WO2022110271A1

WO2022110271A1 - Double-wing flying device

Info

Publication number: WO2022110271A1
Application number: PCT/CN2020/133750
Authority: WO
Inventors: 王志成
Original assignee: 广东国士健科技发展有限公司
Priority date: 2020-11-26
Filing date: 2020-12-04
Publication date: 2022-06-02
Also published as: CN112455650A

Abstract

The present invention relates to the technical field of aircrafts, and specifically refers to a double-wing flying device, which comprises translational wings, a driving device and a carrier. A support is provided on the carrier; the two translational wings which can rotate on the support are provided on the support, and the two translational wings are arranged in pairs at an interval one above the other; and the driving device is fixedly provided on the carrier, and the driving device is transmissionally connected to the two translational wings respectively, thereby enabling the two translational wings to reciprocate up and down along the support respectively. The structure of the present invention is reasonable. The driving device drives the two translational wings on the support to reciprocate up and down, and when the translational wings ascend, the air generates a pressure difference between front side curved surfaces and rear part smooth surfaces of the spoiler airflow to thereby promote the translational wings to rotate in one direction; and when the translational wings descend, a vertical upward acting force is generated between the flapping airfoil and the air. The translational wings convert the up-and-down reciprocating motion of the driving device into rotating motion of the translational wings, and then a lift force is generated by means of the rotating motion to enable the carrier to obtain the lift force, so as to achieve the objective of flying.

Description

A biplane flying device

technical field

The invention relates to the technical field of aircraft, in particular to a biplane flying device.

Background technique

The lift device of an aircraft is a mechanism based on aerodynamics. According to the structure, it can be divided into fixed wings and rotors. Fixed-wing aircraft generally have a fuselage and symmetrically arranged fixed wings, which are powered by propellers to obtain greater flight speed. and mobility. The flight principle is that there is a relative speed between the fixed wing and the air, and the interaction between the air and the surfaces of the fixed wing generates lift so that the aircraft can gain flight ability. The disadvantage of fixed-wing aircraft is that it cannot hover in the air, and it needs to take off or land on the runway and support the construction of airport facilities. Rotorcraft, such as helicopters, are characterized in that they do not need a runway when taking off, and can hover in the air. The power system includes an engine and a rotor. The engine drives the rotor to rotate to generate a downward force, which is the lift force to overcome the earth's gravity to make the aircraft fly off the ground. . Its drawbacks are low cruising speed, low carrying capacity, low efficiency, but little reliance on ground facilities.

The autogyro is a combination of fixed-wing and rotary-wing aircraft. Its main structure includes a rotor, a wheeled landing gear and a propeller. The propeller drives the autogyro to glide on the runway. During the gliding process, the air and the rotor blades interact with each other. The air can push the rotor blades to rotate, and the rotation of the rotor blades produces a force relative to the sliding direction. When the rotation speed of the rotor blades is high enough, the force makes the aircraft lift off to achieve flight. The advantage is that it has lower requirements on the take-off runway but still requires a taxiing distance, and cannot hover in the air with limited application range.

Therefore, the existing technology still needs to be improved and developed.

technical solutions

The purpose of the present invention is to provide a biplane flying device with reasonable structure, multi-layer layout, good safety, and helicopter hovering, aiming at the defects and deficiencies of the prior art.

In order to achieve the above object, the present invention adopts the following technical solutions:

The dual-wing flying device of the present invention includes a translation wing, a driving device and a carrier, the carrier is provided with a bracket, and the bracket is provided with two translation wings that can be rotated on it, the two translation wings The upper and lower intervals are arranged in pairs; the driving device is fixedly arranged on the carrier, and the driving device drives and connects the two translation wings respectively, so that the two translation wings reciprocate up and down along the bracket respectively.

According to the above solution, the drive device includes a first drive shaft and a second drive shaft, and the first drive shaft and the second drive shaft are respectively mounted on the bracket through sliding bearings; the rotation center of the translation wing is provided with a rotation bearing One of the translation wings is mounted on the upper end of the first drive shaft through a rotary bearing, the rotary bearing on the other translation wing is mounted on the first drive shaft through a sliding bearing, and the upper end of the second drive shaft is fixedly connected to the sliding bearing.

According to the above solution, the driving device further includes a first sliding sleeve and a second sliding sleeve, the first sliding sleeve is sleeved on the bracket with a sliding bearing therebetween, and the second sliding sleeve is sleeved on the first sliding sleeve. A sliding bearing is arranged on the sliding sleeve and between the two; the rotating bearing of one of the translation wings is fixedly connected with the upper end of the first sliding sleeve, and the first drive shaft is fixedly connected with the lower end of the first sliding sleeve; the The rotary bearing of the other translation wing is fixedly connected with the upper end of the second sliding sleeve, and the second drive shaft is fixedly connected with the lower end of the second sliding sleeve.

