CN112455666A

CN112455666A - Four rotor crafts of individual layer

Info

Publication number: CN112455666A
Application number: CN202011346736.6A
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: 2021-03-09

Abstract

The invention relates to the technical field of aircrafts, in particular to a single-layer four-rotor aircraft which comprises a rack, wherein a power device is arranged on the rack, flying devices are respectively arranged at the front end and the rear end of the rack, each flying device comprises a supporting rod, a U-shaped connecting rod and flying units arranged at the two ends of the U-shaped connecting rod, the supporting rods are fixed on the rack, the centers of the U-shaped connecting rods are hinged to the supporting rods, each flying unit comprises a steering engine, a rotating bearing and rotors symmetrically arranged at the two sides of the rotating bearing, the rotating bearing is fixed on the end part of the U-shaped connecting rod through the steering engine, and the power device is connected to. The power device drives the U-shaped connecting rod to move up and down, so that the flying units at the two ends of the U-shaped connecting rod are driven to move up and down, the rotor wing can rotate in the circumferential direction around the rotating bearing, the rotating speed is faster and faster, and when a certain rotating speed is reached, the lifting force can be generated, so that the effect of vertical take-off of the aircraft is achieved.

Description

Four rotor crafts of individual layer

Technical Field

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

Background

The lift device of an aircraft is an aerodynamic device, and can be divided into a fixed wing and a rotor wing according to the structure, the fixed wing aircraft generally has a fuselage and symmetrically arranged fixed wings, and a propeller provides power 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 either a gliding takeoff or landing on a runway and support for airport facility construction. The power system of the rotary wing aircraft, such as a helicopter, is composed of an engine and a rotary wing, wherein the engine drives the rotary wing to rotate to generate a downward acting force, namely a lifting force, and the acting force overcomes the gravity of the earth to enable the aircraft to fly off the ground. 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 rotary wing, and the main structure of the autorotation gyroplane comprises a rotary wing, a wheel type landing frame and a propeller, wherein the propeller drives the autorotation gyroplane to slide on a runway, air and rotary wing blades interact in the sliding process, the air can push the rotary wing blades to rotate, the rotary wing blades rotate and generate acting force in the relative sliding direction, and when the rotating speed of the rotary wing blades is high enough, the acting force enables the aircraft to lift off so as 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 single-layer four-rotor aircraft 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:

the utility model provides a four rotor crafts of individual layer, which comprises a frame, be equipped with power device in the frame, the front end and the rear end of frame are equipped with flight device respectively, flight device includes the bracing piece, the U-shaped connecting rod and the flight unit of locating U-shaped connecting rod both ends, the bracing piece is fixed in the frame, the center of U-shaped connecting rod articulates on the bracing piece, the flight unit includes the steering wheel, the rotor of rotation bearing both sides is located to rolling bearing and symmetry, rolling bearing is fixed in on the tip of U-shaped connecting rod through the steering wheel, power device connects in the U-shaped connecting rod, and can drive the U-shaped.

According to the scheme, the upper side plane of the rotor wing is a turbulent wing surface, and the lower side plane of the rotor wing is a fanning wing surface; the turbulence wing surface is formed by connecting a front curved surface and a rear smooth surface, the front curved surface of the turbulence wing surface is upwards raised relative to the rotating plane of the rotor wing, and the longitudinal projection planes of the turbulence wing surface and the fan-moving wing surface are in an asymmetric structure.

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 power device comprises a motor, a rotating wheel, a transmission belt, a crank rotating wheel, a fixing rod, a first connecting rod and a second connecting rod, the motor is fixed on the rack, the input end of the rotating wheel is connected to the output shaft of the motor through the transmission belt, the output end of the rotating wheel is connected to the crank rotating wheel through the fixing rod respectively, one end of the first connecting rod is fixed on the crank rotating wheel, the other end of the first connecting rod is hinged to the second connecting rod, and the second connecting rod is.

