CN112319787A

CN112319787A - Man-electricity hybrid double-layer rotorcraft

Info

Publication number: CN112319787A
Application number: CN202011341946.6A
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 aircrafts, in particular to a human-electricity hybrid double-layer gyroplane, which comprises a cabin, wherein a human-electricity hybrid power device is arranged in the cabin, the human-electricity hybrid power device comprises a human power driving unit, an electric power driving unit, a crank wheel and a connecting rod, the connecting rod is fixed on the crank wheel, the human power driving unit and the electric power driving unit are respectively connected to the crank wheel through a transmission structure, the top of the cabin is provided with a flying device, the flying device comprises a first flying unit and a second flying unit, the first flying unit comprises a sleeve, a rotating bearing II and lower-layer gyroplanes symmetrically fixed on two sides of the rotating bearing II, the rotating bearing II is fixed on the sleeve, the sleeve is fixed on the cabin, the second flying unit comprises a transmission rod, a rotating bearing I and upper-layer gyroplanes symmetrically fixed on two sides of the rotating, and is hinged with a connecting rod of the human-electricity hybrid power device, and the transmission rod is connected with the sleeve through a linear bearing.

Description

Man-electricity hybrid double-layer rotorcraft

Technical Field

The invention relates to the technical field of aircrafts, in particular to a human-electric hybrid double-layer rotorcraft.

Background

The lift device of an aircraft is an aerodynamic-based device, 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

Aiming at the problems, the invention provides a human-electric hybrid double-layer gyroplane, which effectively solves the defects in the prior art.

In order to achieve the purpose, the technical scheme applied by the invention is as follows:

a man-electricity hybrid double-layer rotorcraft comprises a cabin, a man-electricity hybrid power device is arranged in the cabin, the man-electricity hybrid power device comprises a man-electricity driving unit, an electric driving unit, a crank wheel and a connecting rod, the connecting rod is fixed on the crank wheel, the man-electricity driving unit and the electric driving unit are respectively connected to the crank wheel through a transmission structure, a flying device is arranged at the top of the cabin and comprises a first flying unit and a second flying unit, the first flying unit comprises a sleeve, a second rotating bearing and lower-layer rotors symmetrically fixed on two sides of the second rotating bearing, the second rotating bearing is fixed on the sleeve, the sleeve is fixed on the cabin, the second flying unit comprises a transmission rod, a first rotating bearing and upper-layer rotors symmetrically fixed on two sides of the first rotating bearing, the first rotating bearing is fixed at one end of the transmission rod, the other end of the transmission rod penetrates through the, the transmission rod is connected with the sleeve through a linear bearing, the human-electric hybrid power device drives the transmission rod to vertically reciprocate in the sleeve, relative opening and closing motion is generated between the upper rotor and the lower rotor, the tail of the engine room is provided with a double-propelling device used for pushing the gyroplane to move forward and controlling the direction of the gyroplane, the double-propelling device comprises a first thrust unit and a second thrust unit, and the first thrust unit and the second thrust unit are parallelly fixed on the tail of the engine room side by side.

According to the scheme, the lower-layer rotor wing and the upper-layer rotor wing have the same structure, the upper side plane of the lower-layer rotor wing is a turbulent wing surface, and the lower side plane of the lower-layer rotor 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 rotor, and the spoiler airfoil and the fanning 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; the span meridian H where the maximum arch height point of the front curved surface of the spoiler airfoil is located is close to the front wing edge.

According to the scheme, an attack angle C exists between the fanning wing surface and the rotating plane of the rotor wing, and the value range of C is-2-6 degrees.

According to the scheme, the first thrust unit and the second thrust unit are identical in structure and respectively comprise a fixing rod, a driving motor and an empennage, the fixing rod is fixed at the tail of the cabin, the driving motor and the empennage are fixed on the fixing rod, and the driving motor drives the empennage to rotate.

According to the scheme, a seat and an operating rod are arranged in the engine room, and the operating rod is connected to the second rotating bearing through a lever assembly.

