CN214002037U

CN214002037U - Double-layer autorotation rotor wing lift device

Info

Publication number: CN214002037U
Application number: CN202022775409.4U
Authority: CN
Inventors: 王志成
Original assignee: Foshan Shenfeng Aviation Technology Co Ltd
Current assignee: Xinjiang Kailan Aviation Technology Co.,Ltd.
Priority date: 2020-11-26
Filing date: 2020-11-26
Publication date: 2021-08-20
Anticipated expiration: 2030-11-26

Abstract

A double-layer autorotation rotor wing lift device relates to the technical field of aviation, in particular to a rotor wing lift device, which comprises an upper layer rotor wing, a lower layer rotor wing and a guide rod; a plurality of fins are uniformly arranged around the rotary disc; the leading edges of all the upper-layer vanes face to the same direction; the lower layer turntable is arranged on a sliding block through a rotating bearing, the sliding block is arranged on a guide rod, and the sliding block can flexibly slide up and down along the guide rod; the leading edges of all the lower-layer vanes face to the same direction; the mounting angle of the wing panel is between-1 degree and 4 degrees; the upper rotor wing and the lower rotor wing do reciprocating linear motion under the driving of power, so that the wing panel rotates to generate lift force. The invention has simple and reasonable structure, the rotation directions of the upper wing panel and the lower wing panel are opposite, and the invention is arranged on an aircraft, and the aircraft can take off and land vertically and can also hover in the air. The invention discloses a part of flight principle of large birds, mainly generates thrust when wings flap up, so that the birds fly forward, mainly generates lift force when the wings flap down, and also generates part of thrust.

Description

Double-layer autorotation rotor wing lift device

Technical Field

A double-layer autorotation rotor lift device relates to the technical field of aviation, in particular to a rotor lift device.

Background

The lift device of a low-altitude aircraft is an aerodynamic-based device generally divided into a fixed wing, a flapping wing and a rotor wing, and an aircraft, i.e., a fixed-wing aircraft, is powered by a propeller to obtain a large forward speed to generate aerodynamic pressure difference on the upper and lower surfaces of the fixed wing, and the pressure difference enables the aircraft to take off. The speed of the airplane is high, but the take-off and landing of the airplane needs a runway, the airplane cannot hover, and the safety factor is general. The rotor aircraft is provided with a helicopter, and a rotor rotates at a high speed under the direct drive of an engine to generate lift force for taking off, and is characterized in that no runway is needed during taking off and the rotor aircraft can hover in the air; but the structure is complicated, the operation degree of difficulty is big, and the engine directly drives the rotor and can produce torsion and need unnecessary structure and energy to balance, and factor of safety is not high. The rotary-wing aircraft is provided with a rotary-wing aircraft, the rotary-wing aircraft combines two modes of a fixed wing and a rotary wing, the main structure of the rotary-wing aircraft comprises the rotary wing, a wheel type undercarriage and a propeller, the propeller drives the rotary-wing aircraft to slide on a runway, air and a rotor blade interact in the sliding process, the air can push the rotor blade to rotate, the rotor blade rotates at high speed and generates acting force relative to the sliding direction, and when the rotating speed of the rotor blade is high enough, the acting force enables the rotary-wing aircraft to lift off so as to realize flight; but take-off typically requires a runway and cannot hover in the air.

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

Disclosure of Invention

The invention aims to overcome the defects and shortcomings of the prior art and provide a double-layer autorotation rotor wing lift device which is simple in structure, convenient to operate and high in safety performance.

