LU101146A1 - An open-close wing structure of a combination-drive flapping-wing aircraft - Google Patents

An open-close wing structure of a combination-drive flapping-wing aircraft Download PDF

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Publication number
LU101146A1
LU101146A1 LU101146A LU101146A LU101146A1 LU 101146 A1 LU101146 A1 LU 101146A1 LU 101146 A LU101146 A LU 101146A LU 101146 A LU101146 A LU 101146A LU 101146 A1 LU101146 A1 LU 101146A1
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LU
Luxembourg
Prior art keywords
wing
blades
group
feather
movable
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LU101146A
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French (fr)
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LU101146B1 (en
Inventor
Bing Ji
Qiaolin Zhu
Yushuai Li
Fa Xie
Rui Song
Yibin Li
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Univ Shandong
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C33/00—Ornithopters
    • B64C33/02—Wings; Actuating mechanisms therefor
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/40—Ornithopters

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Remote Sensing (AREA)
  • Toys (AREA)
  • Wind Motors (AREA)

Abstract

The present invention discloses an open-close wing structure of a combination-drive flapping-wing aircraft, comprising a wing body and a primary feather blade group and a secondary feather blade group disposed on the same side of the wing body, wherein each of the primary feather blade group and the secondary feather blade group includes fixed blades and movable blades, the fixed blades are fixed at immobility on the wing body, and the movable blades are movable along sliding grooves; a driving structure comprises a power device, a transmission link I and a transmission link II being articulated with the movable blades, wherein the power device comprises a piston and a wind-driven fan blade group; a piston power device drives a transmission link I, the transmission link I and the transmission link II are respectively connected to a partial internal meshing gear and a partial external meshing gear, and the partial internal meshing gear and the partial external meshing gear mesh with the external meshing pinion located between the primary feather blade group and the secondary feather blade group; a drive shaft is disposed at the center of an external meshing pinion, and the drive shaft end located at the upward side of the wing body is connected with a wind-driven fan blade group. FIG. 1

Description

AN OPEN-CLOSE WING STRUCTURE OF A COMBINATION-DRIVE FLAPPING-WING AIRCRAFTAN OPEN-CLOSE WING STRUCTURE OF A COMBINATION-DRIVE FLAPPING-WING AIRCRAFT

TECHNICAL FIELD [0001] The present invention belongs to the field of mechanical structure design of flapping-wing bionic aircraft, and relates to an open-close wing structure of a combination-drive flapping-wing aircraft.TECHNICAL FIELD The present invention belongs to the field of mechanical structure design of flapping-wing bionic aircraft, and relates to an open-close wing structure of a combination-drive flapping-wing aircraft.

BACKGROUND OF THE INVENTION [0002] A small unmanned aircraft has such advantages as a small size, a light weight, flexible maneuverability and a small space for take-off and landing, etc., and are widely used in both military and civilian fields, such as monitoring, inspection, search and rescue, photography, investigation of the enemy situation, electronic interference, and even active attack and defense and so on. According to the generation and propulsion mechanism of lifting force, a small unmanned aircraft can be divided into a aircraft with fixed wings, a aircraft with rotors and a flapping-wing aircraft, wherein the flapping-wing bionic aircraft is a new type of aircraft that simulates the flight of birds or insects, belongs to both the categories of bionic robots and the aircraft, and involves cross-disciplinary knowledge of multiple disciplines. The search object of the present invention is a flapping-wing aircraft that simulates a flying bird.BACKGROUND OF THE INVENTION [0002] A small unmanned aircraft has such advantages as a small size, a light weight, flexible maneuverability and a small space for take-off and landing, etc., and are widely used in both military and civilian fields, such as monitoring, inspection, search and rescue, photography, investigation of the enemy situation, electronic interference, and even active attack and defense and so on. According to the generation and propulsion mechanism of lifting force, a small unmanned aircraft can be divided into a aircraft with fixed wings, a aircraft with rotors and a flapping-wing aircraft, which the flapping-wing bionic aircraft is a new type of aircraft that simulates the flight of birds or insects, belongs to both the categories of bionic robots and the aircraft, and involves cross-disciplinary knowledge of multiple disciplines. The search object of the present invention is a flapping-wing aircraft that simulates a flying bird.

[0003] The flapping-wing flight is a result of natural selection, and the flying creatures in nature all fly by flapping wings, which is of extreme reasonability. In a PhD thesis entitled The Numerical Study of the Aerodynamic Characteristics of Flapping-wing of Bionic Micro Aircrafts written by Zhang Xingwei of Harbin Institute of Technology in 2001, it is pointed out that in the low Reynolds coefficient environment of a small unmanned aircraft, compared with a flight with fixed wings and a flight with rotors, a flapping-wing flight has the advantages of maneuverability, flexibility, low energy consumption and good stealth, and is more suitable for long-distance flight in the case of no energy supply for a long time. Due to the advantages of the flapping-wing aircraft, the research on the flapping-wing aircraft has aroused key attention of scholars at home and abroad.The flapping-wing flight is a result of natural selection, and the flying creatures in nature all fly by flapping wings, which is of extreme reasonability. In a PhD thesis entitled The Numerical Study of the Aerodynamic Characteristics of Flapping-wing of Bionic Micro Aircrafts written by Zhang Xingwei of Harbin Institute of Technology in 2001, it is pointed out that in the low Reynolds coefficient environment of a small unmanned aircraft, compared with a flight with fixed wings and a flight with rotors, a flapping-wing flight has the advantages of maneuverability, flexibility, low energy consumption and good stealth, and is more suitable for long-distance flight in the case of no energy supply for a long time. Due to the advantages of the flapping-wing aircraft, the research on the flapping-wing aircraft has aroused key attention of scholars at home and abroad.

[0004] In a PhD thesis entitled The Technical Research on Bionic Wing Design of Micro Flapping-wing Aircrafts written by Liu Lan of Northwestern Polytechnical University in 2007, it pointed out that the wing movement of the flying bird is divided into two stages of flapping up and flapping down, wherein the stage of flapping down is the main stage for generating the lifting force. During the process, feathers of wings of the flying bird are tightly closed, so that no air flows between the upper surfaces and lower surfaces, and the air flows from the upper and lower surfaces of the wing, respectively; whereas the stage of flapping up is for returning the wings to the highest point in order to start the next cycle of flapping, and therefore, the flying bird always tries to shorten the process. During the flapping-up process, the flying bird spreads the feathers of wings to promote the air circulation between the upper and lower surfaces of the wings so as to reduce the air resistance encountered when the wings of the flying bird are flapping up. The opening and closing of the feathers during the wing flapping process of the flying birds are achieved by the movement of the primary feathers and the secondary feathers. However, the wing structure adopted in the current research on the flapping-wing aircraft in the prior art can not effectively reduce the air resistance encountered during the flapping-up process by simulating the opening and closing action of the flight feathers of the flying bird, which results in the waste of energy and seriously restricts the flight efficiency of the flapping-wing aircraft.In a PhD thesis entitled The Technical Research on Bionic Wing Design of Micro Flapping-wing Aircrafts written by Liu Lan of Northwestern Polytechnical University in 2007, it pointed out that the wing movement of the flying bird is divided into two stages of flapping up and flapping down, where the stage of flapping down is the main stage for generating the lifting force. During the process, feathers of wings of the flying bird are tightly closed, so that no air flows between the upper surfaces and lower surfaces, and the air flows from the upper and lower surfaces of the wing, respectively; whereas the stage of flapping up is for returning the wings to the highest point in order to start the next cycle of flapping, and therefore, the flying bird always tries to shorten the process. During the flapping-up process, the flying bird spreads the feathers of wings to promote the air circulation between the upper and lower surfaces of the wings so as to reduce the air resistance encountered when the wings of the flying bird are flapping up. The opening and closing of the feathers during the wing flapping process of the flying birds are achieved by the movement of the primary feathers and the secondary feathers. However, the wing structure adopted in the current research on the flapping-wing aircraft in the prior art can not effectively reduce the air resistance encountered during the flapping-up process by simulating the opening and closing action of the flight feathers of the flying bird, which results in the waste of energy and seriously restricts the flight efficiency of the flapping-wing aircraft.

