CN214216133U

CN214216133U - Flapping flight device

Info

Publication number: CN214216133U
Application number: CN202022764284.5U
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: 2021-09-17
Anticipated expiration: 2030-11-26

Abstract

The utility model relates to the technical field of aircrafts, in particular to a flapping flight device; the flapping wing comprises two wings and a rotating bearing, wherein the two wings are oppositely arranged on two sides of the rotating bearing, and the roots of the two wings are respectively hinged on the rotating bearing; the driving device is connected with the rotating bearing so as to be rotationally connected with the flapping wings, and the driving device is respectively in transmission connection with the two wing wings; the utility model has reasonable structure, the driving device drives the flapping wing by up-and-down reciprocating motion, the turbulent wing surface interacts with the air above the flapping wing when the flapping wing ascends, the air generates pressure difference between the front side curved surface and the rear smooth surface of the turbulent wing surface, and the direction of the pressure difference is definite so as to promote the unidirectional rotation of the flapping wing; when the flapping wing descends, the fan-moving wing surface interacts with air below, the rotation of the flapping wing enables the fan-moving wing surface to move downwards to generate a vector attack angle, and the vector attack angle enables the fan-moving wing surface and the air to generate vertical upward acting force.

Description

Flapping flight device

Technical Field

The utility model relates to an aircraft technical field specifically indicates a flapping flight device.

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.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to prior art's defect and not enough, provide a rational in infrastructure, accessible wing flapping drives flapping wing rotation, and output efficiency is high, but the flapping flight device that the helicopter hovered.

In order to achieve the above purpose, the utility model adopts the following technical scheme:

the flapping flight device comprises a flapping wing and a driving device, wherein the flapping wing comprises two wing wings and a rotating bearing, the two wing wings are oppositely arranged on two sides of the rotating bearing, and the wing roots of the two wing wings are respectively hinged on the rotating bearing; the driving device is connected with the rotating bearing so as to be rotationally connected with the flapping wings, and the driving device is respectively in transmission connection with the two wing wings.

According to the scheme, 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 spoiler airfoil is formed by connecting a front curved surface and a rear smooth surface, the front curved surface of the spoiler airfoil protrudes upwards relative to a rotating plane of the flapping wing, and the spoiler airfoil and the fan moving airfoil 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.

According to the scheme, an installation angle C exists between the rotating planes of the flapping wing and the fan wing, and the value range of C is-2-6 degrees.

According to the scheme, the driving device comprises a main shaft, a sliding sleeve and a power device, and the rotating bearing is fixedly connected with the main shaft so that the flapping wing can rotate on the main shaft; the sliding sleeve and the main shaft are arranged concentrically, and a sliding bearing is arranged between the sliding sleeve and the main shaft; the sliding sleeve is rotatably provided with a traction support, the traction support is respectively connected with the corresponding wing through two connecting rods, and the power device is in transmission connection with the sliding sleeve so as to drive the sliding sleeve to reciprocate up and down.

According to the scheme, two groups of flapping wings which are matched up and down are arranged on the driving device, and the two groups of flapping wings are connected to the main shaft through the rotating bearing; the main shaft is provided with two sliding sleeves which can move up and down along the main shaft respectively, and traction supports on the sliding sleeves are connected with corresponding wing wings through connecting rods respectively; and the power devices are respectively in transmission connection with the corresponding sliding sleeves through asynchronous mechanisms.

The utility model discloses beneficial effect does: the utility model has reasonable structure, the driving device drives the flapping wing by up-and-down reciprocating motion, the turbulent wing surface interacts with the air above the flapping wing when the flapping wing ascends, the air generates pressure difference between the front side curved surface and the rear smooth surface of the turbulent wing surface, and the direction of the pressure difference is definite so as to promote the unidirectional rotation of the flapping wing; when the flapping wing descends, the fan-moving wing surface interacts with air below, the rotation of the flapping wing enables the fan-moving wing surface to move downwards to generate a vector attack angle, and the vector attack angle enables the fan-moving wing surface and the air to generate a vertical upward acting force; the flapping wing converts the up-and-down reciprocating motion of the driving device into the self rotary motion, and then the rotary motion generates lift force to enable the flying device 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 view of another mounting structure of the flapping wing of the present invention;

fig. 3 is a schematic view of the cross-section of the wing of the present invention.