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

a double-layer autorotation rotor wing lift device comprises an upper layer rotor wing, a lower layer rotor wing and a guide rod;

the guide rods are vertically arranged;

the upper-layer rotary wing comprises a plurality of upper-layer fins and an upper-layer rotary disc, the upper-layer rotary disc is arranged at the upper end of the guide rod through a rotating bearing, the upper-layer fins are uniformly arranged around the upper-layer rotary disc, and the spreading direction of the upper-layer fins is arranged along the radial direction of the upper-layer rotary disc; the leading edges of all the upper-layer vanes face to the same direction; the wing profile of the upper layer wing panel is a wing profile with a convex upper surface; the upper layer wing piece and the upper layer turntable can flexibly rotate around the guide rod together, and the rotating surface of the upper layer turntable is in a horizontal position; the included angle between the chord direction of the upper layer wing panel and the rotating plane of the upper layer turntable is defined as the installation angle of the upper layer wing panel, the installation angle is positive when the front edge of the upper layer wing panel is higher than the rear edge of the upper layer wing panel, the installation angle is negative when the front edge of the upper layer wing panel is lower than the rear edge of the upper layer wing panel, and the installation angle is between-1 degree and 4 degrees;

the lower-layer rotor wing comprises a plurality of lower-layer fins, a lower-layer turntable and a sliding block, the lower-layer turntable is mounted on the sliding block through a rotating bearing, the sliding block is mounted on the guide rod, the sliding block can flexibly slide up and down along the guide rod, the lower-layer fins are uniformly mounted around the lower-layer turntable, and the spreading direction of the lower-layer fins is arranged along the radial direction of the lower-layer turntable; the leading edges of all the lower-layer vanes face to the same direction; the wing profile of the lower layer wing panel is a wing profile with a convex upper surface; the lower layer wing pieces can flexibly rotate around the guide rod together with the lower layer turntable, and the rotating surface of the lower layer turntable is in a horizontal position; the included angle between the chord direction of the lower layer wing panel and the rotating plane of the lower layer turntable is defined as the installation angle of the lower layer wing panel, the installation angle is positive when the front edge of the lower layer wing panel is higher than the rear edge of the lower layer wing panel, the installation angle is negative when the front edge of the lower layer wing panel is lower than the rear edge of the lower layer wing panel, and the installation angle is between-1 degrees and 4 degrees;

the upper rotor and the lower rotor are both horizontally arranged;

the leading edge of the upper layer wing panel and the leading edge of the lower layer wing panel face opposite directions;

the front edges of the upper layer fins and the lower layer fins are rounded, and the rear edges of the upper layer fins and the lower layer fins are sharp;

the upper layer wing panel and the lower layer wing panel are rigid; the distance from the maximum thickness position of the airfoil of the upper layer airfoil to the trailing edge is greater than that to the leading edge;

the power drive upper rotor and lower floor's rotor do straight line about the guide arm direction and open and shut the motion, and upper rotor and lower floor's rotor all can rotate under the effect of aerodynamic force, and the pivoted opposite direction of upper rotor and lower floor's rotor.

The stagger angles of all the vanes should satisfy the condition: taking a horizontal plane passing through the trailing edge of the wing panel as a reference plane, wherein the area of the wing panel distributed above the reference plane is larger than the area distributed below the reference plane;

the slider is replaced by a linear bearing.

Preferably, all of the fins are identical in shape and configuration.

Preferably, all of the upper layer flaps are of the same construction. All the lower flaps are of the same construction.

Preferably, the maximum thickness of the airfoil of all the blades is close to the leading edge and far from the trailing edge, and the maximum thickness of the airfoil is between 25% and 35% of the chord length.

Preferably, the double-deck self-rotating rotor lift device of the present invention further comprises: the device comprises a rod sleeve, a swing rod and a driving device;

the driving device is fixedly arranged on the guide rod, the driving device is connected with the lower-layer rotor wing through a crank connecting rod mechanism, and a connecting point is positioned on the sliding block;

the rod sleeve is movably sleeved on the lower section of the guide rod, and the guide rod can flexibly reciprocate to move linearly along the rod sleeve;

the middle point of the swing rod is movably hinged on the rod sleeve, and the swing rod can flexibly swing back and forth around the middle point of the swing rod; one end of the swing rod is hinged with a slide block on the lower rotor wing through a connecting rod; the other end of the swing rod is hinged with the lower end of the guide rod through a connecting rod; the length of the connecting slide block is equal to that of the two connecting rods connected with the lower end of the guide rod;

