CN117902080A - Fixed wing aircraft capable of taking off and landing vertically and control method thereof - Google Patents

Abstract

The application belongs to an aircraft structure and a control method thereof, and provides a fixed wing aircraft capable of taking off and landing vertically and a control method thereof, which aim at solving the technical problems that the existing high-speed vertical take-off and landing aircraft cannot achieve both high-speed flat flight and small overall dimension and control is complex. The power devices are positioned on the front sides of the wings, lifting pieces are arranged at the rear ends of the wings, and the control surfaces are correspondingly arranged on the wings respectively. Through the cooperation of all the components, the aircraft provided by the application has the capabilities of vertical take-off and landing and high-speed plane flight and is compact in volume.

Description

Fixed wing aircraft capable of taking off and landing vertically and control method thereof

Technical Field

The application belongs to an aircraft structure and a control method thereof, and particularly relates to a fixed wing aircraft capable of taking off and landing vertically and a control method thereof.

Background

The high-speed vertical take-off and landing aircraft combines the advantages of the rotor wing and the fixed wing aircraft, and has the characteristics of vertical take-off and landing, high-speed flight, hovering stability, a hybrid power system and the like.

In order to meet the requirement of vertical take-off and landing in a narrow space, the appearance of the high-speed vertical take-off and landing aircraft needs to be designed to be extremely compact, and in order to meet the requirement of compactness, no wing is usually adopted, or a wing with a small span size is adopted. The aerodynamic lift-drag ratio of the aircraft designed in the way is low when in flat flight, and long-endurance and high-speed flat flight are difficult to realize. In order to reduce the energy consumption of the aircraft during flat flight and improve the flat flight speed, a fixed wing is generally added to improve the lift-drag ratio, and the overall dimension of the aircraft is greatly increased, so that the aircraft cannot adapt to vertical take-off and landing tasks such as urban floors, ship decks, mountain areas and air lands. Therefore, how to make the aircraft meet the requirements of vertical take-off and landing in a narrow space and high-speed flat flight simultaneously is an important problem for popularization and application of the high-speed vertical take-off and landing aircraft.

The power plant of the high-speed vertical takeoff and landing aircraft can take various forms. The ducted fan has higher pneumatic efficiency than the rotor wings with the same diameter, and is good in safety and low in noise, and becomes an important power device of the electric aircraft. Taking a ducted fan as an example, a number of ducted fan aircrafts have been disclosed, but the above problems have not been solved well. For example, chinese patent No. CN108583868a proposes a ducted fan vertical take-off and landing aircraft that provides lift by using ground effect, and the shape of the fuselage and the ducted fan are integrated, but no wing is adopted, and only flies at the height close to the ground, and also does not have high-speed flat flight capability. The Chinese patent with publication number of CN219406885U proposes a double-wing layout tilting four-duct aircraft, which adopts a traditional fixed-wing aircraft configuration, 4 duct fans are arranged at the tail ends of two rows of wings, and vertical take-off and landing and high-speed flat flight are realized through the tilting duct fans, but the traditional aircraft body and wing layout has larger wingspan and cannot be used for vertical take-off and landing in a narrow space. The Chinese patent with publication number CN112849393A proposes a single duct miniaturized aircraft which has small size and flexible take-off and landing, but has low flying speed and small take-off weight, and cannot be used for large-load tasks. The Chinese patent application with the publication number of CN117228019A provides a variant aircraft based on ducted fan power, 4 ducted fans are arranged at the tail of the aircraft in a binding mode, a folding wing is designed on the aircraft body, the aircraft body can take off and land vertically, the lifting force during flat flight is increased by the wing, the appearance of the aircraft body is columnar, the loading space is limited, the folding wing compresses the space and the structure of the aircraft body, and the operation and the control are complex. The Chinese patent with publication number of CN218317306U proposes a vertical take-off and landing aircraft layout with a combination of a ducted fan and a propeller, wherein the propeller and the ducted fan are respectively arranged on a front wing and a rear wing, and the tilting ducted fan can provide vertical take-off and landing and flat flying thrust, but the front wing and the propeller thereof enable the wingspan to be larger, so that the problem of complex control during tilting transition of the ducted fan exists.

