CN112429225A

CN112429225A - Single aircraft

Info

Publication number: CN112429225A
Application number: CN202011342449.8A
Authority: CN
Inventors: 王志成
Original assignee: Foshan Shenfeng Aviation Technology Co Ltd
Current assignee: Foshan Shenfeng Aviation Technology 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 single aircraft; the flapping wing type air conditioner comprises a translational wing, a flapping wing and a carrier, wherein a machine table is arranged on the carrier, a central shaft is vertically arranged on the machine table, a sliding bearing is arranged between the central shaft and the machine table, and the translational wing is rotatably arranged at the upper end of the central shaft; the two sides of the central shaft are symmetrically provided with flapping wings, and the two flapping wings are respectively and rotatably connected with the machine platform; the carrier is provided with a driving device, and the driving device is respectively connected with the central shaft and the two flapping wings through a transmission chain; the invention has reasonable structure, a person stands on the bottom plate of the carrier to drive the hand-held frame or the pedal plate, the transmission chain zooms the force of an operator and then drives the translational wing and the two flapping wings, the translational wing rotates to generate lift force when reciprocating up and down, and the flapping wings generate both lift force and forward propulsion force; the purpose of low-idling flying is achieved, when the aircraft loses power, the translational wings can continuously rotate to generate the idling force when falling, and the safety of the aircraft and personnel is guaranteed.

Description

Single aircraft

Technical Field

The invention relates to the technical field of aircrafts, in particular to a single aircraft.

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.

There are also unmanned aerial vehicles that are now relatively common, but manned flight has not been possible due to power and power consumption issues. The structure of the existing aircraft is too complex, and no unpowered aircraft capable of realizing single person exists. Accordingly, the prior art is yet to be improved and developed.

Disclosure of Invention

The invention aims to provide a single aircraft which is reasonable in structure, capable of realizing manned flight, various in driving mode, free of power stagnation and high in safety, 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 single aircraft which comprises a translational wing, a flapping wing and a carrier, wherein the carrier is provided with a machine table, a central shaft is vertically arranged on the machine table, a sliding bearing is arranged between the central shaft and the machine table, and the upper end of the central shaft is rotatably provided with the translational wing; the two sides of the central shaft are symmetrically provided with flapping wings, and the two flapping wings are respectively and rotatably connected with the machine platform; the carrier is provided with a driving device, and the driving device is respectively connected with the central shaft and the two flapping wings through a transmission chain.

According to the scheme, the driving device comprises a hand rest, a reinforcing rod is transversely arranged in the middle of the carrier, the hand rest is rotationally connected with the reinforcing rod, and the hand rest is respectively connected with the central shaft and the two flapping wings through a transmission chain; the transmission chain is a lever mechanism, a pulley mechanism and other devices capable of conducting force and action.

According to the scheme, the lower end of the carrier is provided with the bottom plate, the bottom plate is provided with the pedal, the pedal is rotatably connected with the bottom plate, and the pedal is in linkage with the hand frame.

According to the above scheme, the driving device further comprises an auxiliary motor and an energy storage battery.

According to the scheme, the flapping wing comprises two wing wings and a rotating bearing, the rotating bearing is fixedly connected with the central shaft, and the two wing wings are oppositely arranged on two sides of the rotating bearing and fixedly connected with the rotating bearing.

According to the scheme, the flapping wing comprises a wing and a driving connecting rod, the root of the wing is rotatably connected with the machine table through a rotating hinge, one end of the driving connecting rod is fixedly connected with the wing, and the other end of the driving connecting rod is connected with the transmission chain in a matched mode.

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 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, a person stands on the bottom plate of the carrier to drive the hand-held frame or the pedal plate, the transmission chain zooms the force of an operator and then drives the translational wing and the two flapping wings, the translational wing rotates to generate lift force when reciprocating up and down, and the flapping wings generate both lift force and forward propulsion force; the purpose of low-idling flying is achieved, when the aircraft loses power, the translational wings can continuously rotate to generate the idling force when falling, and the safety of the aircraft and personnel is guaranteed.

Drawings

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

FIG. 2 is a schematic view of the wing to center shaft assembly of the present invention;

FIG. 3 is a schematic cross-sectional view of a wing of the present invention.

