CN219029777U

CN219029777U - Unmanned aerial vehicle

Info

Publication number: CN219029777U
Application number: CN202223048754.3U
Authority: CN
Inventors: 吴旭民; 潘屹峰; 李勇; 朱杰; 马进超; 黄吴蒙; 赵晓丹
Original assignee: Guangzhou Imapcloud Intelligent Technology Co ltd
Current assignee: Guangzhou Imapcloud Intelligent Technology Co ltd
Priority date: 2022-11-16
Filing date: 2022-11-16
Publication date: 2023-05-16
Anticipated expiration: 2032-11-16

Abstract

The utility model discloses an unmanned aerial vehicle, which comprises a machine body; the arm wings are arranged on two sides of the machine body and comprise front arm wings and rear arm wings; the power device is arranged on the arm wing to provide power for the unmanned aerial vehicle to move, and the power devices are arranged on the front arm wing and the rear arm wing; the unmanned aerial vehicle is provided with a rotor wing mode and a fixed wing mode, and when the unmanned aerial vehicle is in the rotor wing mode, the power devices on the front arm wing and the rear arm wing are arranged in front of and behind each other in the horizontal direction. According to the layout of the horn wings and the power device, the front and rear pairs of horn wings respectively bear the driving force of the power device, so that moment can be shared, and the two pairs of horn wings are larger in lifting body area. Moreover, the aircraft can fly in two modes of the rotor wing and the fixed wing, and the advantages of multiple rotor wings without runway and the advantage of long-time endurance of the fixed wing can be simultaneously considered.

Description

Unmanned aerial vehicle

Technical Field

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

Background

Along with the rapid development of science and technology, in recent years, unmanned aerial vehicles are increasingly widely applied and developed to various industries, and the application of unmanned aerial vehicles in the present stage already relates to the fields of aerial photography, agriculture and forestry plant protection, geological exploration, electric power inspection, oil and gas pipeline inspection, expressway accident management, forest fire prevention inspection, environmental pollution inspection, emergency rescue and rescue, rescue and disaster relief, inspection and the like.

The existing fixed-wing unmanned aerial vehicle and the multi-rotor unmanned aerial vehicle generally comprise the fixed-wing unmanned aerial vehicle and the multi-rotor unmanned aerial vehicle, the fixed-wing unmanned aerial vehicle has the advantage of long endurance time, but the runway for long-distance sliding is generally needed for taking off and landing, the multi-rotor unmanned aerial vehicle can take off and land vertically without the runway, and the endurance time is lower. Research has unmanned aerial vehicle of many rotor unmanned aerial vehicle take off and land conveniently and fixed wing unmanned aerial vehicle duration advantage concurrently is a big hotspot in the trade

Disclosure of Invention

The utility model provides an unmanned aerial vehicle, and aims to solve the problem that the existing unmanned aerial vehicle cannot have the advantages of fixed wings and multiple rotors.

In order to solve the technical problems, the utility model provides an unmanned aerial vehicle, which comprises:

a body;

the arm wings are arranged on two sides of the machine body and comprise front arm wings and rear arm wings;

the power device is arranged on the arm wing to provide power for the unmanned aerial vehicle to move, and the power devices are arranged on the front arm wing and the rear arm wing;

the unmanned aerial vehicle is provided with a rotor wing mode and a fixed wing mode, and when the unmanned aerial vehicle is in the rotor wing mode, the power devices on the front arm wing and the rear arm wing are arranged in front of and behind each other in the horizontal direction.

The utility model has the beneficial effects that:

when the power output by the power device of the unmanned aerial vehicle is in the direction vertical to the horizontal plane, the unmanned aerial vehicle vertically takes off, lands and hovers in a rotor wing mode, the output of the power device on the rear arm wing is increased, the unmanned aerial vehicle can rotate around the gravity center positioned in the middle of the machine body, the power output by the power device generates force in the horizontal direction, and the unmanned aerial vehicle is switched from the rotor wing mode to the fixed wing mode. When the unmanned aerial vehicle is in a rotor wing mode, the power devices on the front arm wing and the rear arm wing are arranged in front of and behind each other on the horizontal plane, the layout of the front arm wing and the power devices can share moment by respectively bearing the driving force of the power devices through the front arm wing and the rear arm wing, and the lifting body area of the two pairs of the arm wings is larger.

