CN107697284A - A kind of two section type bionic flapping-wing unmanned plane wing - Google Patents

Abstract

The invention discloses a double-stage bionic flapping wing unmanned aerial vehicle wing, which is hinged sequentially from the body, the aileron and the main wing from the inside to the outside; The main wing is composed of No. 1 bionic airfoil rib, No. 2 bionic airfoil rib and transmission rod. The maximum thickness of the No. 1 bionic airfoil rib is located at 19.86% of the chord length, and the maximum camber is at At the position of 49.32% of the chord length, when the chord length is unit length 1, the maximum thickness is 0.1076, and the maximum camber is 0.1089; Located at 42.68% of the chord length, when the chord length is unit length 1, the maximum thickness is 0.1084, and the maximum camber is 0.1097. The invention inherits the good characteristics of the homing pigeon, and performs bionic design on the main and aileron plane parameters and section airfoil of the wing, which improves the aerodynamic efficiency and flexibility of the aircraft, and the flight rises and falls faster, indicating that it has good lift-drag characteristics and flexibility.

Description

A double-stage bionic flapping wing UAV wing

technical field

The invention belongs to the technical field of aviation, and in particular relates to a double-stage bionic flapping-wing unmanned aerial vehicle wing.

Background technique

Research on unmanned aircraft is the research focus in the military field of various countries today, and miniaturized and miniaturized aircraft is a new trend in the development of unmanned aerial vehicles.

The flying speed of micro air vehicles is only tens of kilometers per hour, and the flying Reynolds number is about 2×10 ⁵ . On the one hand, at such a low Reynolds number, the aerodynamic viscous force and drag are more prominent; the boundary layer of the fuselage tends to be laminar; the boundary layer of the wing tends to separate from the wing, thereby losing lift. Therefore, the traditional fixed-wing and rotary-wing aircraft research methods are no longer applicable, and the flapping-wing flight method must be studied. On the other hand, the micro-aircraft is small in size, and it is necessary to improve the aerodynamic efficiency and flexibility of the aircraft while reducing the weight. The wing is the main part of the aircraft to generate lift, the aerodynamic performance of the wing is the basis of the design of the aircraft, and the factors that affect the aerodynamic performance are the wing plane parameters and the airfoil. Therefore, it is the key to improve the aerodynamic efficiency to obtain the wing plane parameters and airfoil with excellent performance.

Contents of the invention

Aiming at the deficiencies in the above-mentioned prior art, the present invention provides, for example, a double-stage bionic flapping-wing unmanned aerial vehicle wing, so as to improve the aerodynamic efficiency and flexibility of the wing while reducing the weight of the wing. In conjunction with the accompanying drawings of the description, the technical solution of the present invention is as follows:

A two-stage bionic flapping-wing unmanned aerial vehicle wing is composed of an aileron 2, a main wing 1 and a body 3, and each side is formed by connecting the aileron 2 and the main wing 1, wherein the inner side of the aileron 2 is connected to the body 3 Connected by a rotating shaft 4, the main wing 1 is connected to the outside of the aileron 2 through a hinge block 9;

The aileron 2 is composed of four bionic airfoil ribs No. 1 5, two transmission rods 7 and a support rod 8. The four bionic airfoil ribs No. 1 5 are vertically installed on two vertically parallel On the transmission rod 7 of the transmission rod 7, the support rod 8 is installed on the four bionic airfoil ribs No. 5 in parallel with the transmission rod 7, and the support rod 8 is located at the rear side of the transmission rod 7, and the two transmission rods 7 are respectively Hinged on one side of hinge block 9;

The main wing 1 is composed of a bionic airfoil rib No. 1 5, four bionic airfoil rib No. 6 and a transmission rod 7. The bionic airfoil rib No. 1 5 and the bionic airfoil rib No. 2 No. 6 is installed vertically on a transmission rod 7, and the transmission rod 7 is hinged on the other side of the hinge block 9.

