WO2024077523A1

WO2024077523A1 - Unmanned aerial vehicle

Info

Publication number: WO2024077523A1
Application number: PCT/CN2022/124918
Authority: WO
Inventors: 舒展; 李日照; 赵进
Original assignee: 深圳市大疆创新科技有限公司
Priority date: 2022-10-12
Filing date: 2022-10-12
Publication date: 2024-04-18

Abstract

An unmanned aerial vehicle (100). The unmanned aerial vehicle (100) comprises a vehicle body (10) and vehicle arm assemblies (20), wherein two vehicle arm assemblies (20) are provided, and the two vehicle arm assemblies (20) are symmetrically arranged on opposite sides of the vehicle body (10); each vehicle arm assembly (20) comprises a vehicle arm (21) and power components (22) arranged on the vehicle arm (21); the vehicle arm (21) comprises a first end (211) and a second end (212) which are arranged opposite each other, the first end (211) being rotatably connected to the vehicle body (10) to enable the vehicle arm (21) to be collapsed or expanded relative to the vehicle body (10), and the second end (212) extending in a direction away from the first end (211); the power components (22) on each vehicle arm (21) are arranged at intervals in the direction in which the first end (211) extends toward the second end (212); and each power component (22) comprises a drive member (221) and a blade (222) connected to the drive member (221), the drive member (221) being mounted on the vehicle arm (21).

Description

Unmanned aerial vehicles

Technical Field

The present application relates to the technical field of unmanned aerial vehicles, and in particular to an unmanned aerial vehicle.

Background technique

With the rapid development of UAV technology, multi-rotor UAVs are widely used in more and more fields as mainstream models. Multi-rotor UAVs have high flight safety and reliability. Multi-rotor UAVs are generally driven by a power component on one arm. They have a complex structure, large size and high production cost. Therefore, how to simplify the structure of multi-rotor UAVs while ensuring good comprehensive performance to improve their convenience and reduce production costs is an urgent problem to be solved.

Summary of the invention

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

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.

In the unmanned aerial vehicle of the embodiment of the present application, two arms are symmetrically arranged on opposite sides of the body, and each arm is provided with multiple power components at intervals along its extension direction. In this way, multiple power components are arranged on the same arm, so that the number of arms is reduced while ensuring good overall performance of the unmanned aerial vehicle, thereby simplifying the overall structure of the unmanned aerial vehicle and reducing the manufacturing cost. At the same time, the arms are rotatably connected to the body so that the arms can be folded or unfolded relative to the body, reducing the volume of the unmanned aerial vehicle when stored, and improving the flexibility and convenience of the unmanned aerial vehicle.

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.

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.

In some embodiments, 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 respectively arranged on opposite sides of the machine arm.

In some embodiments, when a plurality of the blades are arranged on the same side of the machine arm, the paddle disks formed by any two of the blades are arranged at intervals 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.

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 in the direction along the rotation axis of the blades.

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

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

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.

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.

In some embodiments, the arm is connected to the head portion or the tail portion of the body;

When the machine arm is connected to the nose part, the machine arm can be folded toward the tail part;

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

In some 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.

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.

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

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 between them in the direction of the body roll axis is L, and the distance between the center of gravity line and the geometric center line is D, wherein 0≤D≤0.15L.

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

When the machine arm is folded relative to the machine body, the radial direction of the duct is parallel to the yaw axis of the unmanned aerial vehicle.

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.

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.

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

In certain embodiments, the driving mechanism is disposed 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.

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

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

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.

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.

In some embodiments, the nozzle is disposed 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.

In certain embodiments, 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.

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

In some embodiments, the liquid 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.

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

Additional aspects and advantages of the present application will be given in part in the description below, and in part will become apparent from the description below, or will be learned through the practice of the present application.