The unmanned aerial vehicle provided by the utility model can fly in two modes of the rotor wing and the fixed wing, can simultaneously take into account the advantages of multiple rotor wings without a runway and the advantages of long-time endurance of the fixed wing, is different from the conventional rotor unmanned aerial vehicle with a composite wing or a tilting mechanism, can switch the unmanned aerial vehicle from the rotor wing mode to the fixed wing mode through the output difference of the power devices on the front arm wing and the rear arm wing, has simple control logic required in the whole flying process, and can safely and effectively switch the gesture.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings needed in the description of the embodiments will be briefly introduced below, and it is obvious that the drawings in the following description are some embodiments of the present application, and other drawings may be obtained by those skilled in the art without inventive effort.

FIG. 1 is a schematic view of a rotor mode structure of a drone according to an embodiment of the present utility model;

FIG. 2 is a schematic view of a model structure of a fixed wing of an unmanned aerial vehicle according to an embodiment of the present utility model;

FIG. 3 is a schematic illustration of a switching of a rotor mode to a fixed wing mode of the drone in an embodiment of the present utility model;

fig. 4 is a schematic view of a rotor mode structure of an unmanned aerial vehicle according to an embodiment of the present utility model;

fig. 5 is a schematic view of a rotor mode structure of a drone according to another embodiment of the present utility model;

FIG. 6 is a schematic view of a fixed wing mode structure of the unmanned aerial vehicle according to another embodiment of the present utility model;

fig. 7 is a schematic view of another view angle structure of a drone according to another embodiment of the present utility model;

FIG. 8 is a schematic illustration of a switching of a rotor mode to a fixed wing mode of the drone in another embodiment of the present utility model;

reference numerals illustrate:

1. the intelligent parking device comprises a machine nest, 11, a parking slope, 12, a stop structure, 13, a bottom plate, 14, a bin cover, 15, a back plate, 110, a limiting inclined plane, 120, a contact inclined plane, 130, a guide part, 140, a limiting pile, 150, a limiting table, 160, an avoidance space, 170, a rotating frame, 180, tarpaulin, 101, a sensing patch radar, 102, a positive electrode charging mandril, 103 and a negative electrode tabletting;

2. unmanned aerial vehicle 210, organism, 220, guide bar, 230, horn wing, 231, forearm wing, 232, back arm wing, 240, power pole, 250, screw, 260, electric tuning, 270, vertical connection wing, 280, vertical wing, 201, anodal charging socket, 202, negative pole charging paster.

Detailed Description

The following description of the embodiments of the present utility model will be made clearly and fully with reference to the accompanying drawings, in which it is evident that the embodiments described are some, but not all embodiments of the utility model. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.

In the description of the present utility model, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings are merely for convenience in describing the present utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present utility model. Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include one or more of the described features. In the description of the present utility model, the meaning of "a plurality" is two or more, unless explicitly defined otherwise.

It is also to be understood that the terminology used in the description of the utility model is for the purpose of describing particular embodiments only and is not intended to be limiting of the utility model. As used in this specification and the appended claims, the singular forms "a," "an," and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise.

It should be further understood that the term "and/or" as used in the present specification and the appended claims refers to any and all possible combinations of one or more of the associated listed items, and includes such combinations.

