CN107697284B - Double-section bionic flapping wing unmanned aerial vehicle wing - Google Patents
Double-section bionic flapping wing unmanned aerial vehicle wing Download PDFInfo
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- CN107697284B CN107697284B CN201710815461.8A CN201710815461A CN107697284B CN 107697284 B CN107697284 B CN 107697284B CN 201710815461 A CN201710815461 A CN 201710815461A CN 107697284 B CN107697284 B CN 107697284B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C33/00—Ornithopters
- B64C33/02—Wings; Actuating mechanisms therefor
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
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Abstract
The invention discloses a double-section bionic flapping wing unmanned aerial vehicle wing which is sequentially hinged by a body, an aileron and a main wing from inside to outside; the main wing comprises a bionic wing-shaped rib plate I, a bionic wing-shaped rib plate II and a transmission rod, the maximum thickness of the bionic wing-shaped rib plate I is positioned at the position 19.86% of the chord length, the maximum curvature is positioned at the position 49.32% of the chord length, when the chord length is 1 unit length, the maximum thickness is 0.1076, and the maximum curvature is 0.1089; the maximum thickness of the bionic wing-shaped rib plate II No. 6 is located at the position of 16.64% of the chord length, the maximum bending degree is located at the position of 42.68% of the chord length, and when the chord length is the unit length 1, the maximum thickness is 0.1084, and the maximum bending degree is 0.1097. The invention inherits the good characteristics of the carrier pigeon, carries out bionic design on the plane parameters and the section wing profiles of the main wing and the auxiliary wing of the wing, improves the pneumatic efficiency and the flexibility of the aircraft, has faster flight lifting, and shows that the carrier pigeon has good lift-drag characteristics and flexibility.
Description
Technical Field
The invention belongs to the technical field of aviation, and particularly relates to a double-section bionic flapping wing unmanned aerial vehicle wing.
Background
The research of unmanned planes is the key point of the research in the military field of all countries, and the miniaturized and miniaturized aircraft is a new trend of unmanned plane development.
The flying speed per hour of the micro aircraft is only dozens of kilometers, and the flying Reynolds number is 2 multiplied by 105Left and right. On one hand, the pneumatic viscous force and the resistance are more prominent under the condition of low Reynolds number; the boundary layer of the fuselage tends to have laminar flow characteristics; separation of the boundary layer of the wing from the wing is liable to occurAnd loses lift. Therefore, the traditional fixed wing and rotor aircraft research method is not applicable any more, and the flapping wing flight mode needs to be researched. On the other hand, the miniature aircraft is small in size, and the aerodynamic efficiency and flexibility of the aircraft must be improved while the weight is reduced. The wings are main components of the aircraft for generating lift force, the aerodynamic performance of the wings is the basis of the design of the aircraft, and factors influencing the aerodynamic performance are wing plane parameters and wing profiles. Therefore, obtaining wing plane parameters and airfoils with excellent performance is the key to improving aerodynamic efficiency.
Disclosure of Invention
Aiming at the defects in the prior art, the invention provides a double-section bionic flapping wing unmanned aerial vehicle wing, so that the aerodynamic efficiency and flexibility of the wing are improved while the weight of the wing is reduced. The technical scheme of the invention is as follows by combining the attached drawings of the specification:
a double-section bionic flapping wing unmanned aerial vehicle wing comprises an aileron 2, a main wing 1 and a vehicle body 3, wherein each side of the wing is formed by connecting the aileron 2 and the main wing 1, the inner side of the aileron 2 is connected with the vehicle body 3 through a rotating shaft 4, and the main wing 1 is connected with the outer side of the aileron 2 through a hinge block 9;
the aileron 2 consists of four bionic wing-shaped rib plates I5, two transmission rods 7 and a support rod 8, wherein the four bionic wing-shaped rib plates I5 are vertically arranged on the two transmission rods 7 which are arranged in parallel up and down, the support rod 8 and the transmission rods 7 are arranged on the four bionic wing-shaped rib plates I5 in parallel, the support rod 8 is positioned at the rear side of the transmission rods 7, and the two transmission rods 7 are respectively hinged to one side of a hinge block 9;
the main wing 1 consists of a bionic wing-shaped rib plate I5, four bionic wing-shaped rib plates II 6 and a transmission rod 7, wherein the bionic wing-shaped rib plates I5 and the bionic wing-shaped rib plates II 6 are vertically arranged on the transmission rod 7, and the transmission rod 7 is hinged to the other side of the hinging block 9.