According to the scheme, the lever assembly comprises a first lever and a second lever, the operating rod is connected to the first lever, the first lever is connected to the second lever, and the second lever is connected to the second rotating bearing.

According to the scheme, the undercarriage is arranged at the bottom of the cabin and comprises a roller type undercarriage.

The invention has the beneficial effects that:

the structure is adopted, the crank wheel is driven to rotate by the manual driving unit and the electric driving unit, the transmission rod is pulled to vertically reciprocate in the sleeve under the driving of the crank wheel and the limiting action of the sleeve, so that the upper-layer rotor wings on the two sides of the first rotary bearing and the first rotary bearing are driven to vertically reciprocate, the upper-layer rotor wings can circumferentially rotate around the first rotary bearing, the rotating speed of the upper-layer rotor wings is faster and faster along with the vertical motion, when a certain rotating speed is reached, the lifting force can be generated, the vertical take-off effect of the gyroplane is achieved, the gyroplane can be pushed to move forwards and the flying direction of the gyroplane can be controlled by the double propelling devices, and the structure is simple and compact, and the cost is low.

Drawings

FIG. 1 is an overall block diagram of the present invention;

FIG. 2 is a top view of the dual propulsion apparatus of the present invention;

FIG. 3 is a schematic view of the flight device of the present invention in an operational state;

FIG. 4 is a cross-sectional view of the heeling apparatus of the present invention;

figure 5 is a cross-sectional view of a rotor of the present invention.

In the figure: 1. a nacelle; 2. a landing gear; 3. fixing the rod; 4. a drive motor; 5. a tail wing; 6. an upper rotor; 7. a lower rotor; 8. rotating the first bearing; 9. a transmission rod; 10. rotating a second bearing; 11. a sleeve; 12. a human powered drive unit; 13. an electric drive unit; 14. a first connecting rod; 15. a second connecting rod; 16. a seat; 17. a first thrust unit; 18. a crank wheel; 19. a second thrust unit; 20. a spoiler airfoil; 21. a fanning airfoil; 22. a leading fin edge; 23. the rear wing tail; 24. a straight-through bearing; 25. a connecting rod; 30. a joystick; 31. a first lever; 32. a second lever;

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 to 5, the invention relates to a human-electric hybrid double-layer rotorcraft, which comprises a cabin 1, wherein a human-electric hybrid power device is arranged in the cabin 1, the human-electric hybrid power device comprises a human power driving unit 12, an electric power driving unit 13, a crank wheel 18 and a connecting rod 25, the connecting rod 25 is fixed on the crank wheel 18, the human power driving unit 12 and the electric power driving unit 13 are respectively connected to the crank wheel 18 through a transmission structure, a flying device is arranged at the top of the cabin 1, the flying device comprises a first flying unit and a second flying unit, the first flying unit comprises a sleeve 11, a second rotating bearing 10 and lower-layer rotors 7 symmetrically fixed on two sides of the second rotating bearing 10, the second rotating bearing 10 is fixed on the sleeve 11, the sleeve 11 is fixed on the cabin 1, the second flying unit comprises a transmission rod 9, a first rotating bearing 8 and upper-layer rotors 6 symmetrically fixed on two sides, the rotating bearing I8 is fixed at one end of the transmission rod 9, the other end of the transmission rod 9 penetrates through the sleeve 11 and is hinged to a connecting rod 25 of the human-electric hybrid power device, the transmission rod 9 is connected with the sleeve 11 through a linear bearing 24, the human-electric hybrid power device drives the transmission rod 9 to vertically reciprocate in the sleeve 11, so that relative opening and closing movement is generated between the upper rotor wing 6 and the lower rotor wing 7, a double-propelling device used for pushing the gyroplane to move forwards and controlling the direction of the gyroplane is arranged at the tail of the cabin 1 and comprises a first thrust unit 17 and a second thrust unit 19, and the first thrust unit 17 and the second thrust unit 19 are parallelly fixed on the tail of the cabin 1 side by side. The above constitutes the basic structure of the present invention.

