211) and a second end (212) which are oppositely arranged. Each arm (21) comprises a first end (211) and a second end (212), the first end (211) is rotatably connected with the body (10) so as to fold or unfold the arm (21) relative to the body (10), the second end (212) extends in a direction away from the first end (211), the plurality of power components (22) on each arm (21) are arranged at intervals along the extension direction of the first end (211) towards the second end (212), each power component (22) comprises a driving part (221) and a paddle (222) connected with the driving part (221), and the driving part (221) is mounted on the arm (21).

Description

Unmanned aerial vehicles Technical Field

[0001] The present application relates to the technical field of unmanned aerial vehicles, and in particular to an unmanned aerial vehicle. Background Art

[0002] With the rapid development of drone technology, multi-rotor drones have become a mainstream model and are widely used in an increasing number of fields. Multi-rotor drones offer high flight safety and reliability. However, they are typically driven by a single power unit mounted on a single arm, resulting in a complex structure, large size, and high production costs. Therefore, how to simplify the structure of multi-rotor drones while maintaining good overall performance, thereby improving their convenience and reducing production costs is a pressing issue.

[0003] Summary of the Invention

[0004] An embodiment of the present application provides an unmanned aerial vehicle.

[0005] The unmanned aerial vehicle of the embodiment of the present application includes a body and an arm assembly, there are two arm assemblies, the two arm assemblies are symmetrically arranged on opposite sides of the body, each arm assembly includes an arm and a power component arranged on the arm, the arm includes a first end and a second end arranged opposite to each other, the first end is rotatably connected to the body so that the arm can be folded or unfolded relative to the body, there are multiple power components on each arm, and the multiple power components are spaced apart along the extension direction of the first end toward the second end, the power component includes a driving member and a blade connected to the driving member, and the driving member is installed on the arm.

[0006] In the unmanned aerial vehicle (UAV) of the present application, two arms are symmetrically arranged on opposite sides of the UAV body, with each arm having multiple power components spaced apart along its extension. This arrangement of multiple power components on a single arm reduces the number of arms while maintaining good overall performance, thereby simplifying the overall structure of the UAV and reducing manufacturing costs. Furthermore, the arms are pivotally connected to the UAV body, enabling them to be folded or unfolded relative to the body, reducing the size of the UAV when stored and enhancing its flexibility and convenience.

[0007] In some embodiments, when the arms are deployed relative to the body, the power components located on the same arm are not collinear in the roll axis direction of the UAV.

[0008] In some embodiments, when the arm is unfolded relative to the body, on the same arm, the distance between the power component near the second end and the roll axis of the unmanned aerial vehicle is greater than the distance between the power component near the first end and the roll axis of the unmanned aerial vehicle.

[0009] In some embodiments, on the same aircraft arm, the plurality of blades are arranged on the same side of the aircraft arm; or

[0010] The plurality of blades are respectively arranged on two opposite sides of the machine arm.

[0011] In some embodiments, when a plurality of blades are arranged on the same side of the machine arm, the paddle disks formed by any two of the blades are spaced apart in the extension direction of the machine arm; and / or

[0012] When the paddle disks formed by the two adjacent blades are located in the same plane and overlap in the extension direction of the machine arm, the two adjacent blades are configured to rotate at the same speed in different time periods.

[0013] In certain embodiments, when the plurality of blades are respectively disposed on opposite sides of the machine arm, the paddle disks formed by two adjacent blades at least partially overlap along the rotation axis direction of the blades.

[0014] In some embodiments, on the same machine arm, one of the power components is disposed at the second end.

[0015] In certain embodiments, on the same machine arm, central axes of the two blades are parallel or form an acute angle.

[0016] In some embodiments, when the arms are folded relative to the body, at least one of the power components is located in the middle of the body.

[0017] In certain embodiments, when the arms are folded relative to the body, at least one of the power components is located in the middle of a side surface of the body.

[0018] In some embodiments, the arm is connected to the nose or tail of the body;

[0019] When the arm is connected to the nose portion, the arm can be folded toward the tail portion;

[0020] When the machine arm is connected to the tail portion, the machine arm can be folded toward the nose portion.

[0021] In certain embodiments, when the aircraft arm is folded, it can be folded downwardly along the direction of the aircraft body from the nose or the tail.

[0022] In certain embodiments, when the arms are unfolded relative to the body, the center of gravity of the UAV passes through a figure enclosed by all the power components on the two arms.

[0023] In some embodiments, each of the arms includes a first power component and a second power component, the first power component is arranged near the first end, and the second power component is arranged at the second end. When the arms are unfolded relative to the body, the center of gravity line of the unmanned aerial vehicle is located at or near the geometric center of the figure enclosed by the first power component and the second power component of the two arms.

[0024] In some embodiments, the line connecting the two first power components and the line connecting the two second power components are parallel to each other, and the distance in the direction of the roll axis of the body is L, and the distance between the center of gravity line and the geometric center line is D, where 0≤D≤0.15L.

[0025] In some embodiments, the arm assembly further includes a duct, and the blade is disposed in and connected to the duct;

[0026] When the aircraft arm is folded relative to the aircraft body, the radial direction of the duct is parallel to the yaw axis of the UAV.

[0027] In some embodiments, the unmanned aerial vehicle further includes a driving mechanism, wherein the driving mechanism is connected to the arm assembly, and the driving mechanism is used to drive the arm assembly to rotate so as to adjust a deployment angle of the arm assembly relative to the body.

[0028] In some embodiments, the driving mechanism includes a motor and a transmission member, and the motor and the transmission member cooperate to enable the arm to rotate during flight to adjust the deployment angle of the arm assembly relative to the body.

[0029] In some embodiments, the transmission member is a gear assembly.

[0030] In some embodiments, the driving mechanism is provided at the connection between the arm assembly and the body, and the driving mechanism is capable of driving the two arms to switch between a substantially parallel state and an extended angle to store or operate the arm assembly.

[0031] In some embodiments, the strength of the portion where the arm is connected to the body is greater than the strength of other portions.

[0032] In some embodiments, the UAV includes a landing gear connected to the arm or the body.

[0033] In certain embodiments, when the landing gear is connected to the arm, the landing gear is connected to a lower side of the second end, and one of the power components is mounted on an upper side of the second end.

