阅读说明：本技术 一种双层旋翼同向同速转动的飞行器 (Double-deck rotor syntropy is with fast pivoted aircraft ) 是由 王志成 于 2020-11-26 设计创作，主要内容包括：本发明涉及飞行器技术领域,特指一种双层旋翼同向同速转动的飞行器,包括机架,机架内设有动力装置,机架顶部设有飞行装置,飞行装置包括第一飞行单元与第二飞行单元,第一飞行单元包括套筒、转动轴承二以及对称固定于转动轴承二两侧的下层旋翼,转动轴承二固定于套筒,套筒固定于机架,第二飞行单元包括传动杆、转动轴承一以及对称固定于转动轴承一两侧的上层旋翼,转动轴承一固定于传动杆一端,传动杆另一端穿过套筒,并与机架内的动力装置连接,传动杆与套筒之间通过直线轴承连接,动力装置驱动传动杆在套筒内垂直上下往复动作,使上层旋翼与下层旋翼之间产生相对的张合运动,转动轴承二两侧的下层旋翼上分别设有直线轴承一与直线轴承二。(The invention relates to the technical field of aircrafts, in particular to an aircraft with double-layer rotary wings rotating in the same direction and at the same speed, which comprises a rack, wherein a power device is arranged in the rack, the top of the rack 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 rotary bearing II and lower rotary wings symmetrically fixed on two sides of the rotary bearing II, the rotary bearing II is fixed on the sleeve, the sleeve is fixed on the rack, the second flying unit comprises a transmission rod, a rotary bearing I and upper rotary wings symmetrically fixed on two sides of the rotary bearing I, the rotary bearing I is fixed at one end of the transmission rod, the other end of the transmission rod penetrates through the sleeve and is connected with the power device in the rack, the transmission rod is connected with the sleeve through a linear bearing, the power device drives the transmission rod to vertically reciprocate in the sleeve, and a linear bearing I and a linear bearing II are respectively arranged on the lower rotor wings at the two sides of the rotating bearing II.)

1. The utility model provides a double-deck rotor syntropy is with fast pivoted aircraft, includes frame (1), its characterized in that:

the aircraft is characterized in that a power device is arranged in the rack (1), a flying device is arranged at the top of the rack (1), the flying device comprises a first flying unit and a second flying unit, the first flying unit comprises a sleeve (11), two rolling bearings (10) and a lower layer rotor wing (7) which is symmetrically fixed at two sides of the two rolling bearings (10), the two rolling bearings (10) are fixed on the sleeve (11), the sleeve (11) is fixed on the rack (1), the second flying unit comprises a transmission rod (9), a first rolling bearing (8) and an upper layer rotor wing (6) which is symmetrically fixed at two sides of the first rolling bearing (8), the first rolling bearing (8) 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 connected with the power device in the rack (1), and the transmission rod (9) and the sleeve (11) are connected through a linear bearing (24), power device drive transfer line (9) reciprocate about sleeve (11) is perpendicular, makes and produces relative opening and shutting motion between upper rotor (6) and lower floor rotor (7), be equipped with linear bearing (17) and linear bearing two (18) on lower floor rotor (7) of rolling bearing two (10) both sides respectively, be equipped with dead lever (15) and dead lever two (16) on upper rotor (6) of rolling bearing one (8) both sides respectively, what dead lever one (15) can move about from top to bottom wears in linear bearing (17), what dead lever two (16) can move about from top to bottom wears in linear bearing two (18), frame (1) afterbody is equipped with the advancing device who is used for promoting the aircraft and moves ahead.

2. The aircraft of claim 1, wherein the double-layer rotors rotate in the same direction and at the same speed, and the double-layer rotors rotate in the same direction and at the same speed: 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 aircraft of claim 2, wherein the double-layer rotors rotate in the same direction and at the same speed, and the double-layer rotors rotate in the same direction and at the same speed: 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 aircraft of claim 2, wherein the double-layer rotors rotate in the same direction and at the same speed, and the double-layer rotors rotate in the same direction and at the same speed: 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 aircraft of claim 1, wherein the double-layer rotors rotate in the same direction and at the same speed, and the double-layer rotors rotate in the same direction and at the same speed: the power device comprises a driving motor (12), a crank wheel (13) and a connecting rod (14), one end of the connecting rod (14) is hinged to the transmission rod (9), the other end of the connecting rod (14) is fixed on the crank wheel (13), and the driving motor (12) drives the crank wheel (13) to rotate through a transmission structure.

6. The aircraft of claim 1, wherein the double-layer rotors rotate in the same direction and at the same speed, and the double-layer rotors rotate in the same direction and at the same speed: the propelling device comprises a fixing rod (3), a driving motor (4) and an empennage (5), the fixing rod (3) is fixed on the tail of the rack (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.

7. The aircraft of claim 1, wherein the double-layer rotors rotate in the same direction and at the same speed, and the double-layer rotors rotate in the same direction and at the same speed: the snow sled type landing gear is characterized in that a landing gear (2) is arranged at the bottom of the rack (1), and the landing gear (2) comprises a snow sled type landing gear.

Technical Field

The invention relates to the technical field of aircrafts, in particular to an aircraft with double-layer rotors rotating in the same direction and at the same speed.