Disclosure of Invention

The application provides a fixed wing aircraft capable of taking off and landing vertically and a control method thereof, aiming at the technical problems that the existing high-speed vertical take-off and landing aircraft cannot achieve both high-speed flat flight and small overall dimension and is complicated to control.

In order to achieve the above purpose, the application is realized by adopting the following technical scheme:

In a first aspect, the application provides a fixed wing aircraft capable of taking off and landing vertically, which comprises a fuselage, a plurality of control surfaces, a plurality of power devices and a plurality of wings;

Defining one side of the fuselage, which is close to the forward direction of flight, as the front;

The power devices and the wings are arranged on the aircraft body, and the power devices are positioned on the front side of the wings; the rear end of each wing is provided with a lifting piece;

the control surfaces are correspondingly arranged on the wings respectively.

Further, the power devices and the wings are uniformly distributed along the circumferential direction of the fuselage.

Further, the power device is a ducted fan;

the front edges of the power devices are positioned on the same plane, and the power devices are positioned at the rear side of the top point of the front end of the machine body;

The distance s between the front edge of the power device and the top point of the front end of the machine body is as follows:

s≥1.2D1

wherein D1 is the diameter of the ducted fan.

Further, the wing adopts a sweepback fixed wing; the span length L of the wing meets the following conditions:

1.5D1≤L≤0.5D2

Wherein D2 is the maximum envelope diameter of the aircraft.

Further, the following are satisfied between D1 and D2:

D2≥2.5D1。

Further, the power device and the wing are respectively provided with four wheels;

The power device is positioned at the front end of the fuselage, and the wings are positioned at the rear end of the fuselage;

The positions of the four wings on the projection surface are respectively positioned between two adjacent power devices, and the included angle between the four wings and the power devices is 45 degrees;

The projection surface is the same plane where the front edge of the power device is located.

Further, the body adopts a streamline structure, and the front end of the body adopts a mandibular configuration.

Further, the lifting piece adopts a supporting foot type universal wheel;

The landing gear extends to the exterior of the wing.

Further, the wing comprises a bearing beam and a frame type skin structure coated outside the bearing beam;

the landing gear is mounted on the load beam.

In a second aspect, the present application provides a control method for the vertical take-off and landing fixed wing aircraft, including:

The attitude of the aircraft is adjusted through differential control of a plurality of power devices;

and/or, carrying out attitude adjustment on the aircraft by operating a plurality of control rudders.

Further, when the aircraft vertically takes off, lands, hovers or moves transversely at a low speed, the attitude of the aircraft is adjusted through differential control of a plurality of power devices;

When the aircraft flies at a high speed, the attitude of the aircraft is adjusted by operating a plurality of control rudders.

Compared with the prior art, the application has the following beneficial effects:

The application provides a fixed wing aircraft capable of taking off and landing vertically, a plurality of power devices and a plurality of wings are arranged on the aircraft body, the power devices are positioned at the front sides of the wings, the plurality of power devices can provide large thrust required by taking off and landing vertically, the attitude of the aircraft can be adjusted through the speed difference of each power device, and the plurality of wings can be adopted to increase aerodynamic lift required by flying horizontally. The control surfaces are correspondingly arranged on the wings respectively and can control the aircraft to pitch or yaw in cooperation with the power device. The rear end of each wing is provided with a landing gear, which can serve as a landing gear of the aircraft, and the wing and the landing gear are integrally designed to reduce the span and the structural weight. By integrating the components and the integral structure of the application, the vertical take-off and landing and high-speed flat flight capacity of the aircraft can be simultaneously achieved.

The application also provides a control method of the vertical take-off and landing fixed wing aircraft, which has all the advantages of the vertical take-off and landing fixed wing aircraft and can ensure the stable and efficient operation of the aircraft.

Drawings

For a clearer description of the technical solutions of the embodiments of the present application, the drawings that are needed in the embodiments will be briefly described below, it being understood that the following drawings only illustrate some embodiments of the present application and should not be considered as limiting the scope, and other related drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.

