CN116692043A - Vertical lifting fixed wing unmanned plane - Google Patents

Abstract

The invention discloses a vertical lifting fixed wing unmanned aerial vehicle. Comprising the following steps: a body; wings are connected to two sides of the fuselage; the lifting systems are arranged on wings on two sides of the machine body, and can generate thrust in the vertical direction; the propulsion system is arranged on wings on two sides of the machine body, and the propulsion system can change the thrust direction of the propulsion system so that the propulsion system has a first state when providing lift force in the vertical direction and a second state when providing thrust force in the horizontal direction; the vertical lifting fixed wing unmanned aerial vehicle is provided with a lifting state when the propulsion system is in a first state and a cruising state when the propulsion system is in a second state, and at least one of the propulsion system and the lifting system provides lifting force in the vertical direction when the vertical lifting fixed wing unmanned aerial vehicle is in the lifting state. The vertical lifting fixed wing unmanned aerial vehicle has higher safety performance, and can ensure the safe landing of the unmanned aerial vehicle when part of power fails.

Description

Vertical lifting fixed wing unmanned plane

Technical Field

The invention relates to the technical field of unmanned aerial vehicles, in particular to a vertical lifting fixed wing unmanned aerial vehicle.

Background

With the rapid development of unmanned aerial vehicle technology, civil unmanned aerial vehicle has obtained wide application in fields such as take photo by plane, survey and drawing, commodity circulation, plant protection, electric power inspection, and traditional unmanned aerial vehicle mainly includes rotor unmanned aerial vehicle and fixed wing unmanned aerial vehicle, and rotor unmanned aerial vehicle has the shortcoming such as the navigation of time of the journey is short, and the flight speed is low, and fixed wing unmanned aerial vehicle then must take off and land based on the running, is limited to take off and land the requirement can't obtain the application in some complicated topography, so has developed vertical lift fixed wing unmanned aerial vehicle gradually.

The vertical lifting fixed wing unmanned aerial vehicle has the characteristics of vertical take-off and landing of the rotor wing type aircraft and the advantages of high flight efficiency and high flight speed of the fixed wing, can meet the take-off and landing and operation requirements of complex terrains, has the advantages of long endurance, large load and high efficiency, has wide application prospect, and mainly comprises: the rotor wing is used as a vertical lift rotor wing when taking off and landing vertically, and is also used as a fixed wing pulling force/propelling propeller, but in the lifting and cruising process of the unmanned aerial vehicle, any propeller breaks down, and the unmanned aerial vehicle cannot lift and cruise normally.

Disclosure of Invention

The present invention aims to solve at least one of the technical problems existing in the prior art. Therefore, the invention provides the vertical lifting fixed wing unmanned aerial vehicle, which can improve the safety performance of the unmanned aerial vehicle and ensure the safe landing of the unmanned aerial vehicle when part of power fails.

According to a first aspect of the present invention, a vertical lift fixed wing unmanned aerial vehicle includes:

a body;

the wings are connected to two sides of the fuselage;

the lifting systems are arranged on the wings on two sides of the machine body, and can generate thrust in the vertical direction;

the propulsion system is arranged on the wings on two sides of the fuselage and can change the thrust direction of the propulsion system so that the propulsion system has a first state when providing lift force in the vertical direction and a second state when providing thrust force in the horizontal direction;

wherein the vertical lift fixed wing unmanned aerial vehicle has a lift state when the propulsion system is in the first state and a cruise state when the propulsion system is in the second state, and at least one of the propulsion system and the lift system provides lift in a vertical direction when the vertical lift fixed wing unmanned aerial vehicle is in the lift state.

