CN115610640B - Flapping wing folding mechanism for flapping wing aircraft - Google Patents
Flapping wing folding mechanism for flapping wing aircraft Download PDFInfo
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- CN115610640B CN115610640B CN202211101009.2A CN202211101009A CN115610640B CN 115610640 B CN115610640 B CN 115610640B CN 202211101009 A CN202211101009 A CN 202211101009A CN 115610640 B CN115610640 B CN 115610640B
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- 230000006978 adaptation Effects 0.000 claims abstract description 12
- 238000003780 insertion Methods 0.000 claims abstract description 11
- 230000037431 insertion Effects 0.000 claims abstract description 11
- 238000000034 method Methods 0.000 claims description 3
- 230000033001 locomotion Effects 0.000 description 7
- 230000005540 biological transmission Effects 0.000 description 4
- 238000009434 installation Methods 0.000 description 3
- 230000001360 synchronised effect Effects 0.000 description 3
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 2
- 238000012544 monitoring process Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000002146 bilateral effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000009977 dual effect Effects 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 239000011664 nicotinic acid Substances 0.000 description 1
- 230000002265 prevention Effects 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/30—Parts of fuselage relatively movable to reduce overall dimensions of aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C33/00—Ornithopters
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C33/00—Ornithopters
- B64C33/02—Wings; Actuating mechanisms therefor
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Toys (AREA)
Abstract
The invention discloses a flapping wing folding mechanism for a flapping wing aircraft, and belongs to the technical field of flapping wing aircraft. Comprises a folding structure and an axial locking structure; the turning structure comprises two tangent plane cylinders and a cylinder connecting structure; the two tangent plane cylinders are connected together through a cylinder connecting structure, the inner ends of the two tangent plane cylinders are cylinder connecting ends, and the two cylinder connecting ends are mutually matched oblique planes; the column connecting structure comprises a core body and a core body assembling cavity arranged in the connecting column; the core body comprises a rotating shaft and a rotating shaft positioning piece, wherein the rotating shaft positioning piece comprises a threaded connector arranged at one end of the rotating shaft and a sliding connector arranged at the other end of the rotating shaft; the core assembly cavity comprises a core insertion hole, a sliding connector adaptation cavity, a rotating shaft sliding adaptation cavity and a threaded connector adaptation cavity which are communicated in sequence; the axial locking structure comprises a connecting column fixing sleeve and a connecting column fixing external thread arranged at the outer end of a tangent plane cylinder. Has the characteristics of convenient operation, reasonable structure, convenient outdoor carrying and the like.
Description
Technical Field
The invention relates to the technical field of flapping wing aircrafts.
Background
The bionic ornithopter has the advantages of simulating flying organisms, has the characteristics of good concealment, high flying efficiency, small noise, good maneuvering performance and the like, and can assist land battlefield operations, urban cluster operations, aerial concealed patrol and the like in the military field. The system can be used for tasks such as bird expelling at airports, forest fire prevention monitoring, environment management, traffic monitoring, burst field rescue, urban security supervision and the like in the civil field.
For most single-section flapping wings, the occupied area of the flapping wings is large, the whole area can not be reduced by folding a horn like a four-rotor wing, so that the flapping wings are convenient to carry, the phenomenon is particularly obvious on the flapping wings with large wingspan, for example, the flapping wings of the flapping wing aircraft in the field are deployed to 1.8m, the width of a body part is not more than 0.2m, the flapping wings are single-section wings, and the flapping wings must be detached when the flapping wings are carried, so that the flapping wings are very inconvenient to carry.
Disclosure of Invention
The invention aims to solve the technical problem of providing a flapping wing folding mechanism for a flapping wing aircraft, which has the characteristics of convenience in operation, reasonable structure, convenience in outdoor carrying and the like.