[0034] In some embodiments, the unmanned aerial vehicle includes a spraying system, which includes a spray head and a fluid circuit assembly connected to the spray head, the spray head is disposed on the arm assembly, and the fluid circuit assembly is at least partially disposed on the body.

[0035] In some embodiments, the nozzle is provided on the machine arm and located between two adjacent power components; and / or,

[0036] The nozzle is arranged below the blade and located on the central axis of the blade.

[0037] In some embodiments, the arm assembly further includes a duct, the blade is disposed in and connected to the duct, and the nozzle is disposed on the duct.

[0038] In some embodiments, there are multiple nozzles on each duct, and the multiple nozzles are arranged at intervals along the circumference of the duct.

[0039] In some embodiments, the fluid circuit assembly includes a water tank and a water pump, the water pump is connected between the water tank and the nozzle, and the water tank and the water pump are both arranged on the machine body.

[0040] In some embodiments, the unmanned aerial vehicle includes a gimbal camera disposed on the nose side of the vehicle body.

[0041] Additional aspects and advantages of the present application will be given in part in the description below, and in part will become obvious from the description below, or will be learned through practice of the present application. BRIEF DESCRIPTION OF THE DRAWINGS

[0042] The above and / or additional aspects and advantages of the present application will become apparent and easily understood from the description of the embodiments in conjunction with the following drawings, in which:

[0043] FIG1 is a perspective schematic diagram of an unmanned aerial vehicle according to an embodiment of the present application when deployed;

[0044] FIG2 is a perspective schematic diagram of the unmanned aerial vehicle in FIG1 when folded;

[0045] FIG3 is a front view of the unmanned aerial vehicle in FIG1 ;

[0046] FIG4 is a top view of the UAV in FIG1 ;

[0047] FIG5 is a top view of the UAV in FIG2 ;

[0048] FIG6 is a perspective schematic diagram of another unfolded unmanned aerial vehicle according to an embodiment of the present application;

[0049] FIG7 is a front view of the UAV in FIG6;

[0050] FIG8 is a perspective schematic diagram of another unfolded unmanned aerial vehicle according to an embodiment of the present application;

[0051] FIG9 is a front view of the UAV in FIG8 ;

[0052] FIG10 is a left side view of the unmanned aerial vehicle in FIG1;

[0053] FIG11 is a perspective schematic diagram of another unfolded unmanned aerial vehicle according to an embodiment of the present application;

[0054] FIG12 is a perspective schematic diagram of the unmanned aerial vehicle in FIG11 when folded;

[0055] FIG13 is a perspective schematic diagram of another folded unmanned aerial vehicle according to an embodiment of the present application;

[0056] FIG14 is a perspective schematic diagram of another unfolded unmanned aerial vehicle according to an embodiment of the present application;

[0057] FIG15 is an enlarged schematic diagram of the UAV at position XV in FIG14;

[0058] FIG16 is a perspective schematic diagram of another unfolded unmanned aerial vehicle according to an embodiment of the present application;

[0059] FIG17 is a perspective schematic diagram of the unmanned aerial vehicle in FIG16 when folded;

[0060] FIG18 is a top view of the UAV in FIG16 ;

[0061] FIG19 is a perspective schematic diagram of another unfolded unmanned aerial vehicle according to an embodiment of the present application;

[0062] FIG20 is a perspective schematic diagram of the unmanned aerial vehicle in FIG19 when folded;

[0063] FIG21 is a top view of the UAV in FIG19 .

[0064] Description of main component symbols:

[0065] Unmanned aerial vehicle 100, body 10, arm assembly 20, arm 21, first end 211, second end 212, power component 22, drive member 221, blade 222, duct ring 223, drive mechanism 30, transmission member 31, landing gear 40, spray system 50, fluid circuit assembly 51, water tank 511, water pump 512, nozzle 52, gimbal camera 60. DETAILED DESCRIPTION

[0066] The embodiments of the present invention are described in detail below, and examples of the embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention, and should not be understood as limiting the present invention.

[0067] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise" and the like, indicating directions or positional relationships, are based on the directions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific direction, be constructed and operated in a specific direction, and therefore cannot be understood as limiting the present invention. In addition, the terms "first" and "second" are used for descriptive purposes only and cannot be understood as indicating or implying relative importance or implicitly indicating the number of the technical features indicated. Therefore, the features defined as "first" and "second" may explicitly or implicitly include one or more of the said features. In the description of the present invention, "multiple" means two or more, unless otherwise clearly and specifically defined.

[0068] In the description of this utility model, it should be noted that, unless otherwise expressly specified or limited, the terms "installed," "connected," and "connected" should be understood in a broad sense. For example, they can refer to fixed connections, detachable connections, or integral connections; mechanical connections, electrical connections, or mutual communication; direct connections or indirect connections through an intermediate medium; and internal communication between two components or interaction between two components. Those skilled in the art will understand the specific meanings of the above terms in this utility model based on specific circumstances.

[0069] In the present invention, unless otherwise expressly specified or limited, a first feature being "above" or "below" a second feature may include the first and second features being in direct contact, or may include the first and second features being in contact not directly but through another feature between them. Moreover, a first feature being "above," "above," and "above" a second feature may include the first feature being directly above or obliquely above the second feature, or may simply mean that the first feature is higher in level than the second feature. A first feature being "below," "below," and "below" a second feature may include the first feature being directly below or obliquely below the second feature, or may simply mean that the first feature is lower in level than the second feature.

[0070] The disclosure below provides many different embodiments or examples for realizing different structures of the present invention. In order to simplify the disclosure of the present invention, the components and settings of specific examples are described below. Of course, they are merely examples and are not intended to limit the present invention. In addition, the present invention may repeat reference numbers and / or reference letters in different examples. Such repetition is for the purpose of simplicity and clarity and does not in itself indicate the relationship between the various embodiments and / or settings discussed. In addition, the present invention provides examples of various specific processes and materials, but a person of ordinary skill in the art will recognize the application of other processes and / or the use of other materials.

[0071] In recent years, unmanned aerial vehicle technology has continued to develop at a high speed and has been widely used in more and more fields, such as aerial photography, surveying and mapping, agriculture, logistics, manned and other fields. The configuration of unmanned aerial vehicles can include single-rotor configuration, dual-rotor configuration and multi-rotor configuration. Among them, unmanned aerial vehicles with a single-rotor configuration can include helicopter-type drones, which have a relatively complex pitch structure, poor controllability, and are relatively unstable during flight. Unmanned aerial vehicles with a dual-rotor configuration are more compact and more convenient to fold. However, unmanned aerial vehicles with a dual-rotor configuration generally have both power motors and tilt motors on the arms to achieve flight. The transmission structure of the tilt motor is relatively complex and the production cost is relatively high. At the same time, the control safety and flexibility of dual-rotor drones are also relatively poor.