The invention has the beneficial effects that:

the invention adopts the structure, the U-shaped connecting rod is driven to move up and down by the power device, and then the flying units at the two ends of the U-shaped connecting rod are driven to move up and down, so that the rotor wing can rotate in the circumferential direction around the rotating bearing, the rotating speed is faster and faster, when a certain rotating speed is reached, the lifting force can be generated, and the effect of vertical takeoff of the aircraft is achieved.

Drawings

FIG. 1 is an overall top view of the present invention;

FIG. 2 is a structural view of the flying unit of the present invention;

figure 3 is a cross-sectional view of a rotor of the present invention.

In the figure: 1. a frame; 2. a flying device; 3. a motor; 4. a rotating wheel; 5. a transmission belt; 6. a crank runner; 7. fixing the rod; 8. a first connecting rod; 9. a second connecting rod; 10. a support bar; a U-shaped link; 12. a rotor; 13. a rotating bearing; 14. a steering engine; 20. a spoiler airfoil; 21. a fanning airfoil surface; 22. a leading fin edge; 23. the rear wing tail;

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 and 2, the single-layer four-rotor aircraft comprises a frame 1, wherein a power device is arranged on the frame 1, a flying device 2 is respectively arranged at the front end and the rear end of the frame 1, the flying device comprises a support rod 10, a U-shaped connecting rod 11 and flying units arranged at two ends of the U-shaped connecting rod 11, the support rod 10 is fixed on the frame 1, the center of the U-shaped connecting rod 11 is hinged to the support rod 10, the flying units comprise a steering engine 14, a rotating bearing 13 and rotors 12 symmetrically arranged at two sides of the rotating bearing 13, the rotating bearing 13 is fixed on the end part of the U-shaped connecting rod 11 through the steering engine 14, and the power device is connected to the U-shaped connecting rod 11 and can drive the U-shaped connecting rod. The above constitutes the basic structure of the present invention.

By adopting the structure, the U-shaped connecting rod 11 is driven to move up and down by the power device, so that the flying units at two ends of the U-shaped connecting rod 11 are driven to move up and down, the rotor wing 12 can rotate in the circumferential direction around the rotating bearing 13, the rotating speed is faster and faster, and when a certain rotating speed is reached, the lifting force is generated, so that the effect of vertical takeoff of the aircraft is achieved.

In practical application, the steering engine 14 is used for changing the attack angles of the rotary bearing 13 and the rotary wings 12 symmetrically arranged on two sides of the rotary bearing 13, so as to control the flight attitude of the aircraft. The control mode can adopt a remote control mode, and is similar to the control of an unmanned aerial vehicle.

It should be noted that the phase difference between the flying device 2 at the front end and the flying device 2 at the rear end of the frame 1 is 180 degrees, that is, when the flying device 2 at the front end of the frame 1 swings to the left, the flying device 2 at the rear end of the frame 1 swings to the right.

As shown in fig. 3, the upper plane of the rotor 12 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 reciprocate up and down in the sleeve 11, when the rotor wing 12 ascends, the spoiler wing surface 20 interacts with air above, the air generates pressure difference between the front curved surface and the rear smooth surface of the spoiler wing surface 20, and the pressure difference pushes the upper layer rotor wing 6 to move forward, so that the rotor wing 12 rotates unidirectionally by taking the rotating bearing I8 as the center; when the rotor wing 12 descends, the fanning wing surface 21 interacts with the air below, the rotation motion of the rotor wing 12 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 upward acting force to be generated between the fanning wing surface 21 and the air; the rotor 12 converts the up-and-down reciprocating motion of the driving component into the self rotary motion, the rotating speed of the rotor is faster and faster along with the up-and-down reciprocating motion, and when the rotor reaches a certain rotating speed, the rotor generates lift force to enable the flying device to obtain the lift force to achieve the flying purpose.

