CN210761299U

CN210761299U - Unmanned aerial vehicle and unmanned aerial vehicle system

Info

Publication number: CN210761299U
Application number: CN201921577794.2U
Authority: CN
Inventors: 黄建新; 肖寒; 刘岩磊
Original assignee: Beijing HWA Create Co Ltd
Current assignee: Beijing HWA Create Co Ltd
Priority date: 2019-09-20
Filing date: 2019-09-20
Publication date: 2020-06-16
Anticipated expiration: 2029-09-20

Abstract

The utility model provides an unmanned aerial vehicle and unmanned aerial vehicle system relates to the aircraft field, and this unmanned aerial vehicle includes that fuselage and symmetry set up in the first flank and the second flank of the both sides of fuselage, all disposes duct power component in the one end that is close to the fuselage of the one end of first flank and the one end that is close to the fuselage of second flank, and duct power component configures to the lift that provides the upward movement for first flank and second flank. Therefore, the embodiment of the utility model provides a technical scheme all disposes duct power component through two flanks at the fuselage, can alleviate the problem that can produce the vortex and lead to the flight stability decline when rotatory between many rotor unmanned aerial vehicle's the rotor among the prior art, has improved flight stability.

Description

Unmanned aerial vehicle and unmanned aerial vehicle system

Technical Field

The utility model relates to an aircraft field particularly, relates to an unmanned aerial vehicle and unmanned aerial vehicle system.

Background

An unmanned aerial vehicle is called an unmanned aerial vehicle for short, and the unmanned aerial vehicle is an unmanned aerial vehicle operated by utilizing radio remote control equipment and a self-contained program control device. The unmanned aerial vehicle is provided with an automatic pilot, an information acquisition device and other instruments, but is not provided with a cockpit. The unmanned aerial vehicle can take off like a common airplane or launch by a boosting rocket under the radio remote control, and can also be carried to the air by a mother aircraft to launch and fly, and operators on the ground, a naval vessel or a mother aircraft remote control station can track, position, remotely control, telemeter and digitally transmit the unmanned aerial vehicle through equipment such as radars and the like.

In recent years, along with the progress of artificial intelligence and advanced manufacturing technology, the application range of the unmanned aerial vehicle is continuously expanded. Besides military use, the unmanned aerial vehicle has good application in civil fields such as agricultural plant protection, power inspection, police law enforcement, geological exploration, environment monitoring, forest fire prevention, environment monitoring, emergency rescue, film and television aerial photography, and the application scene and the use mode of the unmanned aerial vehicle are also in rapid iteration.

At present, the existing unmanned aerial vehicle is mainly a fixed-wing unmanned aerial vehicle, the fixed-wing unmanned aerial vehicle usually needs to run to take off and land, and needs to finish taking off and landing by means of a runway, and some fixed-wing unmanned aerial vehicles finish launching by utilizing an ejection rack or a hand throw, and recycle is realized by utilizing a recycling net and a stopping rope. The existing fixed-wing aircraft needs to finish take-off and landing by means of a runway or other launching and recovery equipment, and the flight cost is invisibly increased.

In order to solve the problem that a runway and other supporting equipment are required to be built for a fixed-wing unmanned aerial vehicle, so that the flying cost is high, a rotor-wing unmanned aerial vehicle is developed. Because the rotary wing type unmanned aerial vehicle can take off and land vertically and hover in the air, the rotary wing type unmanned aerial vehicle is widely applied to the civil field.

Rotor type unmanned aerial vehicle includes single rotor unmanned aerial vehicle and many rotor unmanned aerial vehicle, compares in single rotor unmanned aerial vehicle, and many rotor unmanned aerial vehicle have better flight stability and the nature controlled and obtained more extensive application. What is more common on the market at present is four rotor unmanned aerial vehicle, and its four rotors are the stability of rectangular distribution in order to guarantee flight, and the direction of rotation of two adjacent rotors is opposite to offset the reaction force that produces the fuselage when the rotor is rotatory, guarantee unmanned aerial vehicle's the nature controlled.

However, because unmanned aerial vehicle's miniaturization requirement, two adjacent rotors of current four rotor unmanned aerial vehicle are closer apart from than, and the rotor can produce the vortex when rotatory and exert an influence to other rotors, leads to flight stability to descend.

SUMMERY OF THE UTILITY MODEL

In view of this, the utility model aims at providing an unmanned aerial vehicle and unmanned aerial vehicle system can alleviate the lower problem of flight stability who exists among the prior art.

