CN111976954A - A fixed-wing unmanned aerial vehicle that can realize vertical take-off and landing and its realization method - Google Patents

Abstract

The invention relates to a fixed-wing unmanned aerial vehicle that can realize vertical take-off and landing and a realization method. The fixed-wing unmanned aerial vehicle that can realize vertical take-off and landing at least comprises: a control part, a fuselage, a wing, a wing and a fuselage The top of the fuselage is fixedly connected to the nose fairing, and the four sides of the fuselage at the lower end of the nose fairing are respectively hinged with a first control rudder surface, a second control rudder surface, and a third control rudder surface. and the fourth control rudder surface; the tail of the fuselage is fixedly connected with a landing gear mechanism, and a coaxial double propeller power source is arranged under the fuselage. The method of the present invention controls the course of the aircraft by separately operating different deployment angles of the control surfaces. The invention has the characteristics of good stability, strong aircraft maneuverability, low cost and good manufacturability, and can realize vertical take-off and landing.

Description

A fixed-wing unmanned aerial vehicle that can realize vertical take-off and landing and its realization method

technical field

The invention relates to an unmanned aerial vehicle, in particular to a fixed-wing unmanned aerial vehicle that can realize vertical take-off and landing and a realization method thereof. It belongs to the field of drone technology.

Background technique

At present, UAV technology has been widely used in agriculture, aerial survey, military and other fields. The technology of vertical take-off and landing of fixed-wing aircraft can reduce the dependence of fixed-wing aircraft on the size of the airport, greatly enhance the application scenarios of fixed-wing drones, and become a breakthrough technology for the development of fixed-wing drones, with extremely broad development. prospect.

Patent application number: 201810808993.3 proposes a technology for vertical take-off and landing of a fixed-wing UAV. As shown in Figure 1, an integral control blade 12 is used to generate thrust and the blade deflection is used to generate the torque required for aircraft control. It is not difficult to see that the power of a single propeller will have a reverse torque effect on the aircraft when it is working (under the effect of the reverse torque, the aircraft will generate a rolling moment, causing the fuselage to rotate in the opposite direction of the propeller speed), and it is necessary to balance the reverse torque through technical means. The torque increases the overall cost of the aircraft and consumes excess power; the integral control blade not only needs to provide power, but also generates the torque required for control, which requires higher technical means and increases the cost.

SUMMARY OF THE INVENTION

The purpose of the present invention is to provide a fixed-wing unmanned aerial vehicle with good aircraft stability, strong aircraft maneuverability, low cost and good manufacturability, which can realize vertical take-off and landing, and a realization method thereof.

Technical scheme of the present invention: a fixed-wing unmanned aerial vehicle that can realize vertical take-off and landing, at least comprising: a control part, a fuselage, and a wing, the wings and the fuselage are fixedly connected together, and the top of the fuselage is fixedly connected The nose fairing is hinged with the first control rudder surface, the second control rudder surface, the third control rudder surface and the fourth control rudder surface on the four sides of the fuselage at the lower end of the nose fairing; the tail of the fuselage is fixedly connected There is a landing gear mechanism, and a coaxial double propeller power source is arranged under the fuselage.

The first control rudder surface, the second control rudder surface, the third control rudder surface, and the fourth control rudder surface are evenly distributed along the four sides of the fuselage. , The third control surface and the fourth control surface are equal in size and have the same height in the axial direction of the fuselage.

The tail of the fuselage is also provided with an aerodynamic stabilization surface, the aerodynamic stabilization surface includes eight aerodynamic stabilization surfaces, and two aerodynamic stabilization surfaces are distributed on each side of the tail of the fuselage.

A method for realizing a fixed-wing unmanned aerial vehicle capable of vertical take-off and landing, at least comprising: four sides of the fuselage are respectively hinged with a first control rudder surface, a second control rudder surface, a third control rudder surface, and a fourth control rudder The aircraft heading is controlled by operating different control surfaces to expand the angles.

The control of the plane's course includes the control and take-off stage, the plane is standing on the ground, the nose is vertically upward, and under the thrust of the coaxial double propeller power source, the plane moves up in the vertical direction, and after reaching a certain safe height, the second The control surface is opened, and under the action of aerodynamic force, a bowing moment is generated, which makes the aircraft bow its head and switch to a level flight state.

