CN213620213U

CN213620213U - Can realize fixed wing unmanned aerial vehicle of VTOL

Info

Publication number: CN213620213U
Application number: CN202022012049.2U
Authority: CN
Inventors: 杨轲
Original assignee: Individual
Current assignee: Individual
Priority date: 2020-09-15
Filing date: 2020-09-15
Publication date: 2021-07-06
Anticipated expiration: 2030-09-15

Abstract

The utility model relates to a can realize fixed wing unmanned aerial vehicle of VTOL, it includes at least: the aircraft comprises a control component, an aircraft body and wings, wherein the wings are fixedly connected with the aircraft body, the top end of the aircraft body is fixedly connected with an aircraft nose fairing, and four side surfaces of the aircraft body at the lower end of the aircraft nose fairing are respectively hinged with a first control surface, a second control surface, a third control surface and a fourth control surface; the tail part of the machine body is fixedly connected with a lifting frame mechanism, and a coaxial double-propeller power source is arranged below the machine body. The utility model discloses a fixed wing unmanned aerial vehicle of VTOL can be realized to this kind, through operating different control surface expansion angles respectively, controls aircraft course. The utility model has the characteristics of the vertical take-off and landing can be realized that stability is good, aircraft mobility is strong, with low costs, manufacturability is good.

Description

Can realize fixed wing unmanned aerial vehicle of VTOL

Technical Field

The utility model relates to an unmanned aerial vehicle, very much fixed is a fixed wing unmanned aerial vehicle that can realize VTOL. Belong to unmanned aerial vehicle technical field.

Background

At present, the unmanned aerial vehicle technology is widely applied to the fields of agriculture, aerial survey, military and the like. The fixed-wing aircraft vertical take-off and landing technology can reduce the dependence of the fixed-wing aircraft on the size of an airport, greatly enhances the application scene of the fixed-wing unmanned aerial vehicle, becomes a fixed-wing unmanned aerial vehicle development breakthrough point technology, and has extremely wide development prospect.

Patent application No.: 201810808993.3 proposes a technique for vertical take-off and landing of fixed wing drones, as shown in fig. 1, which uses integrated control blades 12 to generate thrust and to generate the moment required for the airplane to maneuver through the deflection of the blades. It can be seen that the single-propeller power can generate a reaction torque effect on the airplane during operation (the airplane can generate a rolling torque under the reaction torque effect, so that the airplane body rotates in a direction opposite to the rotating speed of the propeller), the reaction torque needs to be balanced by a technical means, so that the whole airplane is increased, and redundant power is consumed; the integral control blade needs to provide power and generate torque required by operation, so that high technical means are required, and the cost is increased.

SUMMERY OF THE UTILITY MODEL

The utility model aims at providing a can realize fixed wing unmanned aerial vehicle of VTOL. It has good stability, strong maneuverability of the airplane, low cost and good manufacturability.

The technical scheme of the utility model: design a can realize fixed wing unmanned aerial vehicle of VTOL, it includes at least: the aircraft comprises a control component, an aircraft body and wings, wherein the wings are fixedly connected with the aircraft body, the top end of the aircraft body is fixedly connected with an aircraft nose fairing, and four side surfaces of the aircraft body at the lower end of the aircraft nose fairing are respectively hinged with a first control surface, a second control surface, a third control surface and a fourth control surface; the tail part of the machine body is fixedly connected with a lifting frame mechanism, and a coaxial double-propeller power source is arranged below the machine body.

The first control surface, the second control surface, the third control surface and the fourth control surface are uniformly distributed along four side surfaces of the fuselage, the first control surface, the second control surface, the third control surface and the fourth control surface are equal in size, and the heights of the axial positions of the fuselage are the same.

The tail part of the machine body is also provided with pneumatic stabilizing surfaces, the pneumatic stabilizing surfaces comprise eight pneumatic stabilizing surfaces, and two pneumatic stabilizing surfaces are distributed on each side surface of the tail part of the machine body.