In order to solve the technical problems, the invention adopts the following technical scheme:
A flapping wing folding mechanism for a flapping wing aircraft comprises a folding structure and an axial locking structure;
the turning structure comprises two tangent plane cylinders and a cylinder connecting structure;
The two tangent plane cylinders are connected together through a cylinder connecting structure, the inner ends of the two tangent plane cylinders are cylinder connecting ends, and the two cylinder connecting ends are mutually matched chamfer surfaces, so that when the two chamfer surfaces are integrally and correspondingly closely attached together, the two tangent plane cylinders form a coaxial connecting column;
the column connecting structure comprises a core body and a core body assembling cavity arranged in the connecting column;
The core body comprises a rotating shaft and a rotating shaft positioning piece, wherein the rotating shaft positioning piece comprises a threaded connector arranged at one end of the rotating shaft and a sliding connector arranged at the other end of the rotating shaft, a screw hole or a threaded hole is formed in the threaded connector, the sliding connector is a truncated cone body or a tangential sphere coaxial with the rotating shaft, the diameter of the tangential sphere is smaller than that of the sphere, and the small bottom surface of the truncated cone body or the tangential surface of the tangential sphere is fixedly connected with the other end of the rotating shaft;
The core assembly cavity comprises a core insertion hole, a sliding connector adaptation cavity, a rotating shaft sliding adaptation cavity and a threaded connector adaptation cavity which are communicated in sequence; the core body inserting hole is communicated with the cylindrical surface of one of the tangent plane cylinders and is used for inserting a core body, the core body inserting hole passes through the centers of the oblique planes of the two tangent plane cylinders, the line perpendicular to the oblique planes of the two tangent plane cylinders is the axial lead of the core body assembling cavity, the core body assembling cavity is arranged along the axial lead of the core body assembling cavity, the threaded connector assembling cavity is used for accommodating a threaded connector, a bolt mounting hole leading to the threaded connector assembling cavity is radially arranged along the tangent plane cylinders, the rotating shaft sliding cavity is used for being in sliding fit with the rotating shaft so that the two tangent plane cylinders are rotationally connected together through the rotating shaft, the cavity wall of the sliding connector assembling cavity, which is close to one side of the rotating shaft sliding matching cavity, is a sliding connector stop wall, and the sliding connector stop wall is in sliding fit with the contact surface of the sliding connector;
One end of the threaded connector of the core body is inserted by the core body insertion hole until the sliding connector is stopped by the stop wall of the sliding connector, so that the core body is determined to be installed in place, and a bolt is fixedly connected with a screw hole or a threaded hole of the threaded connector through a bolt installation hole in a threaded manner so as to be matched with the stop wall of the sliding connector to axially and fixedly connect the two tangent plane cylinders together; so that the inclined surfaces of the two tangent plane cylinders are closely adhered together and can relatively rotate by taking the rotating shaft as the axis, and coaxial connecting columns or connecting columns with different turning angles are formed in the process of relatively rotating;
The axial locking structure comprises a connecting column fixing sleeve and a connecting column fixing external thread arranged at the outer end of one tangent plane cylinder, wherein the connecting column fixing sleeve is coaxially provided with a connecting column fixing internal thread matched with the connecting column fixing external thread and a column cavity matched with the connecting column;
the end part of the connecting column fixing external thread is used for fixedly connecting with other parts and is an external connecting end of the folding structure; the outer end part of the tangent plane cylinder which is not provided with the external thread for fixing the connecting column is used for being fixedly connected with other parts and is an external connecting end of another turning structure.
The invention is further improved in that:
The threaded connection body is a square body, the threaded connection body adapting cavity is a sliding matching cavity adapting to the square body, so that the core body is circumferentially positioned in the core body assembling cavity, and after the core body is installed in place, a screw hole or a threaded hole on the threaded connection body is just aligned with the bolt installing hole, so that the installation of the bolt is facilitated.
The core body insertion hole is positioned on a tangent plane cylinder provided with a connecting column fixing external thread.
The beneficial effects of adopting above-mentioned technical scheme to produce lie in:
The pair of flapping arms are connected with the pair of flapping arm connecting beams through a flapping wing folding mechanism; the auxiliary beams are hinged with the machine body through a detachable structure; the flapping wings are in a waiting state through the coaxial locking state of the flapping wing folding mechanism; the flapping wings can be in a folding state through the folding state of the flapping wing folding mechanism, so that the occupied area of the flapping wings is reduced, and the carrying is convenient.
The portable outdoor portable device has the characteristics of convenience in operation, reasonable structure, convenience in outdoor carrying and the like.