[0072] Unmanned aerial vehicles with multi-rotor configurations can include quad-rotors, hexa-rotors, and octa-rotors, etc. Multi-rotor unmanned aerial vehicles have better controllability and higher structural reliability, and are the mainstream model among existing models. In the prior art, multi-rotor unmanned aerial vehicles generally have one rotor installed for each arm, which results in too many arms and increases the production cost. At the same time, it makes the unmanned aerial vehicle larger and cannot be folded, making it inconvenient to store and transport. Furthermore, the embodiment of the present application improves the configuration of the unmanned aerial vehicle and provides a dual-arm multi-rotor configuration, which not only ensures good overall flight performance, but also enables the arms to be folded for easy storage and transportation, thereby improving the user experience.

[0073] Please refer to Figures 1 to 5. The unmanned aerial vehicle 100 of the embodiment of the present application includes a body 10 and an arm assembly 20. There are two arm assemblies 20, and the two arm assemblies 20 are symmetrically arranged on opposite sides of the body 10. Each arm assembly 20 includes an arm 21 and a power component 22 arranged on the arm 21. The arm 21 includes a first end 211 and a second end 212 arranged opposite to each other. The first end 211 is rotatably connected to the body 10 so that the arm 21 can be folded or unfolded relative to the body 10. There are multiple power components 22 on each arm 21, and the multiple power components 22 are spaced apart along the extension direction of the first end 211 toward the second end 212. The power component 22 includes a driving member 221 and a blade 222 connected to the driving member 221. The driving member 221 is installed on the arm 21.

[0074] In the unmanned aerial vehicle 100 of the present embodiment, two arms 21 are symmetrically arranged on opposite sides of the body 10. Each arm 21 is equipped with multiple power components 22 spaced apart along its extension direction. By arranging multiple power components 22 on the same arm 21, the number of arms 21 is reduced while maintaining good overall performance. This simplifies the overall structure of the unmanned aerial vehicle 100 and reduces manufacturing costs. Furthermore, the arms 21 are pivotally connected to the body 10, allowing them to be folded or unfolded relative to the body 10, reducing the size of the unmanned aerial vehicle 100 when stored and enhancing its flexibility and convenience.

[0075] The unmanned aerial vehicle 100 in the embodiment of the present application includes but is not limited to various aircraft such as agricultural drones, logistics drones, manned drones, aerial photography drones, and surveying drones.

[0076] Specifically, the body 10 is primarily used to assemble functional components to achieve the specific functional requirements of the unmanned aerial vehicle 100, such as batteries, radar, and cameras. The overall shape of the body 10 can be set to be rectangular, circular, etc., and this application does not impose any restrictions on the shape of the body 10. Two arm assemblies 20 are symmetrically connected to either side of the body 10. The arm assemblies 20 are primarily used to provide power support for the unmanned aerial vehicle 100, enabling the unmanned aerial vehicle 100 to fly.

[0077] The arm assembly 20 includes an arm 21 and a plurality of power components 22 disposed on the arm 21. The arm 21 primarily serves as a support and connection, and the power components 22 provide power support for the flight of the entire UAV 100. The arm assembly 20 can be connected to the body 10 via the arm 21. The first end 211 can be the end of the arm 21 connected to the body 10, and the second end 212 can be the end of the arm 21 away from the body 10. The second end 212 extends in a direction away from the first end 211.

[0078] The arms 21 can be made of materials such as lightweight metal or hard plastic, which not only provides good structural strength but also effectively reduces the overall mass of the UAV 100, preventing breakage due to excessive force during flight. The arms 21 can be configured as a bar or rod structure to reduce resistance during flight.

[0079] As shown in Figure 1, the power component 22 may include a driving member 221 and blades 222. The driving member 221 may be a power element such as an electric motor, and the blades 222 may be a two-blade propeller, a three-blade propeller, etc. This application does not limit the type of the driving member 221 and the number and shape of the blades 222. Multiple power components 22 may be installed on the same arm 21, and the multiple power components 22 are spaced apart along the extension direction of the arm 21. In other words, multiple driving members 221 are spaced apart along the extension direction of the arm 21, and multiple blades 222 are correspondingly mounted on the driving member 221. The driving member 221 can drive the blades 222 to rotate and thereby drive the unmanned aerial vehicle 100 to fly.

[0080] Multiple power components 22 provided on the same arm 21 may include two power components 22, three power components 22, or four power components 22 installed on the same arm 21. If two power components 22 are spaced apart on the same arm 21, the unmanned aerial vehicle 100 has a dual-arm 21 quad-rotor configuration. If three power components 22 are spaced apart on the same arm 21, the unmanned aerial vehicle 100 has a dual-arm 21 hexacopter configuration, and so on. The selection can be made based on the specific circumstances of the unmanned aerial vehicle 100. The more power components 22 there are, the greater the weight that the unmanned aerial vehicle 100 can carry. This application does not impose any restrictions on the number of power components 22.

[0081] As shown in FIG3 and FIG4 , it should be noted that the number of power components 22 on the arms 21 on both sides is the same and their positions are symmetrical, so that the UAV 100 can maintain good balance during flight.

[0082] Among them, when the arm 21 is folded relative to the body 10, the arm assembly 20 is in a folded state; when the arm 21 is unfolded relative to the body 10, the arm assembly 20 is in an unfolded state, and the power component 22 located on the same arm 21 is not collinear in the roll axis direction of the unmanned aerial vehicle 100.

[0083] As shown in Figure 1, one end of the arm 21 is rotatably connected to the body 10, and the two arms 21 are symmetrically connected to the left and right sides of the body 10. When the unmanned aerial vehicle 100 is ready to fly, the arms 21 on both sides will be unfolded relative to the body 10, that is, the entire arm assembly 20 will be unfolded relative to the body 10, and the unmanned aerial vehicle 100 will be able to fly. At this time, the arms 21 on both sides are opened at a certain angle relative to the roll axis direction of the unmanned aerial vehicle 100. Correspondingly, the power component 22 on the arm 21 will also be at a certain angle relative to the roll axis direction, thereby enabling the body 10 of the unmanned aerial vehicle 100 to better maintain balance during flight and avoid deflection in the forward and backward directions. Among them, the roll axis direction can be understood as the forward and backward direction of the unmanned aerial vehicle 100.