According to the above solution, the driving device is provided with two output shafts, and the two output shafts are respectively rotatably connected to the first drive shaft and the second drive shaft.

According to the above solution, the translation wing includes two wing fins and a rotating bearing, the two wing fins are arranged oppositely on both sides of the rotating bearing, and the wing roots of the two wing fins are respectively fixedly connected to the rotating bearing; The upper plane of the fin is a spoiler airfoil, and the lower plane of the wing is a flapping airfoil; the spoiler airfoil is formed by connecting the front curved surface and the rear smooth surface, and the front curved surface of the spoiler airfoil is opposite to the The rotation plane of the translation wing protrudes upward, and the longitudinal projection planes of the spoiler airfoil and the fan airfoil are asymmetrical structures.

According to the above scheme, the front side edges of the spoiler airfoil and the fan airfoil are mutually closed to form a front wing edge, and the spoiler airfoil and the rear side edges of the fan airfoil are mutually closed to form a rear wing tail; The spanwise meridian H, where the point of maximum camber of the curved surface is located, is close to the fore wing edge.

beneficial effect

The beneficial effects of the invention are as follows: the structure of the invention is reasonable, the two translation wings on the driving device drive the bracket to reciprocate up and down, and the air creates a pressure difference between the front curved surface and the rear smooth surface of the spoiler when the translation wings rise. Thereby, the translation wing rotates in one direction; the translation wing generates a vertical upward force between the fan surface and the air when it descends; the translation wing converts the up and down reciprocating motion of the drive device into its own rotational motion, and then rotates The movement generates lift so that the carrier obtains lift to achieve the purpose of flight.

Description of drawings

Fig. 1 is the structural representation of embodiment 1 of the present invention;

2 is a schematic structural diagram of Embodiment 2 of the present invention;

3 is a schematic diagram of the installation structure of the translation wing according to Embodiment 1 of the present invention;

FIG. 4 is a schematic view of the cross-sectional structure of the translation wing of the present invention.

In the picture:

1. Translating wing; 2. Driving device; 3. Carrier; 10. Wing; 11. Spoiler surface; 12. Fanning wing surface; 13. Front wing edge; 14. Rear wing tail; 15. Swivel bearing; 21 22, the second drive shaft; 23, the sliding bearing; 24, the first sliding sleeve; 25, the second sliding sleeve; 26, the output shaft; 31, the bracket.

BEST MODE FOR CARRYING OUT THE INVENTION

The technical solutions of the present invention will be described below with reference to the accompanying drawings and embodiments.

Example 1

As shown in Figures 1, 3, and 4, a biplane flying device according to the present invention includes a translation wing 1, a driving device 2 and a carrier 3. The carrier 3 is provided with a bracket 31, and the bracket 31 is provided with two There are two translation wings 1 that can be rotated on it, and the two translation wings 1 are arranged in pairs at an upper and lower interval; the driving device 2 is fixedly arranged on the carrier 3, and the driving device 2 drives and connects the two translation wings 1 respectively, so that the The two translation wings 1 reciprocate up and down along the bracket 31 respectively. The carrier 3 is the main body of the flying device for carrying people and objects. The driving device 2 drives the two translation wings 1 to reciprocate up and down. 1 rotates to generate lift to achieve the purpose of carrier 3 flying.

The translation wing 1 includes two wings 10 and a rotary bearing 15, the two wings 10 are arranged on both sides of the rotary bearing 15 oppositely, and the wing roots of the two wings 10 are respectively fixedly connected to the rotary bearing 15; The upper plane of the wing 10 is a spoiler airfoil 11 , and the lower plane of the wing 10 is a fan wing surface 12 ; the spoiler airfoil 11 is formed by connecting a front curved surface and a rear smooth surface. The front curved surface of the airfoil 11 protrudes upward relative to the rotation plane of the translation wing 1 , and the spoiler airfoil 11 and the fan airfoil 12 have an asymmetric structure in the longitudinal projection plane. The drive mechanism 2 drives the translation wing 1 to reciprocate up and down. When the translation wing 1 rises, the turbulent airfoil 11 of the wing 10 interacts with the air above, and the air interacts with the front curved surface of the turbulent airfoil 11 and the air above. A pressure difference is generated between the rear smooth surfaces, and the pressure difference pushes the wings 10 to move forward, and the two wings 10 act in the same direction so that the translation wing 1 rotates in one direction with the rotating bearing 15 as the center; the translation When the wing 1 is descending, the flapping airfoil 12 of the wing 10 interacts with the air below, and the rotational motion of the translational wing 1 combined with the downward motion causes the flapping airfoil 12 to form a vector angle of attack C, and the vector angle of attack C makes the flapping wing A vertical upward force is generated between the surface 12 and the air; the translation wing 1 converts the up and down reciprocating motion of the drive mechanism 2 into its own rotational motion, and then generates lift through the rotational motion to enable the flying device to obtain lift to achieve the purpose of flight.

