CN112429194A

CN112429194A - Double-wing flight structure

Info

Publication number: CN112429194A
Application number: CN202011342082.XA
Authority: CN
Inventors: 王志成
Original assignee: Guangdong Guoshijian Technology Development Co Ltd
Current assignee: Guangdong Guoshijian Technology Development Co Ltd
Priority date: 2020-11-26
Filing date: 2020-11-26
Publication date: 2021-03-02

Abstract

The invention relates to the technical field of aircrafts, in particular to a double-wing flight structure; the device comprises a translational wing, a driving device and a carrier, wherein the carrier is provided with a support and a central shaft, the lower end of the support is fixedly connected with the carrier, the central shaft is rotatably connected with the upper end of the support, and the support is provided with an angle adjusting device for changing the inclination angle of the central shaft; the central shaft is provided with two translational wings which are spaced up and down, and the translational wings are connected with the central shaft in a matching way; the driving device is respectively connected with the two translational wings in a transmission way, so that the two translational wings can respectively reciprocate up and down along the central shaft; the invention has reasonable structure, the central shaft and the upper translational wing structure thereof can be integrally rotated on the bracket to adjust the output angle of the lift force, the driving device drives the two translational wings to reciprocate up and down through the crank connecting rod to realize synchronous opening and closing movement, the pressure difference of the translational wings when ascending promotes the translational wings to rotate in one direction, the translational wings when descending generate vertical upward acting force between the fanning wings and the air, and further the carrier obtains the lift force to realize the flying purpose.

Description

Double-wing flight structure

Technical Field

The invention relates to the technical field of aircrafts, in particular to a double-wing flight structure.

Background

The lift device of an aircraft is an aerodynamic-based mechanism, and can be divided into a fixed wing and a rotor wing according to the structure, and the fixed wing aircraft generally has a fuselage and symmetrically arranged fixed wings, and is powered by a propeller to obtain larger flight speed and maneuverability. The flying principle of the airplane is that relative speed exists between the fixed wing and air, and the air and all surfaces of the fixed wing interact to generate lift force so as to enable the airplane to obtain flying capability. Fixed wing aircraft have the disadvantages of being unable to hover in the air, requiring taxiing takeoff or landing on a runway and support for airport facility construction. A rotary-wing aircraft such as helicopter features that it can take off without runway and hover in sky, and its power system is composed of engine and rotary wings. The defects of the method are that the cruising speed is low, the load capacity is not high, the efficiency is low, but the dependence on ground facilities is little.

The autorotation gyroplane is an aircraft combining two modes of a fixed wing and a rotor wing, and the main structure of the autorotation gyroplane comprises the rotor wing, a wheel type undercarriage and a propeller, wherein the propeller drives the autorotation gyroplane to slide on a runway, air and rotor blades interact in the sliding process, the air can push the rotor blades to rotate, the rotor blades rotate and generate acting force in the relative sliding direction, and when the rotating speed of the rotor blades is high enough, the acting force makes the aircraft lift off to realize flight. Its advantages are low requirement to take-off runway, long running distance, and limited application range.

Accordingly, the prior art is yet to be improved and developed.

Disclosure of Invention

The invention aims to provide a double-wing flying structure which is reasonable in structure, adjustable in lift-off angle, high in output efficiency and capable of vertically lifting and hovering, aiming at the defects and shortcomings of the prior art.

In order to achieve the purpose, the invention adopts the following technical scheme:

the invention relates to a double-wing flying structure which comprises a translational wing, a driving device and a carrier, wherein the carrier is provided with a support and a central shaft, the lower end of the support is fixedly connected with the carrier, the central shaft is rotatably connected with the upper end of the support, and the support is provided with an angle adjusting device for changing the inclination angle of the central shaft; the central shaft is provided with two translational wings which are spaced up and down, and the translational wings are connected with the central shaft in a matching way; the driving device is respectively connected with the two translational wings in a transmission way, so that the two translational wings can respectively reciprocate up and down along the central shaft.

According to the scheme, the rotating center of the translational wing is provided with the rotating bearing, and the rotating bearing is connected with the central shaft in a matched mode through the sliding bearing.

According to the scheme, the driving device is arranged between the two translational wings and is fixedly connected with the central shaft; the driving device is provided with two crank connecting rods which are respectively connected with the sliding bearings on the corresponding translation wings in a matching way; the driving device also comprises a power source which can be a battery, an oil engine and other equipment capable of providing continuous power output.