The embodiment of the utility model provides an unmanned aerial vehicle 2, as shown in fig. 1-8, including a machine body 210, a horn wing 230 and power devices, where the horn wing 230 is disposed at two sides of the machine body 210, and includes a front arm wing 231 and a rear arm wing 232 at the front, the power devices are disposed on the horn wing 230 to provide power for the movement of the unmanned aerial vehicle 2, at least one power device is disposed on each horn wing 230, the power devices are disposed on the front arm wing 231 and the rear arm wing 232, the unmanned aerial vehicle 2 can be rotated by adjusting the output of the power devices, when the rotor wing mode and the fixed wing mode are switched, the unmanned aerial vehicle 2 takes off, lands and hovers vertically in the rotor wing mode when the power output of the power devices is in the direction of the vertical horizontal plane, the power devices on the rear arm wing 232 can rotate around the center of gravity at the middle of the machine body 210, the power output of the power devices generates a force in the horizontal direction, and the unmanned aerial vehicle 2 is switched from the rotor wing mode to the fixed wing mode. And the power units located on the forearm wings 231 and the rear arm wings 232 are positioned in tandem in the horizontal direction when the drone 2 is in rotor mode. In this layout of the arm wing 230 and the power unit, the front and rear pairs of arm wings 230 bear the driving force of the power unit, respectively, so that the moment can be shared, and the lift body area of the two pairs of arm wings 230 is larger.

The embodiment of the utility model provides an unmanned aerial vehicle 2, which can fly in two modes of a rotor wing and a fixed wing, can simultaneously consider the advantages of multiple rotor wings without a runway and the advantages of long-time endurance of the fixed wing, and is different from the traditional 4+1 composite wing or the rotor unmanned aerial vehicle 2 with a tilting mechanism, the unmanned aerial vehicle 2 can be switched from the rotor wing mode to the fixed wing mode through the output difference of power devices on a front arm wing 231 and a rear arm wing 232, the required control logic in the whole flying process is simple, and the gesture switching can be safely and effectively carried out.

In an alternative embodiment, the power device comprises a power rod 240, a propeller 250 and an electric adjuster 260, wherein the power rod 240 is arranged on the horn wing 230, a motor is arranged in the power rod, the propeller 250 is arranged at the front end of the power rod 240 and is connected with the motor, when the unmanned aerial vehicle 2 is in a rotor wing mode, the power rod 240 is vertical, the propeller 250 on the horn wing 230 presents a multi-rotor wing layout, the electric adjuster 260 is used for adjusting the output of the motor, the rotating speed of the propeller 250 is adjusted, and the unmanned aerial vehicle 2 is rotated by adjusting the output of the power device to switch between the rotor wing mode and the fixed wing mode.

In a specific embodiment, as shown in fig. 1-4, the unmanned aerial vehicle 2 is designed to have better rotor flight efficiency, the machine body 210 and the arm wings 230 are designed based on the multi-rotor unmanned aerial vehicle 2, four arms are optimized to be the arm wings 230, and when the unmanned aerial vehicle 2 is in a rotor mode, two front arm wings 231 and two rear arm wings 232 are both acute angles to the horizontal, so that when the power device drives the unmanned aerial vehicle, the front arm wings 231 and the rear arm wings 232 can both increase the lift force in the flight of the unmanned aerial vehicle 2. The rotor wing mode is shown in fig. 1, the machine body 210 has a certain upward inclination angle, the fixed wing mode is shown in fig. 2, the power direction provided by the propeller 250 has a certain included angle with the horizontal plane, and the unmanned aerial vehicle 2 is switched from the rotor wing mode to the fixed wing mode as shown in fig. 3.

The power units on the front arm wing 231 and the two rear arm wings 232 have two layout modes, the power rod 240 is arranged at the end part of the arm wing 230 and has a certain included angle with the arm wing 230, and in one layout mode, when the unmanned aerial vehicle 2 is in a rotor wing state, the propeller 250 arranged on the front arm wing 231 is positioned above the arm wing 230, and the propeller 250 arranged on the rear arm wing 232 is positioned below the arm wing 230. In another arrangement, when the unmanned aerial vehicle 2 is in the rotor state, the propeller 250 provided on the front arm wing 231 is located below the arm wing 230, and the propeller 250 provided on the rear arm wing 232 is located above the arm wing 230. Both layout modes can enable one of the power device of the unmanned aerial vehicle 2 positioned on the front arm wing 231 and the power device of the unmanned aerial vehicle positioned on the rear arm wing 232 to play a role in pushing and the other plays a role in pulling in the flying process, and the modal performance of the rotor wing of the unmanned aerial vehicle 2 can be greatly improved.