In the figure:

1. a translational wing; 2. flapping wings; 3. a carrier; 4. a drive device; 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 drive link; 22. rotating the hinge; 31. a machine platform; 32. a central shaft; 33. a sliding bearing; 41. a hand-held rack; 42. a reinforcing rod; 43. a base plate; 44. a foot pedal.

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 single-person aircraft comprises a translational wing 1, a flapping wing 2 and a carrier 3, wherein a machine table 31 is arranged on the carrier 3, a central shaft 32 is vertically arranged on the machine table 31, a sliding bearing 33 is arranged between the central shaft 32 and the machine table 31, and the translational wing 1 is rotatably arranged at the upper end of the central shaft 32; the flapping wings 2 are symmetrically arranged on two sides of the central shaft 32, and the two flapping wings 2 are respectively and rotatably connected with the machine table 31; the carrier 3 is provided with a driving device 4, and the driving device 4 is respectively connected with the central shaft 32 and the two flapping wings 2 through a transmission chain. The translational wing 1 can reciprocate up and down on the platform 31 through the central shaft 32, the translational wing 1 can rotate on the central shaft 32, and the two flapping wings 2 only swing up and down on two sides of the platform 31. The motion directions of the translational wing 1 and the flapping wing 2 at the same time point are opposite, so that the stability of the aircraft is ensured, namely the translational wing 1 and the flapping wing counteract vibration through synchronous opposite motion or back motion. The translational wing 1 obtains rotary power in the up-and-down reciprocating motion process, the rotary translational wing 1 can provide lift force to enable the aircraft to take off, the downward flapping stroke of the flapping wing 2 can provide the lift force, the upward flapping stroke of the flapping wing 2 can generate forward driving force to enable the aircraft to generate displacement, and an operator drives the translational wing 1 and the flapping wing 2 on the carrier 3 through the driving device 4 respectively to achieve the purpose of manned flight.

The driving device 4 comprises a hand frame 41, a reinforcing rod 42 is transversely arranged in the middle of the carrier 3, the hand frame 41 is rotatably connected with the reinforcing rod 42, and the hand frame 41 is respectively connected with the central shaft 32 and the two flapping wings 2 through a transmission chain; the transmission chain is a lever mechanism, a pulley mechanism and other devices capable of conducting force and action. The transmission chain transmits the power applied by the hands of the operator on the hand-held frame 41 to the translational wing 1 and the flapping wing 2 to enable the translational wing 1 and the flapping wing 2 to work, thereby achieving the purpose of flying.

The lower end of the carrier 3 is provided with a bottom plate 43, the bottom plate 43 is provided with a pedal plate 44, the pedal plate 44 is rotatably connected with the bottom plate 43, and the pedal plate 44 is linked with the hand frame 41. The operator can also realize the purpose of power output through the pedal 44, realize the purpose of hand and foot alternative output, and the flight time can be prolonged better to operator's physical power.

The driving device 4 further comprises an auxiliary motor and an energy storage battery, the auxiliary motor is respectively connected with the transmission chain and the energy storage battery, the auxiliary motor can be used for driving the translational wing 1 in advance to obtain a certain initial speed, the use of manpower is reduced, the flight starting time is shortened, the auxiliary motor can be used as standby power to output, and the safe landing of the aircraft can be guaranteed under the condition of insufficient manpower.

The flapping wing 2 comprises two wings 10 and a rotating bearing 15, the rotating bearing 15 is fixedly connected with a central shaft 32, and the two wings 10 are oppositely arranged on two sides of the rotating bearing 15 and fixedly connected with the rotating bearing 15; the flapping wing 2 comprises a wing 10 and a driving connecting rod 21, the root of the wing 10 is rotatably connected with the machine table 31 through a rotating hinge 22, one end of the driving connecting rod 21 is fixedly connected with the wing 10, and the other end of the driving connecting rod 21 is connected with a transmission chain in a matching mode. The transmission chain drives the two flapping wings 2 to vibrate up and down on two sides of the platform 31 through the driving connecting rod 21, and the flapping wings 2 achieve the vertical lift-off force and the horizontal propelling force through the aerodynamic design of the 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 translational wing 1, and the spoiler airfoil 11 and the fanning airfoil 12 are in an asymmetric structure in the longitudinal projection plane. The translational 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 span warp line H, the pressure difference forms a forward driving force for the wing 10 to enable the translational wing 1 to rotate, at the moment, the front wing edge 13 generates differential speed relative to the air to form resistance for the translational wing 1, and the driving force overcomes the resistance to drive the translational wing 1 to rotate; the fan-moving wing surface 12 moves downwards, when the rotating speed of the translational wing 1 is very low, the attack angle is small, so that the acting force of the air relative to the fan-moving wing surface 12 is basically vertical to the rotating plane of the translational wing 1, the resistance of the lower layer air to the forward rotating motion of the wing 10 is very small, and therefore the translational wing 1 can obtain higher rotating speed after reciprocating up and down for a period of time. When the rotating speed of the translational 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 rotating plane of the translational wing 1 is larger than the installation angle C, namely, the lifting force generated by the fanning wing surface 12 is larger as the rotating speed of the translational wing 1 is faster, and the rotating speed of the translational wing 1 can be improved by controlling the up-and-down movement frequency of the translational wing 1, so that the lifting force generated by the translational wing 1 is improved. The translational wing 1 can convert the up-and-down reciprocating motion into the self rotary motion, and then the rotary motion generates lift force to achieve the flying purpose.