Drawings
FIG. 1 is a schematic structural view of a flapping-wing aircraft with foldable flapping wings;
FIG. 2 is a schematic structural view of a flapping wing of the ornithopter in a folded state;
FIG. 3 is a schematic view of the flapping-wing and double-wing flapping mechanism and fuselage connection structure of FIG. 1;
FIG. 4 is a schematic view of the assembled structure of the flap folding mechanism of FIG. 1;
FIG. 5 is a cross-sectional view A-A of FIG. 4;
FIG. 6 is a schematic view of the structure of the core of FIG. 4;
FIG. 7 is a schematic view of the structure of the flapping wing folding mechanism connected with the flapping arm in a coaxially locked state;
FIG. 8 is a schematic view of the structure of the flapping wing folding mechanism in a folded state connected with the flapping arm;
FIG. 9 is a B-B cross-sectional view of FIG. 8;
FIG. 10 is a schematic view of a connection structure of a flapping wing and a flapping wing folding mechanism in a standby state;
FIG. 11 is a schematic diagram of a connection structure of a flapping wing to a folding state of a flapping wing folding mechanism;
FIG. 12 is a schematic structural view of the dual wing flutter mechanism of FIG. 1;
In the drawings: 1. a body; 2. tail rudders; 3. a flapping arm; 4. a wing body; 5. the flutter arm is connected with the beam; 6. an auxiliary beam; 7. cutting a cylinder; 7-1, chamfering; 8. a rotating shaft; 9. a threaded connection; 9-1, a threaded hole; 10. cutting a sphere; 11. a core insertion hole; 12. a sliding connector adapter cavity; 13. a rotating shaft sliding cavity; 14. a threaded connector adapter cavity; 14-1, bolt mounting holes; 15. a connecting column fixing sleeve; 16. the connecting column is fixedly provided with external threads; 17. a flapping wing drive motor; 18. a driving arm; 19. a drive gear; 20. a crank; 21. a motor shaft gear; 22. a primary gear; 23. a secondary gear.
Detailed Description
The invention will be described in further detail with reference to the drawings and the specific embodiments.
For ease of illustration, a flapping-wing aircraft with foldable flapping wings will be described in detail as an example.
Standard parts used in the invention can be purchased from the market, special-shaped parts can be customized according to the description of the specification and the drawings, and the specific connection modes of the parts adopt conventional means such as mature bolts, rivets, welding, pasting and the like in the prior art, and the detailed description is omitted.
As can be seen from the embodiments shown in fig. 1 to 12, the present embodiment includes a fuselage 1, a flight control system [ Pixracer Mini flight control system ], a double-wing flapping mechanism including a pair of flapping arms 3, a pair of flapping-arms 2 symmetrically disposed on left and right sides of the double-wing flapping mechanism, the flapping wings including a wing body 4, a flapping-arm connecting beam 5 and an auxiliary beam 6, respectively; the flapping arm connecting beam 5 is arranged at the front end of one side of the wing body 4 close to the body 1 and is used for being connected with the flapping arm 3, and the pair of flapping arms 3 symmetrically arrange the pair of flapping wings at the left side and the right side of the double-wing flapping mechanism through the flapping arm connecting beam 5; the auxiliary beam 6 is arranged at the rear end of one side of the wing body 4, which is close to the machine body 1, and is used for being hinged with the machine body 1 to generate auxiliary support for the flapping wings, and the double-wing flapping mechanism drives a pair of flapping wings to generate flapping wing movement through a pair of flapping arms 3;
the pair of flapping arms 3 are connected with the pair of flapping arm connecting beams 5 through a flapping wing folding mechanism; a pair of auxiliary beams 6 are hinged with the machine body 1 through a detachable structure;
The flapping wing folding mechanism comprises a folding structure and an axial locking structure;
the turning structure comprises two tangent plane cylinders 7 and a cylinder connecting structure;
the two tangent plane cylinders 7 are connected together through a cylinder connecting structure, the inner ends of the two tangent plane cylinders 7 are cylinder connecting ends, and the two cylinder connecting ends are mutually matched chamfer surfaces 7-1, so that when the two chamfer surfaces 7-1 are integrally and correspondingly closely attached together, the two tangent plane cylinders 7 form a coaxial connecting column;
the column connecting structure comprises a core body and a core body assembling cavity arranged in the connecting column;
The core body comprises a rotating shaft 8 and a rotating shaft positioning piece, wherein the rotating shaft positioning piece comprises a threaded connector 9 arranged at one end of the rotating shaft 8 and a sliding connector arranged at the other end of the rotating shaft 8, a screw hole or a screw hole 9-1 is arranged on the threaded connector 9, the sliding connector is a truncated cone body or a tangential plane sphere 10 coaxial with the rotating shaft 8, the diameter of the tangential plane sphere 10 is smaller than that of the sphere, and the small bottom surface of the truncated cone body or the tangential plane of the tangential plane sphere 10 is fixedly connected with the other end of the rotating shaft 8;