In an alternative embodiment, when the unmanned aerial vehicle 2 is in the rotor mode, the height difference of the propeller 250 on the front arm wing 231 and the rear arm wing 232 is 0% -50% of the center distance between the motors on the front arm wing 231 and the rear arm wing 232, so that the flying capability of the rotor mode of the unmanned aerial vehicle 2 can be ensured, and when the height difference exceeds 50%, the unmanned aerial vehicle is difficult to fly. In a preferred embodiment, the propellers 250 on the forearm wings 231 are at substantially the same height or level as the propellers 250 on the rear arm wings 232 when the drone 2 is in rotor mode, in which way the rotor mode of the drone 2 will have better lateral movement performance. As shown in fig. 4, when the unmanned aerial vehicle 2 is in the rotor mode, the propeller 250 provided at the front arm wing 231 is located below the arm wing 230, and the propeller 250 provided at the rear arm wing 232 is located above the arm wing 230, but the present utility model is not limited to this embodiment.

The plane of the arm wing 230 optimized by the multi-rotor unmanned aerial vehicle arm is close to a triangle, so that a triangle wing shape is formed, and the front arm wing 231 and the rear arm wing 232 are oppositely arranged, that is, the tip of the triangle faces the middle part of the machine body 210, so that a good effect can be achieved.

In another specific embodiment, as shown in fig. 5-8, the unmanned aerial vehicle 2 is designed to have better flying efficiency of fixed wing, the body 210 and the arm wing 230 are designed based on the fixed wing aircraft, the rotor wing mode is shown in fig. 5, the whole body 210 is vertical, the fixed wing mode is shown in fig. 6, the whole body 210 is horizontal, and the unmanned aerial vehicle 2 is switched from the rotor wing mode to the fixed wing mode as shown in fig. 8.

The forearm wing 231 of unmanned aerial vehicle 2 sets up in the lower part of organism 210, and the rear arm wing 232 sets up in the upper portion of organism 210, and the arm wing 230 constitutes the tandem wing overall arrangement, and fixed wing flight performance has very big promotion than traditional fixed wing unmanned aerial vehicle 2, can carry out the continuation of the journey flight of longer time.

The longitudinal connecting wing 270 is further arranged between the front arm wing 231 and the rear arm wing 232, so that the strength of the arm wing 230 can be enhanced, and the vertical stability can be improved.

The horn wing 230 is further provided with a vertical wing 280, the power rod 240 is arranged on the horn wing 230 in parallel to the axis of the machine body 210, and the propeller 250 is positioned beyond the front end surface of the horn wing 230, and the forward extension surface of the horn wing 230 is outside the diameter of the propeller 250. The vertical wing 280 can rack the power bar 240 far, on the one hand, locating the propeller 250 at a position that pays out the horn wing 230 and that does not intersect the horn wing 230, while also increasing the pitch of the propeller 250 on the forearm wing 231 and the propeller 250 on the trailing arm wing 232. The two aeroplane arm wings 230 bear the driving force of the two sets of propellers 250 respectively to share moment, the two aeroplane arm wings 230 increase the lifting body area, and the two sets of propellers 250 vertically stop the wind field to surround all the lifting aeroplane arm wings 230, so that crosswind is blocked, the incoming flow of the crosswind has larger influence on vertical flight, and the wind resistance is stronger. The propeller 250 is outside the horn airfoil 230, and the high-speed air flow of the fixed-wing fly does not pass through the surface of the horn airfoil 230, so that the lift force efficiency is increased. On the other hand, the vertical wing 280 can also play a role of a vertical tail, so as to help the unmanned aerial vehicle 2 keep balanced, assist in completing steering actions and the like, and an RTK antenna can be arranged in the vertical wing 280.