[0084] As shown in Figure 4, at the same time, when the arm 21 is unfolded relative to the body 10, the power component 22 located on the same arm 21 is not collinear in the roll axis direction of the unmanned aerial vehicle 100, which can provide a forward and backward pitch torque for the unmanned aerial vehicle 100 during flight, making the unmanned aerial vehicle 100 more flexible during flight and easier to control.

[0085] As shown in Figures 2 and 5 , when the UAV 100 completes flight and is ready for storage and transport, the arms 21 on either side can be folded relative to the body 10, that is, the arms 21 rotate toward the side of the body 10. Accordingly, the entire arm assembly 20 folds relative to the body 10, thereby reducing the size of the UAV 100 and facilitating its storage and transport. At this point, the arms 21 on either side can be parallel to the roll axis of the UAV 100.

[0086] In certain embodiments, when the arms 21 are deployed relative to the body 10, the distance between the power component 22 near the second end 212 of the same arm 21 and the roll axis of the UAV 100 is greater than the distance between the power component 22 near the first end 211 and the roll axis of the UAV 100. In this way, the power component 22 can better maintain the balance and stability of the UAV 100 during flight.

[0087] Please refer to FIG. 6 and FIG. 7 . In some embodiments, on the same arm 21 , the multiple blades 222 on the arm 21 are disposed on the same side of the arm 21 .

[0088] It is understood that the paddles 222 are connected to the driving member 221 and driven to rotate by the driving member 221, which is connected to the aircraft arm 21. Multiple driving members 221 are spaced apart on the aircraft arm 21, and the multiple driving members 221 can all face the same direction, so that the paddles 222 on the driving members 221 all face the same side relative to the aircraft arm 21. For example, if the multiple driving members 221 all face upwards towards the aircraft arm 21, the corresponding paddles 222 mounted on the driving members 221 are mounted on the upper side of the aircraft arm 21; if the multiple driving members 221 all face downwards towards the aircraft arm 21, the corresponding paddles 222 mounted on the driving members 221 are mounted on the lower side of the aircraft arm 21.

[0089] As shown in FIG6 , in some embodiments, when multiple blades 222 are arranged on the same side of the arm 21, the paddle disk formed by any two blades 222 is spaced apart in the extension direction of the arm 21, and adjacent blades 222 can rotate at the same speed or at different speeds without interfering with each other.

[0090] Alternatively, when multiple blades 222 are arranged on the same side of the arm 21, and the paddle disk formed by two adjacent blades 222 is located in the same plane and overlaps in the extension direction of the arm 21, the two adjacent blades 222 are configured to rotate at the same speed in different time periods and will not interfere with each other.

[0091] Of course, in some other embodiments, when multiple blades 222 are arranged on the same side of the arm 21, when the number of blades 222 is greater than or equal to three, the blades 222 in the middle position and the propeller disk formed by the blades 222 on one side are spaced apart in the extension direction of the arm 21, and overlap with the propeller disk formed by the blades 222 on the other side in the extension direction of the arm 21 and rotate at the same speed in different time periods, and the multiple blades 222 will not interfere with each other.

[0092] In this way, when the blades 222 are arranged on the same side of the arm 21, the distribution of the blades 222 can be distributed in the same manner as in the above-mentioned embodiment, which can avoid interference between any two blades 222 on the arm 21 during rotation, thereby avoiding damage to the blades 222 and affecting the normal flight of the unmanned aerial vehicle 100.

[0093] Please refer to FIG. 1 , FIG. 3 , FIG. 8 and FIG. 9 . In some embodiments, on the same arm 21 , the plurality of blades 222 on the arm 21 are respectively disposed on opposite sides of the arm 21 .

[0094] It is understood that the multiple driving members 221 are spaced apart on the arm 21 and can face different directions of the arm 21, so that the blades 222 on the driving members 221 face different sides relative to the arm 21. For example, two adjacent driving members 221 face opposite directions, with one facing upward and the other facing downward, so that the two adjacent blades 222 are respectively located on the upper and lower sides of the arm 21. In this way, the propeller disks formed by the two adjacent blades 222 during rotation do not interfere with each other, thereby facilitating the operation of the unmanned aerial vehicle 100.

[0095] To further illustrate, when two power components 22 are included on the same arm 21, the two driving members 221 can be respectively arranged in the middle of the arm 21 and at the end of the arm 21 away from the body 10. As shown in Figures 1 and 3, the driving member 221 in the middle of the arm 21 can face downward, and the blades 222 are then mounted on the lower side of the arm 21. The driving member 221 at the end of the arm 21 can face upward, and the blades 222 are then mounted on the upper side of the arm 21. Of course, as shown in Figures 8 and 9, the driving member 221 in the middle of the arm 21 can also face upward, and the blades 222 are mounted on the upper side of the arm 21, while the driving member 221 at the end of the arm 21 can face downward, and the blades 222 are mounted on the lower side of the arm 21.

[0096] Similarly, when three, four, or more power components 22 are included on the same arm 21, the installation position of the blades 222 can be selected and set according to the actual situation. Preferably, two adjacent blades 222 can be installed on different sides of the arm 21. This application does not impose specific restrictions on this.

[0097] It should be noted that no matter whether the multiple blades 222 are arranged on the same side of the arm 21 or on opposite sides, the arm assemblies 20 on both sides of the body 10 need to be arranged symmetrically, so that the unmanned aerial vehicle 100 can maintain a good flight state during flight and avoid deflecting to one side and affecting the flight.

[0098] 3 and 9 , in some embodiments, when the plurality of blades 222 are respectively disposed on opposite sides of the arm 21 , the paddle disks formed by two adjacent blades 222 at least partially overlap along the rotation axis of the blades 222 .

[0099] In this way, while ensuring the normal operation of the UAV 100, the length of the arm 21 is reduced, the maneuverability of the UAV 100 is improved, and the volume of the UAV 100 during storage and transportation can also be reduced, making it easier to store and transport.

[0100] Specifically, when two adjacent blades 222 are respectively arranged on opposite sides of the arm 21, one blade 222 is arranged on the upper side of the arm 21, and the other blade 222 is arranged on the lower side of the arm 21, so that no interference or collision will occur between the propeller disks formed by the two blades 222 during rotation.