SUMMARY OF THE INVENTION [0005] In order to solve this problem, the present invention designs an open-close wing structure of a combination-drive flapping-wing aircraft according to the flight mechanism of the flying bird. By means of simulating the opening and closing actions of the feathers during the wing flapping up and down process of the flying bird, the wing structure proposed by the present invention can effectively reduce the air resistance encountered during the flapping-up process of the wing without affecting generating the lifting force during the flapping-down process, and improve the flight efficiency of the flapping-wing aircraft so as to solve the problem of low flight efficiency caused by a larger air resistance during the wing flapping up process of the flapping-wing aircraft in the current research. The combination-drive in the present invention refers to simultaneous drives of both the piston under the action of the wing pressure and the blade groups driven by the wind for the opening and closing actions of the flapping-wing aircraft.SUMMARY OF THE INVENTION In order to solve this problem, the present invention designs an open-close wing structure of a combination-drive flapping-wing aircraft according to the flight mechanism of the flying bird. By means of simulating the opening and closing actions of the feathers during the wing flapping up and down process of the flying bird, the wing structure proposed by the present invention can effectively reduce the air resistance encountered during the flapping-up process of the wing without affecting generating the lifting force during the flapping-down process, and improve the flight efficiency of the flapping-wing aircraft so as to solve the problem of low flight efficiency caused by a larger air resistance during the wing flapping up process of the flapping-wing aircraft in the current research. The combination-drive in the present invention refers to simultaneous drives of both the piston under the action of the wing pressure and the blade groups driven by the wind for the opening and closing actions of the flapping-wing aircraft.

[0006] The present invention adopts the technical solutions as follows:The present invention adopts the technical solutions as follows:

[0007] An open-close wing structure of a combination-drive flapping-wing aircraft comprises a wing body and a primary feather blade group and a secondary feather blade groups disposed on the same side of the wing body, wherein each of the primary feather blade group and the secondary feather blade group includes a plurality of fixed blades and movable blades at interval distribution, respectively, the plurality of fixed blades are fixed at immobility on the wing body, and the plurality of movable blades are driven by a driving structure to move along sliding grooves located on the wing body;An open-close wing structure of a combination-drive flapping-wing aircraft comprised of a wing body and a primary feather blade group and a secondary feather blade groups disposed on the same side of the wing body, which each of the primary feather blade group and the secondary feather blade group includes a plurality of fixed blades and movable blades at interval distribution, respectively, the plurality of fixed blades are fixed at immobility on the wing body, and the plurality of movable blades are driven by a driving structure to move along sliding grooves located on the wing body;

[0008] the driving structure comprises a power device, a transmission link I and a transmission link II, and both the transmission link I and the transmission link II are articulated with the movable blades;The driving structure understood a power device, a transmission link I and a transmission link II, and both the transmission link I and the transmission link II are articulated with the movable blades;

[0009] the power device includes a piston and a wind-driven fan blade group, the piston is mounted on a wing base of the wing body, a piston-driven link connected to the piston is connected to a pedestal, and the transmission link I is connected to the pedestal; the wind-driven fan blade group is located at the upward side of the wing body, and connected to a drive shaft disposed at the center of an external meshing pinion;The power device includes a piston and a wind-driven fan blade group, the piston is mounted on a wing base of the wing body, a piston-driven link connected to the piston is connected to a pedestal, and the transmission link I is connected to the pedestal; the wind-driven fan blade group is located at the upward side of the wing body, and connected to a drive shaft disposed at the center of an external meshing pinion;

[0010] the piston power device drives the transmission link I, the transmission link I and the transmission link II are respectively connected to a partial internal meshing gear and a partial external meshing gear, and the partial internal meshing gear and the partial external meshing gear mesh with the external meshing pinion located between the primary feather blade group and the secondary feather blade group.The piston power device drives the transmission link I, the transmission link I and the transmission link II are respectively connected to a partial internal meshing gear and a partial external meshing gear, and the partial internal meshing gear and the partial external meshing gear mesh with the external meshing pinion located between the primary feather blade group and the secondary feather blade group.

[0011] The working mechanism of the technical solution is as follows:The working mechanism of the technical solution is as follows:

[0012] When the wing is at the initial state, the power device drives the transmission link I and the transmission link II into the position of being stretched to be the longest, and the entire feather blade group constitutes a closed wing plane.When the wing is at the initial state, the power device drives the transmission link I and the transmission link II into the position of being stretched to be the longest, and the entire feather blade group constitutes a closed wing plane.

[0013] The flapping-up process of the wing is as follows:The flapping-up process of the wing is as follows:

[0014] On the one hand, the wind-driven fan blade group located on the wing flapping-up surface rotates in a counterclockwise direction (the top view of the wing flapping-up surface) under the action of air resistance encountered on the wing flapping-up surface, and drives the external meshing pinion to rotate in a clockwise direction (the top view of the wing flapping-down surface); according to the law of gear meshing and transmission, the external meshing pinion drives the partial internal meshing gear and the partial external meshing gear to perform a transmission, and then the partial external meshing gear and the partial internal meshing gear respectively drive the transmission link I and the transmission link II to perform a transmission.On the one hand, the wind-driven fan blade group located on the wing flapping-up surface rotates in a counterclockwise direction (the top view of the wing flapping-up surface) under the action of air resistance encountered on the wing flapping-up surface, and drives the external meshing pinion to rotate in a clockwise direction (the top view of the wing flapping-down surface); according to the law of gear meshing and transmission, the external meshing pinion drives the partial internal meshing gear and the partial external meshing gear to perform a transmission, and then the partial external meshing gear and the partial internal meshing gear respectively drive the transmission link I and the transmission link II to perform a transmission.