The utility model provides a technical scheme:

in a first aspect, the embodiment of the utility model provides an unmanned aerial vehicle, including fuselage and symmetry set up in the first flank and the second flank of the both sides of fuselage be close to of first flank the one end of fuselage with being close to of second flank the one end of fuselage all disposes duct power component, duct power component configure into do first flank with the second flank provides upward movement's lift.

In combination with the first aspect, embodiments of the present invention provide a first possible implementation manner of the first aspect, wherein the ducted power assembly includes: the ducted propeller and the ducted motor are arranged inside the ducted body, the ducted body is provided with a through hole, and the through hole is configured to allow airflow to flow inside the ducted body; the ducted electric motor is configured to drive the ducted propeller to rotate to generate an upward lift force.

In combination with the first aspect, embodiments of the present invention provide a second possible implementation manner of the first aspect, where the first side wing and the second side wing both include a wing, and an aileron is configured at one end of the wing far away from the ducted power assembly.

In combination with the first aspect, the embodiment of the utility model provides a third possible implementation mode of the first aspect, wherein, unmanned aerial vehicle still including set up in the inside steering wheel of fuselage and set up in the fuselage both sides just are close to the power component that verts at the rear portion of fuselage, the power component that verts with the steering wheel is connected, the power component that verts configure into for unmanned aerial vehicle provides the lift of upward movement and for unmanned aerial vehicle provides the thrust of forward motion.

With reference to the third possible implementation manner of the first aspect, an embodiment of the present invention provides a fourth possible implementation manner of the first aspect, wherein the tilting power assembly includes a tilting propeller, a tilting motor, and a connecting rod, which are connected in sequence, and one end of the connecting rod, which is far away from the tilting motor, is connected to the steering engine; the steering wheel is configured to pass through the connecting rod drives the tilting motor rotates to horizontal direction or vertical direction, the tilting motor is configured to drive the tilting propeller rotates to generate forward motion thrust or upward motion lift.

With reference to the fourth possible implementation manner of the first aspect, an embodiment of the present invention provides a fifth possible implementation manner of the first aspect, wherein the steering engine includes a steering engine main body and a transmission gear set connected to the steering engine main body, and the steering engine main body is connected to the connecting rod through the transmission gear set.

In combination with the first aspect, an embodiment of the present invention provides a sixth possible implementation manner of the first aspect, wherein the unmanned aerial vehicle further includes an empennage disposed at the rear portion of the fuselage, and the empennage is a vertical fin type fixed wing.

In combination with the sixth possible implementation manner of the first aspect, an embodiment of the present invention provides a seventh possible implementation manner of the first aspect, wherein the vertical fixed wing includes a fixed wing disposed in the fuselage and in parallel with the ground and in both sides of the fuselage vertical tail body and in both sides of the tail body.

In combination with the first aspect, an embodiment of the present invention provides an eighth possible implementation manner of the first aspect, wherein the unmanned aerial vehicle further includes a main flight caster arranged at the lower portion of the fuselage, a first flight caster arranged at the lower portion of the first side wing, and a second flight caster arranged at the lower portion of the second side wing.

In a second aspect, an embodiment of the present invention provides an unmanned aerial vehicle system, including a controller and an unmanned aerial vehicle as in any one of the first aspect and its possible implementation manners, the controller with unmanned aerial vehicle wireless connection.

The embodiment of the utility model provides a following beneficial effect has been brought:

the embodiment of the utility model provides an unmanned aerial vehicle and unmanned aerial vehicle system, wherein, this unmanned aerial vehicle includes that fuselage and symmetry set up in the first flank and the second flank of the both sides of fuselage, all disposes duct power component in the one end that is close to the fuselage of the one end of first flank and the one end that is close to the fuselage of second flank, and duct power component configures to the lift that provides the upward movement for first flank and second flank. Therefore, the embodiment of the utility model provides a technical scheme all disposes duct power component through two flanks at the fuselage, can alleviate the problem that can produce the vortex and lead to the flight stability decline when rotatory between many rotor unmanned aerial vehicle's the rotor among the prior art, has improved flight stability.

In order to make the aforementioned and other objects, features and advantages of the present invention comprehensible, preferred embodiments accompanied with figures are described in detail below.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings that are required to be used in the embodiments will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present invention, and therefore should not be considered as limiting the scope, and for those skilled in the art, other related drawings can be obtained according to the drawings without inventive efforts.