The vertical lifting fixed wing unmanned aerial vehicle provided by the embodiment of the invention has at least the following beneficial effects:

the vertical lifting fixed wing unmanned aerial vehicle is provided with two power systems: the unmanned aerial vehicle is provided with a lifting state and a second state, the unmanned aerial vehicle is provided with a lifting state corresponding to the first state and a cruising state corresponding to the second state, when the unmanned aerial vehicle is in the lifting state, at least one of the lifting system and the propulsion system (in the first state) works to provide thrust in the vertical direction, so that the unmanned aerial vehicle is vertically lifted, when the unmanned aerial vehicle is cruising, the propulsion system is converted into the second state to provide thrust in the horizontal direction for the unmanned aerial vehicle, the fixed wing provides thrust in the vertical direction for the unmanned aerial vehicle, the unmanned aerial vehicle cruises at a high speed, and no matter whether the unmanned aerial vehicle is in the lifting state or the cruising state, any one power system fails, the other power system can provide thrust in the vertical direction for the unmanned aerial vehicle, and the unmanned aerial vehicle is ensured to smoothly fall, so that the crash of the unmanned aerial vehicle is avoided.

In other embodiments of the invention, the propulsion system comprises at least one propeller connected to the wing and being capable of rotation in a vertical direction with respect to the wing to switch the propulsion system between the first state and the second state.

In other embodiments of the present invention, the propulsion system includes a first connector and a plurality of propellers, the first connector is disposed on the wing parallel to the central axis of the fuselage, each of the propellers is divided into two groups, and the two groups of propellers are respectively disposed at two ends of the first connector in the axial direction.

In other embodiments of the invention, the propeller on the front side of the fuselage is defined as a first propeller and the propeller on the rear side of the fuselage is defined as a second propeller, the first propeller having a first rotational action to switch the first propeller between the first state and the second state, the second propeller having a second rotational action to switch the second propeller between the first state and the second state, and the rotational directions of the first and second rotational actions being opposite.

In other embodiments of the invention, the propeller located at the front side of the fuselage is defined as a first propeller, the propeller located at the rear side of the fuselage is defined as a second propeller, both the first propeller and the second propeller are capable of rotating in a vertical direction relative to the first connection, and the first propeller is located vertically above the first connection and/or the second propeller is located vertically below the first connection when the propulsion system is in the first state.

In other embodiments of the present invention, the vertical lift fixed wing unmanned aerial vehicle further has a landing gear, the first connection member is disposed under the wing in a vertical direction, and the landing gear is connected to the first connection member.

In other embodiments of the present invention, the lifting system includes a second connecting member and a plurality of propellers, the second connecting member is disposed parallel to the central axis of the fuselage and is disposed on the wing, each of the propellers is divided into two groups, and the two groups of propellers are disposed on two ends of the second connecting member in the axial direction.

In other embodiments of the invention, the propeller is arranged at a side of the second connection piece remote from the wing.

In other embodiments of the present invention, the vertical lift fixed wing unmanned aerial vehicle further includes an aileron and a flap, where the aileron and the flap each have two groups, the two groups of ailerons are symmetrically disposed on the wings on two sides of the fuselage along a central axis of the fuselage, the two groups of flaps are symmetrically disposed on the wings on two sides of the fuselage along the central axis of the fuselage, and each of the aileron and each of the flap can independently swing in a vertical direction relative to the wings.

In other embodiments of the present invention, the lifting system is disposed on a side of the wing that is relatively far from the fuselage, the propulsion system is disposed on a side of the wing that is relatively close to the fuselage, or the lifting system is disposed on a side of the wing that is relatively close to the fuselage, and the propulsion system is disposed on a side of the wing that is relatively far from the fuselage.

Additional aspects and advantages of the invention will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention.

Drawings

The invention is further described with reference to the accompanying drawings and examples, in which:

FIG. 1 is a schematic perspective view of a vertical lift fixed wing unmanned aerial vehicle in an embodiment of an aspect of the present invention;

FIG. 2 is a top view of a vertical lift tab drone in an embodiment of an aspect of the present invention;

fig. 3 is a front view of a vertical lift tab unmanned aerial vehicle in an embodiment of an aspect of the present invention.

Reference numerals:

a fuselage 100;

wing 200, aileron 210, flap 220;

propulsion system 300, first connector 310, first propeller 320, second propeller 330;

a lifting system 400, a second connector 410;

landing gear 500.