Further, the maximum thickness t of the bionic airfoil rib No. 5 is 19.86% of the chord length c, the maximum curvature f is 49.32% of the chord length c, when the chord length c is 1, the maximum thickness t is 0.1076, and the maximum curvature f is 0.1089;
the maximum thickness t of the bionic wing-shaped rib plate II No. 6 is located at the position of 16.64% of the chord length c, the maximum curvature f is located at the position of 42.68% of the chord length c, and when the chord length c is the unit length 1, the maximum thickness t is 0.1084, and the maximum curvature f is 0.1097.
More closely, the coordinate values corresponding to the airfoils of the bionic airfoil rib plate I5 and the bionic airfoil rib plate II 6 are as follows:
compared with the prior art, the invention has the beneficial effects that:
the invention provides a novel double-section bionic flapping wing unmanned aerial vehicle wing by utilizing the bionics principle, and improves the pneumatic efficiency and flexibility of an aircraft. The carrier pigeon can fly for a long time and a long distance, and the flying lift is fast, which shows that the carrier pigeon has good lift-drag characteristics and flexibility. The flapping wing unmanned aerial vehicle wing provided by the invention inherits the good characteristics of a homing pigeon, carries out bionic design on the plane parameters and the section wing profile of the main wing and the auxiliary wing of the wing, and has advancement and practicability. The wing provided by the invention has the advantages of simple structure, light weight, simple pneumatic layout, strong flexibility and the like.
Drawings
FIG. 1 is a schematic view of the overall structure of a wing of a dual-stage bionic flapping-wing unmanned aerial vehicle according to the invention;
FIG. 2 is a schematic view of a single-sided wing three-dimensional structure of a wing of a dual-section bionic flapping wing unmanned aerial vehicle according to the invention;
FIG. 3 is a schematic view of a connection structure between a main wing and an aileron in a wing of a dual-stage bionic flapping wing unmanned aerial vehicle according to the invention;
FIG. 4 is a schematic view of a first bionic wing rib plate in a wing of a dual-section bionic flapping wing unmanned aerial vehicle according to the invention;
FIG. 5 is a schematic view of a carrier pigeon wing shape I in a wing of a dual-stage bionic flapping wing unmanned aerial vehicle according to the present invention;
FIG. 6 is a schematic diagram of a second bionic wing-shaped rib plate in a wing of a dual-section bionic flapping wing unmanned aerial vehicle according to the invention;
FIG. 7 is a schematic view of a carrier pigeon wing shape II in a wing of a dual-stage bionic flapping wing unmanned aerial vehicle according to the present invention;
FIG. 8 shows that the angle of attack of the carrier pigeon wing type I, carrier pigeon wing type II and standard wing type NACA2412 is 0-20 deg. and Reynolds number is 105A time lift-drag ratio comparison curve chart;
FIG. 9 shows the angle of attack of the carrier pigeon wing type I, carrier pigeon wing type II and standard wing type NACA2412 of the present invention is 0-20 deg. and Reynolds number is 105Lift coefficient versus time plot.
In the figure:
1 main wing, 2 ailerons, 3 machine bodies, 4 rotating shafts,
5 bionic wing-shaped rib plates I, 6 bionic wing-shaped rib plates II, 7 transmission rods, 8 support rods,
9 hinging the block.
Detailed Description
The invention improves the defects of the existing wing-shaped wing by taking the characteristics of bird wings in the nature as reference, and takes the fact that the operation conditions of carrier pigeon flight and flapping wing aircrafts are most similar, the wing-shaped bionic flapping wing unmanned aerial vehicle wing is optimized by carrier pigeon wing plane parameters and wing-shaped sections obtained by reverse engineering, and the wing-shaped bionic flapping wing unmanned aerial vehicle wing is provided, so that the aerodynamic efficiency and flexibility of the wing are improved while the weight of the wing is reduced. In order to further illustrate the technical scheme of the invention, the specific implementation mode of the invention is as follows by combining the attached drawings of the specification:
as shown in figure 1, the invention provides a double-section bionic flapping wing unmanned aerial vehicle wing, which is a double-section wing and consists of an aileron 2, a main wing 1 and a body 3. The wing is of an axisymmetric structure, each side of the wing is formed by connecting an aileron 2 and a main wing 1, wherein the inner side of the aileron 2 is connected with a machine body 3 through a rotating shaft 4, and the main wing 1 is connected with the outer side of the aileron 2 through a hinged block 9.
As shown in fig. 2 and 3, the aileron 2 is composed of four bionic wing-shaped rib plates I5, two transmission rods 7 and a support rod 8; the main wing 1 consists of a bionic wing-shaped rib plate I5, four bionic wing-shaped rib plates II 6 and a transmission rod 7; two transmission rods 7 of the ailerons 2 are arranged in parallel up and down and are respectively hinged with one side of the hinge block 9 at two points up and down, one transmission rod 7 of the main wing 1 is hinged with one point above the other side of the hinge block 9, so that the main wing 1 is hinged with the ailerons 2 through the hinge block 9, and the main wing 1 and the ailerons 2 can swing up and down relatively in the vertical direction.