In the take-off stage of the described control aircraft heading, if the aircraft is disturbed to generate pitch and yaw moments, the pitch of the aircraft is adjusted by opening the first control rudder surface and the second control rudder surface, and if the aircraft bows its head, the first control rudder surface is opened. , to make the aircraft return to the positive heading. If the aircraft looks up, turn on the second control surface to make the aircraft return to the positive heading; the third and fourth control surfaces are used to adjust the yaw of the aircraft. If the aircraft yaw to the left, Then you need to open the fourth control surface to adjust the heading. If the aircraft yaw to the right, you need to open the third control surface to adjust the heading.

The control of the aircraft heading further includes a control and landing stage. When the aircraft needs to land, the first control rudder surface is opened, and under the action of aerodynamic force, a head-up moment is generated, and the aircraft attitude is adjusted to a vertical state, and the nose of the aircraft is vertically upward. Adjust the thrust of the coaxial double propeller power source, and under the combined action of thrust and gravity, the aircraft moves downward until the aircraft lands smoothly.

In the landing stage of the described control aircraft heading, if the aircraft is disturbed to generate pitch and yaw moment, the pitch of the aircraft is adjusted by opening the first control rudder surface and the second control rudder surface, and the third control rudder surface and the fourth control rudder are opened. To adjust the yaw of the aircraft, control the rudder surface to open in the opposite direction to the take-off phase.

The advantages of the present invention are: by using the coaxial double propeller power to balance the reaction torque effect of the single propeller power, the technical difficulty is reduced, and the overall cost of the aircraft is also reduced. By adding four rudder surfaces at the nose to generate the moment required for the maneuvering operation of the aircraft, and the rudder surfaces are further away from the focus of the aircraft, the aerodynamic efficiency is higher than the technology described in Patent Application No. 201810808993.3, and the aircraft maneuverability is stronger. And eight aerodynamic stabilization surfaces are added to the tail part to increase the stability of the aircraft.

Description of drawings

Below in conjunction with embodiment and accompanying drawing, the present invention is further described:

1 is a schematic diagram of the prior art structure;

2 is a schematic structural diagram of an embodiment of the present invention;

Fig. 3 is the control surface adjustment schematic diagram that the take-off stage of the present invention is turned into the level flight stage;

Fig. 4 is the control surface adjustment schematic diagram of the present invention when the level flight stage is turned into the landing stage;

FIG. 5 is a schematic diagram of the adjustment of the control rudder surface after being disturbed in the landing stage of the present invention.

In the figure, 1, the first control surface; 2, the second control surface; 3, the third control surface; 4, the fourth control surface; 5, the nose fairing; 6, the fuselage; 7, the machine Wing; 8. Landing gear mechanism; 9. Coaxial twin propeller power source; 10. Ailerons; 11. Aerodynamic stabilization surface; A, represents the direction of speed.

Detailed ways

Example 1

As shown in FIG. 2, a fixed-wing UAV that can realize vertical take-off and landing at least includes: a control part, a fuselage 6, and a wing 7, and the wing 7 and the fuselage 6 are fixedly connected together. The top end of the body 6 is fixedly connected to the nose fairing 5, and the four sides of the fuselage 6 at the lower end of the nose fairing 5 are respectively hinged with the first control rudder surface 1, the second control rudder surface 2, the third control rudder surface 3 and the third control rudder surface. Four control rudder surfaces 4; a landing gear mechanism 8 is fixedly connected to the tail of the fuselage, and a coaxial double propeller power source 9 is arranged below the fuselage.

By using the coaxial double propeller power to balance the reaction torque effect of the single propeller power, the invention reduces the technical difficulty and also reduces the overall cost of the aircraft. The torque required for the maneuvering operation of the aircraft is generated by adding four rudder surfaces at the nose, and the rudder surfaces are further away from the focus of the aircraft, resulting in higher aerodynamic efficiency and stronger aircraft maneuverability.

Example 2

On the basis of Embodiment 1, further, the first control surface 1 , the second control surface 2 , the third control surface 3 , and the fourth control surface 4 are evenly distributed along the four sides of the fuselage 6 , the first control surface 1 , the second control surface 2 , the third control surface 3 and the fourth control surface 4 are equal in size and have the same height in the axial direction of the fuselage.