[0015] On the other hand, the piston-driven link is gradually compressed under the action of the pressure of the wing. When at the position of being compressed to the shortest, the piston-driven link starts to drive the pedestal, and the movable blades of the secondary feather blade group fixed at the downward side of the pedestal slide along the sliding grooves towards the external meshing pinion; during the sliding process, the transmission link I fixed at the downward side of the movable blades of the secondary feather blade group drives the partial internal meshing gear to perform a transmission, and then the partial internal meshing gear, the external meshing pinion and the partial external meshing gear make a meshing motion, and the transmission link II fixedly connected to the partial external meshing gear also performs a transmission along the direction of the external meshing pinion.On the other hand, the piston-driven link is gradually compressed under the action of the pressure of the wing. When at the position of being compressed to the shortest, the piston-driven link starts to drive the pedestal, and the movable blades of the secondary feather blade group fixed at the downward side of the pedestal slide along the sliding grooves towards the external meshing pinion ; during the sliding process, the transmission link I fixed at the downward side of the movable blades of the secondary feather blade group drives the partial internal meshing gear to perform a transmission, and then the partial internal meshing gear, the external meshing pinion and the partial external meshing gear make a meshing motion, and the transmission link II fixedly connected to the partial external meshing gear also performs a transmission along the direction of the external meshing pinion.

[0016] Under the action of the above two aspects, the movable blades of the primary feather blade group perform a blade-opening movement under the drive of the transmission link II, and the movable blades of the secondary feather blade group perform a blade-opening movement under the drive of the transmission link I and the driving pedestal; the movement directions of the above-mentioned movable feather blades are all along the direction of the external meshing pinion.Under the action of the above two aspects, the movable blades of the primary feather blade group perform a blade-opening movement under the drive of the transmission link II, and the movable blades of the secondary feather blade group perform a blade- opening movement under the drive of the transmission link I and the driving pedestal; the movement directions of the above-mentioned movable feather blades are all along the direction of the external meshing pinion.

[0017] The flapping-down process of the wing is as follows:The flapping-down process of the wing is as follows:

The piston-driven link is gradually stretched under the drive of the wing. When being at the position of being stretched to the longest, the piston-driven link starts to drive the driving pedestal to move towards the wing base, and meanwhile the driving pedestal drives the movable blades of the secondary feather blade group to move along the direction of the wing body, and the transmission link I connected to the movable secondary feather blade group drives the partial internal meshing gear to move towards the wing body; the partial internal meshing gear drives the partial external meshing gear to move towards the wing body via the external meshing pinion; the partial external meshing gear drives the movable primary feather blade group to move towards the wing body via the transmission link II; the movable blade group and the fixed blade group constitute a closed wing plane when the wing surface and the side profile of the wing body form an angle of approximately 90°. The wing continues to flap down until the wing is at the initial state.The piston-driven link is gradually stretched under the drive of the wing. When being at the position of being stretched to the longest, the piston-driven link starts to drive the driving pedestal to move towards the wing base, and meanwhile the driving pedestal drives the movable blades of the secondary feather blade group to move along the direction of the wing body, and the transmission link I connected to the movable secondary feather blade group drives the partial internal meshing gear to move towards the wing body; the partial internal meshing gear drives the partial external meshing gear to move towards the wing body via the external meshing pinion; the partial external meshing gear drives the movable primary feather blade group to move towards the wing body via the transmission link II; the movable blade group and the fixed blade group constitute a closed wing plane when the wing surface and the side profile of the wing body form an angle of approximately 90 °. The wing continues to flap down until the wing is at the initial state.

[0018] Further, the wing body comprises a wing base, a wing vein and a wing membrane; the wing base is used to connect with a fuselage, a plurality of wing veins are connected with the wing base, and the wing membrane is laid between a plurality of wing veins to form the wing body.Further, the wing body included a wing base, a wing vein and a wing membrane; the wing base is used to connect with a fuselage, a plurality of wing veins are connected with the wing base, and the wing membrane is laid between a plurality of wing veins to form the wing body.

[0019] Further, the wing vein comprises main wing veins for forming a contour of the wing and a plurality of branch wing veins for dividing the interior of the wing, wherein a branch wing vein I is substantially parallel to one side of the main wing vein to form a space for installing the primary feather blade group and the secondary feather blade group; the primary feather blade group and the secondary feather blade group are separated by a branch wing vein II, and the drive shaft is mounted on the branch wing vein II.Further, the wing vein included main wing veins for forming a contour of the wing and a plurality of branch wing veins for dividing the interior of the wing, whereas a branch wing vein I is substantially parallel to one side of the main wing vein to form a space for installing the primary feather blade group and the secondary feather blade group; the primary feather blade group and the secondary feather blade group are separated by a branch wing vein II, and the drive shaft is mounted on the branch wing vein II.

[0020] Further, sliding grooves are provided at corresponding positions on the branch wing vein I and the main wing vein for installing the primary feather blade group and the secondary feather blade group.Further, sliding grooves are provided at corresponding positions on the branch wing vein I and the main wing vein for installing the primary feather blade group and the secondary feather blade group.

[0021] Further, an effective width of the sliding groove is equal to a sum of the thickness of the fixed feather blade and the thickness of the movable feather blade.[0021] Further, an effective width of the sliding groove is equal to a sum of the thickness of the fixed feather blade and the thickness of the movable feather blade.

[0022] Further, the respective fixed blades and movable blades of the primary feather blade group and secondary feather blade group have the same size and shape, and the width of the movable blade is slightly larger than a blank distance between two fixed blades.[0022] Further, the respective fixed blades and movable blades of the primary feather blade group and secondary feather blade group have the same size and shape, and the width of the movable blade is slightly larger than a blank distance between two fixed blades.

[0023] Further, the secondary feather blade group comprises two fixed blades and two movable blades, wherein one movable blade is adjacent to the wing base, and then one fixed blade, the other movable blade and the other fixed blade are successively arranged in the direction of extending outward along the wing; and the two movable blades are respectively connected with the transmission link I.Further, the secondary feather blade group including two fixed blades and two movable blades, where one movable blade is adjacent to the wing base, and then one fixed blade, the other movable blade and the other fixed blade are successively arranged in the direction of extending outward along the wing; and the two movable blades are respectively connected with the transmission link I.

[0024] Further, the primary feather blade group comprises two fixed blades and two movable blades, wherein one fixed blade is adjacent to the secondary feather blade group, and then one movable blade, the other fixed blade and the other movable blade are successively arranged in the direction of extending outward along the wing; and the two movable blades are respectively connected with the transmission link II.Further, the primary feather blade group including two fixed blades and two movable blades, which one fixed blade is adjacent to the secondary feather blade group, and then one movable blade, the other fixed blade and the other movable blade are successively arranged in the direction of extending outward along the wing; and the two movable blades are respectively connected with the transmission link II.

[0025] Further, the single movement of the piston in the piston-driven link to the farthest position is synchronized with the single movement of the driving pedestal to the farthest position of the left end of the fixed secondary blade.Further, the single movement of the piston in the piston-driven link to the farthest position is synchronized with the single movement of the driving pedestal to the farthest position of the left end of the fixed secondary blade.