BRIEF DESCRIPTION OF THE DRAWINGS

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:

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

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

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

FIG4 is a top view of the unmanned aerial vehicle in FIG1 ;

FIG5 is a top view of the unmanned aerial vehicle in FIG2;

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

FIG7 is a front view of the unmanned aerial vehicle in FIG6;

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

FIG9 is a front view of the unmanned aerial vehicle in FIG8;

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

FIG11 is a perspective schematic diagram of another unmanned aerial vehicle in an embodiment of the present application when it is deployed;

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

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

FIG14 is a perspective schematic diagram of another unmanned aerial vehicle in an embodiment of the present application when it is deployed;

FIG15 is an enlarged schematic diagram of the unmanned aerial vehicle at position XV in FIG14;

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

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

FIG18 is a top view of the unmanned aerial vehicle in FIG16;

FIG19 is a perspective schematic diagram of another unmanned aerial vehicle in an embodiment of the present application when it is deployed;

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

FIG. 21 is a top view of the UAV in FIG. 19 .

Description of main component symbols:

Unmanned aerial vehicle 100, body 10, arm assembly 20, arm 21, first end 211, second end 212, power component 22, driving member 221, blade 222, duct 223, driving 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 ways

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 cannot be understood as limiting the present invention.

In the description of the present utility model, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present utility model and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present utility model. In addition, the terms "first" and "second" are only used for descriptive purposes, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of 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 utility model, the meaning of "multiple" is two or more, unless otherwise clearly and specifically defined.

In the description of the present utility model, it should be noted that, unless otherwise clearly specified and limited, the terms "installation", "connection" and "connection" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection, an electrical connection, or mutual communication; 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. For ordinary technicians in this field, the specific meanings of the above terms in the present utility model can be understood according to specific circumstances.

In the present utility model, unless otherwise clearly specified and 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 includes the first feature being directly above and obliquely above the second feature, or simply indicates that the first feature is higher in level than the second feature. A first feature being "below", "below" and "below" a second feature includes the first feature being directly below and obliquely below the second feature, or simply indicates that the first feature is lower in level than the second feature.

The disclosure below provides many different embodiments or examples for realizing different structures of the utility model. In order to simplify the disclosure of the utility model, the components and settings of specific examples are described below. Of course, they are merely examples, and the purpose is not to limit the utility model. In addition, the utility model can repeat reference numbers and/or reference letters in different examples, and this repetition is for the purpose of simplification and clarity, and does not indicate the relationship between the various embodiments and/or settings discussed in itself. In addition, the utility model provides various specific examples of processes and materials, but those of ordinary skill in the art can be aware of the application of other processes and/or the use of other materials.

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 single-rotor configuration can include helicopter-type drones, which have a relatively complex variable pitch structure, poor controllability, and are relatively unstable during flight. Unmanned aerial vehicles with dual-rotor configurations have a relatively compact structure and are more convenient after folding. However, unmanned aerial vehicles with dual-rotor configurations 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.

Unmanned aerial vehicles with multi-rotor configurations may include quad-rotors, hexa-rotors, and octa-rotors, etc. Multi-rotor unmanned aerial vehicles have good controllability and high structural reliability, and are the mainstream models among existing models. In the prior art, multi-rotor unmanned aerial vehicles generally have a rotor installed for each arm, which results in too many arms and increases the production cost. At the same time, the size of the unmanned aerial vehicle is larger and cannot be folded, making it inconvenient to store and transport. Furthermore, the implementation method 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 comprehensive flight performance, but also the arms can be folded for easy storage and transportation, thereby improving the user experience.

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, which 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 that are relatively arranged. 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. 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.

In the unmanned aerial vehicle 100 of the embodiment of the present application, two arms 21 are symmetrically arranged on opposite sides of the body 10, and each arm 21 is provided with a plurality of power components 22 at intervals along its extension direction. In this way, by providing a plurality of power components 22 on the same arm 21, the number of arms 21 is reduced while ensuring good overall performance of the unmanned aerial vehicle 100, thereby simplifying the overall structure of the unmanned aerial vehicle 100 and reducing the manufacturing cost. At the same time, the arms 21 are rotatably connected to the body 10 so that the arms 21 can be folded or unfolded relative to the body 10, reducing the volume of the unmanned aerial vehicle 100 when stored, and improving the flexibility and convenience of the unmanned aerial vehicle 100.

The unmanned aerial vehicle 100 in the implementation manner 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.