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. With such a structural arrangement, the leading wing edge 22 is a curved surface so as to respectively continue the leading edges of the spoiler airfoil 20 and the fanning airfoil 21, the leading wing edge 22 can improve the structural strength of the airfoil rotor, and the leading wing edge 22 is located at the front side of the rotation direction of the rotor, and the curved leading wing edge 22 can reduce the air resistance received by the rotor during rotation, thereby improving the power conversion efficiency of the driving device. 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 spoiler airfoil 20 along the X direction is in a curve shape relative to the rotating plane of the rotor 12, 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 wing ascends, the spoiler wing surface 20 interacts with the air above, pressure difference is generated between the front side and the rear side of the span longitude line H of the spoiler wing surface 20 by the air, and the pressure difference pushes the rotor wing 12 to move forwards.

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 wing surface 21 moves downwards, when the rotary speed of the rotor wing is very low, the attack angle C makes the air basically perpendicular to the rotary plane of the rotor wing relative to the acting force of the fanning wing surface 21, then the lower air causes very little resistance to the forward rotary motion of the rotor wing, therefore the rotor wing 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 power device includes a motor 3, a rotating wheel 4, a transmission belt 5, a crank rotating wheel 6, a fixing rod 7, a first connecting rod 8 and a second connecting rod 9, the motor 3 is fixed on the frame 1, an input end of the rotating wheel 4 is connected to an output shaft of the motor 3 through the transmission belt 5, an output end of the rotating wheel 4 is connected to the crank rotating wheel 6 through the fixing rod 7, one end of the first connecting rod 8 is fixed on the crank rotating wheel 6, the other end of the first connecting rod 8 is hinged to the second connecting rod 9, and the second connecting rod 9 is fixed on the U. By adopting the structure, the motor 3 drives the rotating wheel 4 to rotate, the rotating wheel 4 drives the crank rotating wheel 6 to rotate through the fixed rod 7, and the crank rotating wheel 6 drives the U-shaped connecting rod 11 to swing up and down through the connecting rod I8 and the connecting rod II 9.

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

Claims

1. A four-rotor aircraft monolayer, comprising a frame (1), characterized in that: the aircraft is characterized in that a power device is arranged on the rack (1), the front end and the rear end of the rack (1) are respectively provided with a flying device (2), the flying device comprises a support rod (10), a U-shaped connecting rod (11) and flying units arranged at two ends of the U-shaped connecting rod (11), the support rod (10) is fixed on the rack (1), the center of the U-shaped connecting rod (11) is hinged to the support rod (10), the flying units comprise steering engines (14), rotating bearings (13) and rotors (12) symmetrically arranged on two sides of the rotating bearings (13), the rotating bearings (13) are fixed on the end parts of the U-shaped connecting rod (11) through the steering engines (14), and the power device is connected to the U-shaped connecting rod (11) and can drive the U-shaped connecting rod (11) to move up and.

2. A single-tier, four-rotor aircraft according to claim 1, wherein: the upper side plane of the rotor wing (12) is a spoiler wing surface (20), and the lower side plane 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. A single-tier, quad-rotor aircraft 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. A single-tier, quad-rotor aircraft 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. A single-tier, four-rotor aircraft according to claim 1, wherein: the power device comprises a motor (3), a rotating wheel (4), a transmission belt (5), a crank rotating wheel (6), a fixing rod (7), a first connecting rod (8) and a second connecting rod (9), wherein the motor (3) is fixed on the rack (1), the input end of the rotating wheel (4) is connected to the output shaft of the motor (3) through the transmission belt (5), the output end of the rotating wheel (4) is connected to the crank rotating wheel (6) through the fixing rod (7), one end of the first connecting rod (8) is fixed on the crank rotating wheel (6), the other end of the first connecting rod (8) is hinged to the second connecting rod (9), and the second connecting rod (9) is fixed on a U-shaped connecting rod (11).