[0026] Further, the slope of the whole wing surface with respect to the base body connecting the wing with the fuselage is within the range of 45°-150°.Further, the slope of the whole wing surface with respect to the base body connecting the wing with the fuselage is within the range of 45 ° -150 °.

[0027] The beneficial effects of the present invention are as follows:The beneficial effects of the present invention are as follows:

[0028] Based on the characteristic of wing flapping of the flapping-wing aircraft, the present invention designs the above mechanical structure to achieve the synchronization between the automatic opening-closing action of the movable feather blades of the wing and the flapping up and down of the wing, so that the air resistance is effectively reduced during the flapping-up process without affecting generating the lift force during the flapping-down process; meanwhile during the flapping-up process, the power for opening the movable feather blades of the wing is partially derived from the rotation of the fan blade group driven by the air resistance encountered on the wing flapping-up surface, so that the energy utilization is further improved.Based on the characteristic of wing flapping of the flapping-wing aircraft, the present invention designs the above mechanical structure to achieve the synchronization between the automatic opening-closing action of the movable feather blades of the wing and the flapping up and down of the wing, so that the air resistance is effectively reduced during the flapping-up process without affecting generating the lift force during the flapping-down process; meanwhile during the flapping-up process, the power for opening the movable feather blades of the wing is partially derived from the rotation of the fan blade group driven by the air resistance encountered on the wing flapping-up surface, so that the energy utilization is further improved.

BRIEF DESCRIPTION OF THE DRAWINGS [0029] The accompanying drawings of the description as a part of the present invention are intended to provide a further understanding of the present invention, and the illustrative embodiments of the present invention and the description thereof are intended to explain the present invention, but do not constitute an improper limitation to the present invention.BRIEF DESCRIPTION OF THE DRAWINGS The accompanying drawings of the description as a part of the present invention are intended to provide a further understanding of the present invention, and the illustrative embodiments of the present invention and the description thereof are intended to explain the present invention, but do not constitute an improper limitation to the present invention.

[0030] FIG. 1 is an axonometric view of the wing at the initial closed state in the present invention (the hidden structure is shown in dashed lines).FIG. 1 is an axonometric view of the wing at the initial closed state in the present invention (the hidden structure is shown in dashed lines).

[0031] FIG. 2 is a structure schematic diagram of the flapping-up surface of the wing at the closed state in the present invention.FIG. 2 is a structure schematic diagram of the flapping-up surface of the wing at the closed state in the present invention.

[0032] FIG. 3 is a structure schematic diagram of the flapping-down surface of the wing at the closed state in the present invention.FIG. 3 is a structure schematic diagram of the flapping-down surface of the wing at the closed state in the present invention.

[0033] FIG. 4 is an axonometric view of the wing at the open state in the present invention (the hidden structure is shown in dashed lines).FIG. 4 is an axonometric view of the wing at the open state in the present invention (the hidden structure is shown in dashed lines).

[0034] FIG. 5 is a structure schematic diagram of the flapping-up surface of the wing at the open state in the present invention.FIG. 5 is a structure schematic diagram of the flapping-up surface of the wing at the open state in the present invention.

[0035] FIG. 6 is a structure schematic diagram of the flapping-down surface of the wing at the open state in the present invention.FIG. 6 is a structure schematic diagram of the flapping-down surface of the wing at the open state in the present invention.

[0036] FIG. 7 is an axonometric view of the wind-driven fan blade group in the present invention.FIG. 7 is an axonometric view of the wind-driven fan blade group in the present invention.

[0037] FIG. 8 is a module schematic diagram of an opening-closing transmission of the present invention.FIG. 8 is a module schematic diagram of an opening-closing transmission of the present invention.

[0038] FIG. 9 is a module schematic diagram of a gear transmission in the present invention.FIG. 9 is a module schematic diagram of a gear transmission in the present invention.

[0039] FIG. 10 is a module schematic diagram of a piston-driven link and an axonometric view of a piston-driven link of the present invention (the hidden structure is shown in dashed lines).FIG. 10 is a module schematic diagram of a piston-driven link and an axonometric view of a piston-driven link of the present invention (the hidden structure is shown in dashed lines).

[0040] FIG. 11 is a structure schematic diagram of the sliding grooves in the present invention.FIG. 11 is a structure schematic diagram of the sliding grooves in the present invention.

[0041] Reference signs in the drawings: 1-wing base;Reference signs in the drawings: 1-wing base;

2A, 2B, 2C, 2D, 2E-wingvein2A, 2B, 2C, 2D, 2E-wingvein

3A, 3B, 3C, 3D-wing membrane;3A, 3B, 3C, 3D-wing membrane;

4A, 4B-fixed primary feather blade group;4A, 4B-fixed primary feather blade group;

5A, 5B-fixed secondary feather blade group;5A, 5B-fixed secondary feather blade group;

6A, 6B-movable primary feather blade group;6A, 6B-movable primary feather blade group;

7A, 7B-movable secondary feather blade group;7A, 7B-movable secondary feather blade group;

8A, 8B- primary feather sliding groove group; 9A, 9B- secondary feather sliding groove group;8A, 8B- primary feather sliding groove group; 9A, 9B- secondary feather sliding groove group;

10- wind-driven fan blade group;10- wind-driven fan blade group;

11- piston-driven link;11- piston-driven link;

12A, 12B- driving pedestal;12A, 12B- driving pedestal;

13A, 13B, 13C, 13D-fixed handle;13A, 13B, 13C, 13D-fixed handle;

14- transmission link II;14- link II transmission;

15- partial external meshing gear;15- partial external meshing gear;

16- partial internal meshing gear;16- partial internal meshing gear;

17- transmission link I;17- link I transmission;

18- external meshing pinion;18- external meshing pinion;

19- rotating shaft.19- rotating shaft.

DETAILED DESCRIPTION OF THE EMBODIMENTS [0042] It should be noted that the following detailed description is illustrative and is intended to provide a further description of the present invention. Unless otherwise indicated, all technical and scientific terms used in the present invention have the same meaning as commonly understood by those skilled in the art to which the present invention belongs.DETAILED DESCRIPTION OF THE EMBODIMENTS It should be noted that the following detailed description is illustrative and is intended to provide a further description of the present invention. Unless otherwise indicated, all technical and scientific terms used in the present invention have the same meaning as commonly understood by those skilled in the art to which the present invention belongs.

[0043] It is to be noted that the terms used herein are merely for describing specific embodiments, but are not intended to limit the exemplary embodiments of the present invention. As used herein, unless otherwise clearly indicated in the context, a singular form is also intended to include the plural form. In addition, it shall be also understood that when the term comprise and/or include is used in the specification, it is intended to indicate the presence of features, steps, operations, devices, components, and/or combinations thereof.It is to be noted that the terms used herein are merely for describing specific embodiments, but are not intended to limit the exemplary embodiments of the present invention. As used herein, unless otherwise clearly indicated in the context, a singular form is also intended to include the plural form. In addition, it shall also be understood that when the term understood and / or include is used in the specification, it is intended to indicate the presence of features, steps, operations, devices, components, and / or combinations thereof.