[0101] The propeller discs formed by the rotation of two adjacent propeller blades 222 can at least partially overlap in the direction of the rotation axis of the propeller blades 222. As a result, the airflow generated by the two propeller blades 222 can cooperate with each other to reduce the power output of the motor and improve the endurance of the unmanned aerial vehicle 100. At the same time, the distance between two adjacent drive members 221 is also reduced, thereby shortening the overall length of the arm 21, improving maneuverability, and reducing the overall volume during storage and transportation.

[0102] Of course, in some embodiments, the propeller disk formed by the rotation of two adjacent blades 222 can also be arranged at intervals in the direction of the rotation axis of the blade 222. This application does not impose any restrictions on this, as long as it can ensure that the unmanned aerial vehicle 100 can fly normally in good condition.

[0103] 1 and 6 , in some embodiments, one power component 22 is located on the same arm 21 at the second end 212, i.e., the end of the arm 21 away from the body 10. This allows the power component 22 at the second end 212 to provide better power output to the UAV 100, while also improving the controllability and reliability of the UAV 100.

[0104] Referring to FIG. 10 , in some embodiments, on the same arm 21 , the central axes of two blades 222 are parallel or form an acute angle.

[0105] In this way, when the central axes of the two blades 222 are parallel, the blades 222 can provide more sufficient power support for the unmanned aerial vehicle 100 under the drive of the driving member 221; when the central axes of the two blades 222 are at an acute angle, the controllability of the drone is more flexible, providing the unmanned aerial vehicle 100 with a forward and backward pitch torque, thereby improving the flexibility of the unmanned aerial vehicle 100.

[0106] Specifically, on the same arm 21 , multiple blades 222 can be arranged on the same side of the arm 21 , or on opposite sides of the arm 21 , and the central axes of the multiple blades 222 can be arranged perpendicular to the arm 21 .

[0107] Among them, all the blades 222 on the same arm 21 can be facing upward or downward relative to the arm 21, that is, the central axes of the blades 222 are all perpendicular to the arm 21 in the up and down directions, and then the central axes of the blades 222 are parallel to each other. The blades 222 can provide better power support to the unmanned aerial vehicle 100 under the drive of the driving member 221.

[0108] Of course, in some embodiments, some blades 222 on the same arm 21 may be oriented obliquely upward or downward relative to the arm 21. That is, the central axes of some blades 222 are perpendicular to the arm 21 but tilted at an acute angle to the vertical direction, and thus the central axes of these blades 222 are arranged at an acute angle to the central axes of the blades 222 arranged in the vertical direction. In this case, the blades 222 arranged at an oblique angle can provide torque for the pitch movement of the UAV 100, making the UAV 100 more flexible and maneuverable.

[0109] Referring to Figures 1, 2, 11, and 12, in some embodiments, the arm 21 is connected to the nose or tail of the body 10. When the arm 21 is connected to the nose, it can be folded toward the tail; when the arm 21 is connected to the tail, it can be folded toward the nose.

[0110] In this way, since the arm 21 extends straight, it is easier to fold and store the arm 21 when it is rotatably connected to the nose or tail of the machine, thereby reducing the overall volume when stored.

[0111] Specifically, as shown in Figures 1 and 2, the arms 21 can be connected to the nose of the body 10 on both sides. When the arms 21 are folded relative to the body 10, the arm assembly 20 can be attached to the side of the body 10 along the nose-to-tail direction of the body 10. The arm assembly 20 and the body 10 can at least partially overlap, thereby reducing the overall volume of the folded UAV 100 and facilitating the storage and transportation of the UAV 100.

[0112] As shown in Figures 11 and 12, the arms 21 can also be connected to the tail positions on both sides of the body 10. Similarly, when the arms 21 are folded relative to the body 10, the arm assembly 20 can be attached to the side of the body 10 from the tail to the nose of the body 10, and the arm assembly 20 and the body 10 can at least partially overlap, thereby reducing the overall volume of the folded UAV 100 and facilitating the storage and transportation of the UAV 100.

[0113] Please refer to Figure 13. In some embodiments, the arm 21 can be folded downward from the nose or tail along the body 10 when folded, so that the overlapping length of the arm 21 and the body 10 is longer, avoiding the situation where the arm 21 is too long and extends out of the body 10 when folded, making the unmanned aerial vehicle 100 smaller in size when folded, and convenient for storage and transportation.

[0114] Please refer to Figure 4. It should be noted that in some embodiments, no matter whether the arm 21 is connected to the nose or the tail, when the arm 21 is in the deployed state, the center of gravity of the UAV 100 passes through the figure surrounded by all the power components 22.

[0115] In this way, the UAV 100 can maintain good balance during flight, preventing the UAV 100 from tilting forward or backward after takeoff, thereby affecting the flight state.

[0116] Specifically, the center of gravity of the UAV 100 can be the line that defines the center of gravity of the entire UAV 100. All power components 22 of the UAV 100 are capable of providing the power required for flight. The fact that the center of gravity of the UAV 100 passes through the shape formed by all power components 22 allows the UAV 100 to maintain good balance during flight, thereby improving the stability, reliability, and safety of the UAV 100.

[0117] As shown in Figure 4, each arm 21 is provided with a first power component 221 and a second power component 222, the first power component 221 is provided near the first end 211, and the second power component 222 is provided at the second end 212. When the arms 21 are unfolded relative to the body 10, the center of gravity line of the unmanned aerial vehicle 100 is located at or near the geometric center of the figure enclosed by the first power components 221 and the second power components 222 of the two arms 21.

[0118] In some embodiments, the line connecting the two first power components 221 and the line connecting the two second power components 222 are parallel to each other, and the distance between them in the roll axis direction of the body 10 is L, and the distance between the center of gravity line and the geometric center line is D, where 0≤D≤0.15L. This can better ensure the stable balance of the UAV 100 during flight.

[0119] Referring to Figure 5 , in certain embodiments, when the arm 21 is folded relative to the body 10, at least one power component 22 is located in the middle of the side of the body 10. This ensures that the power component 22's location in the middle of the body 10 does not prevent the arm 21 from folding toward the body 10, allowing the arm 21 to fold toward the body 10, thereby reducing the volume of the folded device and facilitating storage and transport.