Specifically, the body 10 is mainly used to assemble some functional components to achieve the specific functional requirements of the unmanned aerial vehicle 100, such as batteries, radars, cameras, etc. The overall shape of the body 10 can be set to be rectangular, circular, etc., and the present application does not limit the shape of the body 10. Two arm assemblies 20 are symmetrically connected to both sides of the body 10, and the arm assemblies 20 are mainly used to provide power support for the unmanned aerial vehicle 100 so that the unmanned aerial vehicle 100 can fly.

The arm assembly 20 includes an arm 21 and a plurality of power components 22 disposed on the arm 21. The arm 21 mainly serves as a supporting connection. The power components 22 provide power support for the flight of the entire unmanned aerial vehicle 100. The arm assembly 20 can be connected to the body 10 through 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.

The arm 21 can be made of light metal or hard plastic, etc., which not only has good structural strength, but also can effectively reduce the overall mass of the unmanned aerial vehicle 100 to avoid breaking due to excessive force during flight. The arm 21 can be set to a strip or rod structure to reduce resistance during flight.

As shown in FIG1 , the power component 22 may include a driving member 221 and a blade 222. The driving member 221 may be a power element such as an electric motor, and the blade 222 may be a two-blade blade, a three-blade blade, etc. The present application does not limit the type of the driving member 221 and the number and shape of the blades of the blade 222. A plurality of power components 22 may be installed on the same arm 21, and the plurality of power components 22 are arranged at intervals along the extension direction of the arm 21. In other words, a plurality of driving members 221 are arranged at intervals along the extension direction of the arm 21, and a plurality of blades 222 are correspondingly installed on the driving member 221. The driving member 221 can drive the blade 222 to rotate and thereby drive the unmanned aerial vehicle 100 to fly.

The 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. Two power components 22 are arranged at intervals on the same arm 21, and the unmanned aerial vehicle 100 is a dual-arm 21 quad-rotor configuration. Three power components 22 are arranged at intervals on the same arm 21, and the unmanned aerial vehicle 100 is a dual-arm 21 six-rotor configuration, and so on. It can be selected according to the specific situation of the unmanned aerial vehicle 100. The more power components 22, the greater the weight that the unmanned aerial vehicle 100 can carry. The present application does not limit the number of power components 22.

As shown in FIG. 3 and FIG. 4 , it should be noted that the number of power components 22 on the arms 21 on both sides is the same and the positions are symmetrical, so that the UAV 100 can maintain good balance during flight.

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 colinear in the roll axis direction of the unmanned aerial vehicle 100.

As shown in FIG1 , 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 can 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, and correspondingly, the power component 22 on the arm 21 will also be at a certain angle relative to the roll axis direction, so that the body 10 of the unmanned aerial vehicle 100 can 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.

As shown in FIG. 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, thereby making the unmanned aerial vehicle 100 more flexible during flight and easier to control.

As shown in FIG. 2 and FIG. 5 , when the UAV 100 is ready for storage and transportation after the flight, the arms 21 on both sides can be folded relative to the body 10, that is, the arms 21 are rotated toward one side of the body 10. Correspondingly, the entire arm assembly 20 will be folded relative to the body 10, thereby reducing the volume of the UAV 100, so as to facilitate the storage and transportation of the UAV 100. At this time, the arms 21 on both sides can be parallel to the roll axis direction of the UAV 100.

In some embodiments, when the arm 21 is deployed relative to the body 10, on the same arm 21, the distance between the power component 22 near the second end 212 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.

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

It can be understood that the paddle 222 is connected to the driving member 221 and driven to rotate by the driving member 221, and the driving member 221 is connected to the machine arm 21. Multiple driving members 221 are arranged on the machine arm 21 at intervals, and the orientations of the multiple driving members 221 can all be oriented in the same direction, so that the paddles 222 on the driving members 221 are all oriented to the same side relative to the machine arm 21. For example, multiple driving members 221 are all oriented toward the top of the machine arm 21, and the corresponding paddles 222 installed on the driving members 221 are installed on the upper side of the machine arm 21; multiple driving members 221 are all oriented toward the bottom of the machine arm 21, and the corresponding paddles 222 installed on the driving members 221 are installed on the lower side of the machine arm 21.