[0044] The Term Explanation Section: the wing base, wing vein, and wing membrane described in the present invention have no specific meanings, and are equivalent to a main beam, a base plate and the like of a wing at present.The Term Explanation Section: the wing base, wing vein, and wing membrane described in the present invention have no specific meanings, and are equivalent to a main beam, a base plate and the like of a wing at present.

[0045] As described in the background art, the wing structure adopted in the current research on the flapping-wing aircraft in the prior art can not effectively reduce the air resistance encountered during the wing flapping-up process by simulating the opening and closing action of the feathers of the flying bird, which results in the waste of energy and seriously restricts the flight efficiency of the flapping-wing aircraft. In order to solve this problem, the present invention provides an open-close wing structure of a combination-drive flapping-wing aircraft. By means of simulating the opening and closing actions of the feathers during the wing flapping up and down process of the flying bird, the wing structure proposed by the present invention can effectively reduce the air resistance encountered during the wing flapping-up process without affecting generating the lifting force during the wing flapping-down process, and improve the flight efficiency of the flapping-wing aircraft so as to solve the problem of low flight efficiency caused by a larger air resistance during the wing flapping-up process of the flapping-wing aircraft in the current research.As described in the background art, the wing structure adopted in the current research on the flapping-wing aircraft in the prior art can not effectively reduce the air resistance encountered during the wing flapping-up process by simulating the opening and closing action of the feathers of the flying bird, which results in the waste of energy and seriously restricts the flight efficiency of the flapping-wing aircraft. In order to solve this problem, the present invention provides an open-close wing structure of a combination-drive flapping-wing aircraft. By means of simulating the opening and closing actions of the feathers during the wing flapping up and down process of the flying bird, the wing structure proposed by the present invention can effectively reduce the air resistance encountered during the wing flapping-up process without affecting generating the lifting force during the wing flapping-down process, and improve the flight efficiency of the flapping-wing aircraft so as to solve the problem of low flight efficiency caused by a larger air resistance during the wing flapping-up process of the flapping-wing aircraft in the current research.

[0046] In a typical embodiment of the present invention, as is shown in FIG. 1, an open-close wing structure of a combination-drive flapping-wing aircraft is provided, comprising a wing base 1, wing veins 2A, 2B, 2C, 2D, 2E, wing membranes 3A, 3B, 3C, 3D, a fixed primary feather blade group 4A, 4B, a fixed secondary feather blade group 5A, 5B, a movable primary feather blade group 6A, 6B, a movable secondary feather blade group 7A, 7B, a primary feather sliding groove group 8A, 8B, a secondary feather sliding groove group 9A, 9B, a piston-driven link 11, driving pedestals 12A, 12B, a wind-driven fan blade group 10, a rotating shaft 19, an external meshing pinion 18, a partial external meshing gear 15, a partial internal meshing gear 16, a transmission link II 14, a transmission link 117 and fixed handles 13A, 13B, 13C, 13D.In a typical embodiment of the present invention, as is shown in FIG. 1, an open-close wing structure of a combination-drive flapping-wing aircraft is provided, comprising a wing base 1, wing veins 2A, 2B, 2C, 2D, 2E, wing membranes 3A, 3B, 3C, 3D, a fixed primary feather blade group 4A, 4B, a fixed secondary feather blade group 5A, 5B, a movable primary feather blade group 6A, 6B, a movable secondary feather blade group 7A, 7B, a primary feather sliding groove group 8A, 8B, a secondary feather sliding groove group 9A, 9B, a piston-driven link 11, driving pedestals 12A, 12B, a wind-driven fan blade group 10, a rotating shaft 19, an external meshing pinion 18, a partial external meshing gear 15, a partial internal meshing gear 16, a transmission link II 14, a transmission link 117 and fixed handles 13A, 13B, 13C, 13D.

[0047] The entire wing is connected to the fuselage via the wing base, and rotates around the fuselage with the wing vein 2A as an axis; the piston-driven link 11 are connected with the wing base 1 and the movable secondary feather blade group 7A, 7B via the driving pedestals 12A, 12B, and rotate around the driving pedestals 12A, 12B; the wind-driven fan blade group 10 is connected to the external meshing pinion 18 via the rotating shaft 19; the fixed primary feather blade group 4A, 4B and the fixed secondary feather blade group 5A, 5B are fixed at the positions of the upper half contact surfaces of the sliding grooves of the primary feather sliding groove group 8A, 8B and the secondary feather sliding groove group 9A, 9B, respectively. [0048] The movable primary feather blade group 6A, 6B and the movable secondary feather blade group 7A, 7B are mounted at the positions of the lower half contact surfaces of the sliding grooves of the primary feather sliding groove group 8A, 8B and the secondary feather sliding groove group 9A, 9B, respectively.The entire wing is connected to the fuselage via the wing base, and rotates around the fuselage with the wing vein 2A as an axis; the piston-driven link 11 are connected with the wing base 1 and the movable secondary feather blade group 7A, 7B via the driving pedestals 12A, 12B, and rotate around the driving pedestals 12A, 12B; the wind-driven fan blade group 10 is connected to the external meshing pinion 18 via the rotating shaft 19; the fixed primary feather blade group 4A, 4B and the fixed secondary feather blade group 5A, 5B are fixed at the positions of the upper half contact surfaces of the sliding grooves of the primary feather sliding groove group 8A, 8B and the secondary feather sliding groove group 9A, 9B, respectively. The movable primary feather blade group 6A, 6B and the movable secondary feather blade group 7A, 7B are mounted at the positions of the lower half contact surfaces of the sliding grooves of the primary feather sliding groove group 8A, 8B and the secondary feather sliding groove group 9A, 9B, respectively.

[0049] The transmission link II 14 and the transmission link I 17 are fixed to the movable primary feather blade group 6A, 6B and the movable secondary feather blade group 7A, 7B via the fixed handles 13A, 13B, 13C, 13D, respectively; the partial external meshing gear 15 and the partial internal meshing gear 16 are fixed on 5 the transmission link II and the transmission link I, respectively; the partial external meshing gear 15 and the partial internal meshing gear 16 perform a gear transmission via the external meshing pinion 18.The transmission link II 14 and the transmission link I 17 are fixed to the movable primary feather blade group 6A, 6B and the movable secondary feather blade group 7A, 7B via the fixed handles 13A, 13B, 13C, 13D, respectively; the partial external meshing gear 15 and the partial internal meshing gear 16 are fixed on 5 the transmission link II and the transmission link I, respectively; the partial external meshing gear 15 and the partial internal meshing gear 16 perform a gear transmission via the external meshing pinion 18.

[0050] The transmission link I 17 is connected to the driving pedestal 12A, and the driving pedestal 12A is connected to the piston-driven link 11, the piston to which 10 the piston-driven link 11 is connected is mounted on the driving pedestal 12B, and the driving pedestal 12B is connected to the wing base 1.The transmission link I 17 is connected to the driving pedestal 12A, and the driving pedestal 12A is connected to the piston-driven link 11, the piston to which 10 the piston-driven link 11 is connected is mounted on the driving pedestal 12B, and the driving pedestal 12B is connected to the wing base 1.