Further, the tail of the fuselage 6 is also provided with an aerodynamic stabilization surface 11, the aerodynamic stabilization surface 11 includes eight aerodynamic stabilization surfaces, and two aerodynamic stabilization surfaces are distributed on each side of the fuselage tail. Eight aerodynamic stabilization surfaces are added to the tail part to increase the stability of the aircraft.

Further, the coaxial double propeller power source 9 is located at the bottom of the fuselage 6 to provide stable power required for flight.

Further, the wing is connected with the fuselage through a tenon-and-mortise structure. Ailerons 10 are provided on the wings.

Example 3

On the basis of Embodiment 1 or 2, the present invention provides a method for realizing a fixed-wing unmanned aerial vehicle that can realize vertical take-off and landing, at least including: four sides of the fuselage 6 are respectively hinged with the first control rudder surface 1, The second control surface 2 , the third control surface 3 , and the fourth control surface 4 control the direction of the aircraft by operating different control surface deployment angles respectively.

Further, as shown in Figure 3, the direction of the arrow in the figure is the direction of the speed, and the described control of the aircraft heading, including the control take-off stage, the aircraft stands upright on the ground, the nose is vertically upward, and under the thrust of the coaxial double propeller power source 9 , the aircraft moves upwards in the vertical direction. After reaching a certain safe height, the second control rudder surface 2 opens, and under the action of aerodynamic force, a bowing moment is generated, which makes the aircraft bow its head and switch to a level flight state.

In the state of level flight, the operating principle of the aircraft is the same as that of the general fixed-wing aircraft, and it can be used as a general fixed-wing aircraft to fly. The required lift can reduce energy consumption and increase cruising range.

Further, the described control aircraft heading is in the take-off stage, if the aircraft is disturbed to generate pitch and yaw moment, the aircraft pitch is adjusted by opening the first control rudder surface 1 and the second control rudder surface 2, if the aircraft bows its head, then open the first control rudder surface 1 and the second control rudder surface 2. 1. Control the rudder surface 1 to make the aircraft return to the positive heading. If the aircraft looks up, open the second control rudder surface 2 to make the aircraft return to the positive heading; the third control rudder surface 3 and the fourth control rudder surface 4 are used to adjust the yaw of the aircraft , if the aircraft yaw to the left, you need to open the fourth control surface 4 to adjust the heading, if the aircraft yaw to the right, you need to open the third control surface 3 to adjust the heading.

Further, as shown in FIG. 4 , the direction of the arrow in the figure is the speed direction, and the described control of the aircraft heading further includes the control and landing stage. When the aircraft needs to land, the first control surface 1 is opened, and under the action of aerodynamic force, the Head up moment, adjust the attitude of the aircraft to a vertical state, and the nose of the aircraft is vertically upward. At this time, adjust the thrust of the coaxial double propeller power source 9. Under the combined action of thrust and gravity, the aircraft moves downward until the aircraft lands smoothly.

Further, as shown in Figure 5, the direction of the arrow in the figure is the speed direction, the described control aircraft heading is in the landing stage, if the aircraft is disturbed to generate pitch and yaw moments, by opening the first control rudder surface 1 and the second control rudder Face 2 to adjust the pitch of the aircraft, open the third control rudder surface 3 and the fourth control rudder surface 4 to adjust the yaw of the aircraft, and the opening direction of the control rudder surface is opposite to the take-off stage.

In a word, because the present invention adopts the coaxial double propeller power source, it can effectively solve the anti-torque effect of the single propeller power source on the aircraft (under the action of the anti-torque, the aircraft will generate a rolling moment, making the fuselage move in the opposite direction of the propeller rotation speed). Rotation), thereby achieving the stability of the aircraft during the take-off and landing phases.

Through different operations on the four rudder surfaces of the nose, the arm of the aerodynamic surface is increased, the aerodynamic efficiency is improved, and the maneuverability of the aircraft is enhanced. And in the take-off and landing stages, the course of the aircraft can be adjusted effectively, so that the maneuverability and safety performance of the aircraft are increased.

Since there is no integral control blade in the tail part, the structure is simplified, and eight aerodynamic stabilization surfaces can be added, which can automatically restore the original flight state when encountering disturbances, which enhances the pitch stability and yaw stability of the aircraft during flight. .