According to the scheme, a synchronous hinge is arranged between the two translational wings, a central fulcrum of the synchronous hinge is hinged with a central shaft, and two end parts of the synchronous hinge are respectively connected with corresponding sliding bearings; the driving device is fixedly arranged on the bracket or the carrier, and the driving device is connected with a sliding bearing on one of the translation wings through a crank connecting rod.

According to the scheme, the translational wing comprises two wings which are oppositely arranged on two sides of the rotating bearing, and the wing roots of the two wings are respectively and fixedly connected with the rotating bearing; the upper side plane of the wing is a turbulent wing surface, and the lower side plane of the wing is a fanning wing surface; the vortex wing surface is formed by connecting a front curved surface and a rear smooth surface, the front curved surface of the vortex wing surface is upwards raised relative to a rotating plane of the translational wing, and the vortex wing surface and the fan-moving wing surface are in an asymmetric structure in the longitudinal projection plane.

According to the scheme, the front side edges of the turbulence wing surface and the fanning wing surface are mutually closed to form a front wing edge, and the rear side edges of the turbulence wing surface and the fanning wing surface are mutually closed to form a rear wing tail; and the span longitude line H where the maximum arch height point of the front curved surface of the spoiler airfoil is positioned is close to the front wing edge.

The invention has the beneficial effects that: the structure of the invention is reasonable, the central shaft and the upper translational wing structure thereof can be integrally rotated on the bracket to adjust the lift output angle, the driving device drives the two translational wings to reciprocate up and down through the crank connecting rod to realize synchronous opening and closing movement, and when the translational wings ascend, air generates pressure difference between the front side curved surface and the rear smooth surface of the spoiler wing surface so as to promote the unidirectional rotation of the translational wings; when the translational wing descends, a vertical upward acting force is generated between the fanning wing surface and the air, so that the carrier obtains a lifting force to achieve the flying purpose.

Drawings

FIG. 1 is a schematic view of the overall structure of embodiment 1 of the present invention;

FIG. 2 is a schematic view of the overall structure of embodiment 2 of the present invention;

FIG. 3 is a schematic view of the assembly structure of the translational wing of the present invention on the central shaft;

fig. 4 is a structural diagram of a translational wing section of the invention.

In the figure:

1. a translational wing; 2. a drive device; 3. a carrier; 10. a wing; 11. a spoiler airfoil; 12. a fanning airfoil; 13. a leading fin edge; 14. the rear wing tail; 15. a rotating bearing; 21. a crank connecting rod; 22. a power source; 23. a sliding bearing; 24. a synchronous hinge; 31. a support; 32. a central shaft; 33. an angle adjusting device.

Detailed Description

The technical solution of the present invention is described below with reference to the accompanying drawings and examples.

Example 1

As shown in fig. 1, 3 and 4, the double-wing flying structure of the invention comprises a translational wing 1, a driving device 2 and a carrier 3, wherein the carrier 3 is provided with a support 31 and a central shaft 32, the lower end of the support 31 is fixedly connected with the carrier 3, the central shaft 32 is rotatably connected with the upper end of the support 31, and the support 31 is provided with an angle adjusting device 33 for changing the inclination angle of the central shaft 32; the central shaft 32 is provided with two vertically spaced translation wings 1, and the translation wings 1 are connected with the central shaft 32 in a matching manner; the driving device 2 is respectively connected with the two translational wings 1 in a transmission way, so that the two translational wings 1 can respectively reciprocate up and down along the central shaft 32. The central shaft 32 and the two translational wings 1 on the central shaft can be integrally rotated on the bracket 31 through the angle adjusting device 33 to adjust the lift output angle, the driving device 2 drives the two translational wings 1 to reciprocate up and down to realize synchronous opening and closing motion, the translational wings 1 generate rotation action under the action of air in the ascending stroke, and the two translational wings 1 generate lift through rotation and combination of descending action, so that the purpose of flying the carrier 3 is realized.

The rotation center of the translational wing 1 is provided with a rotating bearing 15, and the rotating bearing 15 is connected with the central shaft 32 in a matching way through a sliding bearing 23. The translational wing 1 has horizontal rotation and vertical reciprocating motion on the central shaft 32, and the translational wing 1 and the central shaft 32 are in motion fit through the rotary bearing 15 and the sliding bearing 23.