In an alternative embodiment, the unmanned aerial vehicle 2 further includes guide bars 220, the guide bars 220 are disposed on two sides of the body 210, the guide bars 220 may be disposed at rear ends of the power bars 240, and the guide bars 220 guide the unmanned aerial vehicle to drop into the nest when the unmanned aerial vehicle 2 drops.

In an alternative embodiment, a battery is disposed in the body 210, and as shown in fig. 5 and 7, a positive charging socket 201 and a negative charging patch 202 are disposed at the tail of the body 210. The rear part of the machine body 210 is provided with a battery equipment bin, a battery is arranged in the battery equipment bin, the tail part of the machine body 210 is provided with a connector for being connected with a machine nest for battery charging, wherein the positive charging jack 201 is positioned at the lower side of the tail part of the machine body 210, and the negative charging patch 202 is positioned at the upper side of the tail part of the machine body 210, so that the unmanned aerial vehicle 2 can be conveniently charged when being parked on the machine nest.

In this embodiment the drone 2 adopts a charging mode, the battery of which may be designed to be either detachable or non-detachable. Of course, a battery replacing mode can be adopted independently, and no charging structure is designed in the tail part and the groove of the machine body 210.

In an alternative embodiment, the head of the body 210 is provided with an acrylic hood, in which a tri-axial cradle head is mounted, and the unmanned aerial vehicle 2 can perform shooting operations in both a rotor mode and a fixed wing mode. A flight control arrangement and an umbrella bin device are provided at the upper part of the body 210.

The foregoing is merely a specific embodiment of the present application, but the protection scope of the present application is not limited thereto, and any equivalent modifications or substitutions will be apparent to those skilled in the art within the scope of the present application, and these modifications or substitutions should be covered in the protection scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.

Claims

1. An unmanned aerial vehicle, comprising:

a body;

2. The unmanned aerial vehicle of claim 1, wherein the power device comprises:

the power rod is arranged on the arm wing, a motor is arranged in the power rod, and the power rod is vertical to the horizontal plane when the unmanned aerial vehicle is in a rotor wing mode;

the propeller is arranged at the front end of the power rod and is connected with the motor;

and the electric power is used for adjusting the output of the motor.

3. The unmanned aerial vehicle of claim 2, wherein,

when the unmanned aerial vehicle is in a rotor wing mode, the horn wing and the horizontal plane form an acute angle;

the propeller on the forearm wing is located above the horn wing, the propeller on the rear arm wing is located below the horn wing, or,

the propeller on the forearm wing is located below the horn wing and the propeller on the rear arm wing is located above the horn wing.

4. The unmanned aerial vehicle of claim 2, wherein the propeller height difference on the forearm wing and the rear arm wing is 0% -50% of the motor center-to-center distance on the forearm wing and the rear arm wing when the unmanned aerial vehicle is in rotor mode.

5. The unmanned aerial vehicle of claim 1, wherein the forearm wing and the rear arm wing are both delta wings and are oppositely disposed.

6. The unmanned aerial vehicle of claim 2, wherein the forearm wing is located in a lower portion of the airframe and the rear arm wing is located in an upper portion of the airframe;

the power device on the forearm wing is positioned at the lower part of the forearm wing, and the power device on the rear arm wing is positioned at the upper part of the rear arm wing.

7. The drone of claim 6, further comprising a longitudinal connection wing connecting the forearm wing and the trailing arm wing.

8. The unmanned aerial vehicle of claim 6, further comprising a vertical wing disposed on the horn wing, the power lever disposed on the vertical wing, and such that

The propeller is located at a position beyond the front end face of the horn wing, and the forward extension face of the horn wing is located outside the diameter of the propeller.

9. The unmanned aerial vehicle of claim 2, further comprising a guide bar disposed on both sides of the body, the guide bar being disposed at a rear end of the power bar.

10. The unmanned aerial vehicle of claim 1, wherein a battery is provided in the body and a positive charging socket and a negative charging patch are provided at the tail of the body.