In the figure:

1. flapping wings; 10. a wing; 11. a spoiler airfoil; 12. a fanning airfoil; 13. a leading fin edge; 14. the rear wing tail; 21. a rotating bearing; 22. a main shaft; 23. a sliding sleeve; 24. a sliding bearing; 25. a traction support; 26. a connecting rod.

Detailed Description

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

As shown in fig. 1-3, the flapping flight device of the present invention comprises a flapping wing 1 and a driving device, wherein the flapping wing 1 comprises two wings 10 and a rotating bearing 21, the two wings 10 are oppositely disposed on two sides of the rotating bearing 21, and the roots of the two wings 10 are respectively hinged on the rotating bearing 21; the driving device is connected with the rotating bearing 21 so as to be rotationally connected with the flapping wing 1, and the driving device is respectively in transmission connection with the two wing wings 10. 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 flapping 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 drives the two wings 10 of the flapping wing 1 to rotate around the rotating bearing 21, and the two wings 10 move synchronously along the S1 direction relatively so as to simulate the flapping action of birds. When the wings 10 rotate upwards, the spoiler 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 spoiler wing surfaces 11, the pressure difference pushes the wings 10 to move forwards, and the two wings 10 act in the same direction, so that the flapping wings 1 rotate unidirectionally by taking the rotating bearing 21 as the center; when the flapping wing 1 descends, the fanning wing surface 12 of the wing 10 interacts with the air below, the rotation motion of the flapping wing 1 is combined with the downward motion to enable the fanning wing surface 12 to form a vector attack angle, and the vector attack angle enables the fanning wing surface 12 and the air to generate a vertical upward acting force; the flapping wing 1 converts the up-and-down reciprocating motion of the driving device into the self rotary motion, and then generates the 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 flapping wing 1, the front wing edge 13 is positioned at the front side of the flapping wing 1 in the rotating direction, and the curved front wing edge 13 can reduce the air resistance when the flapping wing 1 rotates, so that the power conversion efficiency of the driving device is improved. As shown in fig. 3, 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 flapping wing 1, the highest point of the contour line forms a span meridian H along the Z direction, and the span meridian 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 wings 10 of the flapping wing 1 vibrate upwards, the spoiler wing surfaces 11 interact with air above, pressure difference is generated between the air and the front side and the rear side of the span longitude line H of the spoiler wing surfaces 11, the pressure difference pushes the wing wings 10 to move forwards, and the two wing surfaces 10 act in the same direction, so that the flapping wing 1 rotates in a single direction by taking the rotating bearing 21 as the center.

An installation angle C exists between the fanning wing surface 12 and the rotating plane of the flapping wing 1, and the value range of C is-2 degrees to 6 degrees. The flapping wing 1 reciprocates up and down after being started, the spoiler wing surfaces 11 move upwards, air flows through the spoiler wing surfaces 11 to generate pressure difference on the front side and the rear side of a wing span meridian H, the pressure difference forms a forward driving force for the wing wings 10 to enable the flapping wing 1 to rotate, at the moment, the front wing edges 13 generate differential speed relative to the air to form resistance for the flapping wing 1, and the driving force overcomes the resistance to drive the flapping wing 1 to rotate; the flapping wing surface 12 moves downwards, when the rotating speed of the flapping wing 1 is very low, the installation angle C enables the acting force of air relative to the flapping wing surface 12 to be basically vertical to the rotating plane of the flapping wing 1, and the resistance of the lower layer of air to the forward rotating motion of the wing 10 is very small, so that the flapping wing 1 can obtain a high rotating speed after reciprocating up and down for a period of time. When the rotation speed of the flapping wing 1 is high, the fanning wing surface 12 moves both downwards and forwards, the vector angle of the vector motion formed by the superposition of the two relative to the rotation plane of the flapping wing 1 is larger than the installation angle C, namely the lift force generated by the fanning wing surface 12 is larger as the rotation speed of the flapping wing 1 is faster, and the rotation speed of the flapping wing 1 can be improved by controlling the vertical vibration frequency of the flapping wing 1 so as to change the lift force generated by the flapping wing 1.