the driving device drives the lower rotor wing to do vertical reciprocating linear motion through the crank-link mechanism, and the guide rod does vertical reciprocating linear motion along the rod sleeve under the action of the oscillating rod and the connecting rods at the two ends of the oscillating rod, so that the upper rotor wing is driven by the guide rod to do vertical reciprocating linear motion; therefore, the upper rotor wing and the lower rotor wing do symmetrical opening and closing reciprocating linear motion; for the rod sleeve, if the rod sleeve is supposed to be still, if the upper rotor wing moves downwards, the lower rotor wing moves upwards; if the upper rotor goes upward, then the lower rotor goes downward, and the magnitude of the instantaneous speed of upper rotor and lower rotor is equal.

A linear bearing is arranged in the rod sleeve, and the guide rod passes through the linear bearing.

The upper part of the aircraft body is connected with the rod sleeve.

Preferably, a spring is arranged between the upper-layer rotor wing and the lower-layer rotor wing, the upper end of the spring is fixedly connected to the position, close to the upper-layer turntable, of the guide rod, and the lower end of the spring is fixedly connected to the upper end of the sliding block; the driving device is arranged on the guide rod and is connected with the sliding block through a crank connecting rod mechanism; the lower end of the guide rod is arranged above the body of the aircraft; the lower rotor wing can not fall down due to the existence of the spring. When the power driving slide block makes up-and-down reciprocating linear motion, the upper rotor wing also makes reciprocating linear motion;

the driving device with the crank link mechanism is replaced by a linear motor, a stator of the linear motor is arranged on the guide rod, and a screw driver of the linear motor is connected with the sliding block. The upper rotor and the lower rotor are driven by the linear motor to do reciprocating linear motion.

Preferably, the airfoil profile of all the blades adopts an asymmetric airfoil profile, such as a NACA2412 airfoil profile; the setting angle of all the fins is 2 degrees.

Preferably, the wing profiles of all the wings adopt upper-lower flat or upper-lower concave wing profiles, such as AH 79-100C, NACA4415 or FX 63-137 wing profile profiles; the setting angle of all the fins is 0 degree.

Preferably, in order to quickly start the double-layer autorotation rotor lift device, the upper rotor and the lower rotor are respectively provided with a prerotation device, and the structure of the prerotation device is the same as that of a motor starting prerotation device of a traditional autorotation rotor machine.

Preferably, all the wings are provided with angle of attack regulators, and the angle of attack regulators are remotely controlled by using steering engines or are provided with automatic angle of attack regulators. The automatic attack angle regulator has the following structure: the connecting sleeve is arranged at the joint of the root of the wing and the rotary table, one end of the connecting sleeve is fixedly arranged on the rotary table, the angle modulation spring is arranged in the connecting sleeve, a shell of the connecting sleeve is provided with a spiral groove, the root of the wing is of a cylindrical structure with steps, one end of the root of the wing is sleeved in the connecting sleeve, the root of the wing is propped against the root of the wing by the angle modulation spring to enable the wing to be close to the center of the rotary table, a positioning pin is arranged on the root of the wing at the corresponding position of the spiral groove, the elastic wing of the angle modulation spring is overcome to displace outwards along with the acceleration of the rotating speed of the rotor under the action of centrifugal force, and the wing rotates by an angle in the unfolding direction under the limitation of the spiral groove of the connecting sleeve and the positioning pin at the root of the wing, so that the attack angle of the wing is increased; if the rotating speed of the rotor wing is changed from fast to slow, the centrifugal force is reduced, the wing piece is pushed by the spring to move inwards, and the wing piece reversely rotates for an angle around the unfolding direction under the limitation of the spiral groove of the connecting sleeve and the positioning pin at the root part of the wing piece, so that the attack angle of the wing piece is reduced;

the angle of attack of the wings increases with the increase of the rotor speed, which corresponds to a small setting angle at standstill or at low speed of rotation of the rotor, facilitating starting. And when the aircraft freely falls after losing power in air flight, the lift force is increased along with the increase of the attack angle of the rotating speed, so that the falling speed when the aircraft falls on the ground is greatly reduced, and the safety is improved.