As shown in FIG. 6 , in certain embodiments, when a plurality of blades 222 are disposed on the same side of the arm 21 , the paddle disk formed by any two blades 222 are spaced apart in the extension direction of the arm 21 , and adjacent blades 222 may rotate at the same speed or at different speeds without interfering with each other.

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 without interfering with each other.

Of course, in some other embodiments, when multiple blades 222 are arranged on the same side of the arm 21, when the number of the 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.

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 manner of 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.

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 .

It is understandable that the multiple driving members 221 are arranged at intervals on the machine arm 21 and the multiple driving members 221 can face different directions of the machine arm 21, and then the blades 222 on the driving members 221 face different sides relative to the machine arm 21. For example, the directions of two adjacent driving members 221 are opposite, one is arranged upward and the other is arranged downward, and then the two adjacent blades 222 are also arranged on the upper side and the lower side of the machine arm 21, respectively, so that the propeller discs formed by the two adjacent blades 222 when rotating will not interfere with each other, which is convenient for the operation of the unmanned aerial vehicle 100.

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 the end of the arm 21 away from the body 10. As shown in FIGS. 1 and 3, the driving member 221 in the middle of the arm 21 can face downward, and the blade 222 is installed on the lower side of the arm 21, and the driving member 221 at the end of the arm 21 can face upward, and the blade 222 is installed on the upper side of the arm 21. Of course, as shown in FIGS. 8 and 9, the driving member 221 in the middle of the arm 21 can also face upward, and the blade 222 is installed on the upper side of the arm 21, and the driving member 221 at the end of the arm 21 can face downward, and the blade 222 is installed on the lower side of the arm 21.

By analogy, 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 set on different sides of the arm 21. This application does not make specific restrictions on this.

It should be noted that no matter 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 symmetrically arranged, 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.

Please refer to FIG. 3 and FIG. 9 . In certain embodiments, when a plurality of blades 222 are respectively disposed on opposite sides of the machine arm 21 , the paddle disks formed by two adjacent blades 222 at least partially overlap along the rotation axis direction of the blades 222 .

In this way, while ensuring that the UAV 100 can operate normally, 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.

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.

The propeller discs formed by the rotation of two adjacent propeller blades 222 can be at least partially overlapped in the direction of the rotation axis of the propeller blades 222, so that the airflows formed 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 interval between two adjacent driving members 221 will also be reduced accordingly, thereby shortening the overall length of the machine arm 21, improving the maneuverability, and reducing the overall volume during storage and transportation.

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. The present application does not impose any restrictions on this, as long as it can ensure that the unmanned aerial vehicle 100 can fly normally in a good condition.

1 and 6 , in some embodiments, on the same arm 21, one of the power components 22 is disposed at the second end 212, that is, the end of the arm 21 away from the body 10. In this way, the power component 22 at the second end 212 can provide better power output for the UAV 100, and can also improve the controllability and reliability of the UAV 100.

Please refer to FIG. 10 . In some embodiments, on the same machine arm 21 , the central axes of two blades 222 are parallel or form an acute angle.

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.

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 .

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.

Of course, in some embodiments, some of the blades 222 on the same arm 21 may also be oriented obliquely upward or obliquely downward relative to the arm 21, that is, the central axis of some of the blades 222 is perpendicular to the arm 21 but is inclined at an acute angle to the up-down direction, and thus the central axis of some of the blades 222 is arranged at an acute angle to the central axis of the blades 222 arranged in the up-down direction. In this case, the blades 222 arranged at an inclined angle can provide torque for the pitching action of the unmanned aerial vehicle 100, so that the control of the unmanned aerial vehicle 100 can be more flexible and maneuverable.

Referring to Figures 1, 2, 11 and 12, in some embodiments, the arm 21 is connected to the head portion or the tail portion of the body 10. When the arm 21 is connected to the head portion, the arm 21 can be folded toward the tail portion; when the arm 21 is connected to the tail portion, the arm 21 can be folded toward the head direction.

In this way, since the machine arm 21 extends straightly, the machine arm 21 is rotatably connected to the front or rear of the machine, which makes it easier to fold and store, thereby reducing the overall volume when stored.