Detailed Description

Embodiments of the present invention are described in detail below, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to like or similar elements or elements having like or similar functions throughout. The embodiments described below by referring to the drawings are illustrative only and are not to be construed as limiting the invention.

In the description of the present invention, it should be understood that references to orientation descriptions such as upper, lower, front, rear, left, right, etc. are based on the orientation or positional relationship shown in the drawings, are merely for convenience of description of the present invention and to simplify the description, and do not indicate or imply that the apparatus or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus should not be construed as limiting the present invention.

In the description of the present invention, the meaning of a number is one or more, the meaning of a number is two or more, and greater than, less than, exceeding, etc. are understood to exclude the present number, and the meaning of a number is understood to include the present number. The description of the first and second is for the purpose of distinguishing between technical features only and should not be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated or implicitly indicating the precedence of the technical features indicated.

In the description of the present invention, unless explicitly defined otherwise, terms such as arrangement, installation, connection, etc. should be construed broadly and the specific meaning of the terms in the present invention can be reasonably determined by a person skilled in the art in combination with the specific contents of the technical scheme.

In the description of the present invention, the descriptions of the terms "one embodiment," "some embodiments," "illustrative embodiments," "examples," "specific examples," or "some examples," etc., mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the present invention. In this specification, schematic representations of the above terms do not necessarily refer to the same embodiments or examples. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.

The invention provides a vertical lifting fixed wing unmanned aerial vehicle, which can improve the safety performance of the unmanned aerial vehicle and prevent the unmanned aerial vehicle from crashing when part of power fails. In order to achieve the above purpose, the vertical lifting fixed wing unmanned aerial vehicle provided by the invention comprises a fuselage, wings and two sets of power systems: the system comprises a lifting system and a propulsion system, wherein the propulsion system is provided with a first state and a second state, so that the unmanned aerial vehicle is provided with a lifting state when the propulsion system is in the first state and a cruising state when the propulsion system is in the second state, and in any state, if one power system fails and cannot provide power, the other power system can ensure that the unmanned aerial vehicle falls safely. Embodiments of the present invention are specifically described below with reference to the accompanying drawings.

In some embodiments, referring to fig. 1 to 3, a vertical lift fixed wing unmanned aerial vehicle (hereinafter referred to as an unmanned aerial vehicle) according to the present invention includes a fuselage 100 and a wing 200, and two power systems: a lift system 400 and a propulsion system 300, wherein the lift system 400 is capable of generating a thrust in a vertical direction, the thrust direction of the propulsion system 300 being switchable between a vertical direction and a horizontal direction such that the propulsion system 300 has a first state when the thrust direction is in the vertical direction and a second state when the thrust direction is in the horizontal direction.

It should be noted that, the fuselage 100 is the main body of the unmanned aerial vehicle, the wings 200 are symmetrically disposed on two sides of the fuselage 100 along the central axis of the fuselage 100, the lifting system 400 and the propulsion system 300 are both provided with two sets of wings 200 and are also symmetrically disposed on two sides along the central axis of the fuselage 100, so as to ensure that the unmanned aerial vehicle can be used normally, the unmanned aerial vehicle has a lifting state when the propulsion system 300 is in the first state and a cruising state when the propulsion system 300 is in the second state, it can be understood that when the unmanned aerial vehicle is lifted vertically, at least one of the lifting system 400 and the propulsion system 300 is required to provide thrust in the vertical direction so as to enable normal lifting, generally in order to ensure rapid lifting, the lifting system 400 and the propulsion system 300 can simultaneously provide thrust in the vertical direction for the unmanned aerial vehicle, so that the unmanned aerial vehicle rises fast (it should be noted that, in some actual use cases, the propulsion system 300 does not need to work when the unmanned aerial vehicle is lifted, only the lifting system 400 provides power to lift the unmanned aerial vehicle), after reaching the expected height, the unmanned aerial vehicle can keep a hovering state in the air to shoot or other works, when the unmanned aerial vehicle is required to cruise at high speed, the propulsion system 300 needs to be switched from a first state to a second state, that is, the unmanned aerial vehicle provides thrust in the water direction, at this moment, the lifting system 400 can stop running, only the propulsion system 300 provides thrust in the water direction, and the fixedly arranged wing 200 provides thrust in the vertical direction for the unmanned aerial vehicle, so that the unmanned aerial vehicle can fly at high speed in the air to realize cruise.