The invention has the beneficial effects that: the invention has simple and reasonable structure and double-layer structure, the rotating directions of the upper wing panel and the lower wing panel are opposite, when the aircraft flies forwards, the forward wing panel and the backward wing panel are alternately carried out from left to right, the imbalance of left and right lifting forces is not required to be adjusted by installing a waving device like the traditional autorotation gyroplane, the left and right lifting forces can be kept basically balanced, and the stable flight is convenient. The invention discloses a part of flight principle of large birds, mainly generates thrust when wings flap up, so that the birds fly forward, mainly generates lift force when the wings flap down, and also generates part of thrust. The invention is safe, simple in structure, and can be installed on the aircraft, the aircraft does not need a tail rotor to balance torque, and the aircraft can take off and land vertically and can hover in the air.

Drawings

FIG. 1 is a schematic diagram of the overall structure of the scheme of the invention;

FIG. 2 is a schematic diagram of the automatic angle of attack regulator of the present invention;

FIG. 3 is a schematic illustration of an upstream air flow analysis on a fin in the apparatus of the present invention;

FIG. 4 is a schematic view of the aerodynamic force analysis of the device of the present invention with the airfoil traveling downward;

FIG. 5 is a schematic view of the lift curve of the device of the present invention during normal operation

FIG. 6 is a schematic view of the area distribution of the airfoil profile of an airfoil relative to a reference plane in the inventive apparatus.

In the figure:

1. an upper rotor wing 11, an upper wing 111, a wing root 112, a wing leading edge 113 and a wing trailing edge; 12. an upper layer turntable; 2. the lower rotor wing 21, the lower wing panel 22, the lower turntable 23 and the sliding block; 3. a guide bar; 4. a drive device 41, a crank link mechanism; 5. a rod sleeve; 6. a swing rod 7, a connecting rod 8 and a spring; 9. a body;

101. a connecting sleeve 102, an angle adjusting spring 103, a spiral groove 114 and a positioning pin;

A. b, streamline indication of airflow when the wing panel ascends;

C. the mounting angle of the wing panel, D, the instantaneous attack angle of the wing panel;

E. the area of the wing profile on the upper part of the reference surface F and the area of the wing profile on the lower part of the reference surface G;

u1, the preceding speed of wing, U2, the descending speed of wing, the preceding speed with descending of U3 wing, L, the relative lift of wing, Z, the relative resistance of wing, f, the lift of wing, the lift curve of f1, upper rotor, the lift curve of f2, the lift curve of lower floor's rotor, f3, the lift curve of combining of upper rotor and upper rotor.

Detailed Description

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

A double-layer autorotation rotor wing lift device comprises an upper layer rotor wing 1, a lower layer rotor wing 2 and a guide rod 3;

the guide rod 3 is vertically arranged;

the upper-layer rotor wing 1 comprises a plurality of upper-layer fins 11 and an upper-layer turntable 12, the upper-layer turntable 12 is installed at the upper end of the guide rod 3 through a rotating bearing, the plurality of upper-layer fins 11 are evenly installed around the upper-layer turntable 12, and the spreading direction of the upper-layer fins 11 is arranged along the radial direction of the upper-layer turntable 12; the leading edges of all the upper layer fins 11 face the same direction; the wing profile of the upper layer wing panel 11 is a wing profile with a convex upper surface; the upper layer wing pieces 11 can flexibly rotate around the guide rods 3 together with the upper layer rotary table 12, and the rotating surface of the upper layer rotary table 12 is in a horizontal position; an included angle between the chord direction of the upper-layer wing piece 11 and the rotation plane of the upper-layer turntable 12 is defined as an installation angle of the upper-layer wing piece 11, the installation angle is positive when the front edge of the upper-layer wing piece 11 is higher than the rear edge of the upper-layer wing piece 11, the installation angle is negative when the front edge of the upper-layer wing piece 11 is lower than the rear edge of the upper-layer wing piece 11, and the installation angle is between-1 degrees and 4 degrees;