Specifically, as shown in Figures 1 and 2, the arms 21 can be connected to the nose positions on both sides of the body 10. 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 direction from the nose to the tail of the body 10, and the arm assembly 20 and the body 10 can at least partially overlap to reduce the overall volume of the folded unmanned aerial vehicle 100, which is convenient for storage and transportation of the unmanned aerial vehicle 100.

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 to reduce the overall volume of the folded unmanned aerial vehicle 100, which is convenient for storage and transportation of the unmanned aerial vehicle 100.

Please refer to Figure 13. In some embodiments, the arm 21 can be folded downward along the direction of the body 10 from the nose or the tail 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.

Please refer to FIG. 4 . It should be noted that, in certain embodiments, no matter the arm 21 is connected to the front portion or the rear portion, 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 .

In this way, the UAV 100 can maintain good balance during flight, and avoid the UAV 100 tilting forward or backward after taking off, thereby affecting the flight state.

Specifically, the center of gravity of the UAV 100 can be a straight line where the center of gravity of the entire UAV 100 is located, and all power components 22 of the UAV 100 can provide the power required for the entire UAV to fly. The center of gravity of the UAV 100 passes through the figure surrounded by all power components 22, so that the UAV 100 can maintain good balance during flight, thereby improving the stability, reliability and safety of the UAV 100.

As shown in FIG4 , each of the arms 21 is provided with a first power component 221 and a second power component 222, wherein the first power component 221 is provided close to 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 fuselage 10, the center of gravity of the unmanned aerial vehicle 100 is located at or close to the geometric center of a figure enclosed by the first power components 221 and the second power components 222 of the two arms 21.

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 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, wherein 0≤D≤0.15L. This can better ensure the stable balance of the unmanned aerial vehicle 100 during flight.

Please refer to FIG. 5 , in some 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. In this way, when the arm 21 is folded relative to the body 10, the power component 22 is located in the middle of the body 10 and does not prevent the arm 21 from folding toward the body 10, so that the arm 21 can be folded toward the body 10 to reduce the volume of the whole machine after folding, which is convenient for storage and transportation.

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, thereby preventing the connection between the arm 21 and the body 10 from being damaged due to excessive torque during flight of the unmanned aerial vehicle 100, thereby extending the service life of the unmanned aerial vehicle 100.

Please refer to Figures 1 and 2. In some embodiments, the unmanned aerial vehicle 100 also 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.

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

Specifically, the driving mechanism 30 can be disposed on the body 10, and specifically can be disposed at the connection position between the arm 21 and the body 10. The driving mechanism 30 can adjust the deployment angle of the arm 21 relative to the body 10, so that the UAV 100 can adjust the direction during flight, thereby improving the flexibility of the UAV 100.

Of course, the arm 21 can be automatically unfolded or folded relative to the body 10 through the driving mechanism 30 to avoid damage to the arm 21 due to excessive force during manual operation, or the arm 21 is not in the correct position during manual folding and unfolding, which affects the operation or storage of the unmanned aerial vehicle 100.

Further, as shown in Figures 14 and 15, the driving mechanism 30 may include a motor and a transmission member 31, which are located inside the connection between the body 10 and the arm 21. The motor is not shown in the figure. The motor plays a role of power output. Through the cooperation of the motor and the transmission member 31, the arm 21 can rotate during flight to adjust the deployment angle of the arm assembly 20 relative to the body 10.

The driving mechanism 30 is disposed at the connection between the arm assembly 20 and the body 10. The driving mechanism 30 can drive the two arms 21 to switch between a substantially parallel state and an extended angle to store or operate the arm assembly 20. Thus, the unmanned aerial vehicle 100 can not only realize the extension and retraction of the arm assembly 20 through the driving mechanism 30, but also better realize the angle adjustment during the flight through the driving mechanism 30, which is beneficial to the steering and other operations of the unmanned aerial vehicle 100. Among them, the transmission member 31 may include a gear assembly, which may be composed of a plurality of gears of different sizes that can cooperate with each other.

Please refer to FIGS. 16-18 . In certain embodiments, the arm assembly 20 further includes a duct 223 . The blades 222 are disposed in the duct 223 and connected to the duct 223 .