Further, the maximum thickness t of the bionic airfoil rib No. 1 is located at 19.86% of the chord length c, and the maximum camber f is located at 49.32% of the chord length c. When the chord length c is a unit length 1, The maximum thickness t is 0.1076, and the maximum curvature f is 0.1089;

The maximum thickness t of the bionic airfoil rib No. 2 is located at 16.64% of the chord length c, and the maximum camber f is located at 42.68% of the chord length c. When the chord length c is a unit length 1, the maximum thickness t is 0.1084, the maximum curvature f is 0.1097.

Further, the coordinate values corresponding to the airfoils of the bionic airfoil ribs No. 1 5 and bionic airfoil rib No. 2 6 are:

.

Compared with prior art, the beneficial effect of the present invention is:

The invention utilizes the principle of bionics to propose a novel double-stage bionic flapping-wing unmanned aerial vehicle wing, which improves the aerodynamic efficiency and flexibility of the aircraft. Homing pigeons can fly for a long time and long distance, and the flight rises and falls quickly, which shows that they have good lift-drag characteristics and flexibility. The wing of the flapping-wing unmanned aerial vehicle provided by the present invention inherits the good characteristics of the carrier pigeon, and performs bionic design on the main and aileron plane parameters and cross-sectional airfoil of the wing, which is advanced and practical. The wing shape provided by the invention has the advantages of simple structure, light weight, simple aerodynamic layout, strong flexibility and the like.

Description of drawings

Fig. 1 is the overall structure schematic diagram of a kind of two-stage bionic flapping wing unmanned aerial vehicle wing of the present invention;

Fig. 2 is a schematic diagram of the three-dimensional structure of a single-sided wing of a double-section bionic flapping-wing unmanned aerial vehicle wing according to the present invention;

Fig. 3 is a schematic diagram of the connection structure between the main wing and the aileron in the wing of a kind of double-stage bionic flapping wing UAV described in the present invention;

Fig. 4 is a schematic diagram of the No. 1 bionic airfoil rib in the wing of a kind of double-stage bionic flapping wing UAV described in the present invention;

Fig. 5 is a schematic diagram of carrier pigeon wing shape No.

Fig. 6 is a schematic diagram of the No. 2 bionic airfoil rib in the wing of a double-stage bionic flapping-wing unmanned aerial vehicle according to the present invention;

Fig. 7 is a schematic diagram of carrier pigeon wing shape No.

Fig. 8 is the lift-to-drag ratio comparison graph when the angle of attack is 0° to 20° and the Reynolds number is ¹⁰ for the No. 1 pigeon wing shape, the No. 2 pigeon wing shape and the standard airfoil NACA2412 in the present invention;

Fig. 9 is a graph comparing the lift coefficients of the No. 1 Pigeon Wing, No. 2 Pigeon Wing and the standard airfoil NACA2412 at an angle of attack of 0° to 20° and a Reynolds number of 10 ⁵ in the present invention.

In the picture:

1 main wing, 2 ailerons, 3 fuselage, 4 rotating shafts,

5 No. 1 bionic airfoil rib, 6 No. 2 bionic airfoil rib, 7 Transmission rod, 8 Support rod,

9 hinged blocks.

detailed description

The present invention uses the characteristics of bird wings in nature to improve the existing defects of the wing shape. Considering that the operating conditions of carrier pigeons and flapping aircraft are the most similar, the present invention adopts the plane parameters of carrier pigeon wings obtained by reverse engineering. And the airfoil, optimize the wing shape of the flapping wing UAV, and provide a two-stage bionic flapping wing UAV wing, in order to reduce the weight of the wing while improving the aerodynamic efficiency and flexibility of the wing . In order to further illustrate the technical solution of the present invention, in conjunction with the accompanying drawings, the specific implementation of the present invention is as follows:

As shown in FIG. 1 , the present invention provides a two-stage bionic flapping-wing unmanned aerial vehicle wing, which is a two-stage wing and consists of an aileron 2 , a main wing 1 and a body 3 . The wing is an axisymmetric structure, and each side is composed of an aileron 2 connected to a main wing 1, wherein the inner side of the aileron 2 is connected to the body 3 through a rotating shaft 4, and the main wing 1 is connected to the aileron 2 through a hinge block 9. External connection.