the lower-layer rotor wing 2 comprises a plurality of lower-layer wing pieces 21, a lower-layer rotating disc 22 and a sliding block 23, the lower-layer rotating disc 22 is installed on the sliding block 23 through a rotating bearing, the sliding block 23 is installed on the guide rod 3, the sliding block 23 can flexibly slide up and down along the guide rod 3, the lower-layer wing pieces 21 are evenly installed on the periphery of the lower-layer rotating disc 22, and the spreading direction of the lower-layer wing pieces 21 is arranged along the radial direction of the lower-layer rotating disc 22; the leading edges 112 of all the lower airfoils 21 face in the same direction; the wing profile of the lower layer wing panel 21 is a wing profile with a convex upper surface; the lower layer wing piece 21 and the lower layer turntable 22 can flexibly rotate around the guide rod 3, and the rotating surface of the lower layer turntable 22 is in a horizontal position; the included angle between the chord direction of the lower layer wing panel 21 and the rotation plane of the lower layer turntable 22 is defined as the installation angle of the lower layer wing panel 21, the installation angle is positive when the front edge of the lower layer wing panel 21 is higher than the rear edge of the lower layer wing panel 21, the installation angle is negative when the front edge of the lower layer wing panel 21 is lower than the rear edge of the lower layer wing panel 21, and the installation angle is between-1 degree and 4 degrees;

the upper rotor wing 1 and the lower rotor wing 2 are both horizontally arranged;

the leading edge of the upper airfoil 11 faces in the opposite direction to the leading edge of the lower airfoil 21;

the front edges of the upper layer fins 11 and the front edges of the lower layer fins 21 are rounded, and the rear edges of the upper layer fins 11 and the rear edges of the lower layer fins 21 are sharp;

both the upper layer fins 11 and the lower layer fins 21 are rigid; the distance from the maximum thickness position of the airfoil of the upper-layer airfoil 11 to the trailing edge is greater than that to the leading edge;

the upper rotor wing 1 and the lower rotor wing 2 are driven by power to do vertical linear opening and closing motion along the direction of the guide rod 3, the upper rotor wing 1 and the lower rotor wing 2 both rotate under the action of aerodynamic force, and the rotating directions of the upper rotor wing 1 and the lower rotor wing 2 are opposite;

all the upper layer fins 11 have the same structure; all the lower fins 21 are identical in structure;

the stagger angle C of all the vanes should satisfy the condition: taking a horizontal plane passing through the trailing edge of the wing panel as a reference plane E, wherein the area of the wing profile of the wing panel distributed above the reference plane E is larger than the area distributed below the reference plane E; the maximum thickness of the airfoil of all the blades is close to the leading edge and far from the trailing edge, and the maximum thickness of the airfoil is between 25% and 35% of the chord length;

the slide 23 is replaced by a linear bearing.

Preferably, all of the fins are identical in shape and configuration.

Preferably, the double-deck self-rotating rotor lift device of the present invention further comprises: a rod sleeve 5, a swing rod 6 and a driving device 4;

the driving device 4 is fixedly arranged on the guide rod 3, the driving device 4 is connected with the lower-layer rotor wing 2 through a crank-link mechanism, and a connecting point is positioned on the sliding block 23;

the rod sleeve 5 is movably sleeved on the lower section of the guide rod 3, and the guide rod 3 can flexibly reciprocate to move linearly along the rod sleeve 5;

the middle point of the swing rod 6 is movably hinged on the rod sleeve 5, and the swing rod 6 can flexibly swing back and forth around the middle point of the swing rod 6; one end of the swing rod 6 is hinged with a slide block 23 on the lower rotor wing 2 through a connecting rod 7; the other end of the swing rod 6 is hinged with the lower end of the guide rod 3 through a connecting rod 7; the length of the connecting slide block 23 is equal to that of the two connecting rods 7 at the lower end of the connecting guide rod 3;