The core assembly cavity comprises a core insertion hole 11, a sliding connector adaptation cavity 12, a rotating shaft sliding adaptation cavity 13 and a threaded connector adaptation cavity 14 which are communicated in sequence; the core inserting hole 11 is communicated with the cylindrical surface of one of the tangent plane cylinders 7 and is used for inserting a core, the core passes through the centers of the oblique planes 7-1 of the two tangent plane cylinders 7, the line perpendicular to the oblique planes 7-1 of the two tangent plane cylinders 7 is the axial lead of a core assembling cavity, the core assembling cavity is arranged along the axial lead of the core assembling cavity, the threaded connector assembling cavity 14 is used for accommodating the threaded connector 9, the threaded connector assembling cavity 14 is radially provided with a bolt mounting hole 14-1 leading to the threaded connector assembling cavity 14 along the tangent plane cylinders 7, the rotating shaft sliding matching cavity 13 is used for sliding fit with the rotating shaft 8 so that the two tangent plane cylinders 7 are connected together through the rotating shaft 8 in a rotating way, the cavity wall of one side of the sliding connector assembling cavity 12, which is close to the rotating shaft sliding matching cavity 13, is a sliding connector stop wall, and the sliding connector contact surface is in sliding fit;
one end of the threaded connector 9 of the core is inserted into the core insertion hole 11 until the sliding connector is stopped by the stop wall of the sliding connector, so that the core is fixed in place, and a bolt is fixedly connected with a screw hole or a screw hole 9-1 of the threaded connector 9 through a bolt mounting hole 14-1 in a threaded manner so as to be matched with the stop wall of the sliding connector to axially and fixedly connect the two tangent plane cylinders 7 together; so that the inclined planes 7-1 of the two tangent plane cylinders 7 are closely adhered together and can relatively rotate by taking the rotating shaft 8 as the axis, and coaxial connecting columns or connecting columns with different turning angles are formed in the process of relatively rotating;
The axial locking structure comprises a connecting column fixing sleeve 15 and a connecting column fixing external thread 16 arranged at the outer end of one tangent plane cylinder 7, wherein a connecting column fixing internal thread matched with the connecting column fixing external thread 16 and a column cavity matched with the connecting column are arranged on the coaxial center of the connecting column fixing sleeve 15, when two tangent plane cylinders 7 form a coaxial connecting column, the connecting column fixing sleeve 15 and the connecting column fixing external thread 16 are screwed together, and the connecting column is fixed by the column cavity to prevent the two tangent plane cylinders 7 from rotating relative to the rotating shaft 8, so that the connecting column is prevented from being folded;
the end part of the connecting column fixing external thread 16 is used for fixedly connecting with other parts and is an external connecting end of a folding structure; the outer end part of the tangent plane cylinder 7 without the connecting column fixing external thread 16 is used for fixedly connecting with other parts and is an external connecting end of another turning structure;
The external connecting ends of the two folding structures are fixedly connected with the flapping arm 3 and the flapping arm connecting beam 5 respectively; when the flapping wing aircraft is ready to take off, the two tangent plane cylinders 7 are relatively rotated to form a coaxial connecting column, the connecting column fixing sleeve 15 is screwed with the connecting column fixing external screw thread 16, and the connecting column is fixed by the column cavity, so that a pair of flapping wings are symmetrically arranged on the left side and the right side of the double-wing flapping mechanism; when the flapping wing aircraft is carried, the pair of auxiliary beams 6 are detached from the aircraft body 1 through the detachable structure, the connecting column fixing sleeve 15 is separated from the connecting column fixing external threads 16, the constraint on the connecting column is relieved by the column type cavity, the two tangent plane cylinders 7 are relatively rotated to form a certain degree of turning angle, and the pair of flapping wings are in a folded state, so that the occupation area of the flapping wings is reduced, and the flapping wing aircraft is convenient to carry.
The pair of flapping wings can be folded into an upward vertical state through the flapping wing folding mechanism, the folding angle and the folding direction of the flapping wings are related to the inclination angles of the two chamfer surfaces 7-1 and the directions of the chamfer surfaces, and the flapping wings can be obtained through calculation or limited times of experiments and are not repeated herein.
The threaded connector 9 is a square body, the threaded connector adapting cavity 14 is a sliding matching cavity adapting to the square body, so that the core body is circumferentially positioned in the core body assembling cavity, and after the core body is installed in place, a screw hole or a threaded hole 9-1 on the threaded connector 9 is just aligned with the bolt installing hole 14-1, so that the installation of a bolt is facilitated.