And no matter unmanned aerial vehicle is in lifting state or cruising state, arbitrary driving system breaks down, another driving system homoenergetic is enough to ensure unmanned aerial vehicle safety landing, prevent unmanned aerial vehicle to lose the power crash, for convenience description, we exemplify the circumstances that probably appears, for example unmanned aerial vehicle is in lifting state wherein lifting system 400 breaks down and can't provide power, propulsion system 300 is in first state this moment, can continue to provide thrust on the vertical direction to unmanned aerial vehicle, ensure unmanned aerial vehicle continuously accomplish lift and hover or emergency landing, overhaul the trouble, unmanned aerial vehicle then can not crash from the sky because of power loss, for example, propulsion system 300 breaks down under cruising state again, unmanned aerial vehicle can't continue high-speed flight, wing 200 can not provide thrust on the vertical direction to unmanned aerial vehicle, lifting system 400 can start, provide thrust on the vertical direction to unmanned aerial vehicle, ensure that work is accomplished smoothly, or with unmanned aerial vehicle landing, to overhaul the trouble, in any driving system of unmanned aerial vehicle is in what state, when unmanned aerial vehicle breaks down, another driving system can ensure that unmanned aerial vehicle safety to land down, the accident can not take place, thereby the security performance of unmanned aerial vehicle has been improved.

In some embodiments, the propulsion system 300 includes at least one propeller, and it can be appreciated that the propeller is the most concise and practical solution among the power sources of the unmanned aerial vehicle, most of the existing unmanned aerial vehicles use propeller rotation to provide power, the propeller is connected to the wing 200 and can rotate in a vertical direction relative to the wing 200 (meaning that the propeller integrally rotates relative to the wing 200 instead of the rotation of the propeller), it is required that the propeller can be disposed at any position on the wing 200, but the propellers on both sides of the wing 200 must be symmetrically disposed along the central axis of the fuselage 100 to ensure that the unmanned aerial vehicle can normally operate, the propulsion system 300 is in a first state when the thrust direction generated by the rotation of the propeller is in a vertical direction, and the propulsion system 300 is in a second state when the thrust direction generated by the rotation of the propeller is in a horizontal direction, so that the unmanned aerial vehicle can switch between a lifting state and a cruising state.

In some embodiments, referring to fig. 1 and 2, the propulsion system 300 includes a first connector 310 and a plurality of propellers, the plurality of propellers are divided into two groups, the two groups of propellers are respectively disposed at two ends of the first connector 310 in the axial direction, in the illustrated embodiment, the number of propellers is two, the two propellers are disposed at two ends of the first connector 310 in the axial direction, the axis of the first connector 310 and the central axis of the fuselage 100 are disposed in parallel, and the first connector 310 is connected to the wing 200, it can be understood that the propellers are disposed at the two ends of the first connector 310 in the axial direction, so that when each propeller works, the unmanned aerial vehicle can be ensured to fly stably without deflection and shaking, and thus, the unmanned aerial vehicle can be ensured to lift and cruise normally.

In some embodiments, for convenience of description, we define the propeller located at the front side of the fuselage 100 to be the first propeller 320, the propeller located at the rear side of the fuselage 100 to be the second propeller 330, and both the first propeller 320 and the second propeller 330 are capable of rotating in a vertical direction with respect to the first link 310 (meaning that the propeller as a whole rotates with respect to the first link 310, rather than the rotation of the propeller), so that the propulsion system 300 is switched between a first state and a second state, wherein the rotating action of the first propeller 320 with respect to the first link 310 is a first rotating action, the rotating action of the second propeller 330 with respect to the first link 310 is a second rotating action, and the directions of the first rotating action and the second rotating action are opposite, that is, one of the first propeller 320 and the second propeller 330 rotates upward in a vertical direction with respect to the first link 310, and the other rotates downward in a vertical direction with respect to the first link 310.