According to the structure, the crank wheel 18 is driven to rotate by the manual driving unit 12 and the electric driving unit 13, the transmission rod 9 is pulled to vertically reciprocate in the sleeve 11 under the driving of the crank wheel 18 and the limiting effect of the sleeve 11, so that the rotary bearing I8 and the upper rotary wings 6 on two sides of the rotary bearing I8 are driven to vertically reciprocate, the upper rotary wings 6 can circumferentially rotate around the rotary bearing I8, the rotating speed of the upper rotary wings is faster and faster along with the vertical motion, when a certain rotating speed is reached, the lifting force can be generated, the vertical take-off effect of the gyroplane is achieved, the gyroplane can be pushed to move forwards through the double propelling devices, the flying direction of the gyroplane can be controlled, and the structure is simple and compact, and the cost is low.

In practical application, when the first thrust unit 17 and the second thrust unit 19 are at the same power, the rotorcraft is smoothly pushed to fly forward, when the power of the first thrust unit 17 is greater than that of the second thrust unit 19, the rotorcraft can fly toward the second thrust unit 19, and when the power of the first thrust unit 17 is less than that of the second thrust unit 19, the rotorcraft can fly toward the first thrust unit 17.

In practical application, the human-electricity hybrid power device is adopted, so that energy consumption is effectively saved, and a large amount of cost is saved.

In this embodiment, the lower rotor 7 and the upper rotor 6 have the same structure, and the upper plane is a spoiler wing 20 and the lower plane is a fanning wing 21; the spoiler airfoil 20 is formed by connecting a front curved surface and a rear smooth surface, the front curved surface of the spoiler airfoil 20 protrudes upwards relative to the rotating plane of the rotor, and the spoiler airfoil 20 and the fanning airfoil 21 are in an asymmetric structure in the longitudinal projection plane. By adopting the structure, the driving component drives the transmission rod 9 to vertically reciprocate in the sleeve 11, when the upper-layer rotor wing 6 ascends, the turbulent wing surface 20 of the upper-layer rotor wing interacts with air above, the air generates pressure difference between the front curved surface and the rear smooth surface of the turbulent wing surface 20, and the pressure difference pushes the upper-layer rotor wing 6 to move forwards, so that the upper-layer rotor wing 6 rotates unidirectionally by taking the rotating bearing I8 as the center; when the upper rotor wing 6 descends, the fanning wing surface 21 interacts with the air below, the rotating motion of the upper rotor wing 6 is combined with the descending motion to enable the fanning wing surface 21 to form a vector attack angle C, and the vector attack angle C enables the fanning wing surface 21 and the air to generate vertical upward acting force; the upper rotor 6 turns into drive assembly's up-and-down reciprocating motion self rotary motion, and its rotation rate can be along with reciprocating motion from top to bottom is more and more fast, when reacing certain rotational speed, produces lift and makes the flying device obtain lift and realize the flight purpose, because produce relative opening and shutting motion between upper rotor 6 and the lower floor rotor 7, and then drive lower floor rotor 7 with two 10 center unidirectional rotations of rolling bearing, and then can improve the lift effect.

In the present embodiment, the front side edges of the spoiler airfoil 20 and the fanning airfoil 21 are closed to form a front wing edge 22, and the rear side edges of the spoiler airfoil 20 and the fanning airfoil 21 are closed to form a rear wing tail 23; the spanwise meridian H at which the maximum camber point of the leading airfoil surface 20 is located is proximate the leading fin edge 22. By adopting the structure, the front wing edge 22 is a curved surface so as to respectively continue the front side edges of the spoiler airfoil 20 and the fanning airfoil 21, the structural strength of the airfoil rotor wing can be improved due to the front wing edge 22, the front wing edge 22 is positioned on the front side of the rotation direction of the rotor wing, and the curved front wing edge 22 can reduce the air resistance borne by the rotor wing during rotation and improve the power conversion efficiency of the driving device. As shown in fig. 4, 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 spoiler airfoil 20 along the X direction is in a curve shape relative to the rotating plane of the rotor wing, 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 spoiler airfoil 20 and is close to the front wing edge 22, so that the spoiler airfoil 20 is in a front-back asymmetric structure. When the rotor wings ascend, the spoiler wing surfaces 20 interact with air above, pressure difference is generated between the front side and the rear side of the wingspan longitude line H of the spoiler wing surfaces 20 by the air, the rotor wings are pushed to move forwards by the pressure difference, and the two rotor wings act in the same direction and rotate unidirectionally by taking the rotating bearing as the center.