Fig. 1 is a schematic structural diagram of an unmanned aerial vehicle according to an embodiment of the present invention;

fig. 2 is a schematic structural diagram of a ducted power assembly according to an embodiment of the present invention;

fig. 3 is a schematic structural diagram of a first wing or a second wing according to an embodiment of the present invention;

fig. 4 is a top view of a first side wing including a ducted power assembly or a second side wing including a ducted power assembly according to an embodiment of the present invention;

fig. 5 is a front view of a first side wing including a ducted power assembly or a second side wing including a ducted power assembly according to an embodiment of the present invention;

fig. 6 is a bottom view of a first side wing including a ducted power assembly or a second side wing including a ducted power assembly according to an embodiment of the present invention;

fig. 7 is a schematic structural diagram of another unmanned aerial vehicle in a vertical take-off and landing state according to an embodiment of the present invention;

fig. 8 is a schematic structural diagram of another unmanned aerial vehicle in a flat flight state according to an embodiment of the present invention;

fig. 9 is a schematic view of a steering engine according to an embodiment of the present invention;

fig. 10 is a schematic view of an unmanned aerial vehicle system provided by the embodiment of the present invention.

Detailed Description

In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. The components of embodiments of the present invention, as generally described and illustrated in the figures herein, may be arranged and designed in a wide variety of different configurations.

Thus, the following detailed description of the embodiments of the present invention, presented in the accompanying drawings, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative efforts belong to the protection scope of the present invention.

It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined and explained in subsequent figures.

In the description of the present invention, it is to be understood that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, or orientations or positional relationships that are conventionally placed when the products of the present invention are used, or orientations or positional relationships that are conventionally understood by those skilled in the art, and are merely for convenience of description of the present invention and for simplicity of description, and do not indicate or imply that the equipment or components that are referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention.

Furthermore, the terms "first," "second," and the like are used merely to distinguish one description from another, and are not to be construed as indicating or implying relative importance.

In the description of the present invention, it should also be noted that, unless otherwise explicitly specified or limited, the terms "disposed," "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood in specific cases to those skilled in the art.

Based on this, the embodiment of the utility model provides an unmanned aerial vehicle and unmanned aerial vehicle system can alleviate and can produce the problem that vortex interact leads to flight stability to descend when rotatory between many rotor unmanned aerial vehicle's the rotor, can improve flight stability.

The first embodiment is as follows:

referring to fig. 1, the present embodiment provides an unmanned aerial vehicle, which includes a fuselage 5, and a first wing 4 and a second wing 6 symmetrically disposed on two sides of the fuselage, wherein duct power assemblies 3 are disposed at both ends of the first wing close to the fuselage and the second wing close to the fuselage, and the duct power assemblies are configured to provide upward-moving lift force for the first wing and the second wing, that is, the duct power assemblies can provide upward-moving lift force for the whole unmanned aerial vehicle.

In an alternative embodiment, as shown in figure 2, the ducted power assembly comprises: the ducted propeller 31 and the ducted motor (not shown in the figure) are arranged inside the ducted body and connected with the ducted propeller 32, in other words, the ducted propeller and the ducted motor are both arranged inside the ducted body and connected with the ducted motor; the duct body is provided with a through hole 33 which is configured to allow airflow to flow inside the duct body; the ducted motor is configured to drive the ducted propeller to rotate so as to generate lift force moving upwards, and the ducted motor drives the propeller to work when the unmanned aerial vehicle vertically takes off or lands, so that the lift force moving upwards is provided for the whole unmanned aerial vehicle body.

The ducted propeller comprises a paddle disk 321 and blades 322 arranged in the paddle disk, and the blades of the ducted propeller are parallel to the ground.

The ducted propeller works under the driving of the ducted motor, airflow continuously passes through the ducted propeller from a ducted inlet (located at one end, far away from the ground, of the ducted body) of the through hole, and flows out of the ducted body from a ducted outlet (one end, close to the ground, of the ducted body) of the through hole in a high-speed and high-pressure state after accelerating and pressurizing at a propeller disc, upward reaction thrust is generated, and lift force for driving the unmanned aerial vehicle to move upwards is generated. The ducted power assembly is combined with the wings (the first side wings or the second side wings), so that the influence on the aerodynamic part of the aircraft wings is reduced, the airflow disturbance is reduced, and the flight stability is improved.

In an alternative embodiment, the number of the paddles is 3-5, and in this embodiment, 4 paddles are selected.

It should be understood that fig. 2 only schematically illustrates the number of blades of the ducted propeller, which may be adjusted according to actual requirements.