FIG. 1 is a schematic view of one embodiment of a vertical takeoff and landing fixed wing aircraft of the present application;

FIG. 2 is a front view of an aircraft in accordance with an embodiment of the present application when the aircraft is vertically taking off and landing;

FIG. 3 is a side view of an aircraft in accordance with an embodiment of the present application when the aircraft is vertically taking off and landing;

FIG. 4 is a top view of an aircraft in accordance with an embodiment of the present application when the aircraft is vertically taking off and landing;

FIG. 5 is a front view of an aircraft in a flat flight in accordance with an embodiment of the present application;

FIG. 6 is a side view of an aircraft in a flat flight in accordance with an embodiment of the present application;

FIG. 7 is a top view of an aircraft in a flat flight in accordance with an embodiment of the present application;

Fig. 8 is a schematic diagram of D1, D2, and L in an embodiment of the present application.

Wherein: 1-power device, 2-wing, 3-fuselage, 4-front wing, 5-landing gear, 6-control surface.

Detailed Description

For the purpose of making the objects, technical solutions and advantages of the embodiments of the present application more apparent, the technical solutions of the embodiments of the present application will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present application, and it is apparent that the described embodiments are some embodiments of the present application, but not all embodiments of the present application. The components of the embodiments of the present application 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 application, as presented in the figures, is not intended to limit the scope of the application, as claimed, but is merely representative of selected embodiments of the application. All other embodiments, which can be made by those skilled in the art based on the embodiments of the application without making any inventive effort, are intended to be within the scope of the application.

It should be noted that: like reference numerals and letters denote like items in the following figures, and thus once an item is defined in one figure, no further definition or explanation thereof is necessary in the following figures.

In the description of the embodiments of the present application, it should be noted that, if the terms "upper," "lower," "horizontal," "inner," and the like indicate an azimuth or a positional relationship based on the azimuth or the positional relationship shown in the drawings, or the azimuth or the positional relationship in which the inventive product is conventionally put in use, it is merely for convenience of describing the present application and simplifying the description, and does not indicate or imply that the apparatus or element to be referred to must have a specific azimuth, be configured and operated in a specific azimuth, and thus should not be construed as limiting the present application. Furthermore, the terms "first," "second," and the like, are used merely to distinguish between descriptions and should not be construed as indicating or implying relative importance.

Furthermore, the term "horizontal" if present does not mean that the component is required to be absolutely horizontal, but may be slightly inclined. As "horizontal" merely means that its direction is more horizontal than "vertical", and does not mean that the structure must be perfectly horizontal, but may be slightly inclined.

In the description of the embodiments of the present application, it should also be noted that, unless explicitly specified and limited otherwise, the terms "disposed," "mounted," "connected," and "connected" should be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the present application can be understood by those of ordinary skill in the art according to the specific circumstances.

The high-speed vertical take-off and landing aircraft is a novel aircraft combining the advantages of a rotor wing and a fixed wing. The aircraft can not only take off, land and hover vertically like a rotor unmanned aerial vehicle, but also fly at high-speed cruising like a fixed-wing unmanned aerial vehicle. With the increasing requirements of various application fields of high-speed vertical take-off and landing aircrafts, how to combine high-speed flat flight with small overall dimensions has become an extremely important application problem.

Based on the above situation, the application provides a fixed wing aircraft capable of taking off and landing vertically and a control method thereof. The application is described in detail below with reference to examples and figures. For convenience of the following description, the side of the fuselage 3 near the forward direction of flight is defined as the front.

As an embodiment of a fixed wing aircraft capable of taking off and landing vertically, the fixed wing aircraft can comprise a fuselage 3, a plurality of control surfaces 6, a plurality of power devices 1 and a plurality of wings 2.

The power devices 1 and the wings 2 are arranged on the fuselage 3, the power devices 1 are positioned on the front sides of the wings 2, and the rear ends of the wings 2 are provided with lifting pieces 5.

In practical application, the specific structure and type of the power device 1 and the landing gear 5 can be adjusted according to the application scene and the actual requirement of the aircraft. For example, the power unit 1 may employ an electric ducted fan, an electric ducted propeller, an open rotor, or the like. The landing gear 5 may be a wheel landing gear, a skid landing gear, a pontoon landing gear, a ski landing gear, or the like. The present application is not limited to a specific structural form.

In practical application, the arrangement mode of the power devices 1 and the wings 2 along the circumferential direction of the fuselage 3 can be adjusted according to the practical power setting requirements. For example, it may be circumferentially uniform, or in some special cases, it may be unevenly disposed.

The control surfaces 6 are respectively and correspondingly arranged on the wings 2.