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 an aircraft with double-layer rotors rotating in the same direction and at the same speed, 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:

an aircraft with double-layer rotors rotating in the same direction and at the same speed comprises a rack, wherein a power device is arranged in the rack, a flying device is arranged at the top of the rack and comprises a first flying unit and a second flying unit, the first flying unit comprises a sleeve, a second rotating bearing and lower 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 rack, the second flying unit comprises a transmission rod, a first rotating bearing and upper 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 sleeve and is connected with the power device in the rack, the transmission rod is connected with the sleeve through a linear bearing, the power device drives the transmission rod to vertically reciprocate up and down in the sleeve, so that relative opening and closing movement is generated between the upper rotors and the lower rotors, the linear bearing I and the linear bearing II are, the upper-layer rotor wings on the two sides of the first rotating bearing are respectively provided with a first fixing rod and a second fixing rod, the first fixing rod can vertically move and penetrate through the first linear bearing, the second fixing rod can vertically move and penetrate through the second linear bearing, and the tail of the rack is provided with a propelling device for propelling the aircraft to move forwards.

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 power device comprises a driving motor, a crank wheel and a connecting rod, one end of the connecting rod is hinged to the transmission rod, the other end of the connecting rod is fixed on the crank wheel, and the driving motor drives the crank wheel to rotate through the transmission structure.

According to the scheme, the propelling device comprises a fixing rod, a driving motor and an empennage, the fixing rod is fixed at the tail of the rack, 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, the undercarriage is arranged at the bottom of the rack and comprises a sled type undercarriage.

The invention has the beneficial effects that:

the invention adopts the structure arrangement, the crank wheel is driven to rotate by the driving motor, the transmission rod is pulled to vertically reciprocate in the sleeve under the driving action 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 rotating bearing and the first rotating bearing are driven to vertically reciprocate, the upper-layer rotor wings can circumferentially rotate around the first rotating bearing, the rotating speed of the upper-layer rotor wings is faster and faster along with the vertical reciprocating action, and when the rotating speed reaches a certain rotating speed, the lifting force can be generated, so that the vertical take-off effect of an aircraft is achieved.

Drawings

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

FIG. 2 is a cross-sectional view of the heeling apparatus 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 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 first transmission rod; 10. rotating a second bearing; 11. a sleeve; 12. a drive motor; 13. a crank wheel; 14. a connecting rod; 15. fixing a rod I; 16. a second fixing rod; 17. a first linear bearing; 18. a second linear bearing; 20. a spoiler airfoil; 21. a fanning airfoil; 22. a leading fin edge; 23. the rear wing tail; 24. the straight through bearing.

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 3, the aircraft with double-layer rotors rotating in the same direction and at the same speed comprises a frame 1, a power device is arranged in the frame 1, a flying device is arranged at the top of the frame 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 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 frame 1, the second flying unit comprises a transmission rod 9, a first rotating bearing 8 and upper rotors 6 symmetrically fixed on two sides of the first rotating bearing 8, the first rotating bearing 8 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 connected with the power device in the frame 1, the transmission rod 9 is connected with the sleeve 11 through a linear bearing 24, the power device drives the transmission rod 9 to vertically reciprocate in the sleeve, make and produce relative opening and shutting motion between upper rotor 6 and the lower floor rotor 7, be equipped with linear bearing one 17 and linear bearing two 18 on the lower floor rotor 7 of rolling bearing two 10 both sides respectively, be equipped with dead lever one 15 and dead lever two 16 on the upper rotor 6 of rolling bearing one 8 both sides respectively, the wearing in linear bearing one 17 of dead lever one 15 activity from top to bottom, the wearing in linear bearing two 18 of dead lever two 16 activity from top to bottom, 1 afterbody in the frame is equipped with the advancing device who is used for promoting the aircraft and moves ahead. The above constitutes the basic structure of the present invention.

The invention adopts the structure arrangement, the transmission rod 9 is driven by the power device to vertically reciprocate in the sleeve 11, so as to drive the rotary bearing I8 and the upper-layer rotor wing 6 at the two sides of the rotary bearing I8 to vertically reciprocate, the upper-layer rotor wing 6 can circumferentially rotate around the rotary bearing I8, the rotating speed of the upper-layer rotor wing is faster and faster along with the vertical reciprocating motion, when reaching a certain rotating speed, the lifting force can be generated, thereby achieving the effect of vertical take-off of the aircraft, meanwhile, because the upper-layer rotor wing 6 can vertically movably penetrate through the linear bearing I17 and the linear bearing II 18 on the lower-layer rotor wing 7 through the fixed rod I15 and the fixed rod II 16, the upper-layer rotor wing 6 can drive the lower-layer rotor wing 7 to rotate in the same direction and at the same speed in the rotating process, the preheating of the aircraft is further improved, and the effect of improving, the structure is simple and compact, and the cost is low.

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 power device includes a driving motor 12, a crank wheel 13 and a connecting rod 14, one end of the connecting rod 14 is hinged to the transmission rod 9, the other end of the connecting rod 14 is fixed on the crank wheel 13, and the driving motor 12 drives the crank wheel 13 to rotate through a transmission structure. By adopting the structure, the crank wheel 13 is driven to rotate by the driving motor 12, the crank wheel 13 drives the connecting rod 14 to move up and down, and the driving rod 9 is pulled to vertically move up and down in the sleeve 11 under the limiting effect of the sleeve 11.

In this embodiment, the propelling device includes a fixing rod 3, a driving motor 4 and an empennage 5, the fixing rod 3 is fixed at the tail of the frame 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 this embodiment, the undercarriage 2 is arranged at the bottom of the frame 1, and the undercarriage 2 comprises a sled 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.