[0051] An effective width of the sliding grooves of the primary feather sliding groove group 8A, 8B is equal to a sum of the thickness of the fixed feather blade and the thickness of the movable feather blade, and an effective width of the sliding 15 grooves of the secondary feather sliding groove group 9A, 9B is equal to a sum of the thickness of the fixed feather blade and the thickness of the movable feather blade.An effective width of the sliding grooves of the primary feather sliding groove group 8A, 8B is equal to a sum of the thickness of the fixed feather blade and the thickness of the movable feather blade, and an effective width of the sliding 15 grooves of the secondary feather sliding groove group 9A, 9B is equal to a sum of the thickness of the fixed feather blade and the thickness of the movable feather blade.

[0052] The blades of the fixed primary feather blade group 4A, 4B have the same size and shape as those of the blades of the movable primary feather blade group 6A, 20 6B, and the blade width of the movable primary feather blade group is slightly larger than the blank distance among the blades of the fixed primary feather blade group; the blades of the movable secondary feather blade group 7A, 7B have the same size and shape as those of the blades of the fixed secondary feather blade group 5A, 5B, respectively, and the blade width of the movable secondary feather blade group is 25 slightly larger than the blank distance among the blades of the fixed secondary feather blade group.The blades of the fixed primary feather blade group 4A, 4B have the same size and shape as those of the blades of the movable primary feather blade group 6A, 20 6B, and the blade width of the movable primary feather blade group is slightly larger than the blank distance among the blades of the fixed primary feather blade group; the blades of the movable secondary feather blade group 7A, 7B have the same size and shape as those of the blades of the fixed secondary feather blade group 5A, 5B, respectively, and the blade width of the movable secondary feather blade group is 25 slightly larger than the blank distance among the blades of the fixed secondary feather blade group.

[0053] The rotating shaft 19 is mounted on the wing vein 2D; the wind-driven fan blade group 10 located on the wing flapping-up surface is connected to the rotating shaft 19, and the plane on which the blades of the wind-driven fan blade group 10 are 30 located inclines with respect to the wing flapping-up surface, and the inclination is in a clockwise direction, clockwise herein means the direction of the wing flapping-up surface; the effective meshing surface width of the external meshing pinion 18 is equal to the sum of the meshing surface width of a partial external meshing gear 15 and the meshing surface width of a partial internal meshing gear 16, and the meshing 35 surface width of the partial external meshing gear is equal to that of the partial internal meshing gear, and the position of the partial external meshing gear 15 is closer to the wing surface than that of the local internal gear 16; the height of the effective rotation portion of the piston-driven link 11 (the rotating cylinder in contact with the inner groove of the driving pedestal 12A) is smaller than the distance 40 between the inner grooves of two handles of the driving pedestal 12A.The rotating shaft 19 is mounted on the wing vein 2D; the wind-driven fan blade group 10 located on the wing flapping-up surface is connected to the rotating shaft 19, and the plane on which the blades of the wind-driven fan blade group 10 are 30 located inclines with respect to the wing flapping -up surface, and the inclination is in a clockwise direction, clockwise herein means the direction of the wing flapping-up surface; the effective meshing surface width of the external meshing pinion 18 is equal to the sum of the meshing surface width of a partial external meshing gear 15 and the meshing surface width of a partial internal meshing gear 16, and the meshing 35 surface width of the partial external meshing gear is equal to that of the partial internal meshing gear, and the position of the partial external meshing gear 15 is closer to the wing surface than that of the local internal gear 16; the height of the effective rotation portion of the piston-driven link 11 (the rotating cylinder in contact with the inner groove of the driving pedestal 12A) is smaller than the distance 40 between the inner grooves of two handles of the driving pedestal 12A.

[0054] The slope of the whole wing surface with respect to the base body connecting the wing with the fuselage is within the range of 45°-150° (i.e., the process of the movable blades from being “open” to “close”).The slope of the whole wing surface with respect to the base body connecting the wing with the fuselage is within the range of 45 ° -150 ° (ie, the process of the movable blades from being “open” to “close” ).

[0055] The single movement of the piston in the piston-driven link 11 to the farthest position is synchronized with the single movement of the driving pedestal 12A to the farthest position of the left end of the fixed secondary blade 5B.The single movement of the piston in the piston-driven link 11 to the farthest position is synchronized with the single movement of the driving pedestal 12A to the farthest position of the left end of the fixed secondary blade 5B.

[0056] The detail movement flow of the present invention is as follows:The detail movement flow of the present invention is as follows:

[0057] 1. When the wing is at the initial state, as is shown in FIG. 1, the piston-driven link is at the position of being stretched to the longest(at this point, the angle between link and the fuselage is within the range of 120°-150°), and the entire feather blade group constitutes a closed wing plane, and the initial meshing positions among the partial external meshing gear, the partial internal meshing gear and the external meshing pinion are shown in FIG. 3.1. When the wing is at the initial state, as is shown in FIG. 1, the piston-driven link is at the position of being stretched to the longest (at this point, the angle between link and the fuselage is within the range of 120 ° -150 °), and the entire feather blade group constitutes a closed wing plane, and the initial meshing positions among the partial external meshing gear, the partial internal meshing gear and the external meshing pinion are shown in FIG. 3.

[0058] 2. The flapping-up process of the wing is as follows:2. The flapping-up process of the wing is as follows:

[0059] On the one hand, the wind-driven fan blade group located on the wing flapping-up surface rotates in a counterclockwise direction (the top view of the wing flapping-up surface) under the action of air resistance encountered on the wing flapping-up surface, and drives the external meshing pinion to rotate in a clockwise direction (the top view of the wing on the wing flapping-down surface); according to the law of gear meshing and transmission, the external meshing pinion drives the partial external meshing gear and the partial internal meshing gear to perform a transmission, and then the partial external meshing gear and the partial internal meshing gear respectively drive the transmission link I and the transmission link II to perform a transmission.On the one hand, the wind-driven fan blade group located on the wing flapping-up surface rotates in a counterclockwise direction (the top view of the wing flapping-up surface) under the action of air resistance encountered on the wing flapping-up surface, and drives the external meshing pinion to rotate in a clockwise direction (the top view of the wing on the wing flapping-down surface); according to the law of gear meshing and transmission, the external meshing pinion drives the partial external meshing gear and the partial internal meshing gear to perform a transmission, and then the partial external meshing gear and the partial internal meshing gear respectively drive the transmission link I and the transmission link II to perform a transmission.