The core body insertion hole 11 is positioned on the tangent plane cylinder 7 provided with a connecting column fixing external thread 16, and the end part of the connecting column fixing external thread 16 is fixedly connected with the flapping arm connecting beam 5.
The specific structure of the pair of auxiliary beams 6 hinged with the machine body 1 through the detachable structure is as follows: the machine body 1 is provided with a hinge shaft which is fixedly connected with the machine body 1 through a nut. The end of the auxiliary beam 6 is provided with a hinge hole which is hinged with a hinge shaft.
The double wing flapping mechanism comprises a flapping wing driving motor 17 [ model: TMotor AT2308 kv 1450) and a flutter motion driving structure; the flapping motion driving structure comprises a pair of flapping arms 3, a flapping arm driving wheel and a pair of driving arms 18, wherein the inner ends of the pair of flapping arms 3 are respectively hinged with the machine body 1; the flapping arm driving wheel comprises a driving gear 19 and a pair of cranks 20, the cranks 20 are symmetrically arranged on the left side and the right side of the driving gear 19, the upper ends of the driving arms 18 are respectively connected with the spherical hinges of the flapping arms 3, and the lower ends of the driving arms 18 are respectively connected with the spherical hinges of the cranks 20, so that the flapping motion driving structure is in a bilateral symmetry structure; the flapping wing driving motor 17 drives the driving gear 19 to rotate through a gear transmission structure so as to make a pair of cranks 20 perform synchronous eccentric motion, and makes a pair of flapping arms 3 perform symmetrical synchronous flapping motion through a pair of driving arms 18 so as to make a pair of flapping wings perform synchronous flapping motion to generate uniform lifting force.
The gear transmission structure in the double-wing flapping mechanism comprises a motor shaft gear 21 arranged on the rotating shaft of the flapping wing driving motor 17, a primary gear 22 and a secondary gear 23, wherein the primary gear 22 and the secondary gear 23 are coaxially arranged, the diameter of the primary gear 22 is larger than that of the secondary gear 23, the motor shaft gear 21 is in meshed transmission connection with the primary gear 22, and the secondary gear 23 is in meshed transmission connection with the driving gear 19.
Claims (3)
1. A flapping wing folding mechanism for a flapping wing air vehicle, which is characterized in that: comprises a folding structure and an axial locking structure;
The folding structure comprises two tangent plane cylinders (7) and a cylinder connecting structure;
The two tangent plane cylinders (7) are connected together through a cylinder connecting structure, the inner ends of the two tangent plane cylinders (7) are cylinder connecting ends, and the two cylinder connecting ends are mutually matched inclined planes (7-1), so that when the two inclined planes (7-1) are integrally and correspondingly closely attached together, the two tangent plane cylinders (7) form a coaxial connecting column;
the cylinder connecting structure comprises a core body and a core body assembling cavity arranged in the connecting column;
The core body comprises a rotating shaft (8) and a rotating shaft positioning piece, wherein the rotating shaft positioning piece comprises a threaded connector (9) arranged at one end of the rotating shaft (8) and a sliding connector arranged at the other end of the rotating shaft (8), a screw hole or a threaded hole (9-1) is formed in the threaded connector (9), the sliding connector is a truncated cone body or a tangent plane sphere (10) coaxial with the rotating shaft (8), the diameter of the tangent plane sphere (10) is smaller than that of the sphere, and the tangent plane of the small bottom surface or the tangent plane sphere (10) of the truncated cone body is fixedly connected with the other end of the rotating shaft (8);
The core assembly cavity comprises a core insertion hole (11), a sliding connector adaptation cavity (12), a rotating shaft sliding adaptation cavity (13) and a threaded connector adaptation cavity (14) which are sequentially communicated; the core inserting hole (11) is communicated with the cylindrical surface of one of the tangent plane cylinders (7) and is used for inserting the core, the center of an inclined tangent plane (7-1) passing through the two tangent plane cylinders (7) is used for enabling the two tangent plane cylinders (7) to be rotationally connected together through the rotating shaft (8), the core assembling cavity is arranged along the core assembling cavity axis, the threaded connector adapting cavity (14) is used for accommodating the threaded connector (9), a bolt mounting hole (14-1) leading to the threaded connector adapting cavity (14) is radially arranged along the tangent plane cylinders (7), the rotating shaft sliding adapting cavity (13) is used for being in sliding fit with the rotating shaft (8), so that the two tangent plane cylinders (7) are rotationally connected together through the rotating shaft (8), and the cavity wall of one side of the sliding connector adapting cavity (12) close to the rotating shaft sliding adapting cavity (13) is a sliding connector stop wall, and the sliding connector stop wall is in sliding contact with the sliding connector surface;