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.

Specifically, the duct 223 can be set as a circular ring structure, and the duct 223 is connected to the blade end of the blade 222. Among them, the unmanned aerial vehicle 100 provided with the duct 223, the arm 21 can be perpendicular to the roll axis direction of the body 10, that is, it can be understood that the multiple driving 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 direction of the body 10, that is, it can be understood that the multiple driving components are not collinearly arranged along the direction perpendicular to the roll axis, and this application does not limit this.

In some embodiments, when multiple driving components of the unmanned aerial vehicle 100 are arranged in a colinear manner along a direction perpendicular to the roll axis, in order to obtain the 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 driving component 221 driving the blade 222 to rotate 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.

Please refer to FIG. 17 . In some embodiments, when the arm 21 provided with the duct 223 is in a folded state, the radial direction of the duct 223 is parallel to the yaw axis of the unmanned aerial vehicle 100. That is, it can be understood that when the arm assembly 20 provided with the duct 223 is folded, the arm 21 can be rotated to a certain angle first, so that the duct 223 changes from horizontal to vertical, and then 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 unmanned aerial vehicle 100. In this way, the volume of the unmanned aerial vehicle 100 can be effectively reduced when folded, so as to facilitate storage and transportation.

1 and 19 , in some embodiments, the UAV 100 includes a landing gear 40, which is connected to the arm 21 or the body 10. Thus, the UAV 100 can support the body 10 through the landing gear 40 during takeoff and landing to prevent the body 10 from being damaged.

Specifically, the landing gear 40 can be made of metal material, has good structural strength, is not easy to be damaged, and can provide good protection and support for the body 10. As shown in the embodiment of FIG1, the support frame can be a bent tubular structure, and the number of the support frames can be two, which are respectively arranged on both sides below the body 10. For example, the landing gear 40 can be connected to the bottom of the body 10 along the direction from the nose to the tail, or connected to the bottom of the body 10 along the left and right direction, so that the unmanned aerial vehicle 100 can better protect the body 10 during takeoff and landing.

Of course, as shown in the embodiment of FIG19 , in some other embodiments, the landing gear 40 can also be set as a columnar structure, and multiple columnar landing gears 40 are symmetrically connected below the arm 21. In this way, the landing gear 40 in this manner can also well support the body 10. The present application does not limit the specific installation position, quantity, specific structure, etc. of the landing gear 40.

Please refer to Figures 17 to 19. In some 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 installed on the upper side of the end of the arm 21 away from the body 10. In this way, the landing gear 40 is prevented from affecting the rotation of the blade 222 driven by the driving member 221.

Please refer to Figures 1-3. In some embodiments, the unmanned aerial vehicle 100 includes a spraying system 50, which includes a nozzle 52 and a liquid circuit assembly 51 connected to the nozzle 52. The nozzle 52 is disposed on the arm assembly 20, and the liquid circuit assembly 51 is at least partially disposed on the body 10.

In this way, the UAV 100 can perform operations through the spraying system 50, making the operations more convenient and quick.

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.

Referring to FIGS. 1 to 3 , in some embodiments, the liquid 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, and both the water tank 511 and the water pump 512 are disposed on the body 10. Thus, the water pump 512 can absorb the liquid in the water tank 511 and spray it out from the nozzle 52, and spray it downward during the flight of the unmanned aerial vehicle 100, making it more convenient and quick for the user to operate.

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.

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 under the body 10, and improving the operating effect of the unmanned aerial vehicle 100.

In some embodiments, the nozzle 52 is disposed on the arm 21 and is located between two adjacent power components 22; or, the nozzle 52 may be disposed below the blade 222 and is located on the central axis of the blade 222; or, part of the nozzle 52 is disposed on the arm 21 and is located between two adjacent power components 22, and part of the nozzle 52 may be disposed below the blade 222 and is located on the central axis of the blade 222. The present application does not limit the specific installation position of the nozzle 52 on the arm 21, as long as the liquid sprayed by the nozzle 52 can be evenly sprinkled under the wind field formed by the power component 22 to avoid leakage.