the driving device 4 drives the lower rotor 2 to do up-and-down reciprocating linear motion through a crank-link mechanism, and the guide rod 3 does up-and-down reciprocating linear motion along the rod sleeve 5 under the action of the oscillating rod 6 and the connecting rods 7 at the two ends of the oscillating rod, so that the upper rotor 1 is driven by the guide rod 3 to do up-and-down reciprocating linear motion; thus, the upper rotor wing 1 and the lower rotor wing 2 do symmetrical opening and closing reciprocating linear motion; relative to the rod sleeve 5, if the rod sleeve 5 is still, the lower rotor 2 moves upwards if the upper rotor 1 moves downwards; if the upper rotor wing 1 moves upwards, the lower rotor wing 2 moves downwards, and the instant speeds of the upper rotor wing 1 and the lower rotor wing 2 are equal in magnitude;

a linear bearing is arranged in the rod sleeve 5, and the guide rod 3 passes through the linear bearing;

the rod sleeve 5 is connected above the aircraft fuselage 9.

Preferably, a spring 8 is arranged between the upper-layer rotor wing 1 and the lower-layer rotor wing 2, the upper end of the spring 8 is fixedly connected to the position, close to the upper-layer turntable 12, of the guide rod 3, and the lower end of the spring 8 is fixedly connected to the upper end of the sliding block 23; the driving device 4 is arranged on the guide rod 3 and is connected with the sliding block 23 through a crank connecting rod mechanism 41; the lower end of the guide rod 3 is arranged above the fuselage 9 of the aircraft; the lower rotor 2 can not fall down due to the existence of the spring 8. When the power driving slide block 23 makes up-and-down reciprocating linear motion, the upper rotor wing 1 also makes reciprocating linear motion;

the drive means 4 with the crank linkage 41 is replaced by a linear motor, the stator of which is mounted on the guide bar 3 and the driver of which is connected to the slide 23. The upper rotor wing 1 and the lower rotor wing 2 are driven by the linear motor to do reciprocating linear motion.

Preferably, the airfoil profile of all the blades adopts an asymmetric airfoil profile, such as a NACA2412 airfoil profile; the setting angle C of all the fins is 2 degrees.

Preferably, the wing profiles of all the wings are upper-lower flat or upper-lower concave wing profiles, such as NACA4415 or FX 63-137 wing profiles; the setting angle C of all the fins is 0 degree.

Preferably, in order to quickly start the double-layer autorotation rotor lift device, the upper rotor 1 and the lower rotor 2 are both provided with prerotation devices, and the structures of the prerotation devices are the same as those of the motor starting prerotation devices of the traditional autorotation rotor aircraft.

Preferably, all the wings are provided with angle of attack regulators, and the angle of attack regulators are remotely controlled by using steering engines or are provided with automatic angle of attack regulators. The automatic attack angle regulator has the following structure: a connecting sleeve 101 is arranged at the joint of a wing root 111 and a rotary disc, one end of the connecting sleeve 101 is fixedly arranged on the rotary disc, an angle modulation spring 102 is arranged in the connecting sleeve 101, a spiral groove 103 is formed in a casing of the connecting sleeve 101, the wing root 111 is of a cylindrical structure with steps, one end of the wing root 111 is sleeved in the connecting sleeve 101, the wing root 111 is propped against the wing by the angle modulation spring 102 to enable the wing to be close to the center of the rotary disc, a positioning pin 114 is arranged on the wing root 111 at the corresponding position of the spiral groove 103, the elastic wing of the angle modulation spring 102 is overcome to displace outwards under the action of centrifugal force along with the acceleration of the rotating speed of the rotor wing, and the wing rotates around the span direction by an angle under the limitation of the spiral groove 103 of the connecting sleeve 101 and the positioning pin 114 of the wing root 111, so that the attack angle of the wing is increased; if the rotating speed of the rotor wing is changed from fast to slow, the centrifugal force is reduced, the wing panel is pushed by the spring to displace inwards, and under the limitation of the spiral groove 103 of the connecting sleeve 101 and the positioning pin 114 at the root 111 of the wing panel, the wing panel reversely rotates for an angle around the span-wise direction, so that the attack angle of the wing panel is reduced;