[0120] In some embodiments, the strength of the portion where the arm 21 is connected to the body 10 is greater than the strength of other portions, thereby making the connection between the arm 21 and the body 10 more secure, preventing the connection between the arm 21 and the body 10 from being damaged by excessive torque during flight of the unmanned aerial vehicle 100, thereby extending the service life of the unmanned aerial vehicle 100.

[0121] Referring to Figures 1 and 2, in some embodiments, the unmanned aerial vehicle 100 further includes a driving mechanism 30, which is connected to the arm assembly 20. The driving mechanism 30 is used to drive the arm assembly 20 to rotate to adjust the deployment angle of the arm assembly 20 relative to the body 10.

[0122] In this way, the flight direction of the UAV 100 can be controlled by adjusting the deployment angle of the arm assembly 20 relative to the body 10 , making the UAV 100 more flexible during flight and easier to control and turn.

[0123] Specifically, the drive mechanism 30 can be disposed on the body 10, specifically at the connection between the arms 21 and the body 10. The drive mechanism 30 can adjust the deployment angle of the arms 21 relative to the body 10, thereby enabling the UAV 100 to adjust its direction during flight, thereby improving the flexibility of the UAV 100.

[0124] Of course, the arm 21 can be automatically unfolded or folded relative to the body 10 through the driving mechanism 30, so as to avoid damage to the arm 21 due to excessive force during manual operation, or the arm 21 being not in the correct position during manual folding and unfolding, thereby affecting the operation or storage of the unmanned aerial vehicle 100.

[0125] Furthermore, as shown in Figures 14 and 15 , the drive mechanism 30 may include a motor and a transmission member 31. The motor and transmission member 31 are located within the connection between the fuselage 10 and the arms 21 (the motor is not shown). The motor provides power output. The motor and transmission member 31 cooperate to allow the arms 21 to rotate during flight, adjusting the deployment angle of the arm assembly 20 relative to the fuselage 10.

[0126] The drive mechanism 30 is disposed at the connection between the arm assembly 20 and the body 10. The drive mechanism 30 is capable of driving the two arms 21 to transition between a substantially parallel state and an extended angle to accommodate or operate the arm assembly 20. Consequently, the UAV 100 can not only deploy and retract the arm assembly 20 through the drive mechanism 30, but also better adjust the angle during flight, facilitating steering and other operations of the UAV 100. The transmission member 31 may include a gear assembly, which may be composed of a plurality of gears of varying sizes that cooperate with each other.

[0127] Please refer to Figures 16 to 18. In some embodiments, the arm assembly 20 further includes a duct ring 223. The blades 222 are disposed in the duct ring 223 and connected to the duct ring 223.

[0128] In this way, the duct ring 223 can protect the blade 222 and also improve the power output effect of the blade 222, so that the blade 222 can output power better.

[0129] Specifically, the duct 223 can be configured as a circular ring structure, connected to the blade end of the blade 222. In the UAV 100 equipped with the duct 223, the arm 21 can be perpendicular to the roll axis of the body 10, that is, it can be understood that the multiple drive components are collinearly arranged along the direction perpendicular to the roll axis. Of course, the arm 21 can also be arranged at a certain angle relative to the roll axis of the body 10, that is, it can be understood that the multiple drive components are not collinearly arranged along the direction perpendicular to the roll axis, and this application does not impose any limitation on this.

[0130] In some embodiments, when multiple driving components of the unmanned aerial vehicle 100 are arranged in a collinear manner along a direction perpendicular to the roll axis, in order to obtain a forward and backward pitch torque, the driving component 221 can be set to a certain inclination angle forward or backward. For example, the driving component close to the side of the base is tilted forward, and the driving component of the arm 21 opposite to the end of the body 10 is tilted backward. Then, the speed difference of the blades 222 driven by the driving component 221 is used to realize the turning, pitching and other operations of the unmanned aerial vehicle 100, making the unmanned aerial vehicle 100 more flexible during flight.

[0131] Referring to Figure 17 , in certain embodiments, when the arm 21 equipped with the duct 223 is in the folded state, the radial direction of the duct 223 is parallel to the yaw axis of the UAV 100. Specifically, it can be understood that when folding the arm assembly 20 equipped with the duct 223, the arm 21 can first be rotated a certain angle so that the duct 223 is oriented from horizontal to vertical. At this point, the duct 223 can be vertically attached to the outside of the body 10, that is, the radial direction of the duct 223 is parallel to the yaw axis of the UAV 100. This effectively reduces the size of the UAV 100 when folded, making it easier to store and transport.

[0132] 1 and 19 , in some embodiments, the UAV 100 includes a landing gear 40 connected to the arms 21 or the body 10. Thus, the UAV 100 can support the body 10 via the landing gear 40 during takeoff and landing to prevent damage to the body 10.

[0133] Specifically, the landing gear 40 can be made of a metal material, which has good structural strength and is not easily damaged, thereby providing good protection and support for the fuselage 10. As shown in the embodiment of FIG1 , the support frame can be a bent tubular structure. There can be two support frames, one on each side below the fuselage 10. For example, the landing gear 40 can be connected to the bottom of the fuselage 10 in the direction from nose to tail, or in the left-right direction. This can provide better protection for the fuselage 10 during takeoff and landing of the UAV 100.

[0134] Of course, as shown in the embodiment of FIG19 , in some other embodiments, the landing gear 40 can also be configured as a columnar structure, with multiple columnar landing gears 40 symmetrically connected below the arm 21. In this manner, the landing gear 40 can also effectively support the fuselage 10. This application does not impose any restrictions on the specific installation location, number, or specific structure of the landing gear 40.

[0135] Referring to Figures 17-19 , in certain embodiments, when the landing gear 40 is connected to the arm 21, the landing gear 40 is connected to the lower side of the end of the arm 21 away from the body 10, and one of the power components 22 is mounted on the upper side of the end of the arm 21 away from the body 10. This prevents the landing gear 40 from interfering with the rotation of the blades 222 driven by the driving member 221.

[0136] Referring to Figures 1-3, in some embodiments, the unmanned aerial vehicle 100 includes a spraying system 50, which includes a nozzle 52 and a fluid circuit assembly 51 connected to the nozzle 52. The nozzle 52 is disposed on the arm assembly 20, and the fluid circuit assembly 51 is at least partially disposed on the body 10.

[0137] In this way, the UAV 100 can perform operations through the spraying system 50 , making the operations more convenient and faster.