The front side edges of the spoiler airfoil 11 and the fan airfoil 12 are closed to each other to form a front wing edge 13 , and the rear side edges of the spoiler airfoil 11 and the fan airfoil 12 are closed to each other to form a rear wing tail 14 ; The spanwise meridian H where the point of maximum crown height of the front curved surface of the face 11 is located is close to the front wing edge 13 . The front wing edge 13 is a curved surface so as to connect the front side edges of the spoiler airfoil 11 and the fan airfoil surface 12 respectively. The existence of the front wing edge 13 can improve the structural strength of the airfoil-type translation wing 1, and the fore wing edge 13 is located in the translation wing. On the front side of the rotation direction, the curved front wing edge 13 can reduce the air resistance received by the translation wing 1 when it rotates, and improve the power conversion efficiency of the driving mechanism. As shown in FIG. 2 , the X direction in the figure is the chord length direction of the airfoil structure, and the Z direction in the figure is the extension direction of the airfoil structure. The contour line of the cross section of the spoiler airfoil 11 along the X direction is curved relative to the rotation plane of the translation wing 1 , and the highest point of the contour line forms the spanwise meridian H along the Z direction, and the spanwise meridian H is in the spoiler. The front curved surface of the airfoil 11 is on and close to the front wing edge 13 , so that the spoiler airfoil 11 has a front-to-rear asymmetric structure. When the translation wing 1 rises, the spoiler airfoil 11 interacts with the air above, and the air generates a pressure difference between the front and rear sides of the span meridian H of the spoiler airfoil 11 , and the pressure difference pushes the wing 10 Moving forward, the two wings 10 act in the same direction so that the translation wing 1 rotates in one direction with the rotating bearing 15 as the center.

The drive device 2 includes a first drive shaft 21 and a second drive shaft 22 . The first drive shaft 21 and the second drive shaft 22 are respectively mounted on the bracket 31 through sliding bearings 23 ; There is a rotary bearing 15, one of the translation wings 1 is mounted on the upper end of the first drive shaft 21 through the rotary bearing 15, and the rotary bearing 15 on the other translation wing 1 is mounted on the first drive shaft 21 through the sliding bearing 23, and The upper end of the second drive shaft 22 is fixedly connected with the sliding bearing 23 . The output power of the drive device 2 drives the first drive shaft 21 and the second drive shaft 22 to reciprocate up and down on the bracket 31 , and the first drive shaft 21 drives one of the translation wings 1 to rotate on it through the rotary bearing 15 to generate lift. , the second drive shaft 22 drives the other translation wing 1 to move up and down along the bracket 31 through the sliding bearing 23, so that it rotates around the bracket 31 through the rotating bearing 15 to generate lift, and the two translation wings 1 work together to output lift-off power to Gives carrier 3 the ability to fly. The flight mode of the translation wing 1 is similar to the helicopter flight mode without the need for taxi take-off and landing, so it has the ability to hover in the air. Since the two translation wings 1 are respectively mounted on the bracket 31 through the rotating bearing 15, when the driving device 2 loses power, the two translation wings 1 can still continue to rotate, and the angle of attack C of the fan airfoil 12 is adjusted to ≤ 0 °, the translation wing 1 will continue to rotate under the action of the falling inertial force, and the actual vector angle of attack of the fan wing surface 12 is greater than or equal to 0° to maintain a certain lift, which can delay the falling speed of the carrier 1 to make it land safely , so as to effectively improve the safety of the flying device.

The driving device 2 is provided with two output shafts 26 , and the two output shafts 26 are rotatably connected to the first driving shaft 21 and the second driving shaft 22 respectively. The drive device 2 includes a motor, a fuel engine, etc. The drive device 2 outputs continuous power to drive the two output shafts 26 to do work, and the two output shafts 26 can drive the first drive shaft 21 and the second drive shaft 22 in time to drive the two output shafts 26. A translational wing 1. The translational wing 1 uses up and down reciprocating motion to achieve rotation to generate lift, while the turbulent airfoil surface 11 and the fan airfoil surface 12 of the wing fin 10 do work in their up and down strokes respectively, so the operation of a single translational wing 1 has lift force. Output gap, and the reciprocating motion of a single translation wing 1 will generate large vibrations that affect the stability of the flight device, while the two up and down opposing translation wing 1 structures can well offset the vibration and make up for the lift output gap, improving flight performance. stability.