In the present embodiment, an attack angle C exists between the flapping wing surface 21 and the rotation plane of the rotor, and the value range of C is-2 ° to 6 °. The rotor has an angle of attack C on the rotary bearing, calculated as the fan blade 21 with respect to the plane of rotation of the rotor. After the rotor wing is started, the spoiler wing surfaces 20 move up and down in a reciprocating mode, air flows through the spoiler wing surfaces 20 to generate pressure difference on the front side and the rear side of the wingspan meridian H, the pressure difference forms forward driving force on the rotor wing to enable the rotor wing to rotate, at the moment, the front wing edge 22 generates differential speed relative to the air to form resistance on the rotor wing, and the driving force overcomes the resistance to drive the rotor wing to rotate; the said fanning wings 21 move downwards, when the rotary speed of the rotor is very low, the angle of attack C makes the air basically perpendicular to the rotary plane of the rotor relative to the acting force of the fanning wings 21, the lower layer air causes very little resistance to the forward rotary motion of the rotor, therefore the rotor can obtain higher rotary speed after reciprocating up and down for a period of time. When the rotating speed of the rotor wing is high, the fanning wing surface 21 moves downwards and forwards, the vector angle of vector motion formed by the superposition of the two relative to the rotating plane of the rotor wing is larger than the attack angle C, namely the lift force generated by the fanning wing surface 21 is larger as the rotating speed of the rotor wing is faster, and the rotating speed of the rotor wing can be improved by controlling the up-and-down movement frequency of the rotor wing, so that the lift force generated by the rotor wing is changed.

In this embodiment, the first thrust unit 17 and the second thrust unit 19 are identical in structure and each include a fixing rod 3, a driving motor 4 and an empennage 5, the fixing rod 3 is fixed at the tail of the nacelle 1, the driving motor 4 and the empennage 5 are fixed on the fixing rod 3, and the driving motor 4 drives the empennage 5 to rotate. With the adoption of the structure, the driving motor 4 drives the tail wing 5 to rotate, so that thrust can be provided for the aircraft, and the aircraft can fly forwards.

In the embodiment, a seat 16 and an operating lever 30 are arranged in the nacelle 1, and the operating lever 30 is connected to the second pivot bearing 10 through a connecting rod assembly. By adopting the structure, the operating rod 17 can be used for finely adjusting the second rotating bearing 10, so that the flying attitude of the aircraft can be controlled.

In practical application, driving motor 4 drive fin 5 is rotatory, when making the aircraft fly forward, can lead to the aircraft's flying device to produce back chamfer, can take place unstable state, is equivalent to gyroplane function, and at this moment, accessible control rod 17 plays the fine setting effect to swivel bearing two 10, and then realizes adjusting the back chamfer of flying device.

In this embodiment, the connecting rod assembly includes a first connecting rod 31 and a second connecting rod 32, the operating rod 30 is connected to the first connecting rod 31, the first connecting rod 31 is connected to the second connecting rod 32, and the second connecting rod 32 is connected to the second pivot bearing 10. Compared with the tilting disk in the prior art, the tilting disk with the structure is simple and compact in structure and low in cost.

In the present embodiment, the bottom of the nacelle 1 is provided with an undercarriage 2, and the undercarriage 2 comprises a roller type undercarriage. By adopting the structure, the supporting and buffering effects during lifting and descending are achieved.

While the embodiments of the present invention have been described, the present invention is not limited to the above-mentioned embodiments, which are only illustrative and not restrictive, and those skilled in the art can make various modifications without departing from the spirit and scope of the present invention as defined by the appended claims.