The driving device comprises a main shaft 22, a sliding sleeve 23 and a power device, wherein the rotating bearing 21 is fixedly connected with the main shaft 22 so that the flapping wing 1 can rotate on the main shaft 22; the sliding sleeve 23 and the main shaft 22 are arranged concentrically, and a sliding bearing 24 is arranged between the sliding sleeve 23 and the main shaft 22; the sliding sleeve 23 is rotatably provided with a traction bracket 25, the traction bracket 25 is respectively connected with the corresponding wing 10 through two connecting rods 26, and the power device is in transmission connection with the sliding sleeve 23 so as to drive the sliding sleeve to reciprocate up and down along the direction of S2. The main shaft 22 is used for mounting the whole flying device on an aircraft, the driving device drives the sliding sleeve 23 to reciprocate up and down along the main shaft 22, the traction support 25 on the sliding sleeve 23 drives the wing 10 through the connecting rod 26, so that the wing 10 vibrates up and down in a reciprocating manner by taking the rotary bearing 21 as a center, the flapping wing 1 rotates on the main shaft 22 through the rotary bearing 21 by the rotating force generated by the wing 10, and then the lifting force is generated by combining the downward flapping action of the wing 10 to achieve the flying purpose.

As shown in fig. 1-2, two groups of flapping wings 1 are provided on the driving device, wherein the two groups of flapping wings 1 are paired up and down, the two groups of flapping wings 1 are both connected to a main shaft 22 through a rotating bearing 21, each group of flapping wings 1 can be respectively installed on the main shaft 2 through a rotating bearing 21, and the two groups of flapping wings 1 can be simultaneously installed on the same rotating bearing 21; the main shaft 22 is provided with two sliding sleeves 23 which can move up and down along the main shaft respectively, and traction brackets 25 on the sliding sleeves 23 are connected with the corresponding wing wings 10 respectively through connecting rods 26; the power devices are respectively in transmission connection with the corresponding sliding sleeves 23 through asynchronous mechanisms. The driving device drives the two groups of flapping wings 1 to act in a time-sharing mode through the asynchronous mechanism, namely one group of flapping wings 1 flap upwards while the other group of flapping wings 1 flap downwards, so that the power output stability of the driving device is ensured. Particularly, the two groups of flapping wings 1 which are paired up and down form opening and closing movement relatively, so that vibration can be well offset, a lift force output gap is made up, and the flying stability is improved.

The above is only the preferred embodiment of the present invention, so all the equivalent changes or modifications made by the structure, features and principles in accordance with the claims of the present invention are included in the claims of the present invention.

Claims

1. A flapping flight device comprises a flapping wing (1) and a driving device, and is characterized in that: the flapping wing (1) comprises two wing fins (10) and a rotating bearing (21), the two wing fins (10) are oppositely arranged on two sides of the rotating bearing (21), and the wing roots of the two wing fins (10) are respectively hinged on the rotating bearing (21); the driving device is connected with the rotating bearing (21) so as to be rotationally connected with the flapping wing (1), and the driving device is respectively in transmission connection with the two wing wings (10).

2. The flapping flight apparatus of claim 1, wherein: 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 a rotating plane of the flapping wing (1), and the spoiler airfoil (11) and the fanning airfoil (12) are in an asymmetric structure in the longitudinal projection plane.

3. The flapping flight apparatus of claim 2, 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).

4. A flapping flight apparatus according to claim 3, wherein: an installation angle C exists between the rotating planes of the flapping wing surface (12) and the flapping wing (1), and the value range of C is-2-6 degrees.

5. The flapping flight apparatus of claim 1, wherein: the driving device comprises a main shaft (22), a sliding sleeve (23) and a power device, wherein the rotating bearing (21) is fixedly connected with the main shaft (22) so that the flapping wing (1) can rotate on the main shaft (22); the sliding sleeve (23) and the main shaft (22) are arranged concentrically, and a sliding bearing (24) is arranged between the sliding sleeve (23) and the main shaft (22); the sliding sleeve (23) is rotatably provided with a traction support (25), the traction support (25) is respectively connected with the corresponding wing (10) through two connecting rods (26), and the power device is in transmission connection with the sliding sleeve (23) so as to drive the sliding sleeve to reciprocate up and down.

6. A flapping flight apparatus according to claim 5, wherein: the driving device is provided with two groups of flapping wings (1) which are matched up and down, and the two groups of flapping wings (1) are connected to a main shaft (22) through a rotating bearing (21); the main shaft (22) is provided with two sliding sleeves (23) which can move up and down along the main shaft respectively, and traction brackets (25) on the sliding sleeves (23) are connected with corresponding wing wings (10) through connecting rods (26) respectively; the power devices are respectively in transmission connection with the corresponding sliding sleeves (23) through asynchronous mechanisms.