[0060] On the other hand, the piston-driven link is gradually compressed under the action of the pressure of the wing. When at the position of being compressed to the shortest,(at this point, the angel between the link and the fuselage is within the range of 45°-60°), the piston-driven link starts to drive the pedestal 12A, and the movable secondary feather blade group fixed at the downward side of the pedestal 12A slides along the secondary feather sliding groove towards the external meshing pinion; during the sliding process, the transmission link I fixed at the downward side of the movable secondary feather blade group drives the partial internal meshing gear to perform a transmission, and then the partial internal meshing gear, the external meshing pinion and the partial external meshing gear make a meshing motion, and the transmission link II fixedly connected to the partial external meshing gear also performs a transmission along the direction of the external meshing pinion.On the other hand, the piston-driven link is gradually compressed under the action of the pressure of the wing. When at the position of being compressed to the shortest, (at this point, the angel between the link and the fuselage is within the range of 45 ° -60 °), the piston-driven link starts to drive the pedestal 12A, and the movable secondary feather blade group fixed at the downward side of the pedestal 12A slides along the secondary feather sliding groove towards the external meshing pinion; during the sliding process, the transmission link I fixed at the downward side of the movable secondary feather blade group drives the partial internal meshing gear to perform a transmission, and then the partial internal meshing gear, the external meshing pinion and the partial external meshing gear make a meshing motion, and the transmission link II fixedly connected to the partial external meshing gear also performs a transmission along the direction of the external meshing pinion.

[0061] Under the action of the above two aspects, the movable primary feather blade group performs a blade- opening movement under the drive of the transmission link II, and the movable secondary feather blade group performs a blade- opening movement under the drive of the transmission link I and the driving pedestal, the movement directions of the above-mentioned movable feather blades are all along the direction of the external meshing pinion.Under the action of the above two aspects, the movable primary feather blade group performs a blade- opening movement under the drive of the transmission link II, and the movable secondary feather blade group performs a blade- opening movement under the drive of the transmission link I and the driving pedestal, the movement directions of the above-mentioned movable feather blades are all along the direction of the external meshing pinion.

ίο [0062] As is shown in FIG. 4, when the wing flaps up to the highest point, the driving pedestal 12A has reached the left edge (not contact) of the fixed secondary feather blade 5B, at the moment the movable blades have been fully opened, and form an angle of 45°-60° to the fuselage, and the meshing positions among the partial external meshing gear, the partial internal meshing gear and the external meshing pinion are shown in FIG. 6.ίο [0062] As is shown in FIG. 4, when the wing flaps up to the highest point, the driving pedestal 12A has reached the left edge (not contact) of the fixed secondary feather blade 5B, at the moment the movable blades have been fully opened, and form an angle of 45 ° -60 ° to the fuselage, and the meshing positions among the partial external meshing gear, the partial internal meshing gear and the external meshing pinion are shown in FIG. 6.

[0063] The flapping-down process of the wing is as follows:The flapping-down process of the wing is as follows:

[0064] The piston-driven link is gradually stretched under the action of driving of the wing. When being at the longest stretching position, the piston-driven link lever starts to drive the driving pedestal to move towards the wing base, and meanwhile the driving pedestal drives the movable secondary feather blade group to move along the direction of the wing body, and the transmission link I connected to the movable secondary feather blade group moves towards the wing body by driving the partial internal meshing gear; the partial internal meshing gear drives the partial external meshing gear to move towards the wing body via the external meshing pinion; the partial external meshing gear drives the movable primary feather blade group to move towards the wing body via the transmission link II; the movable blade group and the fixed blade group constitutes a closed wing plane when the wing surface and the side profile of the wing body form an angle of approximately 90°. The wing continues to flap down until the wing is at the initial state.The piston-driven link is gradually stretched under the action of driving of the wing. When being at the longest stretching position, the piston-driven link lever starts to drive the driving pedestal to move towards the wing base, and meanwhile the driving pedestal drives the movable secondary feather blade group to move along the direction of the wing body, and the transmission link I connected to the movable secondary feather blade group moves towards the wing body by driving the partial internal meshing gear; the partial internal meshing gear drives the partial external meshing gear to move towards the wing body via the external meshing pinion; the partial external meshing gear drives the movable primary feather blade group to move towards the wing body via the transmission link II; the movable blade group and the fixed blade group constitutes a closed wing plane when the wing surface and the side profile of the wing body form an angle of approximately 90 °. The wing continues to flap down until the wing is at the initial state.

[0065] Although the above content describes the embodiments of the present invention with reference to the accompanying drawings, but is not intended to limit the scope of the present invention. It should be understood for those skilled in the art that based on the technical solution of the present invention, various amendments or variations made by those skilled in the art without creative labor still fall into the scope of the present invention.Although the above content describes the embodiments of the present invention with reference to the accompanying drawings, but is not intended to limit the scope of the present invention. It should be understood for those skilled in the art that based on the technical solution of the present invention, various amendments or variations made by those skilled in the art without creative labor still fall into the scope of the present invention.

Claims (9)