The utility model has the advantages that: the fixed wing unmanned aerial vehicle capable of achieving vertical take-off and landing balances the reaction torque effect of single-propeller power through coaxial double-propeller power, so that the technical difficulty is reduced, and the overall cost of the aircraft is reduced. Four control surfaces are designed to be added at the head part to generate the torque required by the maneuvering operation of the airplane, and the control surfaces are farther away from the focus of the airplane, so that the aerodynamic efficiency is higher than that of the technology disclosed in the patent application No. 201810808993.3, and the maneuverability of the airplane is stronger. And eight aerodynamic stabilizing surfaces are added at the tail part of the airplane, so that the stability of the airplane is improved.

Drawings

The present invention will be further explained with reference to the following embodiments and accompanying drawings:

FIG. 1 is a schematic view of a prior art structure;

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

fig. 3 is a schematic diagram illustrating adjustment of the control surface during the takeoff phase of the embodiment of the present invention converted into the level flight phase;

fig. 4 is a schematic diagram of the adjustment of the control surface during the transition from the level flight phase to the landing phase according to the embodiment of the present invention;

fig. 5 is a schematic diagram of the adjustment of the control surface after disturbance in the landing stage according to the embodiment of the present invention.

In the figure, 1, a first control surface; 2. a second control surface; 3. a third control surface; 4. a fourth control surface; 5. a nose fairing; 6. a body; 7. an airfoil; 8. a landing gear mechanism; 9. a coaxial double-paddle power source; 10. an aileron; 11. a pneumatic stabilizing surface; A. representing the direction of the speed.

Detailed Description

Example 1

As shown in fig. 2, the fixed-wing drone capable of taking off and landing vertically at least includes: the aircraft comprises a control component, an aircraft body 6 and wings 7, wherein the wings 7 are fixedly connected with the aircraft body 6, the top end of the aircraft body 6 is fixedly connected with an aircraft nose fairing 5, and four side surfaces of the aircraft body 6 at the lower end of the aircraft nose fairing 5 are respectively hinged with a first control surface 1, a second control surface 2, a third control surface 3 and a fourth control surface 4; the tail part of the machine body is fixedly connected with an undercarriage mechanism 8, and a coaxial double-propeller power source 9 is arranged below the machine body.

The utility model discloses an use coaxial double-oar power to balance the reaction torque effect of single oar power, reduced the technical degree of difficulty, also reduced aircraft overall cost simultaneously. Four control surfaces are added at the head part to generate the moment required by the maneuvering operation of the airplane, and the control surfaces are farther away from the focus of the airplane, so that the aerodynamic efficiency is higher, and the maneuverability of the airplane is stronger.

Example 2

On the basis of the embodiment 1, the first control surface 1, the second control surface 2, the third control surface 3 and the fourth control surface 4 are further uniformly distributed along four side surfaces 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 the heights of the axial positions of the fuselage are the same.

Further, the tail of the machine body 6 is further provided with a pneumatic stabilizing surface 11, the pneumatic stabilizing surface 11 comprises eight pneumatic stabilizing surfaces, and two pneumatic stabilizing surfaces are distributed on each side surface of the tail of the machine body. Eight pneumatic stabilizing surfaces are added on the tail part, so that the stability of the airplane is improved.

Further, the coaxial double-oar power source 9 is positioned at the lowest part of the aircraft body 6 and provides stable power required by flight.

Furthermore, the wings are connected with the fuselage through mortise and tenon structures. An aileron 10 is provided on the wing.

Example 3

On the basis of

embodiment

1 or 2, the embodiment of the utility model provides a this kind of can realize fixed wing unmanned aerial vehicle's of VTOL application method, it includes at least: the four side surfaces of the airplane body 6 are respectively hinged with a first control surface 1, a second control surface 2, a third control surface 3 and a fourth control surface 4, and the course of the airplane is controlled by respectively operating the unfolding angles of the different control surfaces.

Further, as shown in fig. 3, the arrow direction in the figure is the speed direction, the control of the aircraft heading includes the control of the takeoff phase, the aircraft is erected on the ground, the aircraft nose is vertically upward, the aircraft moves upward along the vertical direction under the thrust action of the coaxial double-oar power source 9, after a certain safety height is reached, the second control surface 2 is opened, and the head-lowering moment is generated under the aerodynamic force, so that the aircraft is lowered and converted into the flat flight state.