In other embodiments, the directions of the first rotation and the second rotation can be identical, for example, when the propulsion system 300 is in the first state, the first propeller 320 and the second propeller 330 are both vertically above the first connection member 310, or the first propeller 320 and the second propeller 330 are both vertically below the first connection member 310, and when the first state needs to be switched to the second state, the directions of the rotation of the first propeller 320 and the second propeller 330 are identical, and the first propeller 320 and the second propeller 330 are both rotated downward by 90 ° or upward by 90 ° in the vertical direction relative to the first connection member 310, but after rotation, one of the first propeller 320 and the second propeller 330 needs to reverse the rotation direction, so that the same direction of the thrust generated by the first propeller 320 and the second propeller 330 in the horizontal direction can be ensured, and the unmanned aerial vehicle can cruise at high speed.

It should be noted that, referring to fig. 1 and fig. 2, when the propulsion system 300 is in the first state, the first propeller 320 on the front side is located above the first connector 310 in the vertical direction, the second propeller 330 on the rear side is located below the first connector 310 in the vertical direction, but the thrust directions generated by the rotation of the first propeller 320 and the second propeller 330 are consistent, when the first propeller 320 is required to be switched to the second state, the first propeller 320 rotates downward in the vertical direction relative to the first connector 310, the second propeller 330 rotates upward in the vertical direction relative to the first connector 310, the rotation directions of the first propeller and the second propeller are opposite, after each rotation direction is 90 °, the propulsion system 300 can be switched to the second state, at this time, the thrust directions generated by the rotation of the first propeller 320 and the rotation of the second propeller 330 are not required to be changed, and the thrust directions generated by the rotation of the first propeller 320 are identical, so that the unmanned plane can be applied with the thrust in the horizontal direction, and the unmanned plane can cruise at high speed in air.

In other embodiments, the front first propeller 320 is vertically below the first connector 310, the rear second propeller 330 is vertically above the first connector 310, when the first propeller 320 rotates upward relative to the first connector 310 in the vertical direction and the second propeller 330 rotates downward relative to the first connector 310 in the vertical direction when the second state is required to be converted, the rotation directions of the first propeller 320 and the second propeller 330 are opposite, and after the rotation directions of the first propeller 320 and the second propeller 330 are respectively rotated by 90 °, the rotation directions of the first propeller and the second propeller are also required to be reversed, so that the propulsion system 300 can be switched to the second state, and the unmanned aerial vehicle is switched to the cruising state.

In some embodiments, referring to fig. 1 and 3, the unmanned aerial vehicle further has a landing gear 500, wherein the first connecting piece 310 is disposed under the wing 200 in the vertical direction, the landing gear 500 is connected to the first connecting piece 310, it can be understood that the landing gear 500 can play a supporting role on the unmanned aerial vehicle before the take-off of the unmanned aerial vehicle, the unmanned aerial vehicle is placed on the ground, the landing gear 500 supports the unmanned aerial vehicle, each power system can be started to lift the unmanned aerial vehicle, meanwhile, in the landing process of the unmanned aerial vehicle, the landing gear 500 is required to support the unmanned aerial vehicle, the unmanned aerial vehicle can be stably landed on the ground, and the landing gear 500 is connected to the first connecting piece 310, so that structural space can be saved, compared with the design of directly connecting the landing gear 500 to the fuselage 100, pneumatic assistance in the flight process of the unmanned aerial vehicle can be further reduced, and the whole weight of the unmanned aerial vehicle can also be reduced.