The aerodynamic principle of the flapping wing 2 is the same as that of the translational wing 1, but the flapping wing 2 only swings up and down but does not rotate, when the wing 10 swings upwards, the turbulent wing surface 11 at the upper part of the wing generates pressure difference and converts the pressure difference into forward propelling force, and when the wing 10 swings downwards, the fanning wing surface 12 at the lower part of the wing directly acts with air to generate lift force.

For the sake of safety, the installation angle C of the wing 10 of the translational wing 1 of the present invention is in the range of-2 ° to 6 °, the preferred installation angle C of the wing 10 is 2 °, when the power of an operator is insufficient, the aircraft loses power and falls, the rotational translational wing 1 still continues to rotate under the action of the air below, and the vector attack angle of the wing 10 is greater than 0 °, so that the translational wing 1 provides lift force to make the aircraft obtain the capability of staying empty, and the falling speed of the aircraft is delayed, thereby ensuring the safety of personnel and the aircraft.

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 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 single-man aircraft, includes translational wing (1), flapping wing (2) and carrier (3), its characterized in that: a machine table (31) is arranged on the carrier (3), a central shaft (32) is vertically arranged on the machine table (31), a sliding bearing (33) is arranged between the central shaft (32) and the machine table (31), and the upper end of the central shaft (32) is rotatably provided with a translation wing (1); the two sides of the central shaft (32) are symmetrically provided with flapping wings (2), and the two flapping wings (2) are respectively and rotatably connected with the machine table (31); the carrier (3) is provided with a driving device (4), and the driving device (4) is respectively connected with the central shaft (32) and the two flapping wings (2) through a transmission chain.

2. The single-person aircraft of claim 1, wherein: the driving device (4) comprises a hand-held frame (41), a reinforcing rod (42) is transversely arranged in the middle of the carrier (3), the hand-held frame (41) is rotatably connected with the reinforcing rod (42), and the hand-held frame (41) is respectively connected with the central shaft (32) and the two flapping wings (2) through a transmission chain; the transmission chain is a lever mechanism, a pulley mechanism and other devices capable of conducting force and action.

3. The single-person aircraft of claim 2, wherein: the lower end of the carrier (3) is provided with a bottom plate (43), the bottom plate (43) is provided with a pedal (44), the pedal (44) is rotatably connected with the bottom plate (43), and the pedal (44) and the hand frame (41) are arranged in a linkage manner.

4. The single-person aircraft of claim 2, wherein: the drive device (4) further comprises an auxiliary motor and an energy storage battery.

5. The single-person aircraft of claim 1, wherein: the flapping wing (2) comprises two wing wings (10) and a rotating bearing (15), the rotating bearing (15) is fixedly connected with the central shaft (32), and the two wing wings (10) are oppositely arranged on two sides of the rotating bearing (15) and fixedly connected with the rotating bearing.

6. The single-person aircraft of claim 1, wherein: the flapping wing (2) comprises a wing (10) and a driving connecting rod (21), the root of the wing (10) is rotatably connected with the machine table (31) through a rotating hinge (22), one end of the driving connecting rod (21) is fixedly connected with the wing (10), and the other end of the driving connecting rod (21) is connected with the transmission chain in a matched mode.

7. The single-person aircraft as claimed in any one of claims 1, 5 and 6, 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 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.

8. The single-person aircraft of claim 1, 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).