Revendicationsclaims 1. Structure d'aile ouverte-fermée d'un aéronef à ailes battantes à combinaison, comprenant un corps d'aile et un groupe de pales de plumes primaire et un groupe de pales de plumes secondaire disposés du même côté du corps d'aile, dans laquelle chaque groupe de pales de plumes primaires et groupe de pales de plumes secondaire comprend une pluralité de pales fixes et de pales mobiles réparties à intervalles, respectivement, la pluralité des pales fixes est fixée de manière immobile sur le corps de l'aile, et la pluralité de pales mobiles est entraînée par une structure d'entraînement pour se déplacer le long de rainures de glissement situées sur le corps de l'aile ;1. Open-closed wing structure of a combination wing aircraft, comprising a wing body and a group of primary feather blades and a group of secondary feather blades arranged on the same side of the wing body , wherein each group of primary feather blades and group of secondary feather blades comprises a plurality of fixed blades and movable blades distributed at intervals, respectively, the plurality of fixed blades is fixedly fixed on the body of the wing , and the plurality of movable blades is driven by a drive structure to move along sliding grooves located on the body of the wing; la structure d'entraînement comprend un dispositif d'alimentation, une liaison de transmission I et une liaison de transmission II, la liaison de transmission I et la liaison de transmission II sont respectivement articulées avec les pales mobiles, le dispositif d'alimentation comprend un piston et un groupe de pales de soufflante entraîné par le vent, le piston étant monté sur une base d'aile du corps d'aile, une liaison entraînée par un piston reliée au piston est reliée à un socle et la liaison de transmission I est reliée au socle ; le groupe de pales de soufflante entraîné par le vent est situé du côté supérieur du corps de l'aile, et est relié à un arbre d'entraînement disposé au centre d'un pignon d'engrènement externe ;the drive structure comprises a supply device, a transmission link I and a transmission link II, the transmission link I and the transmission link II are respectively articulated with the movable blades, the supply device comprises a piston and a group of blower blades driven by the wind, the piston being mounted on a wing base of the wing body, a link driven by a piston connected to the piston is connected to a base and the transmission link I is connected to the base; the group of wind-driven fan blades is located on the upper side of the wing body, and is connected to a drive shaft arranged in the center of an external meshing pinion; le dispositif d'alimentation à piston entraîne la liaison de transmission I, la liaison de transmission I et la liaison de transmission II sont respectivement reliées à un engrenage interne partiel et à un engrenage externe partiel, et l'engrenage interne partiel et l'engrenage partiel externe engrènent le pignon d'engrènement externe situé entre le groupe de pales de plumes primaire et le groupe de pales de plumes secondaire ;the piston feeder drives the transmission link I, the transmission link I and the transmission link II are respectively connected to a partial internal gear and to a partial external gear, and the partial internal gear and the gear partial external mesh with the external meshing pinion located between the group of primary feather blades and the group of secondary feather blades; 2. Structure d'aile ouverte-fermée d'un aéronef à ailes battantes à combinaison, selon la revendication 1, dans laquelle le corps de l'aile comprend une base d'aile, une veine d'aile et une membrane d'aile ; la base de l'aile est utilisée pour se connecter à un fuselage, plusieurs veines de l'aile sont connectées à la base de l'aile, et la membrane de l'aile est posée entre plusieurs veines de l'aile pour former le corps de l'aile.2. The open-closed wing structure of a combination wing aircraft, according to claim 1, wherein the wing body comprises a wing base, a wing vein and a wing membrane. ; the base of the wing is used to connect to a fuselage, several veins of the wing are connected to the base of the wing, and the membrane of the wing is placed between several veins of the wing to form the wing body. 3. Structure d'aile ouverte-fermée d'un aéronef à ailes battantes à combinaison, selon la revendication 2, dans laquelle la veine d'aile comprend des veines d'aile principales pour former un contour de l'aile et des veines d'aile de branche pour diviser l'intérieur de l'aile, dans laquelle une veine d'aile de branche I étant sensiblement parallèle à un côté de la veine d'aile principale pour former un espace pour l'installation d'un groupe de pales de plumes primaire et un groupe de lames de plumes secondaire ; le groupe de pales de plumes primaire et le groupe de pales de plumes secondaire sont séparés par une veine d'aile de branche II, et l'arbre d'entraînement est monté sur la veine d'aile de branche II.3. The open-closed wing structure of a combination winged aircraft, according to claim 2, wherein the wing vein comprises main wing veins to form an outline of the wing and of the veins d branch wing to divide the interior of the wing, in which a branch wing vein I being substantially parallel to one side of the main wing vein to form a space for the installation of a group of primary feather blades and a group of secondary feather blades; the primary feather blade group and the secondary feather blade group are separated by a branch wing vein II, and the drive shaft is mounted on the branch wing vein II. 4. Structure d'aile ouverte-fermée d'un aéronef à ailes battantes à combinaison, selon la revendication 3, dans laquelle des rainures de glissement sont prévues aux positions correspondantes de la veine de l'aile de la branche I et de la veine principale pour l'installation du groupe de pales de plumes primaire et du groupe de pales de plumes secondaire.4. Open-closed wing structure of a combination winged aircraft, according to claim 3, in which sliding grooves are provided at the corresponding positions of the branch vein of the branch I and of the vein. main for the installation of the primary feather blade group and the secondary feather blade group. 5. Structure d'aile ouverte-fermée d'un aéronef à ailes battantes à combinaison, selon la revendication 4, dans laquelle une largeur effective de la rainure de glissement est égale à la somme de l'épaisseur de la pale à caractéristique fixe et de l'épaisseur de la pale à caractéristique mobile.5. Open-closed wing structure of a combination winged aircraft, according to claim 4, in which an effective width of the sliding groove is equal to the sum of the thickness of the blade with a fixed characteristic and the thickness of the blade with a moving characteristic. 6. Structure d'aile ouverte-fermée d'un aéronef à ailes battantes à combinaison, selon la revendication 1, dans laquelle les pales fixes et les pales mobiles respectives du groupe de pales de plumes primaire et du groupe de pales de plumes secondaire ont la même taille et la même forme, et la largeur de la pale mobile est légèrement supérieure à la distance vide entre deux pales fixes.The open-closed wing structure of a combination winged aircraft, as claimed in claim 1, wherein the respective fixed blades and movable blades of the primary feather blade group and the secondary feather blade group have the same size and shape, and the width of the movable blade is slightly greater than the empty distance between two fixed blades. 7. Structure d'aile ouverte-fermée d'un aéronef à ailes battantes à combinaison, selon la revendication 1, dans laquelle le groupe de pales de plumes secondaire comprend deux pales fixes et deux pales mobiles, dans laquelle une pale mobile étant adjacente à la base de l'aile, puis une pale fixe, l'autre pale mobile et l'autre pale fixe sont successivement disposées dans le sens allant vers l'extérieur l'aile ; et les deux pales mobiles sont respectivement connectées à la liaison de transmission I.7. Open-closed wing structure of a combination flapping wing aircraft, according to claim 1, in which the group of secondary feather blades comprises two fixed blades and two movable blades, in which a movable blade being adjacent to the base of the wing, then a fixed blade, the other movable blade and the other fixed blade are successively arranged in the outward direction of the wing; and the two movable blades are respectively connected to the transmission link I. 8. Structure d'aile ouverte-fermée d'un aéronef à ailes battantes à combinaison, selon la revendication 1, dans laquelle le groupe de pales de plumes primaire comprend deux pales fixes et deux pales mobiles, dans laquelle une pale fixe étant adjacente au groupe de pales de plumes secondaire, puis une pale mobile, l'autre pale fixe et l'autre pale mobile sont successivement disposées dans la direction d'extension vers l'extérieur le long de l'aile ; et les deux pales mobiles sont respectivement connectées à la liaison de transmission II.8. The open-closed wing structure of a combination winged aircraft, according to claim 1, in which the group of primary feather blades comprises two fixed blades and two movable blades, in which a fixed blade being adjacent to the group of secondary feather blades, then a movable blade, the other fixed blade and the other movable blade are successively arranged in the direction of extension towards the outside along the wing; and the two movable blades are respectively connected to the transmission link II. 9. Structure d'aile ouverte-fermée d'un aéronef à ailes battantes à combinaison, selon la revendication 1, dans laquelle le mouvement unique du piston dans la liai5 son entraînée par le piston vers la position la plus éloignée est synchronisé avec le mouvement unique du socle d'entraînement vers la position la plus éloignée de l’extrémité gauche de la pale secondaire fixe ; et la pente de toute la surface de l'aile par rapport au corps de base reliant l'aile au fuselage est comprise entre 45° et 150 °.9. Open-closed wing structure of a combination winged aircraft, according to claim 1, wherein the single movement of the piston in the link driven by the piston to the most distant position is synchronized with the movement. single from the drive base to the position furthest from the left end of the fixed secondary blade; and the slope of the entire surface of the wing relative to the base body connecting the wing to the fuselage is between 45 ° and 150 °.
LU101146A 2017-10-10 2017-11-06 An open-close wing structure of a combination-drive flapping-wing aircraft LU101146B1 (en)

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CN201710935093.0A CN107757916B (en) 2017-10-10 2017-10-10 Flapping wing aircraft open-close type wing structure based on hybrid drive

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WO2019071676A1 (en) 2019-04-18

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