As shown in Figures 2 and 3, the aileron 2 is composed of four bionic airfoil ribs No. 5, two transmission rods 7 and a support rod 8; the main wing 1 is composed of a bionic airfoil rib No. 1 5, four bionic airfoil ribs No. 2 6 and a transmission rod 7; the two transmission rods 7 of the aileron 2 are arranged in parallel up and down, and are respectively hinged up and down on two sides with one side of the hinge block 9. point, a transmission rod 7 of the main wing 1 is hinged at a point above the other side of the hinge block 9, so that the main wing 1 and the aileron 2 are hinged through the hinge block 9, and the vertical direction of the main wing 1 and the aileron 2 is realized. Relatively swing up and down.

The wing is an axisymmetric structure, the length of the wing on one side is 400±40mm, the length ratio of main and aileron is 3:2, the total area of the wing is 0.09㎡±0.01㎡, and the aspect ratio is 8.1±0.2.

The four bionic airfoil ribs No. 1 and No. 5 of the aileron 2 are equidistantly installed in parallel on the two transmission rods 7 of the aileron 2; the four bionic airfoil ribs No. 1 and 5 are all vertically arranged on the transmission rods 7 On the top, the maximum thickness of the bionic airfoil rib No. 1 is connected with the transmission rod 7, and the support rod 8 is installed on the four bionic airfoil rib No. 1 5 in parallel with the transmission rod 7, and the support rod 8 Located on the rear side of the transmission rod 7.

One bionic airfoil rib No. 1 5 and four bionic airfoil rib No. 6 of the main wing 1 are installed in parallel on a transmission rod 7 of the main wing 1 at equal intervals from the inside to the outside; the bionic airfoil rib The plate No. 1 5 and the bionic airfoil rib No. 2 6 are vertically installed on the transmission rod 7. The maximum thickness t of the bionic airfoil rib No. 1 5 is connected with the transmission rod 7. The bionic airfoil rib No. 2 The maximum thickness t of 6 is connected with transmission rod 7 .

As shown in FIG. 4 , at the position of the maximum thickness t of the bionic airfoil rib No. 1 5 , there are drive rod installation holes and support rod installation holes in the front and rear respectively. As shown in Figure 5, the No. 1 bionic airfoil rib plate No. 5 is taken from the half-span of the pigeon wing. In the area at the 80% position, the maximum thickness t is located at 19.86% of the chord length c, and the maximum camber f is located at 49.32% of the chord length c. When the chord length c is unit length 1, the maximum thickness t is 0.1076, the maximum The camber f is 0.1089.

As shown in Fig. 6, the maximum thickness position of No. 6 of the bionic airfoil rib plate is provided with a transmission rod installation hole. As shown in Figure 7, the No. 2 bionic airfoil rib plate No. 6 is taken from the half-span of the pigeon wing, and the No. 2 bionic airfoil rib plate takes the root of the pigeon wing as the starting position and ends at the half-wing span of the pigeon wing. In the area at the 30% position, the maximum thickness t is located at 16.64% of the chord length c, and the maximum camber f is located at 42.68% of the chord length c. When the chord length c is unit length 1, the maximum thickness t is 0.1084, and the maximum The camber f is 0.1097. The coordinate values corresponding to the airfoil surfaces of the bionic airfoil rib No. 1 and the bionic airfoil rib No. 2 satisfy the following table:

Table 1

As shown in Figure 8, the No. 1 homing pigeon wing shape adopted by the bionic airfoil rib plate No. 5 in the present invention, the homing pigeon wing shape No. 2 adopted by the bionic airfoil rib plate No. 6 and the standard are obtained by computer simulation The airfoil NACA2412 has a lift-to-drag ratio comparison curve when the angle of attack is 3° to 20° and the Reynolds number is 10 ^5. As can be seen from Fig. 8, under this working condition, the main wing 1 of the wing described in the present invention The lift-to-drag ratio of Pigeon Wing II used in the bionic airfoil No. 2 rib plate is higher than that of Pigeon Wing No. 1 and the standard airfoil NACA2412, and the maximum lift-to-drag ratio is increased by 2.19 times.