[0138] Specifically, the unmanned aerial vehicle 100 provided with the spraying system 50 may be an agricultural drone, a plant protection drone, etc., and the spraying system 50 may be used to spray liquids such as pesticides, nutrient solutions or water.

[0139] Referring to Figures 1-3, in certain embodiments, the fluid circuit assembly 51 includes a water tank 511 and a water pump 512. The water pump 512 is connected between the water tank 511 and the nozzle 52. Both the water tank 511 and the water pump 512 are disposed on the body 10. Thus, the water pump 512 can draw liquid from the water tank 511 and spray it through the nozzle 52, spraying it downward during the flight of the UAV 100, making operation more convenient and efficient for the user.

[0140] It should be noted that when components such as the water tank 511 and the water pump 512 are installed on the body 10, the overall center of gravity of the unmanned aerial vehicle 100 can be close to the side where the arm 21 is connected to the body 10, so that the arm assembly 20 of the unmanned aerial vehicle 100 can better maintain the balance of the entire machine during flight, which is conducive to flexible control of the unmanned aerial vehicle 100.

[0141] The motor of the embodiment of the present application is arranged along the extension direction of the arm 21, so that the power component 22 close to the side of the base can complement the wind field directly below the middle of the aircraft, thereby making the nozzle 52 more uniform during spraying, avoiding the situation of spray leakage below the body 10, and improving the operating effect of the unmanned aerial vehicle 100.

[0142] In some embodiments, the nozzle 52 is disposed on the arm 21 and located between two adjacent power components 22; alternatively, the nozzle 52 may be disposed below the blade 222 and located on the central axis of the blade 222; alternatively, some of the nozzles 52 may be disposed on the arm 21 and located between two adjacent power components 22, while some of the nozzles 52 may be disposed below the blade 222 and located on the central axis of the blade 222. This application does not impose any restrictions on the specific installation position of the nozzle 52 on the arm 21, as long as the liquid sprayed by the nozzle 52 is evenly distributed in the wind field generated by the power component 22 to avoid leakage.

[0143] Please refer to FIG. 16 . In some embodiments, the arm assembly 20 further includes a duct 223 . The blades 222 are disposed in and connected to the duct 223 . The nozzle 52 is disposed on the duct 223 .

[0144] In this way, the nozzle 52 is arranged on the duct ring 223 so that the spraying area during spraying can be larger and the spraying effect can be more uniform.

[0145] Specifically, the nozzle 52 can be mounted on the duct 223 of the blade 222 connected to the underside of the arm 21, with the nozzle 52 facing downward. The nozzle 52 on the duct 223 can be used for centrifugal spraying through the rotation of the duct 223, or for pressure spraying via the water pump 512. The nozzle 52 can be located below the center of the drive member 221 or around the outer edge of the sensor.

[0146] 16 , in some embodiments, there are multiple nozzles 52 on each duct 223, and the multiple nozzles 52 are spaced apart along the circumference of the duct 223. In this way, the nozzles 52 can spray over a wider range, spray more evenly, and achieve better results.

[0147] It should be noted that for the unmanned aerial vehicle 100 equipped with a spraying system 50, the spray is generally pressed downward by means of the wind field formed by the power component 22, and the size of the spray width is positively correlated with the flight speed of the unmanned aerial vehicle 100. As a result, the unmanned aerial vehicle 100 may cause uneven spraying or even spray leakage when decelerating and accelerating.

[0148] The embodiment of the present application can solve this technical problem by using the driving mechanism 30 in the above embodiment to actively drive the arms 21. The specific method can be: when the UAV 100 is flying at a constant speed, the driving mechanism 30 can drive the deployment angle of the dual arms 21 to become smaller, so that the span of the UAV 100 is moderate; when the UAV 100 decelerates at the end of the field, the driving mechanism 30 can drive the deployment angle of the dual arms 21 to increase appropriately, so that the span of the UAV 100 is increased, reducing the contraction effect of the spray width of the UAV 100, so as to obtain a stable and balanced spray width, thereby effectively alleviating the problem of uneven spraying or missed spraying when decelerating at the end of the field.

[0149] Referring to Figures 19-21 , in certain embodiments, UAV 100 includes a gimbal camera 60 mounted on the nose of body 10. Specifically, UAVs 100 equipped with a gimbal camera 60 may include consumer drones such as camera drones and FPV drones. Compared to configurations with multiple arms 21, the UAV 100 in this embodiment mitigates the problem of arms 21 and other structures interfering with the camera's viewing angle, allowing for greater flexibility and improved image quality when shooting with the gimbal camera 60.

[0150] It should be noted that this type of UAV 100 may be flown in complex scenarios, and good flexibility and maneuverability are essential for this type of UAV 100. For example, when flying through narrow spaces, an overly long arm 21 may cause scratches and damage to the UAV 100.

[0151] The present embodiment can also utilize the drive mechanism 30 described above to actively drive the arms 21 to address this technical issue. Specifically, when the UAV 100 is flying in a relatively confined space, the drive mechanism 30 can drive the dual arms 21 to appropriately reduce their deployment angles, thereby minimizing the overall size of the UAV 100 while ensuring flight safety, and reducing the difficulty of flying in confined spaces.

[0152] In summary, the UAV 100 of the present application improves upon traditional multi-rotor models to simplify its overall structure and effectively reduce its overall weight, thereby increasing its flexibility and maneuverability. Furthermore, the foldable arm assembly 20 facilitates the storage and transport of the UAV 100, significantly enhancing the user experience.

[0153] Throughout this specification, reference to terms such as "one embodiment," "certain embodiments," "illustrative embodiments," "examples," "specific examples," or "some examples" means that a specific feature, structure, material, or characteristic described in conjunction with the embodiment or example is included in at least one embodiment or example of the present application. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.

[0154] Although the embodiments of the present application have been shown and described, those skilled in the art will appreciate that various changes, modifications, substitutions, and variations may be made to the embodiments without departing from the principles and intent of the present application, and that the scope of the present application is defined by the claims and their equivalents.

Claims

1. An unmanned aerial vehicle, characterized in that: include: body; An arm assembly, wherein the number of the arm assemblies is two, and the two arm assemblies are symmetrically arranged on opposite sides of the body, each arm assembly includes an arm and a power component arranged on the arm, the arm includes a first end and a second end arranged opposite to each other, the first end is rotatably connected to the body so that the arm can be folded or unfolded relative to the body, the number of the power components on each arm is multiple, and the multiple power components are spaced apart along the extension direction from the first end to the second end, the power component includes a driving member and a blade connected to the driving member, and the driving member is mounted on the arm.