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 .

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.

Specifically, the nozzle 52 can be arranged on the duct ring 223 of the blade 222 connected to the lower side of the machine arm 21, and the nozzle 52 faces downward. The nozzle 52 on the duct ring 223 can perform centrifugal spraying through the rotation of the duct ring 223, or can perform pressure spraying through the water pump 512. The nozzle 52 can be arranged below the center of the driving member 221, or can be arranged on the outer peripheral side of the sensor.

Please refer to Fig. 16, in some embodiments, there are multiple nozzles 52 on each duct ring 223, and the multiple nozzles 52 are arranged at intervals along the circumference of the duct ring 223. In this way, the nozzle 52 can spray in a larger range, spray more evenly, and have a better effect.

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.

The embodiment of the present application can use the driving mechanism 30 in the above embodiment to actively drive the machine arm 21 to solve this technical problem. The specific method can be: when the unmanned aerial vehicle 100 is flying at a constant speed, the driving mechanism 30 can drive the deployment angle of the dual machine arms 21 to become smaller, so that the span of the unmanned aerial vehicle 100 is moderate; when the unmanned aerial vehicle 100 decelerates at the head of the field, the driving mechanism 30 can drive the deployment angle of the dual machine arms 21 to increase appropriately, so that the span of the unmanned aerial vehicle 100 is increased, and the contraction effect of the spray width of the unmanned aerial vehicle 100 is reduced, 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 head of the field.

Please refer to Figures 19 to 21. In some embodiments, the unmanned aerial vehicle 100 includes a gimbal camera 60 disposed on the nose side of the body 10, that is, the unmanned aerial vehicle 100 provided with the gimbal camera 60 may include a camera drone, a cross-country drone, and other consumer drones. Compared with the configuration of multiple arms 21, the unmanned aerial vehicle 100 in the embodiment of the present application reduces the problem of the structure such as the arms 21 interfering with the camera's viewing angle, so that the gimbal camera 60 can be more flexible when shooting, and the shooting effect is better.

It should be noted that this type of UAV 100 may fly in some complex scenes, so good flexibility and maneuverability are indispensable for this type of UAV 100. For example, when flying through some narrow spaces, if the arm 21 is too long, it will cause scratches and damage to the UAV 100.

The embodiment of the present application can also solve this technical problem by using the driving mechanism 30 in the above embodiment to actively drive the arms 21. That is, when the UAV 100 flies in a relatively narrow space, the driving mechanism 30 can drive the deployment angle of the dual arms 21 to appropriately reduce, so as to minimize the overall volume of the UAV 100 while ensuring flight, and reduce the difficulty of flying in a narrow environment.

In summary, the unmanned aerial vehicle 100 of the embodiment of the present application simplifies the overall structure of the unmanned aerial vehicle 100 by improving the traditional multi-rotor model, effectively reducing the overall weight, thereby making the unmanned aerial vehicle 100 more flexible and more maneuverable. At the same time, the foldable arm assembly 20 also facilitates the storage and transportation of the unmanned aerial vehicle 100, greatly improving the user experience.

In the description of this specification, the description with reference to the terms "one embodiment", "certain embodiments", "illustrative embodiments", "examples", "specific examples", or "some examples" means that the specific features, structures, materials, or characteristics described in conjunction with the embodiments or examples are 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. Moreover, the specific features, structures, materials, or characteristics described may be combined in any one or more embodiments or examples in a suitable manner.

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 spirit of the present application, and that the scope of the present application is defined by the claims and their equivalents.

Claims

An unmanned aerial vehicle, comprising:

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 of the arm assemblies 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 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.
The unmanned aerial vehicle according to claim 1 is characterized in that, 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 unmanned aerial vehicle.
The unmanned aerial vehicle according to claim 2 is characterized in that, 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.
The unmanned aerial vehicle according to claim 1, characterized in that, on the same arm, a plurality of the blades are arranged on the same side of the arm; or

