CN112319788A

CN112319788A - Double-layer wing unmanned aerial vehicle

Info

Publication number: CN112319788A
Application number: CN202011342076.4A
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: 2021-02-05

Abstract

The invention relates to the technical field of unmanned aerial vehicles, in particular to a double-layer wing unmanned aerial vehicle; the aircraft comprises a carrier and a plurality of flight mechanisms, wherein the flight mechanisms surround the carrier and are symmetrically arranged by taking the carrier as a center, each flight mechanism comprises an expansion arm, a driving device and a flat moving wing, and two ends of each expansion arm are respectively connected with the carrier and the driving device; the upper side and the lower side of the driving device are both provided with central shafts, the central shafts are provided with translational wings which are matched and connected with the central shafts, and the driving device is respectively connected with the translational wings on the two central shafts through asynchronous mechanisms so as to drive the two translational wings to oppositely open and close on the central shafts; the invention has reasonable structure, and when the two translational wings move up and down in a reciprocating way, the air generates pressure difference between the front curved surface and the rear smooth surface of the spoiler wing surface when the translational wings move up, thereby promoting the translational wings to rotate in a single direction; when the translational wing descends, a vertical upward acting force is generated between the moving wing surface of the fan and the air, so that the unmanned aerial vehicle obtains a lift force to achieve the aim of flying.

Description

Double-layer wing unmanned aerial vehicle

Technical Field

The invention relates to the technical field of unmanned aerial vehicles, in particular to a double-layer wing unmanned aerial vehicle.

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 existing unmanned aerial vehicle is a miniaturization scheme of the spiral wing aircraft, a control system and an energy supply battery are arranged on a main body, a plurality of cantilevers extend out of the main body, a motor and spiral wings are arranged at the far ends of the cantilevers, and the motor directly drives the spiral wings to rotate. In case of energy exhaustion, the spiral wing can stop to cause aircraft crash, so that strict electric quantity management and stroke limitation are required, and the safety is not high.

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

Disclosure of Invention

The invention aims to provide a double-layer wing unmanned aerial vehicle which is reasonable in structure, realizes self-rotation and obtains lift force by reciprocally driving two translational wings and has the capability of staying empty, 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-layer wing unmanned aerial vehicle which comprises a carrier and a plurality of flight mechanisms, wherein the flight mechanisms surround the carrier and are symmetrically arranged by taking the carrier as a center, each flight mechanism comprises an expansion arm, a driving device and a translational wing, and two ends of the expansion arm are respectively connected with the carrier and the driving device; the upper side and the lower side of the driving device are both provided with central shafts, the central shafts are provided with translational wings which are connected with the central shafts in a matching way, and the driving device is respectively connected with the translational wings on the two central shafts through asynchronous mechanisms, so that the two translational wings are driven to oppositely open and close on the central shafts.

According to the scheme, the rotating center of the translational wing is provided with the rotating bearing, the rotating bearing is connected with the central shaft in a matched mode through the sliding bearing, and the driving device is respectively connected with the sliding bearings on the upper translational wing and the lower translational wing through the asynchronous mechanism.

According to the scheme, the asynchronous mechanism comprises two crank connecting rods, one end of each crank connecting rod is connected with the output shaft of the driving device, and the other end of each crank connecting rod is connected with the sliding bearing in a matched mode.

According to the scheme, the carrier is provided with the energy accumulator, the controller and the undercarriage, the controller is integrated with the wireless transceiving module, the positioning module and the processing module, and the energy accumulator is electrically connected with the controller and the plurality of driving devices.

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 invention has reasonable structure, and when the two translational wings move up and down in a reciprocating way, the air generates pressure difference between the front curved surface and the rear smooth surface of the spoiler wing surface when the translational wings move up, thereby promoting the translational wings to rotate in a single direction; when the translational wing descends, a vertical upward acting force is generated between the fanning wing surface and air; the translational wing converts the up-and-down reciprocating motion of the driving mechanism into self rotary motion, and then generates lift force through the rotary motion to enable the unmanned aerial vehicle to obtain the lift force to achieve the flying purpose.

Drawings

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

FIG. 2 is a schematic structural view of the aircraft mechanism of the present invention;

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

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; 16. a sliding bearing; 21. a central shaft; 22. a crank connecting rod; 31. stretching the arm; 32. an accumulator; 33. a controller; 34. a landing gear.

Detailed Description

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

As shown in fig. 1, the double-layer wing unmanned aerial vehicle comprises a carrier 3 and a plurality of flight mechanisms, wherein the flight mechanisms surround the carrier 3 and are symmetrically arranged by taking the carrier as a center, each flight mechanism comprises an extending arm 31, a driving device 2 and a translational wing 1, and two ends of the extending arm 31 are respectively connected with the carrier 3 and the driving device 2; the upper side and the lower side of the driving device 2 are both provided with a central shaft 21, the central shaft 21 is provided with translational wings 1 which are connected with the central shaft in a matching way, and the driving device 2 is respectively connected with the translational wings 1 on the two central shafts 21 through asynchronous mechanisms, so that the two translational wings 1 are driven to perform opening and closing movement relatively on the central shaft 21. The carrier 3 is provided with at least two groups of flight mechanisms, namely, a front-back layout, a left-right layout, a cross layout, a star layout and the like around the carrier 3, the carrier 3 is connected with the whole flight mechanism through the spreading arm 31, the driving device 2 can be fixedly installed or installed at the far end of the spreading arm 31 through an angle-adjustable hinge structure, and an angle-adjustable mode of the driving device 2 is used for changing the acting force direction of a single or all flight mechanisms, so that the flight angle of the unmanned aerial vehicle is controlled. The driving device 2 drives the two translational wings 1 to reciprocate up and down on the central shaft 21, and the two translational wings 1 form opening and closing movement which is relatively close to or relatively far away from each other, so that the stability of the flying mechanism during working is ensured.