In an alternative embodiment, as shown in fig. 3, the first wing and the second wing each comprise a wing 41, at the end of which remote from the ducted power assembly an aileron 42 is arranged. Specifically, in the length direction of the wing, the aileron is arranged at one end of the wing, which is far away from the ducted power assembly, in the width direction of the wing, the aileron is arranged at one end of the wing, which is far away from the front part of the fuselage, the cross section of the aileron is rectangular, and the long edge of the aileron is parallel to the long edge of the wing.

In an alternative embodiment, as shown in fig. 4, 5 and 6, the ducted power assembly is fixedly connected with the wing (the first wing or the second wing) by a connecting member, for example, the ducted power assembly is fixedly connected with the wing by an air pin.

Of course, in other embodiments, the ducted power assembly and the wing (first or second wing) may be integrally formed, i.e. by die casting.

The unmanned aerial vehicle provided by the embodiment can improve the flight stability on one hand, reduce the flight weight on the other hand and increase the self load weight of the unmanned aerial vehicle on the other hand by arranging the ducted wing part (comprising the ducted power assembly and the wings) of the fuselage; in addition, this contain duct wing part can also reduce the air resistance of aircraft in the flat flight, promotes flight efficiency, increases unmanned aerial vehicle's duration, and the test shows that this unmanned aerial vehicle's load weight compares and promotes more than 20% in traditional unmanned aerial vehicle's conventional overall arrangement, and duration promotes about 45% than traditional unmanned aerial vehicle's conventional overall arrangement.

In an optional embodiment, the unmanned aerial vehicle further comprises an empennage 1 arranged at the rear part of the fuselage, and the empennage is a vertical fin type fixed wing.

In an alternative embodiment, the vertical fin type fixed wing includes a tail body 11 disposed at the fuselage and perpendicular to the fuselage, and fixed wings 12 disposed at both sides of the tail body and parallel to the horizontal ground.

In other embodiments, the tail wing may also include two fixed wings disposed on the left and right sides of the fuselage, and the two fixed wings are symmetrically disposed with respect to the fuselage and form a predetermined angle (e.g., 45 °) with the horizontal plane where the fuselage is located.

The unmanned aerial vehicle provided by the embodiment comprises a machine body and two duct power assemblies, wherein the machine body comprises a machine body, an empennage and two wings, the empennage is arranged at the rear end of the machine body main body, and the two wings are respectively arranged at the left end and the right end of the machine body and extend outwards along the left end and the right end of the machine body; the two ducted power assemblies are respectively arranged on the two wings and are bilaterally symmetrical relative to the fuselage; the two ducted power assemblies are capable of generating an upward thrust. This unmanned aerial vehicle all disposes duct power component through two flanks at the fuselage, can alleviate among the prior art between many rotor unmanned aerial vehicle's the rotor can produce the problem that the vortex leads to flight stability to descend when rotatory, has improved flight stability.

On the basis of the foregoing embodiment, as shown in fig. 7 and 8, an embodiment of the present invention provides another unmanned aerial vehicle, which further includes: set up in the inside steering wheel of fuselage and set up in the fuselage both sides just are close to the power component 2 that verts at the rear portion of fuselage, the power component that verts with the steering wheel is connected, the power component configuration that verts does unmanned aerial vehicle provides the lift of upward movement and does unmanned aerial vehicle provides the thrust of forward motion.

It should be noted here that during takeoff and landing of the drone, both the tilt power assembly and the ducted power assembly provide lift that moves upwards, but only in a relatively small amount when descending, i.e., lift is greater than gravity when ascending and less than gravity when descending.

Specifically, the steering engine and the tilting power assembly are arranged at the rear part of the fuselage, and for example, the steering engine and the tilting power assembly can be arranged between the wing and the empennage and positioned at one end of the fuselage close to the empennage.

In an optional embodiment, the tilting power assembly comprises a tilting propeller 21, a tilting motor 22 and a connecting rod 23 which are connected in sequence, namely, the tilting propeller is connected with the output end of the tilting motor, the input end of the tilting motor is connected with one end of the connecting rod, the other end of the connecting rod is connected with the steering engine, and specifically, one end of the connecting rod, which is far away from the tilting motor, is connected with the steering engine; the steering wheel is configured to pass through the connecting rod drives the tilting motor rotates to horizontal direction or vertical direction, the tilting motor is configured to drive the tilting propeller rotates to generate forward motion thrust or upward motion lift.