In practical application, the control surfaces 6 are used for changing the attitude, the altitude, the speed and the direction of the aircraft in flight, and more complex and accurate flight control can be realized through each control surface 6.

According to the fixed wing aircraft capable of taking off and landing vertically, the plurality of power devices 1 can provide high thrust required by taking off and landing vertically, the attitude of the aircraft can be adjusted through the speed difference of each power device 1, and the aerodynamic lift required by flat flight can be increased by adopting the plurality of wings 2. The control surfaces 6 are correspondingly arranged on the wings 2 respectively and can control the aircraft to pitch or yaw in cooperation with the power device 1. The rear end of each wing 2 is provided with a landing gear 5 which can serve as a landing gear of the aircraft, so that the vertical take-off and landing and high-speed flat flight capacity of the aircraft can be considered, and the aircraft is compact in size.

As shown in fig. 1, a fixed wing aircraft capable of taking off and landing vertically according to another embodiment of the present application:

The power device 1 adopts an electric ducted fan, and the power device 1 is provided with four. The front edges of the four electric ducted fans are positioned on the same plane, and the electric ducted fans are positioned at the rear side of the top point of the front end of the machine body 3. The wing 2 adopts a sweepback fixed wing 2, and the wing 2 is also provided with four. The power plant 1 is positioned at the front end of the fuselage 3, and the wings 2 are positioned at the rear end of the fuselage 3. Control surfaces 6 are arranged at the trailing edges of the four wings 2, by means of which control surfaces 6 control aerodynamic moments can be generated when turning in order to control the pitch, yaw or roll of the aircraft.

In practical applications, an electric ducted fan is an electric propulsion device, and mainly utilizes a duct to improve the efficiency of the fan, so as to generate larger thrust, wherein the duct is a tubular structure wrapping or surrounding the fan blades. The use of an electric ducted fan as the power plant 1 has the advantage of high efficiency, high thrust and low noise. In other embodiments of the present application, the number of the power units 1 may be further adjusted according to the power requirements, and the present application is not particularly limited.

In particular, in some embodiments of the application, the specific installation position of the electric ducted fan is optimized so that the distance s between the front edge of the electric ducted fan and the vertex of the head of the fuselage 3 is such that:

s≥1.2D1

wherein D1 is the diameter of the electric bypass fan. Through simulation and verification, the design of the installation position enables the head of the machine body 3 to play a role in diversion, and further increases the air inflow of the electric ducted fan.

In practical application, the structure of the sweepback type fixed wing 2 is characterized in that the front edge and the rear edge are sweepback to form a certain sweepback angle, so that the aerodynamic performance of the aircraft at different speeds can be optimized, and the design is optimized for high-speed flight. Because the four wings 2 are uniformly distributed along the circumferential direction of the fuselage 3, an X-shaped layout form is formed at the middle and rear part of the fuselage 3. The wing profiles of the four wings 2 may be identical in practice.

In particular, in some embodiments of the application, the specific mounting locations of the wings 2 are optimized such that the span length L of each wing 2 satisfies:

1.5D1≤L≤0.5D2

Wherein D2 is the maximum envelope diameter of the aircraft.

Fig. 8 is a schematic diagram of D1, D2 and L, for explaining specific meanings of D1, D2 and L.

As a further structural optimization, the following can be satisfied between D1 and D2:

D2≥2.5D1

the maximum diameter D1 of the four electric ducted fans is the same, and the diameter of the ducted fans is coordinated with the size of the whole machine

In addition, the four electric ducted fans and the four wings 2 are arranged in a staggered 45-degree angle in the circumferential direction, so that the wake flow of the electric ducted fans is prevented from being directly hit on the wing surfaces of the wings 2, and the pneumatic interference of the wake flow of the electric ducted fans on the wings 2 is reduced. In other embodiments of the application, the circumferential relative position between the electric ducted fan or other type of power plant 1 and the wing 2 may also be adjusted according to the power requirements.

The landing gear 5 is made of the supporting foot type universal wheels, the four supporting foot type universal wheels are respectively arranged at the tips of the four wings 2, the supporting foot type universal wheels are longer than the machine body 3 so as to avoid the machine body 3 touching the ground during landing, and the supporting foot type universal wheels do not need to be folded or unfolded, so that the landing gear is convenient to manually move on a flat ground or a ship deck. In practical application, the length of the body 3 at the length of the stand bar type universal wheel can be determined according to practical requirements.