The wing is of an axisymmetric structure, the length of a single-side wing is 400 +/-40 mm, the length ratio of a main wing to a secondary wing is 3:2, the total area of the wing is 0.09 square meter +/-0.01 square meter, and the aspect ratio is 8.1 +/-0.2.
The first bionic wing-shaped rib plates 5 of the aileron 2 are arranged on two transmission rods 7 of the aileron 2 in parallel at equal intervals; the first four bionic wing-shaped rib plates 5 are vertically arranged on the transmission rod 7, the maximum thickness position of the first bionic wing-shaped rib plate 5 is connected with the transmission rod 7, the support rods 8 and the transmission rod 7 are arranged on the first four bionic wing-shaped rib plates 5 in parallel, and the support rods 8 are located on the rear side of the transmission rod 7.
A bionic wing-shaped rib plate I5 and four bionic wing-shaped rib plates II 6 of the main wing 1 are sequentially and equidistantly arranged on a transmission rod 7 of the main wing 1 in parallel from inside to outside; the first bionic wing-shaped rib plate 5 and the second bionic wing-shaped rib plate 6 are both vertically arranged on the transmission rod 7, the maximum thickness t of the first bionic wing-shaped rib plate 5 is connected with the transmission rod 7, and the maximum thickness t of the second bionic wing-shaped rib plate 6 is connected with the transmission rod 7.
As shown in fig. 4, a transmission rod mounting hole and a support rod mounting hole are respectively formed in the front and at the rear of the maximum thickness t position of the bionic wing rib plate I No. 5. As shown in fig. 5, the bionic airfoil rib plate number one 5 is taken from the wing half-span of the homing pigeon, the bionic airfoil rib plate number one 5 takes the root of the wing of the homing pigeon as a starting position, and reaches a region at the position of 80% of the wing half-span of the homing pigeon, the maximum thickness t is at the position of 19.86% of the chord length c, the maximum camber f is at the position of 49.32% of the chord length c, and when the chord length c is the unit length 1, the maximum thickness t is 0.1076, and the maximum camber f is 0.1089.
As shown in fig. 6, a transmission rod mounting hole is formed at the maximum thickness position of the bionic wing-shaped rib plate II No. 6. As shown in fig. 7, the bionic airfoil rib plate No. two 6 is taken from the carrier pigeon wing semi-span, the bionic airfoil rib plate No. two 6 takes the root of the carrier pigeon wing as the starting position, and reaches the region at the position of 30% of the carrier pigeon wing semi-span, the maximum thickness t is at the position of 16.64% of the chord length c, the maximum camber f is at the position of 42.68% of the chord length c, when the chord length c is the unit length 1, the maximum thickness t is 0.1084, and the maximum camber f is 0.1097. The coordinate values corresponding to the first bionic wing-shaped rib plate and the second bionic wing-shaped rib plate meet the following table:
TABLE 1
As shown in figure 8, the carrier pigeon wing type I adopted by the bionic wing type rib plate I5, the carrier pigeon wing type II adopted by the bionic wing type rib plate II 6 and the standard wing type NACA2412 in the attack angle of 3-20 degrees and the Reynolds number of 10 are obtained through computer simulation5The comparison curve of lift-drag ratio can be seen from fig. 8, under the working condition, the lift-drag ratio of the carrier pigeon wing type II adopted by the bionic wing type rib plate II 6 in the main wing 1 of the wing is higher than that of the carrier pigeon wing type I and the standard wing type NACA2412, and the maximum lift-drag ratio is improved by 2.19 times.
As shown in fig. 9, the carrier pigeon wing type number one adopted by the bionic wing type rib plate number 5 and the carrier pigeon wing type number two adopted by the bionic wing type rib plate number 6 in the invention and the standard are obtained by computer simulationThe wing shape NACA2412 has an attack angle of 3-20 deg. and Reynolds number of 105The comparison curve of the lift coefficients can be seen from fig. 8, under the working condition, the lift coefficient of the carrier pigeon wing type I adopted by the bionic wing type rib plate I5 in the aileron 2 of the wing is higher than that of the carrier pigeon wing type II and the standard wing type NACA2412, and the maximum lift coefficient is improved by 1.91 times.