The rotating bearing 15 is arranged on the rotating center of the translational wing 1, the rotating bearing 15 is connected with the central shaft 21 in a matching way through a sliding bearing 16, and the driving device 2 is respectively connected with the sliding bearings 16 on the upper translational wing 1 and the lower translational wing 1 through an asynchronous mechanism. The asynchronous mechanism is used for converting the unidirectional rotary motion of the driving device 2 into the stroke motion of the two translational wings 1, so that the motion of the two translational wings 1 is controlled to be opposite opening and closing motion. The translational wing 1 rotates by adopting the up-and-down reciprocating motion to generate lift force, a lift force output gap exists in the operation of the single translational wing 1, the single translational wing 1 can generate larger vibration to influence the stability of the flying device by the reciprocating motion, 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 asynchronous mechanism comprises two crank connecting rods 22, one end of each crank connecting rod 22 is connected with the output shaft of the driving device 2, and the other end of each crank connecting rod 22 is connected with the sliding bearing 16 in a matched mode. The driving device 2 of the present invention is preferably an electric motor, and it is understood that the crank connecting rod 22 includes a crank structure and a connecting rod structure, the crank of the crank connecting rod 22 is rotatably connected with the output end of the driving device 2, and the connecting rod is rotatably connected with the sliding bearings 16, when the driving device 2 drives the crank connecting rod 22 to rotate, so as to drive the two sliding bearings 16 to reciprocate up and down. In order to control the motion of the two translational wings 1 to be opposite opening and closing motions, the two connecting rods form a phase difference of 180 degrees on the crank.

The carrier 3 is provided with an energy accumulator 32, a controller 33 and a landing gear 34, the controller 33 is integrated with a wireless transceiver module, a positioning module and a processing module, and the energy accumulator 32 is electrically connected with the controller 33 and the plurality of driving devices 2. The controller 33 on the carrier 3 is used as a core control component of the unmanned aerial vehicle, and has other functions of remote control, electric quantity management, action control, positioning control and control of the existing unmanned aerial vehicle, which are not repeated herein.

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.

Because the two translational wings 1 are respectively arranged on the central shaft 21 through the rotating bearing 15, when the driving device 2 loses power, the two translational wings 1 can still continue to rotate, the attack angle C of the fanning wing surface 12 is adjusted to be less than or equal to 0 degree, the translational wings 1 can continue to keep a rotating state under the action of the dropping inertia force, the actual vector attack angle of the fanning wing surface 12 is more than or equal to 0 degree to maintain a certain lift force, and the lift force can delay the descending speed of the carrier 3 so as to ensure the safe landing of the carrier, thereby effectively improving the safety of the flying device.

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. The utility model provides a double-deck wing unmanned aerial vehicle, includes carrier (3) and a plurality of flight mechanism, its characterized in that: the flight mechanisms surround the carrier (3) and are symmetrically arranged by taking the carrier as a center, each flight mechanism comprises an expansion arm (31), a driving device (2) and a flat moving wing (1), and two ends of each expansion arm (31) are respectively connected with the carrier (3) and the driving device (2); the upper side and the lower side of the driving device (2) are respectively provided with a central shaft (21), the central shaft (21) is provided with a translational wing (1) which is connected with the central shaft in a matching way, and the driving device (2) is respectively connected with the translational wings (1) on the two central shafts (21) through an asynchronous mechanism, so that the two translational wings (1) are driven to relatively open and close on the central shaft (21).

2. The double-wing drone of claim 1, wherein: the rotating center of the translational wing (1) is provided with a rotating bearing (15), the rotating bearing (15) is connected with the central shaft (21) in a matching way through a sliding bearing (16), and the driving device (2) is respectively connected with the sliding bearings (16) on the upper translational wing (1) and the lower translational wing (1) through asynchronous mechanisms.

3. The double-wing drone of claim 2, wherein: the asynchronous mechanism comprises two crank connecting rods (22), one end of each crank connecting rod (22) is connected with an output shaft of the driving device (2), and the other end of each crank connecting rod (22) is connected with the sliding bearing (16) in a matched mode.

4. The double-wing drone of claim 1, wherein: the carrier (3) is provided with an energy accumulator (32), a controller (33) and an undercarriage, the controller (33) is integrated with a wireless transceiver module, a positioning module and a processing module, and the energy accumulator (32) is electrically connected with the controller (33) and the plurality of driving devices (2).

5. The double-wing drone of any one of claims 1 to 4, characterized in that: 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 double-wing drone 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).