The basic principle of the lift device is as follows: the working principle of the upper rotor wing is the same as that of the lower rotor wing. The upper rotor does up-and-down reciprocating linear motion under the driving of power, when the upper wing moves upwards, the air is extruded into two streams, the small streams flow towards the front edge direction of the wing, and the large streams flow towards the rear edge direction of the wing, so that pressure difference is generated at the front edge and the rear edge of the wing, and the wing can receive forward thrust due to the backward direction of a large amount of air flow according to the Newton's third law. The airfoil rotates in the direction of the leading edge. When the wing panel descends, if the wing panel has an initial speed and the installation angle of the wing panel is not large, the lifting force direction of the wing panel slightly deviates forwards, and a component force is generated in the front direction to enable the wing panel to move towards the front edge direction; with the continuous acceleration of the speed, the effect of rotation will be more and more obvious.

The lift generated by the rotor wing of one layer is similar to the curve of a sine function, the lift generated by the rotor wing at the higher speed of the downward running is larger, the rotating speed is also higher as the speed of the upward running is higher, and the larger lift can be generated when the rotor wing moves downwards next. The two layers of rotors move in an opening and closing way, the lifting forces generated by the two layers of rotors can be complementary, and particularly, when the two layers of rotors move in a completely symmetrical opening and closing way, the resultant force generated by the two layers of rotors can be more stable.

Claims

1. The utility model provides a double-deck rotation rotor lift device which characterized in that: comprises an upper layer rotor (1), a lower layer rotor (2) and a guide rod (3);

the guide rods (3) are vertically arranged;

the upper-layer rotor wing (1) comprises a plurality of upper-layer wing pieces (11) and an upper-layer turntable (12), the upper-layer turntable (12) is installed at the upper end of the guide rod (3) through a rotating bearing, and the plurality of upper-layer wing pieces (11) are evenly installed around the upper-layer turntable (12); the front edges of all the upper-layer vanes (11) face to the same direction; the wing profile of the upper layer wing panel (11) is a wing profile with a convex upper surface; the upper layer wing pieces (11) can flexibly rotate around the guide rod (3) together with the upper layer turntable (12), and the rotating surface of the upper layer turntable (12) is in a horizontal position; the mounting angle of the upper layer wing (11) is between-1 degree and 4 degrees;

the lower-layer rotor wing (2) comprises a plurality of lower-layer wing pieces (21), a lower-layer rotary table (22) and a sliding block (23), the lower-layer rotary table (22) is installed on the sliding block (23) through a rotating bearing, the sliding block (23) is installed on the guide rod (3), the sliding block (23) can flexibly slide up and down along the guide rod (3), and the lower-layer wing pieces (21) are evenly installed on the periphery of the lower-layer rotary table (22); the leading edges (112) of all the lower-layer vanes (21) face to the same direction; the wing profile of the lower layer wing panel (21) is a wing profile with a convex upper surface; the lower layer wing piece (21) and the lower layer turntable (22) can flexibly rotate around the guide rod (3), and the rotating surface of the lower layer turntable (22) is in a horizontal position; the installation angle of the lower layer wing panel (21) is between-1 degree and 4 degrees;

the front edge of the upper layer wing panel (11) and the front edge of the lower layer wing panel (21) face to the opposite direction;

the front edges of the upper layer fins (11) and the lower layer fins (21) are rounded, and the rear edges of the upper layer fins (11) and the lower layer fins (21) are sharp;

the upper layer wing piece (11) and the lower layer wing piece (21) are both rigid; the distance from the maximum thickness position of the airfoil profile of the upper-layer airfoil (11) to the trailing edge is larger than that to the leading edge;

the upper rotor wing (1) and the lower rotor wing (2) are driven by power to do vertical linear opening and closing motion along the direction of the guide rod (3), the upper rotor wing (1) and the lower rotor wing (2) can rotate under the action of aerodynamic force, and the rotating directions of the upper rotor wing (1) and the lower rotor wing (2) are opposite;

the mounting angles (C) of all the vanes should satisfy the condition: and taking the horizontal plane passing through the trailing edge of the wing panel as a reference plane (E), wherein the area of the wing profile of the wing panel distributed above the reference plane (E) is larger than the area distributed below the reference plane (E).