In summary, when the Reynolds number is 105When the attack angle is 3-20 degrees, the lift coefficients of the carrier pigeon wing shape I and the carrier pigeon wing shape II adopted by the wing are higher than those of the standard wing shape NACA2412, and the bionic wing type rib plate II 6 of the main wing 1 of the wing adopts the carrier pigeon wing shape II with higher lift-drag ratio as the bionic wing shape for generating enough thrust; the bionic wing section rib plates I and II 5 of the ailerons 2 adopt the carrier pigeon wing section I with higher lift coefficient as the bionic wing section to generate enough lift. Compared with the existing wings, the double-section bionic flapping wing unmanned aerial vehicle wing has the advantages that the aerodynamic efficiency is obviously improved, the main wing and the auxiliary wing respectively generate thrust and lift, and the flexibility of the flapping wing aircraft is greatly improved.
Claims (1)
1. The utility model provides a bionical flapping wing unmanned aerial vehicle wing of two segmentations, comprises aileron (2), main wing (1) and organism (3), its characterized in that:
each side is formed by connecting an aileron (2) and a main wing (1), wherein the inner side of the aileron (2) is connected with a machine body (3) through a rotating shaft (4), and the main wing (1) is connected with the outer side of the aileron (2) through a hinge block (9);
the aileron (2) consists of four bionic wing-shaped rib plates I (5), two transmission rods (7) and a support rod (8), wherein the four bionic wing-shaped rib plates I (5) are vertically arranged on the two transmission rods (7) which are arranged in parallel up and down, the support rod (8) and the transmission rods (7) are arranged on the four bionic wing-shaped rib plates I (5) in parallel, the support rod (8) is positioned at the rear side of the transmission rods (7), and the two transmission rods (7) are respectively hinged to one side of a hinge block (9);
the main wing (1) consists of a first bionic wing-shaped rib plate (5), a second bionic wing-shaped rib plate (6) and a transmission rod (7), the first bionic wing-shaped rib plate (5) and the second bionic wing-shaped rib plate (6) are vertically arranged on the transmission rod (7), and the transmission rod (7) is hinged to the other side of the hinge block (9);
the maximum thickness (t) of the bionic airfoil rib I (5) is located at the position of 19.86% of the chord length (c), the maximum camber (f) is located at the position of 49.32% of the chord length (c), and when the chord length (c) is 1 unit length, the maximum thickness (t) is 0.1076, and the maximum camber (f) is 0.1089;
the maximum thickness (t) of the bionic wing-shaped rib plate II (6) is positioned at the position of 16.64 percent of the chord length (c), the maximum camber (f) is positioned at the position of 42.68 percent of the chord length (c), when the chord length (c) is the unit length 1, the maximum thickness (t) is 0.1084, and the maximum camber (f) is 0.1097;
the coordinate values corresponding to the first bionic wing rib plate (5) and the second bionic wing rib plate (6) are as follows:
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710815461.8A CN107697284B (en) | 2017-09-12 | 2017-09-12 | Double-section bionic flapping wing unmanned aerial vehicle wing |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710815461.8A CN107697284B (en) | 2017-09-12 | 2017-09-12 | Double-section bionic flapping wing unmanned aerial vehicle wing |
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| Publication Number | Publication Date |
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| CN107697284A CN107697284A (en) | 2018-02-16 |
| CN107697284B true CN107697284B (en) | 2021-02-26 |
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| CN201710815461.8A Expired - Fee Related CN107697284B (en) | 2017-09-12 | 2017-09-12 | Double-section bionic flapping wing unmanned aerial vehicle wing |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN116176836A (en) * | 2023-02-17 | 2023-05-30 | 北京科技大学 | Bionic ornithopter steering mechanism based on cambered surface wings |
| CN116639275B (en) * | 2023-05-18 | 2024-05-28 | 北京科技大学 | Formation method of ornithopter |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR421783A (en) * | 1909-12-29 | 1911-03-04 | Hippolyte Lepape | Improvements made to air navigation devices and, more particularly, to those of these devices belonging to the ornithopter genus |
| FR2687125B1 (en) * | 1992-02-10 | 1997-09-26 | Roland Magallon | PILOTAGE AND PROPULSION DEVICE AND METHOD FOR AIRCRAFT WITH FLEXIBLE ARTICULATED WINGS. |
| RU2452660C2 (en) * | 2010-07-07 | 2012-06-10 | Сергей Николаевич Разумов | Ornithopter |
| CN103612754A (en) * | 2013-11-12 | 2014-03-05 | 北京工业大学 | Bionic double-joint flapping wing air vehicle |
| CN205931253U (en) * | 2016-08-23 | 2017-02-08 | 哈尔滨工业大学深圳研究生院 | Bionic flapping -wing air vehicle |
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