The driving device 2 is arranged between the two translational wings 1, and the driving device 2 is fixedly connected with the central shaft 32; the driving device 2 is provided with two crank connecting rods 21, and the two crank connecting rods 21 are respectively connected with sliding bearings 23 on the corresponding translational wings 1 in a matching way; the drive device 2 further includes a power source 22. the power source 22 may be a battery, an oil-burning engine, or other device that provides a continuous power output. The driving device 2 is arranged between the two translational wings 1 so as to change the output angle of the lift force of the translational wings 1 through the adjustment of the inclination angle of the central shaft 32, and when the rotating plane of the translational wings 1 is parallel to the horizontal plane, the translational wings 1 output the lift force in the vertical direction; when the rotating plane of the translational wing 1 forms an included angle with the horizontal plane, the power output by the translational wing 1 can be decomposed into a lifting force in the vertical direction and a driving force in the horizontal direction, and the carrier 3 and the integral flying mechanism fly in the air under the action of the driving force.

The translational wing 1 comprises two wings 10, the two wings 10 are oppositely arranged on two sides of the rotating bearing 15, and the wing roots of the two wings 10 are respectively fixedly connected with the rotating bearing 15; the upper side plane of the wing 10 is a turbulent wing surface 11, and the lower side plane of the wing 10 is a fanning wing surface 12; the spoiler airfoil 11 is formed by connecting a front curved surface and a rear smooth surface, the front curved surface of the spoiler airfoil 11 protrudes upwards relative to the rotating plane of the translational wing 1, and the spoiler airfoil 11 and the fanning airfoil 12 are in an asymmetric structure in the longitudinal projection plane. The driving device 2 drives the translational wing 1 to reciprocate up and down, when the translational wing 1 ascends, the turbulent wing surfaces 11 of the wings 10 interact with air above, the air generates pressure difference between the front side curved surfaces and the rear smooth surfaces of the turbulent wing surfaces 11, the pressure difference pushes the wings 10 to move forward, and the two wings 10 act in the same direction, so that the translational wing 1 rotates unidirectionally by taking the rotating bearing 15 as the center; when the translational wing 1 descends, the fanning wing surface 12 of the wing 10 interacts with the air below, the rotational motion of the translational wing 1 is combined with the downward motion to enable the fanning wing surface 12 to form a vector attack angle C, and the vector attack angle C enables the fanning wing surface 12 and the air to generate a vertical upward acting force; the translational wing 1 converts the up-and-down reciprocating motion of the driving device 2 into self rotary motion, and then generates lift force through the rotary motion to enable the flying device to obtain the lift force to achieve the flying purpose.

The front side edges of the spoiler airfoil 11 and the fanning airfoil 12 are mutually closed to form a front wing edge 13, and the rear side edges of the spoiler airfoil 11 and the fanning airfoil 12 are mutually closed to form a rear wing tail 14; the span meridian H where the maximum arch height point of the front curved surface of the spoiler airfoil 11 is located is close to the front wing edge 13. The front wing edge 13 is a curved surface so as to respectively continue the front side edges of the spoiler wing surface 11 and the fanning wing surface 12, the existence of the front wing edge 13 can improve the structural strength of the wing type translational wing 1, the front wing edge 13 is positioned at the front side of the rotational direction of the translational wing 1, and the curved front wing edge 13 can reduce the air resistance received by the translational wing 1 during rotation and improve the power conversion efficiency of the driving device. As shown in fig. 2, the X direction in the figure is the chord length direction of the airfoil structure, and the Z direction in the figure is the spanwise direction of the airfoil structure. The contour line of the cross section of the turbulent wing surface 11 along the X direction is in a curve shape relative to the rotating plane of the translational wing 1, the highest point of the contour line forms a span warp H along the Z direction, and the span warp H is positioned on the front curved surface of the turbulent wing surface 11 and is close to the front wing edge 13, so that the turbulent wing surface 11 is in a front-back asymmetric structure. When the translational wing 1 is lifted, the spoiler wing surface 11 interacts with air above, pressure difference is generated between the front side and the rear side of the span longitude line H of the spoiler wing surface 11 by the air, the wing wings 10 are pushed to move forwards by the pressure difference, and the two wing wings 10 act in the same direction, so that the translational wing 1 rotates in a single direction by taking the rotating bearing 15 as the center.