Example 2

As shown in FIG. 2 , the only difference between this embodiment and Embodiment 1 is that the driving device 2 further includes a first sliding sleeve 24 and a second sliding sleeve 25 , and the first sliding sleeve 24 is sleeved on the bracket 31 . A sliding bearing 23 is arranged between the two, the second sliding sleeve 25 is sleeved on the first sliding sleeve 24 and a sliding bearing 23 is arranged between the two; The upper end of the first sliding sleeve 24 is fixedly connected, the first driving shaft 21 is fixedly connected with the lower end of the first sliding sleeve 24; the rotating bearing 15 of the other translation wing 1 is fixedly connected to the upper end of the second sliding sleeve 25, The two drive shafts 22 are fixedly connected to the lower end of the second sliding sleeve 25 . The bracket 31 is used as a central support mechanism, and the first sliding sleeve 24 and the second sliding sleeve 25 are assembled in turn to form a concentric arrangement with the bracket 31, and then realize the time-sharing up and down reciprocating motion under the driving of the driving device 2, driving the two. The translation wing 1 moves relative to the opening and closing so as to achieve the purpose of flight.

The above descriptions are only the preferred embodiments of the present invention, so all equivalent changes or modifications made according to the structures, features and principles described in the scope of the patent application of the present invention are included in the scope of the patent application of the present invention.

Claims

A dual-wing flying device, comprising a translation wing (1), a driving device (2) and a carrier (3), characterized in that: the carrier (3) is provided with a bracket (31), and the bracket (31) is provided with a bracket (31) Two translation wings (1) that can be rotated thereon, the two translation wings (1) are arranged in pairs at an upper and lower interval; the driving device (2) is fixedly arranged on the carrier (3), and the driving device (2) The two translation wings (1) are respectively driven and connected so that the two translation wings (1) reciprocate up and down along the bracket (31).
The biplane flying device according to claim 1, characterized in that: the drive device (2) comprises a first drive shaft (21) and a second drive shaft (22), a first drive shaft (21) and a second drive shaft The shaft (22) is respectively mounted on the bracket (31) through the sliding bearing (23); the rotation center of the translation wing (1) is provided with a rotating bearing (15), and one of the translation wings (1) passes through the rotating bearing (15) is installed on the upper end of the first drive shaft (21), the rotary bearing (15) on the other translation wing (1) is installed on the first drive shaft (21) through the sliding bearing (23), and the second drive The upper end of the shaft (22) is fixedly connected with the sliding bearing (23).
The biplane flying device according to claim 2, characterized in that: the driving device (2) further comprises a first sliding sleeve (24) and a second sliding sleeve (25), the first sliding sleeve (24) The second sliding sleeve (25) is sleeved on the first sliding sleeve (24) and the sliding bearing (23) is arranged between them. ); the rotary bearing (15) of one of the translation wings (1) is fixedly connected to the upper end of the first sliding sleeve (24), and the first drive shaft (21) is fixedly connected to the lower end of the first sliding sleeve (24) ; The rotary bearing (15) of the other translation wing (1) is fixedly connected with the upper end of the second sliding sleeve (25), and the second drive shaft (22) is fixedly connected with the lower end of the second sliding sleeve (25).
The biplane flying device according to claim 2 or 3, characterized in that: the driving device (2) is provided with two output shafts (26), and the two output shafts (26) are respectively rotatably connected to the first driving shaft (21) and the second drive shaft (22).
The biplane flying device according to any one of claims 1-3, characterized in that: the translation wing (1) comprises two wings (10) and a rotating bearing (15), and the two wings (10) are opposite to each other are arranged on both sides of the rotating bearing (15), and the fin roots of the two fins (10) are respectively fixedly connected with the rotating bearing (15); the upper plane of the fins (10) is a spoiler airfoil ( 11), the lower plane of the wing (10) is the fanning airfoil (12); the spoiler airfoil (11) is formed by connecting the front curved surface and the rear smooth surface, and the front of the spoiler airfoil (11) is formed. The partial curved surface protrudes upward relative to the rotation plane of the translation wing (1), and the spoiler airfoil (11) and the fan airfoil (12) have an asymmetric structure on the longitudinal projection plane.
The biplane flying device according to claim 1, characterized in that: the front side edges of the spoiler airfoil (11) and the fan airfoil (12) are mutually closed to form a front wing edge (13), and the spoiler airfoil (11) ) and the rear side edge of the fan airfoil (12) are mutually closed to form a rear wing tail (14); the wingspan meridian H where the maximum arch height of the front curved surface of the spoiler airfoil (11) is located is close to the front wing edge (13). ).