In an optional embodiment, the tilt motor is perpendicular to the blades of the tilt propeller, the connecting rod is also perpendicular to the tilt motor, and the connecting rod and the tilt propeller are respectively arranged at two ends of the tilt motor; the tilting motor is configured to rotate to a horizontal direction or a vertical direction so as to drive the tilting propeller to rotate to generate a forward-moving thrust or an upward-moving lift.

The number of the blades of the tilting propeller can also be set according to actual needs, and in an optional embodiment, the number of the blades of the tilting propeller is 5.

Specifically, as shown in fig. 7, when the unmanned aerial vehicle takes off or lands vertically, the tilting motor is parallel to the ground, the tilting motor drives the tilting propeller to rotate, and the tilting propeller and the ducted propeller driven by the ducted motor provide lifting force for the whole unmanned aerial vehicle to ascend or descend; that is to say, this unmanned aerial vehicle is taking off and landing stage, and the duct screw is in the parallel state with the screw that verts, for example can be on same height, and the simultaneous working provides ascending lift for unmanned aerial vehicle and is used for overcoming the influence of gravity, realizes ascending or descending of aircraft. The unmanned aerial vehicle has the advantages of small requirement on take-off sites by adopting a vertical take-off and landing design, high flying efficiency, flexible and convenient use and capability of hovering and cruising quickly in the air.

As shown in fig. 8, when unmanned aerial vehicle flat flies, the duct motor is out of work or stop work, and the motor that verts truns into perpendicular to ground by being on a parallel with ground, and at this moment, the motor that verts drives the screw rotation that verts, provides the thrust of the forward motion when flat flying for unmanned aerial vehicle.

Power component verts (specifically for the motor that verts) through the rotating design, the switching of aircraft taking off and land and flying has been realized, when taking off, the motor that verts provides power with the duct motor, take off at unmanned aerial vehicle and reach the take-off altitude after, duct power component stop work gradually, and simultaneously, power component verts (specifically for the motor that verts) under the control of steering wheel, its angle begins to change, provide the power of motion forward for unmanned aerial vehicle, at the angle change in-process, unmanned aerial vehicle also can obtain the speed of flying forward, when the contained angle of the motor that verts and the duct body becomes 90 (the motor that verts is on a parallel with ground promptly), unmanned aerial vehicle obtains complete (level) forward thrust, duct power system stop work after the flight is stable. It should be noted that the angle between the tilting motor and the duct body is considered to be 0 ° at the beginning, i.e. the tilting motor is perpendicular to the ground.

In an alternative embodiment, as shown in fig. 9, the steering engine includes a steering engine main body 71 and a transmission gear set connected to the steering engine main body, and the steering engine main body is connected to the connecting rod through the transmission gear set.

Specifically, the transmission gear set comprises a first gear 72 and a second gear 73 which are connected, the first gear is connected with the steering engine main body, and the second gear is connected with the connecting rod.

Here unmanned aerial vehicle rear portion's the connecting rod both ends of verting power component are connected with the motor and the paddle that provide power, drive the rotation of the motor that verts of gear realization on the connecting rod through the gear rotation on the steering wheel to realize that unmanned aerial vehicle switches between VTOL and peaceful flight.

In an alternative embodiment, the tilting power assembly and the ducted power assembly are not in the same horizontal plane, in other words, the overall heights of the tilting power assembly and the ducted power assembly are different or the heights of the tilting power assembly and the ducted power assembly are staggered and not in the same horizontal plane.

In an optional embodiment, the unmanned aerial vehicle further comprises a main flight caster arranged on the lower portion of the body, a first flight caster arranged on the lower portion of the first side wing, and a second flight caster arranged on the lower portion of the second side wing.

In an optional embodiment, the drone further comprises an avionics system.

It should be noted that the tilting power assembly is configured to be rotatable within a predetermined angular range, and therefore in other embodiments, a bypass-containing power assembly that is rotatable may also be used for the tilting power assembly.

The embodiment of the utility model provides an unmanned aerial vehicle through the angle change of verting the motor, for the aircraft provides the lift of taking off and land and the power when flying, optimizes the structure of unmanned aerial vehicle at present stage, realizes that unmanned aerial vehicle switches between VTOL and flying.

Example two:

as shown in fig. 10, the embodiment of the present invention further provides an unmanned aerial vehicle system, which includes the controller 100 and the first unmanned aerial vehicle 200, the controller and the unmanned aerial vehicle wireless connection.