In some embodiments, the lifting system 400 includes a second connector 410 and a plurality of propellers, the plurality of propellers are divided into two groups, the two groups of propellers are respectively disposed at two ends of the second connector 410 in the axial direction, referring to fig. 1 and 2, the second connector 410 is connected to the wing 200, and the axis of the second connector 410 is parallel to the central axis of the fuselage 100, in the illustrated embodiment, the number of propellers is two, and the two propellers are respectively disposed at two ends of the second connector 410 in the axial direction, it can be understood that the second connector 410 and the plurality of propellers are disposed, so that in the lifting process of the unmanned aerial vehicle, at least four propellers can be provided to provide thrust in the vertical direction by autorotation, and the positions of the propellers are symmetrically arranged relative to the fuselage 100, so that the lifting of the unmanned aerial vehicle can be ensured to be more stable, and no deflection and shaking can occur.

In some embodiments, the first connector 310 is disposed below the wing 200 in the vertical direction, and the propeller is disposed on a side, away from the wing 200, of the second connector 410, that is, the propeller is disposed below the second connector 410, where the second connector 410 is disposed below the wing 200, and the propeller is disposed below the second connector 410, so that not only can the propeller be prevented from colliding with the wing 200, but also the air flow generated by the propeller is prevented from being interfered by the wing 200, so that the unmanned aerial vehicle can shake, and the thrust generated by the propeller can be used for lifting the unmanned aerial vehicle to the greatest extent, so that the waste of power can be reduced under the condition that the weight of the unmanned aerial vehicle is fixed.

It should be noted that, in some embodiments, when the second connector 410 is disposed below the wing 200, the propeller can be disposed above the second connector 410, and in other embodiments, when the second connector 410 is disposed above the wing 200, the propeller can also be disposed below the second connector 410, so that the above embodiments can achieve vertical lifting of the unmanned aerial vehicle.

In some embodiments, the unmanned aerial vehicle further has two sets of ailerons 210 and flaps 220, referring to fig. 1 and 2, the ailerons 210 and the flaps 220 are respectively disposed on the wings 200 on two sides, the two sets of flaps 220 are also respectively disposed on the wings 200 on two sides, that is, the ailerons 210 and the flaps 220 are respectively disposed on the wings 200 on two sides of the fuselage 100, and the ailerons 210 and the flaps 220 on two sides are respectively arranged symmetrically along the central axis of the fuselage 100, each aileron 210 and flap 220 can swing in the vertical direction relative to the wing 200, and each flap 220 and flap 210 can be independently controlled, it is to be noted that the ailerons 210 and flaps 220 can control the flight attitude of the unmanned aerial vehicle in the cruising state, and the control of the flight attitude is more accurate, and when any aileron 210 or flap 220 fails, the rest ailerons 210 and flaps 220 can also adjust the flight attitude of the unmanned aerial vehicle, so as to ensure that the unmanned aerial vehicle cannot fall and can lift and further safe landing performance of the unmanned aerial vehicle.

In some embodiments, the wing 200 of the unmanned aerial vehicle is further provided with a winglet at one end far away from the fuselage 100, the winglet can reduce the induced boosting in the flight process so as to ensure the normal flight of the unmanned aerial vehicle, in other embodiments, the tail of the fuselage 100 of the unmanned aerial vehicle is further provided with a tail wing, the tail wing can provide moment in pitching and yawing directions for the unmanned aerial vehicle so as to ensure the normal cruising of the unmanned aerial vehicle, meanwhile, the tail wings can be arranged into two tails, the two tail wings are arranged into a V shape, and the influence of the airflow below the wing 200 and the fuselage 100 on the tail wings can be further reduced so as to reduce the resistance of the unmanned aerial vehicle during flight.

In some embodiments, the lift system 400 is disposed on a side of the wing 200 that is relatively far from the fuselage 100, the propulsion system 300 is disposed on a side of the wing 200 that is relatively close to the fuselage 100, and the lift system 400 and the propulsion system 300 are spaced apart by a distance that is no less than the rotational diameter of the propeller to prevent the two sets of power systems from interfering with each other, in other embodiments, the lift system 400 is disposed on a side of the wing 200 that is relatively close to the fuselage 100, and the propulsion system 300 is disposed on a side of the wing 200 that is relatively far from the fuselage 100.