In the present invention, the control component is a dedicated controller for unmanned aerial vehicles, which belongs to the well-known technology in the art, and will not be described one by one here.

Components and structures not described in detail in the embodiments of the present invention belong to well-known components and common structures or common means in the industry.

Claims (8)

1. A fixed-wing UAV capable of vertical take-off and landing, comprising at least: a control component, a fuselage (6), and a wing (7), wherein the wing (7) and the fuselage (6) are fixedly connected together, It is characterized in that: the top of the fuselage (6) is fixedly connected to the nose fairing (5), and the four sides of the fuselage (6) at the lower end of the nose fairing (5) are respectively hinged with first control rudder surfaces ( 1), the second control rudder surface (2), the third control rudder surface (3) and the fourth control rudder surface (4); the tail of the fuselage (6) is fixedly connected with a landing gear mechanism (8), and the fuselage ( 6) A coaxial double propeller power source (9) is arranged below. 2. A fixed-wing UAV capable of vertical take-off and landing according to claim 1, characterized in that: the first control rudder surface (1), the second control rudder surface (2), the third control rudder surface (2), the third The control rudder surface (3) and the fourth control rudder surface (4) are evenly distributed along the four sides of the fuselage (6). The third control rudder surface (3) and the fourth control rudder surface (4) are equal in size and at the same height in the axial direction of the fuselage. 3. A fixed-wing unmanned aerial vehicle capable of vertical take-off and landing according to claim 1, characterized in that: an aerodynamic stabilization surface (11) is also provided on the tail of the fuselage (6), and the The aerodynamic stabilization surface (11) includes eight aerodynamic stabilization surfaces, and two aerodynamic stabilization surfaces are distributed on each side of the tail of the fuselage. 4. A method for realizing a fixed-wing unmanned aerial vehicle capable of vertical take-off and landing, characterized by at least comprising: four sides of the fuselage (6) are respectively hinged with a first control rudder surface (1), a second control rudder The plane (2), the third control surface (3), and the fourth control surface (4) are used to control the direction of the aircraft by operating different control surfaces to expand their angles. 5. the realization method of a kind of fixed-wing unmanned aerial vehicle that can realize vertical take-off and landing according to claim 4, it is characterized in that: described control aircraft course, comprises control take-off stage, aircraft is upright on the ground, nose lead Vertically, under the thrust of the coaxial double propeller power source (9), the aircraft moves upwards in the vertical direction. After reaching a certain safe height, the second control surface (2) opens, and under the action of aerodynamic force, a bowing moment is generated. , make the aircraft bow its head and switch to level flight. 6. the realization method of a kind of fixed-wing unmanned aerial vehicle that can realize vertical take-off and landing according to claim 5, is characterized in that: described control aircraft heading is in the take-off stage, if aircraft is disturbed to produce pitch, yaw moment , adjust the pitch of the aircraft by opening the first control surface (1) and the second control surface (2). If the aircraft bows its head, open the first control surface (1) to make the aircraft return to the positive heading. Then open the second control surface (2) to make the aircraft return to the positive heading; the third control surface (3) and the fourth control surface (4) are used to adjust the yaw of the aircraft. Turn on the fourth control surface (4) to adjust the heading. If the aircraft yaw to the right, you need to turn on the third control surface (3) to adjust the heading. 7. The realization method of a fixed-wing unmanned aerial vehicle that can realize vertical take-off and landing according to claim 4, characterized in that: the described control aircraft heading further comprises the control and landing stage, when the aircraft is in a level flight state and When it is necessary to land, the first control surface (1) is opened, and under the action of aerodynamic force, a head-up moment is generated, the attitude of the aircraft is adjusted to a vertical state, and the nose is vertically upward. At this time, the coaxial double propeller power source (9) is adjusted. Under the combined action of thrust and gravity, the aircraft moves downward until the aircraft lands smoothly. 8. The method for realizing a fixed-wing unmanned aerial vehicle that can realize vertical take-off and landing according to claim 7, is characterized in that: the described control plane course is in the vertical downward landing stage, if the plane is disturbed to produce pitch , yaw moment, adjust the pitch of the aircraft by opening the first control surface (1) and the second control surface (2), open the third control surface (3) and the fourth control surface (4) to adjust the aircraft's yaw The direction of opening the control surface is opposite to that of adjusting the course during the take-off phase.

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