Claims

1. The utility model provides a double-deck gyroplane of people's electricity thoughtlessly moving, includes cabin (1), its characterized in that:

be equipped with people's electricity hybrid power device in cabin (1), people's electricity hybrid power device includes manpower drive unit (12), electric drive unit (13), crank wheel (18) and connecting rod (25), connecting rod (25) are fixed in on crank wheel (18), manpower drive unit (12) and electric drive unit (13) are connected in crank wheel (18) through transmission structure respectively, cabin (1) top is equipped with flight device, flight device includes first flight unit and second flight unit, first flight unit includes sleeve (11), rolling bearing two (10) and symmetry and is fixed in lower floor rotor (7) of rolling bearing two (10) both sides, rolling bearing two (10) are fixed in sleeve (11), sleeve (11) are fixed in cabin (1), second flight unit includes transfer line (9), A rotating bearing I (8) and upper-layer rotor wings (6) symmetrically fixed at two sides of the rotating bearing I (8), the rotating bearing I (8) is fixed at the upper end of the transmission rod (9), the lower end of the transmission rod (9) penetrates through the sleeve (11), and is hinged with a connecting rod (25) of the human-electric hybrid power device, the transmission rod (9) is connected with the sleeve (11) through a linear bearing (24), the human-electricity hybrid power device drives the transmission rod (9) to vertically reciprocate in the sleeve (11) to generate relative opening and closing motion between the upper rotor wing (6) and the lower rotor wing (7), the tail part of the cabin (1) is provided with a double-propelling device for propelling the gyroplane to move forwards and controlling the direction of the gyroplane, the double propulsion device comprises a first thrust unit (17) and a second thrust unit (19), the first thrust unit (17) and the second thrust unit (19) are fixed on the tail of the engine room (1) in parallel and side by side.

2. The manned-electric hybrid double-deck rotorcraft according to claim 1, wherein: the lower-layer rotor wing (7) and the upper-layer rotor wing (6) are identical in structure, the upper side plane of the lower-layer rotor wing is a spoiler wing surface (20), and the lower side plane of the lower-layer rotor wing is a fanning wing surface (21); the vortex wing surface (20) is connected by anterior curved surface and rear portion smooth surface and constitutes, and the anterior curved surface of vortex wing surface (20) is upwards protruding for the rotation plane of rotor, vortex wing surface (20) and fan move wing surface (21) and be asymmetric structure at fore-and-aft projection plane.

3. The manned-electric hybrid double-deck rotorcraft according to claim 2, wherein: the front side edges of the spoiler airfoil (20) and the fanning airfoil (21) are mutually closed to form a front wing edge (22), and the rear side edges of the spoiler airfoil (20) and the fanning airfoil (21) are mutually closed to form a rear wing tail (23); the span meridian H where the maximum arch height point of the front curved surface of the spoiler airfoil (20) is located is close to the front wing edge (22).

4. The manned-electric hybrid double-deck rotorcraft according to claim 2, wherein: an attack angle C exists between the fanning wing surface (21) and a rotating plane of the rotor wing, and the value range of C is-2-6 degrees.

5. The manned-electric hybrid double-deck rotorcraft according to claim 1, wherein: first thrust unit (17) and second thrust unit (19) structure is the same, all includes dead lever (3), driving motor (4) and fin (5), dead lever (3) are fixed in cabin (1) afterbody, driving motor (4) are fixed in on dead lever (3) with fin (5), driving motor (4) drive fin (5) are rotatory.

6. The manned-electric hybrid double-deck rotorcraft according to claim 1, wherein: a seat (16) and an operating rod (30) are arranged in the engine room (1), and the operating rod (30) is connected to the second rotating bearing (10) through a lever assembly.

7. The manned-electric hybrid double-deck rotorcraft according to claim 6, wherein: the lever assembly comprises a first lever (31) and a second lever (32), the operating rod (30) is connected to the first lever (31), the first lever (31) is connected to the second lever (32), and the second lever (32) is connected to the second rotating bearing (10).

8. The manned-electric hybrid double-deck rotorcraft according to claim 1, wherein: the aircraft is characterized in that an undercarriage (2) is arranged at the bottom of the cabin (1), and the undercarriage (2) comprises a roller type undercarriage.