The embodiments of the present invention have been described in detail with reference to the accompanying drawings, but the present invention is not limited to the above embodiments, and various changes can be made within the knowledge of one of ordinary skill in the art without departing from the spirit of the present invention. Furthermore, embodiments of the invention and features of the embodiments may be combined with each other without conflict.

Claims (10)

1. Vertical lift fixed wing unmanned aerial vehicle, its characterized in that includes:

a body;

the wings are connected to two sides of the fuselage;

the lifting systems are arranged on the wings on two sides of the machine body, and can generate thrust in the vertical direction;

the propulsion system is arranged on the wings on two sides of the fuselage and can change the thrust direction of the propulsion system so that the propulsion system has a first state when providing lift force in the vertical direction and a second state when providing thrust force in the horizontal direction;

wherein the vertical lift fixed wing unmanned aerial vehicle has a lift state when the propulsion system is in the first state and a cruise state when the propulsion system is in the second state, and at least one of the propulsion system and the lift system provides lift in a vertical direction when the vertical lift fixed wing unmanned aerial vehicle is in the lift state.

2. The vertical lift fixed wing unmanned aerial vehicle of claim 1, wherein the propulsion system comprises at least one propeller coupled to the wing and capable of vertical rotation relative to the wing to switch the propulsion system between the first state and the second state.

3. The vertical lift fixed wing unmanned aerial vehicle of claim 1, wherein the propulsion system comprises a first connector and a plurality of propellers, the first connector is parallel to a central axis of the fuselage and is arranged on the wing, each propeller is divided into two groups, and the two groups of propellers are respectively arranged at two ends of the first connector in the axial direction.

4. A vertical lift fixed wing unmanned aerial vehicle according to claim 3, wherein a propeller on the front side of the fuselage is defined as a first propeller, a propeller on the rear side of the fuselage is defined as a second propeller, the first propeller has a first rotational action to switch the first propeller between the first state and the second state, the second propeller has a second rotational action to switch the second propeller between the first state and the second state, and the rotational directions of the first rotational action and the second rotational action are opposite.

5. A vertical lift fixed wing unmanned aerial vehicle according to claim 3, wherein the propeller on the front side of the fuselage is defined as a first propeller and the propeller on the rear side of the fuselage is defined as a second propeller, both the first and second propellers being rotatable in a vertical direction relative to the first connector, and the first propeller being located vertically above the first connector and/or the second propeller being located vertically below the first connector when the propulsion system is in the first state.

6. The vertical lift fixed wing unmanned aerial vehicle of claim 3, further comprising a landing gear, wherein the first connector is disposed vertically below the wing, and wherein the landing gear is connected to the first connector.

7. The vertical lift fixed wing unmanned aerial vehicle of claim 1, wherein the lift system comprises a second connecting piece and a plurality of propellers, the second connecting piece is parallel to the central axis of the fuselage and is arranged on the wing, each propeller is divided into two groups, and the two groups of propellers are respectively arranged at two ends of the second connecting piece in the axial direction.

8. The vertical lift fixed wing unmanned aerial vehicle of claim 7, wherein the propeller is disposed on a side of the second connector remote from the wing.

9. The vertical lift fixed wing unmanned aerial vehicle of claim 1, further comprising an aileron and a flap, wherein the aileron and the flap each have two groups, the two groups of ailerons are symmetrically disposed on the wings on both sides of the fuselage along a central axis of the fuselage, the two groups of flaps are symmetrically disposed on the wings on both sides of the fuselage along the central axis of the fuselage, and each aileron and each flap are independently capable of swinging in a vertical direction relative to the wings.

10. The vertical lift fixed wing unmanned aerial vehicle of claim 1, wherein the lift system is disposed on a side of the wing that is relatively far from the fuselage, the propulsion system is disposed on a side of the wing that is relatively close to the fuselage, or the lift system is disposed on a side of the wing that is relatively close to the fuselage, and the propulsion system is disposed on a side of the wing that is relatively far from the fuselage.