Example 2

As shown in fig. 2, the only difference between the present embodiment and embodiment 1 is that a synchronous hinge 24 is provided between the two translational wings 1, a central fulcrum of the synchronous hinge 24 is hinged to a central shaft 32, and two ends of the synchronous hinge 24 are respectively connected to corresponding sliding bearings 23; the driving device 2 is fixedly arranged on the bracket 31 or the carrier 3, and the driving device 2 is connected with a sliding bearing 23 on one of the translation wings 1 through a crank connecting rod 21. The two translational wings 1 realize opening and closing movement on the central shaft 32 through the synchronous hinge 24, the opening and closing movement comprises relative movement and deviation movement of the two translational wings 1, the translational wings 1 rotate by adopting up-and-down reciprocating movement to generate lift force, and the spoiler wing surfaces 11 and the fanning wing surfaces 12 of the wings 10 do work in up-and-down strokes respectively, so that a lift force output gap exists in the operation of a single translational wing 1, the reciprocating movement of the single translational wing 1 can generate larger vibration to influence the stability of the flying device, and the structures of the two translational wings 1 which move up and down oppositely can well offset the vibration and make up the lift force output gap, so that the flying stability is improved.

The above description is only a preferred embodiment of the present invention, and all equivalent changes or modifications of the structure, characteristics and principles described in the present invention are included in the scope of the present invention.

Claims

1. A double-wing flight structure comprises a translational wing (1), a driving device (2) and a carrier (3), and is characterized in that: a support (31) and a central shaft (32) are arranged on the carrier (3), the lower end of the support (31) is fixedly connected with the carrier (3), the central shaft (32) is rotatably connected with the upper end of the support (31), and an angle adjusting device (33) for changing the inclination angle of the central shaft (32) is arranged on the support (31); the central shaft (32) is provided with two translational wings (1) which are spaced up and down, and the translational wings (1) are connected with the central shaft (32) in a matching way; the driving device (2) is respectively connected with the two translational wings (1) in a transmission way, so that the two translational wings (1) can respectively reciprocate up and down along the central shaft (32).

2. The twin wing flight architecture of claim 1, wherein: the rotating center of the translational wing (1) is provided with a rotating bearing (15), and the rotating bearing (15) is connected with the central shaft (32) in a matching way through a sliding bearing (23).

3. The twin wing flight architecture of claim 2, wherein: the driving device (2) is arranged between the two translational wings (1) and the driving device (2) is fixedly connected with the central shaft (32); the driving device (2) is provided with two crank connecting rods (21), and the two crank connecting rods (21) are respectively matched and connected with sliding bearings (23) on the corresponding translation wings (1); the driving device (2) also comprises a power source (22), and the power source (22) can be a battery, an oil engine and other equipment capable of providing continuous power output.

4. The twin wing flight architecture of claim 2, wherein: a synchronous hinge (24) is arranged between the two translational wings (1), a central fulcrum of the synchronous hinge (24) is hinged with the central shaft (32), and two end parts of the synchronous hinge (24) are respectively connected with corresponding sliding bearings (23); the driving device (2) is fixedly arranged on the bracket (31) or the carrier (3), and the driving device (2) is connected with a sliding bearing (23) on one of the translation wings (1) through a crank connecting rod (21).

5. The twin wing flight architecture according to any one of claims 1 to 4, wherein: the translational wing (1) comprises two wing fins (10), the two wing fins (10) are oppositely arranged on two sides of the rotating bearing (15), and the wing roots of the two wing fins (10) are respectively fixedly connected with the rotating bearing (15); the upper side plane of the wing (10) is a turbulent wing surface (11), and the lower side plane of the wing (10) is a fanning wing surface (12); the vortex wing surfaces (11) are formed by connecting a front curved surface and a rear smooth surface, the front curved surface of the vortex wing surfaces (11) is upwards raised relative to a rotating plane of the translational wing (1), and the vortex wing surfaces (11) and the fanning wing surfaces (12) are in an asymmetric structure in the longitudinal projection plane.

6. The twin wing flight architecture of claim 5, wherein: the front side edges of the turbulent flow wing surfaces (11) and the fanning wing surfaces (12) are mutually closed to form front wing edges (13), and the rear side edges of the turbulent flow wing surfaces (11) and the fanning wing surfaces (12) are mutually closed to form rear wing tails (14); the span meridian H where the maximum arch height point of the front curved surface of the spoiler airfoil (11) is located is close to the front wing edge (13).