As shown in Figure 9, the No. 1 homing pigeon wing shape adopted by the bionic airfoil rib plate No. 5 in the present invention, the homing pigeon wing shape No. 2 adopted by the bionic airfoil rib plate No. 6 and the standard are obtained by computer simulation The airfoil NACA2412 is ³ °～20° at the angle of attack, and the lift coefficient comparison curve when the Reynolds number is 105, as can be seen from Figure 8, under this working condition, in the aileron 2 of the wing described in the present invention The lift coefficient of the pigeon wing No. 1 used in the bionic airfoil rib plate No. 1 is higher than that of the pigeon wing No. 2 and the standard airfoil NACA2412, and the maximum lift coefficient is increased by 1.91 times.

To sum up, when the Reynolds number is 10 ⁵ and the angle of attack is 3° to 20°, the lift coefficients of the No. 1 and No. 2 pigeon wing shapes used in the wings of the present invention are higher than those of the standard wing. Type NACA2412, the bionic airfoil rib No. 2 of the main wing 1 of the wing described in the present invention No. 6 adopts the carrier pigeon wing shape No. 2 with a relatively high lift-drag ratio as the bionic airfoil to generate sufficient thrust; the bionic airfoil of the aileron 2 The airfoil rib No. 1 5 adopts the carrier pigeon wing No. 1 with a higher lift coefficient as the bionic airfoil to generate sufficient lift. Compared with the existing wings, the double-stage bionic flapping wing drone wing described in the present invention has significantly improved aerodynamic efficiency, and the main wing and aileron generate thrust and lift respectively, which greatly improves the flexibility of the flapping wing aircraft .

Claims (3)

1. a kind of two section type bionic flapping-wing unmanned plane wing, it is made up of aileron (2), main wing (1) and body (3), it is characterised in that：

Per side by aileron (2) and main wing (1) connection composition, wherein, pass through rotating shaft (4) with body (3) on the inside of the aileron (2) Connection, the main wing (1) is by hinged block (9) with being connected on the outside of aileron (2)；

The aileron (2) is made up of four bionical aerofoil profile floor No.1s (5), two drive links (7) and a support bar (8), institute Four bionical aerofoil profile floor No.1s (5) are stated to be vertically mounted on about two drive links be arrangeding in parallel (7), support bar (8) with Drive link (7) is arranged on four bionical aerofoil profile floor No.1s (5), and support bar (8) is located at drive link (7) parallelly after Side, two drive links (7) are respectively hinged at the side of hinged block (9)；

The main wing (1) is by a bionical aerofoil profile floor No.1 (5), four bionical aerofoil profile rib plate No.2s (6) and a drive link (7) form, the bionical aerofoil profile floor No.1 (5) and bionical aerofoil profile rib plate No.2 (6) are installed vertically on a drive link (7) On, a drive link (7) is hinged on the opposite side of hinged block (9).

A kind of 2. two section type bionic flapping-wing unmanned plane wing as claimed in claim 1, it is characterised in that：

The maximum gauge (t) of the bionical aerofoil profile floor No.1 (5) is located at 19.86% opening position of chord length (c), maximum camber (f) it is located at 49.32% opening position of chord length (c), when chord length (c) is unit length 1, maximum gauge (t) is 0.1076, maximum Camber (f) is 0.1089；

Bionical aerofoil profile rib plate No.2 (6) maximum gauge (t) is located at 16.64% opening position of chord length (c), maximum camber (f) Positioned at 42.68% opening position of chord length (c), when chord length (c) is unit length 1, maximum gauge (t) is 0.1084, maximum curved It is 0.1097 to spend (f).

A kind of 3. two section type bionic flapping-wing unmanned plane wing as claimed in claim 2, it is characterised in that：

Coordinate value corresponding to the aerofoil of the bionical aerofoil profile floor No.1 (5) and bionical aerofoil profile rib plate No.2 (6) is：

。