The plurality of blades are arranged on opposite sides of the machine arm.
The unmanned aerial vehicle according to claim 4, characterized in that, when a plurality of the 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.
The unmanned aerial vehicle according to claim 4 is characterized in that, when the plurality of blades are arranged on opposite sides of the arm, the propeller disks formed by two adjacent blades at least partially overlap in the direction along the rotation axis of the blades.
The unmanned aerial vehicle according to claim 1 is characterized in that, on the same arm, one of the power components is arranged at the second end.
The unmanned aerial vehicle according to claim 1 is characterized in that, on the same arm, the central axes of the two blades are parallel or form an acute angle.
The unmanned aerial vehicle according to claim 1, characterized in that when the arms are folded relative to the body, at least one of the power components is located in the middle of the body.
The unmanned aerial vehicle according to claim 9, characterized in that when the arms are folded relative to the body, at least one of the power components is located in the middle of the side of the body.
The unmanned aerial vehicle according to any one of claims 1 to 10, characterized in that the arm is connected to the head part or the tail part of the body;

When the machine arm is connected to the nose part, the machine arm can be folded toward the tail part;

When the machine arm is connected to the tail portion, the machine arm can be folded toward the nose portion.
The unmanned aerial vehicle according to claim 11 is characterized in that the arms can be folded downwardly along the direction of the body from the nose or the tail when folded.
The unmanned aerial vehicle according to any one of claims 1 to 10 is characterized in that, when the arms are unfolded relative to the body, the center of gravity of the unmanned aerial vehicle passes through a figure enclosed by all the power components on the two arms.
The unmanned aerial vehicle according to claim 13 is characterized in that each of the arms includes a first power component and a second power component, the first power component is arranged close to the first end, and the second power component is arranged at the second end, and when the arms are unfolded relative to the body, the center of gravity line of the unmanned aerial vehicle is located at or close to the geometric center of the figure enclosed by the first power component and the second power component of the two arms.
The unmanned aerial vehicle according to claim 14 is characterized in that 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 body roll axis is L, and the distance between the center of gravity line and the geometric center line is D, wherein 0≤D≤0.15L.
The unmanned aerial vehicle according to any one of claims 1 to 10, characterized in that the arm assembly further comprises a duct, and the blade is disposed in the duct and connected to the duct;

When the machine arm is folded relative to the machine body, the radial direction of the duct is parallel to the yaw axis of the unmanned aerial vehicle.
The unmanned aerial vehicle according to any one of claims 1-10 is characterized in that the unmanned aerial vehicle also includes a driving mechanism, 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 the deployment angle of the arm assembly relative to the body.
The unmanned aerial vehicle according to claim 17 is characterized in that 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.
The unmanned aerial vehicle according to claim 18, characterized in that the transmission member is a gear assembly.
The unmanned aerial vehicle according to claim 17 is characterized in that 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 basically parallel state and an extended angle to store or operate the arm assembly.
The unmanned aerial vehicle according to any one of claims 1 to 8 is characterized in that the strength of the portion where the arm is connected to the body is greater than the strength of other portions.
The unmanned aerial vehicle according to any one of claims 1-10 is characterized in that the unmanned aerial vehicle includes a landing gear, and the landing gear is connected to the arm or the body.
The unmanned aerial vehicle according to claim 22 is characterized in that, when the landing gear is connected to the 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.
The unmanned aerial vehicle according to any one of claims 1-10 is characterized in that the unmanned aerial vehicle includes a spraying system, the spraying system includes a nozzle and a liquid circuit assembly connected to the nozzle, the nozzle is arranged on the arm assembly, and the liquid circuit assembly is at least partially arranged on the body.
The unmanned aerial vehicle according to claim 24, characterized in that the nozzle is arranged on the 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.
The unmanned aerial vehicle according to claim 24 is characterized in that the arm assembly also includes a duct, the blades are arranged in the duct and connected to the duct, and the nozzle is arranged on the duct.
The unmanned aerial vehicle according to claim 26 is characterized in that there are multiple nozzles on each of the ducts, and the multiple nozzles are arranged at intervals along the circumference of the duct.
The unmanned aerial vehicle according to claim 24 is characterized in that the liquid 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 body.
The unmanned aerial vehicle according to any one of claims 1-10 is characterized in that the unmanned aerial vehicle includes a gimbal camera arranged on the nose side of the body.