In addition, in order to improve the strength and durability of the wing 2, the wing 2 may employ a load beam on which a foot-type universal wheel is mounted and a frame-type skin structure. In practical application, the bearing beam is a main bearing member of the wing 2, bears the action of bending moment and shearing force of the wing 2, and can ensure that the wing 2 has enough strength and rigidity under various flight conditions. The frame skin structure is typically formed by a series of transverse and longitudinal members in combination with a skin, which is the outer surface of the wing 2, which is subjected to aerodynamic loads and transfers the loads to the internal load-carrying structure. This structural design allows for a weight reduction of the wing 2 and an improved carrying capacity and stability of the wing 2.

In the application, four electric ducted fans are arranged at the head of a fuselage 3, four wings 2 with an X-shaped structure are arranged at the rear part of the fuselage 3, the electric ducted fans are uniformly arranged around the fuselage 3, each electric ducted fan is connected with the fuselage 3 through a front wing 4, sufficient power is provided for the vertical take-off and landing or high-speed flat flight of an aircraft, and the four electric ducted fans do not need to tilt. Four wings 2 can increase the lift of the aircraft when flying flat, and four foot-type universal wheels can act as landing gear. To further enhance the performance of the aircraft, the fuselage 3 is of streamlined design and the head of the fuselage 3 is of a mandibular configuration to improve the aerodynamic characteristics of the aircraft.

Overall, evenly arrange four electric ducted fans circumference in the aircraft head, aircraft fuselage 3 adopts streamlined design, and the head adopts the mandibular configuration, can improve aircraft aerodynamic properties to play the water conservancy diversion effect to electric ducted fan, when increasing electric ducted fan air input, improve the rising resistance characteristic when flat flight, reduce flight energy consumption, improve flat flight speed. The design of the wing 2 in this embodiment can reduce the wingspan of the wing 2, ensure enough lifting surface under smaller overall outline size, and is beneficial to improving the flat flight lift, reducing the flight energy consumption and improving the flat flight speed. The landing gear and landing gear assembly has the advantages that the landing gear assembly is connected with the wing 2 through the landing gear assembly 5, the wing 2 structure can integrate the functions of the wing 2 and the landing gear, the folding and unfolding are not needed, the structural weight can be reduced, the universal wheel structure is convenient for the aircraft to move on a flat ground or a ship deck, and the application scene of the aircraft is expanded.

By combining the advantages, the vertical take-off and landing fixed wing aircraft disclosed by the application is compact in appearance, has the vertical take-off and landing, hovering and high-speed flat flight capabilities, is wide in application scene, can flexibly take off and land in urban roofs, ship decks, mountain areas and the like, and is suitable for carrying out the tasks of air passenger transport, rapid freight transport, emergency rescue and the like in urban areas, coastal areas, mountain forests and the like.

Based on the fixed wing aircraft capable of taking off and landing vertically, the application also provides a control method of the fixed wing aircraft capable of taking off and landing vertically, which can comprise the following steps:

The attitude of the aircraft is adjusted through differential control of a plurality of power devices 1; and/or the attitude of the aircraft is adjusted by manipulating a plurality of control surfaces 6.

In practical application, the differential speed of the power device 1 can be used for controlling the aircraft, and the rotational speed difference between different power devices 1 is used for generating force and moment, so that the attitude and the flight direction of the aircraft are changed. The aircraft can also be controlled by controlling the control surfaces 6. In practical application, the control method can be adjusted according to control requirements.

In other embodiments of the control method of the present application, taking four electric ducted fans and four wings 2 as examples, the control can also be performed according to the following method:

Fig. 2 to 4 are schematic views of the vertical take-off and landing states of the aircraft, wherein fig. 2 is a front view of the vertical take-off and landing states of the aircraft, fig. 3 is a side view of the vertical take-off and landing states of the aircraft, and fig. 4 is a top view of the vertical take-off and landing states of the aircraft. Fig. 5 to 7 are schematic views of the attitude of the aircraft in the flat flight, wherein fig. 5 is a front view of the aircraft in the flat flight, fig. 6 is a side view of the aircraft in the flat flight, and fig. 7 is a plan view of the aircraft in the flat flight. When the aircraft vertically takes off, the four ducted fans run to generate thrust exceeding the taking-off weight, and the aircraft takes off or hovers off the ground, and the gesture is adjusted through the differential control of the four ducted fans. When flying flatly, the control surface 6 is controlled to generate pneumatic control force to pitch or yaw, so that the aircraft achieves a flatly flying posture, and the aircraft flies flatly at a high speed under the action of the thrust of the electric ducted fan and the control force of the control surface 6. When the aircraft falls vertically, the control surface 6 is controlled to enable the aircraft to be in a vertical state, the electric ducted fan is adopted for differential control to adjust the gesture, and the aircraft falls stably under the thrust of the ducted fan.