One end of a threaded connector (9) of the core body is inserted into the core body insertion hole (11) until the sliding connector is stopped by the sliding connector stopping wall, so that the core body is fixed in place, and a bolt is fixedly connected with a screw hole or a threaded hole (9-1) of the threaded connector (9) through the bolt mounting hole (14-1) in a threaded manner so as to be matched with the sliding connector stopping wall to axially and fixedly connect the two tangent plane cylinders (7) together; so that the inclined planes (7-1) of the two tangent plane cylinders (7) are closely adhered together and can relatively rotate by taking the rotating shaft (8) as the axis, and connecting columns with the same axis or connecting columns with different turning angles are formed in the process of relatively rotating;
The axial locking structure comprises a connecting column fixing sleeve (15) and a connecting column fixing external thread (16) arranged at the outer end of one tangent plane cylinder (7), wherein a connecting column fixing internal thread matched with the connecting column fixing external thread (16) and a column cavity matched with the connecting column are coaxially arranged on the connecting column fixing sleeve (15), when two tangent plane cylinders (7) form a concentric connecting column, the connecting column fixing sleeve (15) and the connecting column fixing external thread (16) are screwed together, and the column cavity fixes the connecting column so as to prevent the two tangent plane cylinders (7) from rotating relative to the rotating shaft (8), and further prevent the connecting column from being folded;
The end part of the connecting column fixing external thread (16) is used for fixedly connecting with other parts and is an external connecting end of a folding structure; the outer end part of the tangent plane cylinder (7) which is not provided with the connecting column fixing external thread (16) is used for being fixedly connected with other parts and is an external connecting end of another turning structure.
2. A flapping wing folding mechanism for a flapping wing air vehicle according to claim 1, wherein: the threaded connector (9) is a square body, the threaded connector adapting cavity (14) is a sliding cavity adapted to the square body, so that the core body is circumferentially positioned in the core body assembling cavity, and after the core body is installed in place, a screw hole or a threaded hole (9-1) in the threaded connector (9) is just aligned to the bolt installing hole (14-1), so that the bolt is conveniently installed.
3. A flapping wing folding mechanism for a flapping wing air vehicle according to claim 2, wherein: the core body insertion hole (11) is positioned on the tangent plane cylinder (7) provided with the connecting column fixing external thread (16).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211101009.2A CN115610640B (en) | 2022-09-09 | 2022-09-09 | Flapping wing folding mechanism for flapping wing aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211101009.2A CN115610640B (en) | 2022-09-09 | 2022-09-09 | Flapping wing folding mechanism for flapping wing aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN115610640A CN115610640A (en) | 2023-01-17 |
| CN115610640B true CN115610640B (en) | 2024-05-03 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211101009.2A Active CN115610640B (en) | 2022-09-09 | 2022-09-09 | Flapping wing folding mechanism for flapping wing aircraft |
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| CN (1) | CN115610640B (en) |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108945430A (en) * | 2018-07-16 | 2018-12-07 | 武汉科技大学 | A kind of-bionic flapping-wing flying vehicle of active twist combination drive of fluttering-fold |
| WO2020260394A1 (en) * | 2019-06-28 | 2020-12-30 | Airbus Operations Gmbh | Wing for an aircraft |
| CN112590477A (en) * | 2020-12-25 | 2021-04-02 | 南京航空航天大学 | Bird-like robot with air flight and ground running functions |
-
2022
- 2022-09-09 CN CN202211101009.2A patent/CN115610640B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108945430A (en) * | 2018-07-16 | 2018-12-07 | 武汉科技大学 | A kind of-bionic flapping-wing flying vehicle of active twist combination drive of fluttering-fold |
| WO2020260394A1 (en) * | 2019-06-28 | 2020-12-30 | Airbus Operations Gmbh | Wing for an aircraft |
| CN112590477A (en) * | 2020-12-25 | 2021-04-02 | 南京航空航天大学 | Bird-like robot with air flight and ground running functions |
Non-Patent Citations (1)
| Title |
|---|
| 微型扑翼飞行器升力特性研究;张亚锋;宋笔锋;袁昌盛;吉国明;;空气动力学学报;20081215(04);全文 * |
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| CN115610640A (en) | 2023-01-17 |
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