In a flat flight state, the airplane operation principle is consistent with that of a fixed wing airplane with a common layout, and the airplane can fly as a common fixed wing airplane, at the moment, the thrust of the coaxial double-propeller power source 9 can be reduced, the lift force required by the flight is provided by the wings 7, the energy consumption can be reduced, and the endurance mileage can be increased.

Further, in the takeoff stage of controlling the aircraft course, if the aircraft is disturbed to generate pitching and yawing moments, the pitching of the aircraft is adjusted by opening the first control surface 1 and the second control surface 2, if the aircraft is lowered, the first control surface 1 is opened to enable the aircraft to return to the normal navigation direction, and if the aircraft is raised, the second control surface 2 is opened to enable the aircraft to return to the normal navigation direction; the third control surface 3 and the fourth control surface 4 are used for adjusting the yaw of the airplane, if the airplane yaws leftwards, the fourth control surface 4 needs to be opened to adjust the course, and if the airplane yaws rightwards, the third control surface 3 needs to be opened to adjust the course.

Further, as shown in fig. 4, the arrow direction in the figure is the speed direction, the control of the aircraft course further includes the control landing stage, when the aircraft needs to land, the first control surface 1 is opened, under the action of aerodynamic force, a head raising moment is generated, the aircraft attitude is adjusted to be in a plumb state, the aircraft nose is vertically upward, at the moment, the thrust of the coaxial double-oar power source 9 is adjusted, and under the combined action of the thrust and the gravity, the aircraft moves downwards until the aircraft lands stably.

Further, as shown in fig. 5, the arrow direction in the figure is the speed direction, the heading of the controlled aircraft is in the landing stage, if the aircraft is disturbed to generate pitching and yawing moments, the pitching of the aircraft is adjusted by opening the first control surface 1 and the second control surface 2, the yawing of the aircraft is adjusted by opening the third control surface 3 and the fourth control surface 4, and the opening direction of the control surfaces is opposite to the take-off stage.

In a word, the utility model discloses owing to adopted coaxial double-oar power supply, can effectively solve single oar power supply and produce the reaction torque effect to the aircraft (can make the aircraft produce roll-over moment under the reaction torque effect, make the fuselage court with the opposite direction rotation of screw rotational speed), and then realized the aircraft take off with the landing stage stable.

The four control surfaces of the nose are operated differently, so that the moment arm of the aerodynamic surface is increased, the aerodynamic efficiency is improved, and the maneuverability of the airplane is enhanced. And the course of the airplane can be effectively adjusted in the taking-off and landing stages, so that the operability and the safety performance of the airplane are improved.

Because the tail part is not provided with integral control blades, the structure is simplified, eight pneumatic stabilizing surfaces can be added, the original flying state can be automatically recovered when disturbance occurs, and the pitching stability and the yawing stability of the airplane during flying are enhanced.

The utility model discloses well control unit is the dedicated controller of unmanned aerial vehicle, belongs to the well-known technique in this field, and it describes to differ here.

The components and structures of the embodiments of the present invention not described in detail are well known in the art and commonly used structures or means.

Claims

1. A vertical take-off and landing capable fixed wing drone at least comprises: control unit, fuselage (6), wing (7) link firmly together with fuselage (6), characterized by: the top end of the machine body (6) is fixedly connected with a machine head fairing (5), and four side surfaces of the machine body (6) at the lower end of the machine head fairing (5) are respectively hinged with a first control surface (1), a second control surface (2), a third control surface (3) and a fourth control surface (4); the tail part of the machine body (6) is fixedly connected with a lifting frame mechanism (8), and a coaxial double-propeller power source (9) is arranged below the machine body (6).

2. The fixed-wing drone capable of achieving vertical take-off and landing according to claim 1, wherein: the aircraft is characterized in that the first control surface (1), the second control surface (2), the third control surface (3) and the fourth control surface (4) are uniformly distributed along four sides of the aircraft body (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 the heights of the axial positions of the aircraft body are the same.

3. The fixed-wing drone capable of achieving vertical take-off and landing according to claim 1, wherein: the tail part of the machine body (6) is further provided with a pneumatic stabilizing surface (11), the pneumatic stabilizing surfaces (11) comprise eight pneumatic stabilizing surfaces, and two pneumatic stabilizing surfaces are distributed on each side surface of the tail part of the machine body.