If the number and arrangement of the electric ducted fans and the wings 2 are changed, the adaptation can also be made with reference to the principle of the control method described above. The aircraft provided by the application can flexibly take off and land in a narrow space and fly at a high speed.

The above is only a preferred embodiment of the present application, and is not intended to limit the present application, but various modifications and variations can be made to the present application by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application should be included in the protection scope of the present application.

Claims (11)

1. A fixed wing aircraft capable of taking off and landing vertically comprises a fuselage (3), a plurality of control surfaces (6), a plurality of power devices (1) and a plurality of wings (2); the method is characterized in that:

Defining one side of the fuselage (3) close to the flight advancing direction as the front;

The power devices (1) and the wings (2) are arranged on the airframe (3), and the power devices (1) are positioned on the front side of the wings (2); the rear end of each wing (2) is provided with a lifting piece (5);

The control surfaces (6) are respectively and correspondingly arranged on the wings (2).

2. The fixed wing aircraft capable of taking off and landing vertically as recited in claim 1, wherein: the power devices (1) and the wings (2) are uniformly distributed along the circumferential direction of the machine body (3).

3. The fixed wing aircraft of claim 1 or 2, wherein: the power device (1) is a ducted fan;

The front edges of the power devices (1) are positioned on the same plane, and the power devices (1) are positioned at the rear side of the vertex at the front end of the machine body (3);

The distance s between the front edge of the power device (1) and the front end vertex of the machine body (3) is as follows:

s≥1.2D1

wherein D1 is the diameter of the ducted fan.

4. A fixed wing aircraft capable of vertical takeoff and landing according to claim 3, characterized in that: the wing (2) adopts a sweepback fixed wing (2); the span length L of the wing (2) satisfies the following conditions:

1.5D1≤L≤0.5D2

Wherein D2 is the maximum envelope diameter of the aircraft.

5. The fixed wing aircraft of claim 4, wherein the D1 and D2 satisfy:

D2≥2.5D1。

6. The fixed wing aircraft capable of taking off and landing vertically as recited in claim 5, wherein: four power devices (1) and four wings (2) are arranged;

The power device (1) is positioned at the front end of the fuselage (3), and the wings (2) are positioned at the rear end of the fuselage (3);

the positions of the four wings (2) on the projection surface are respectively positioned between two adjacent power devices (1), and the included angle between the four wings and the power devices (1) is 45 degrees;

the projection surfaces are the same plane where the front edge of the power device (1) is located.

7. The fixed wing aircraft capable of taking off and landing vertically as recited in claim 6, wherein: the machine body (3) adopts a streamline structure, and the front end of the machine body (3) adopts a mandibular configuration.

8. The fixed wing aircraft capable of taking off and landing vertically as recited in claim 7, wherein: the lifting piece (5) adopts a supporting leg type universal wheel;

The landing gear (5) extends outside the wing (2).

9. The fixed wing aircraft capable of taking off and landing vertically as recited in claim 8, wherein: the wing (2) comprises a bearing beam and a frame type skin structure coated outside the bearing beam;

The lifting piece (5) is arranged on the bearing beam.

10. A method of controlling a vertical take-off and landing fixed wing aircraft according to any one of claims 1 to 9, comprising:

The attitude of the aircraft is adjusted through differential control of a plurality of power devices (1);

And/or, performing attitude adjustment on the aircraft by manipulating a plurality of control surfaces (6).

11. The control method according to claim 10, characterized in that:

when the aircraft vertically takes off and land, hovers or moves transversely at a low speed, the attitude of the aircraft is adjusted through differential control of a plurality of power devices (1);

When the aircraft flies at a high speed, the attitude of the aircraft is adjusted by operating a plurality of control surfaces (6).