2. The double-deck autogyro lift device of claim 1, wherein: further comprising: a rod sleeve (5), a swing rod (6) and a driving device (4);

the driving device (4) is fixedly arranged on the guide rod (3), the driving device (4) is connected with the lower-layer rotor wing (2) through a crank-link mechanism, and a connection point is positioned on the sliding block (23);

the rod sleeve (5) is movably sleeved on the lower section of the guide rod (3), and the guide rod (3) can flexibly reciprocate to move linearly along the rod sleeve (5);

the middle point of the swing rod (6) is movably hinged on the rod sleeve (5), and the swing rod (6) can flexibly swing back and forth around the middle point of the swing rod (6); one end of the swing rod (6) is hinged with a slide block (23) on the lower rotor wing (2) through a connecting rod (7); the other end of the swing rod (6) is hinged with the lower end of the guide rod (3) through a connecting rod (7); the length of the connecting slide block (23) is equal to that of the two connecting rods (7) at the lower end of the connecting guide rod (3);

the driving device (4) drives the lower rotor (2) to do vertical reciprocating linear motion through a crank-link mechanism, and the guide rod (3) does vertical reciprocating linear motion along the rod sleeve (5) under the action of the swing rod (6) and the connecting rods (7) at the two ends of the swing rod, so that the upper rotor (1) is driven by the guide rod (3) to do vertical reciprocating linear motion; the upper rotor (1) and the lower rotor (2) do symmetrical opening and closing reciprocating linear motion.

3. The double-deck autogyro lift device of claim 2, wherein: all the upper-layer fins (11) have the same structure; all the lower fins (21) have the same structure.

4. The double-deck autogyro lift device of claim 3, wherein: all the fins are identical in shape and structure.

5. The double-deck autogyro lift device of claim 1, wherein: the maximum thickness of the airfoil of all the blades is between 25% and 35% of the chord length.

6. The double-deck autogyro lift device of claim 1, wherein: the slide block (23) is replaced by a linear bearing.

7. The double-deck autogyro lift device of claim 1, wherein: a spring (8) is arranged between the upper-layer rotor wing (1) and the lower-layer rotor wing (2), the upper end of the spring (8) is fixedly connected to the position, close to the upper-layer turntable (12), of the guide rod (3), and the lower end of the spring (8) is fixedly connected to the upper end of the sliding block (23); the driving device (4) is arranged on the guide rod (3) and is connected with the sliding block (23) through a crank connecting rod mechanism (41); the lower end of the guide rod (3) is arranged above a fuselage (9) of the aircraft;

or the driving device (4) with the crank connecting rod mechanism (41) is replaced by a linear motor, the stator of the linear motor is arranged on the guide rod (3), and the screw driver of the linear motor is connected with the sliding block (23).

8. The double-deck autogyro lift device of claim 1, wherein: the upper rotor (1) and the lower rotor (2) are both provided with prerotation devices.

9. A double layer spinning rotor lift system according to any of claims 1 to 8 wherein: all the wings are fitted with angle of attack adjusters.

10. The double-deck autogyro lift device of claim 9, wherein: the attack angle regulator is an automatic attack angle regulator; the automatic attack angle regulator has the following structure: the connecting sleeve (101) is installed at the joint of the wing root (111) and the rotating disc, one end of the connecting sleeve (101) is fixedly installed on the rotating disc, an angle adjusting spring (102) is installed in the connecting sleeve (101), a spiral groove (103) is formed in a casing of the connecting sleeve (101), the wing root (111) is of a cylindrical structure with steps, one end of the wing root (111) is sleeved in the connecting sleeve (101), the wing root (111) is pressed against by the angle adjusting spring (102) to enable the wing to be close to the center of the rotating disc, and a positioning pin (114) is arranged on the wing root (111) at the corresponding position of the spiral groove (103).