2. The unmanned aerial vehicle according to claim 1, wherein: When the arms are unfolded relative to the body, the power components located on the same arm are not collinear in the roll axis direction of the UAV.

3. The unmanned aerial vehicle according to claim 2, wherein: When the arm is unfolded relative to the body, on the same arm, the distance between the power component close to the second end and the roll axis of the unmanned aerial vehicle is greater than the distance between the power component close to the first end and the roll axis of the unmanned aerial vehicle.

4. The unmanned aerial vehicle according to claim 1, wherein: On the same machine arm, the plurality of blades are arranged on the same side of the machine arm; or The plurality of blades are arranged on opposite sides of the machine arm.

5. The unmanned aerial vehicle according to claim 4, characterized in that: In the case where a plurality of blades are arranged on the same side of the machine arm, the paddle disks formed by any two of the blades are spaced apart in the extension direction of the machine arm; and / or When the paddle disks formed by the two adjacent blades are located in the same plane and overlap in the extension direction of the machine arm, the two adjacent blades are configured to rotate at the same speed in different time periods.

6. The unmanned aerial vehicle according to claim 4, characterized in that: When the plurality of blades are arranged on opposite sides of the machine arm, the paddle disks formed by two adjacent blades at least partially overlap in the direction along the rotation axis of the blades.

7. The unmanned aerial vehicle according to claim 1, wherein: On the same machine arm, one of the power components is arranged at the second end.

8. The unmanned aerial vehicle according to claim 1, wherein: On the same machine arm, central axes of two of the blades are parallel or form an acute angle.

9. The unmanned aerial vehicle according to claim 1, wherein: When the machine arm is folded relative to the machine body, at least one of the power components is located in the middle of the machine body.

10. The unmanned aerial vehicle according to claim 9, wherein: When the machine arm is folded relative to the machine body, at least one of the power components is located in the middle of the side surface of the machine body.

11. The unmanned aerial vehicle according to any one of claims 1 to 10, characterized in that: The arm is connected to the nose or tail of the machine body; When the arm is connected to the nose portion, the arm can be folded toward the tail portion; When the machine arm is connected to the tail portion, the machine arm can be folded toward the nose portion.

12. The unmanned aerial vehicle according to claim 11, wherein: When the machine arm is folded, it can be folded downwardly along the direction of the machine body from the nose or the tail.

13. The unmanned aerial vehicle according to any one of claims 1 to 10, characterized in that: When the arms are unfolded relative to the body, the center of gravity of the UAV passes through a figure enclosed by all the power components on the two arms.

14. The unmanned aerial vehicle according to claim 13, wherein: Each of the arms includes a first power component and a second power component, the first power component is arranged near the first end, and the second power component is arranged at the second end. When the arms are unfolded relative to the body, the center of gravity line of the unmanned aerial vehicle is located at or near the geometric center of the figure enclosed by the first power components and the second power components of the two arms.

15. The unmanned aerial vehicle according to claim 14, wherein: The line connecting the two first power components and the line connecting the two second power components are parallel to each other, and the distance between them in the direction of the roll axis of the body is L, and the distance between the center of gravity line and the geometric center line is D, wherein 0≤D≤0.15L.

16. The unmanned aerial vehicle according to any one of claims 1 to 10, characterized in that: The arm assembly further includes a duct, wherein the blade is disposed in the duct and connected to the duct; When the aircraft arm is folded relative to the aircraft body, the radial direction of the duct is parallel to the yaw axis of the UAV.

17. The unmanned aerial vehicle according to any one of claims 1 to 10, characterized in that: The unmanned aerial vehicle further includes a driving mechanism connected to the arm assembly, and the driving mechanism is used to drive the arm assembly to rotate so as to adjust the deployment angle of the arm assembly relative to the body.

18. The unmanned aerial vehicle according to claim 17, wherein: The driving mechanism includes a motor and a transmission member. The motor and the transmission member cooperate to enable the arm to rotate during flight to adjust the deployment angle of the arm assembly relative to the body.

19. The unmanned aerial vehicle according to claim 18, wherein: The transmission member is a gear assembly.

20. The unmanned aerial vehicle according to claim 17, wherein: The driving mechanism is arranged at the connection between the arm assembly and the body, and the driving mechanism can drive the two arms to switch between a substantially parallel state and an extended angle to store or operate the arm assembly.

21. The unmanned aerial vehicle according to any one of claims 1 to 8, characterized in that: The strength of the portion where the machine arm is connected to the machine body is greater than the strength of other portions.

22. The unmanned aerial vehicle according to any one of claims 1 to 10, characterized in that: The unmanned aerial vehicle includes a landing gear connected to the aircraft arm or the aircraft body.

23. The unmanned aerial vehicle according to claim 22, wherein: In the case where the landing gear is connected to the aircraft arm, the landing gear is connected to the lower side of the second end, and one of the power components is installed on the upper side of the second end.

24. The unmanned aerial vehicle according to any one of claims 1 to 10, characterized in that: The unmanned aerial vehicle includes a spraying system, which includes a spray head and a fluid circuit assembly connected to the spray head. The spray head is arranged on the arm assembly, and the fluid circuit assembly is at least partially arranged on the body.

25. The unmanned aerial vehicle according to claim 24, wherein: The nozzle is arranged on the machine arm and located between two adjacent power components; and / or, The nozzle is arranged below the blade and located on the central axis of the blade.

26. The unmanned aerial vehicle according to claim 24, wherein: The arm assembly further includes a duct, the blade is disposed in the duct and connected to the duct, and the nozzle is disposed on the duct.

27. The unmanned aerial vehicle according to claim 26, wherein: There are multiple nozzles on each duct ring, and the multiple nozzles are arranged at intervals along the circumference of the duct ring.

28. The unmanned aerial vehicle according to claim 24, wherein: The liquid circuit assembly includes a water tank and a water pump. The water pump is connected between the water tank and the nozzle. The water tank and the water pump are both arranged on the machine body.

29. The unmanned aerial vehicle according to any one of claims 1 to 10, characterized in that: The unmanned aerial vehicle includes a pan-tilt camera arranged on the nose side of the aircraft body.

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