In alternative embodiments, the controller may be a wireless remote control device or a ground station control terminal.

The use method of the unmanned aerial vehicle system is as follows: the controller sends a flight task, the flight task can include a preset air route and a plurality of task points in the preset air route, the unmanned aerial vehicle can hover in the air according to the flight task, the aircraft can hover in the air, the suspension point that the unmanned aerial vehicle set up on the preset air route, the unmanned aerial vehicle flies to the task point in the air, because of inertia, the aircraft continues flying, simultaneously, duct power component (the component of duct system) begins to work, rear portion tilting motor changes into and provides lift system by providing flat power of flying into, when arriving at the task point, work simultaneously with the duct system makes unmanned aerial vehicle hover and work at the task point, after finishing the task, execute next task point or return voyage. When executing the next task point, it can be executed as follows: the rear tilting motor is controlled by the steering engine, the angle of the rear tilting motor begins to change, forward power of the aircraft is provided, in the angle change process, the aircraft obtains forward flying speed, when the included angle between the tilting motor and the duct is changed into 90 degrees (the initial angle is regarded as 0 degree), the aircraft obtains complete forward thrust, and the duct power assembly stops working after the flight is stable.

The embodiment of the utility model provides an unmanned aerial vehicle system has the same technical characteristic with the unmanned aerial vehicle that above-mentioned embodiment provided, so also can solve the same technical problem, reach the same technological effect.

The embodiment of the utility model provides an unmanned aerial vehicle system, its technological effect that realizes the principle and produce is the same with aforementioned unmanned aerial vehicle embodiment, and for brief description, the part is not mentioned to unmanned aerial vehicle system embodiment part, can refer to corresponding content in the aforementioned unmanned aerial vehicle embodiment.

In all examples shown and described herein, any particular value should be construed as merely exemplary, and not as a limitation, and thus other examples of example embodiments may have different values.

The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. An unmanned aerial vehicle is characterized by comprising a fuselage, a first side wing and a second side wing which are symmetrically arranged on two sides of the fuselage, wherein duct power components are respectively arranged at one end of the first side wing close to the fuselage and one end of the second side wing close to the fuselage, and are configured to provide lifting force for the first side wing and the second side wing to move upwards;

unmanned aerial vehicle still including set up in the inside steering wheel of fuselage and set up in the fuselage both sides just are close to the power component that verts at the rear portion of fuselage, the power component that verts with the steering wheel is connected, the power component configuration that verts does unmanned aerial vehicle provides the lift of upward movement and does unmanned aerial vehicle provides the thrust of forward motion.

2. The drone of claim 1, wherein the ducted power assembly includes: the ducted propeller and the ducted motor are arranged inside the ducted body and are connected, the ducted body is provided with a through hole, and the through hole is configured to allow airflow to flow inside the ducted body; the ducted electric motor is configured to rotate the ducted propeller to generate an upward moving lift force.

3. The drone of claim 1, wherein the first side wing and the second side wing each include a wing with an aileron disposed at an end of the wing distal from the ducted power assembly.

4. The unmanned aerial vehicle of claim 1, wherein the tilting power assembly comprises a tilting propeller, a tilting motor and a connecting rod which are connected in sequence, and one end of the connecting rod, which is far away from the tilting motor, is connected with the steering engine; the steering wheel is configured to pass through the connecting rod drives the tilting motor rotates to horizontal direction or vertical direction, the tilting motor is configured to drive the tilting propeller rotates to generate forward motion thrust or upward motion lift.

5. The unmanned aerial vehicle of claim 4, wherein the steering engine comprises a steering engine main body and a transmission gear set connected with the steering engine main body, and the steering engine main body is connected with the connecting rod through the transmission gear set.

6. The unmanned aerial vehicle of claim 1, further comprising an empennage disposed at a rear portion of the fuselage, the empennage being a vertical fin type fixed wing.

7. An unmanned aerial vehicle as defined in claim 6, wherein the trailing type fixed wing includes a tail body disposed on the fuselage and perpendicular to the fuselage and fixed wings disposed on both sides of the tail body and parallel to the ground.

8. An unmanned aerial vehicle as defined in claim 1, wherein the unmanned aerial vehicle further comprises a main flight caster disposed at the lower portion of the fuselage, a first flight caster disposed at the lower portion of the first side wing, and a second flight caster disposed at the lower portion of the second side wing.

9. A drone system, comprising a drone according to any one of claims 1 to 8 and a controller, the controller being wirelessly connected with the drone.