Pneumatic flapping wing with double-quadrilateral contraction structure

Abstract

The utility model relates to a pneumatic flapping wing with a double-quadrilateral contraction structure. The pneumatic flapping wing comprises a wing root frame, a wing root edge, a first connecting rod, a second connecting rod, a third connecting rod, a fourth connecting rod, a driving rod, a supporting rod, a driven rod, a flange, a first wing rear edge and a second wing rear edge, the wing root frame and the wing root edge are hinged with one end of the first connecting rod; one end of the first connecting rod away from the wing root frame is hinged with the second connecting rod and the second wing rear edge; the ends, away from the first connecting rods, of the second connecting rods are hinged to flange ends. One end of the wing root frame away from the first connecting rod is hinged with the third connecting rod and the supporting rod; one end of the third connecting rod away from the wing root frame is hinged with the fourth connecting rod and the first wing trailing edge; one end, away from the third connecting rod, of the fourth connecting rod is hinged in a strip-shaped through groove of the flange close to the end of the second connecting rod; one end, away from the wing root frame, of the supporting rod is hinged to the driven rod and the driving rod; the driven rod is hinged to the second connecting rod; the end, away from the supporting rod, of the driving rod is hinged into an open through groove in the end, close to the supporting rod, of the wing root frame.

Description

Technical Field

[0001] The utility model relates to the technical field of flapping-wing aircraft, in particular to a pneumatic flapping wing with a double quadrilateral contraction structure. Background Art

[0002] A flapping-wing aircraft is an aircraft that imitates the flight of birds or insects. It generates lift and thrust by imitating the flapping of their wings to achieve aerial flight missions. Flapping-wing aircraft not only have excellent maneuverability, low noise, low cost, easy to carry and simple operation, but also show unique advantages in flight movements such as gliding and diving. In the military field, flapping-wing aircraft can glide like birds, which enables them to glide for a long time at high altitudes and cover a wider reconnaissance area. For example, a flapping-wing aircraft equipped in a soldier's squad can glide silently to the vicinity of the enemy's position to conduct low-altitude reconnaissance and surveillance missions and provide important intelligence to the command. In the civilian field, the gliding ability of flapping-wing aircraft is also of great significance. It can glide in the air for a long time and carry corresponding sensors to monitor air quality, meteorological data, forest fire conditions, etc., providing important support for environmental protection and disaster warning. In war, flapping-wing aircraft can quickly reduce their flight altitude by diving and carry out precise strikes on ground targets. This strike method is not only fast, but also highly accurate, and can effectively destroy important enemy facilities or personnel. Flapping-wing flight has higher energy efficiency than fixed-wing flight and rotary-wing flight. It can use less energy to fly, accelerate or hover for a long time and over a long distance, which allows flapping-wing aircraft to maintain a longer flight time when gliding and diving. Flapping-wing aircraft are highly maneuverable and flexible. It can perform various complex flight maneuvers like birds, including gliding and diving. This allows flapping-wing aircraft to be more flexible and adaptable when performing missions and adapt to various complex environments.

[0003] Domestic and foreign research institutions have achieved remarkable research results in the field of flapping-wing aircraft. For example, the "Microbat" developed by the California Institute of Technology and the "Mentor" developed by the Stanford Research Center (SRI) have already possessed high gliding and diving capabilities. Domestic universities such as Northwestern Polytechnical University and Nanjing University of Aeronautics and Astronautics have also conducted in-depth research in the field of flapping-wing aircraft and have achieved a series of results.

[0004] In summary, the gliding and diving capabilities of flapping-wing aircraft have important application value in both military and civilian fields. With the continuous advancement of technology and in-depth research, it is believed that flapping-wing aircraft will play a more important role in the future.

[0005] At present, flapping-wing aircraft have a short gliding distance and slow dive speed, and there is still much room for improvement in the aerodynamic details compared to birds. Utility Model Content

[0006] The utility model mainly solves the technical problems of the existing segment flapping-wing aircraft, such as short flying gliding distance, low aerodynamic efficiency, frequent flapping during flight, slow diving speed, etc., and proposes an aerodynamic flapping wing with a double quadrilateral contraction structure, which has a fast diving speed, improved flight efficiency, more supports, and ensures the rigidity requirements of the wing during normal flapping.

[0007] The utility model provides a pneumatic flapping wing with a double quadrilateral contraction structure, comprising: a wing root frame, a wing root edge, a first connecting rod, a second connecting rod, a third connecting rod, a fourth connecting rod, a driving rod, a supporting rod, a driven rod, a wing edge, a first wing trailing edge and a second wing trailing edge;

[0008] The wing root frame, the wing root edge and one end of the first connecting rod are hinged; one end of the first connecting rod away from the wing root frame is hinged to the second connecting rod and the second wing trailing edge; one end of the second connecting rod away from the first connecting rod is hinged to the end of the wing edge;

[0009] One end of the wing root frame away from the first connecting rod is hinged to the third connecting rod and the support rod; one end of the third connecting rod away from the wing root frame is hinged to the fourth connecting rod and the first wing trailing edge; one end of the fourth connecting rod away from the third connecting rod is hinged in the long through groove of the wing edge close to the end of the second connecting rod;

[0010] The end of the support rod away from the wing root frame is hinged to the driven rod and the driving rod; the driven rod is hinged to the middle part of the second connecting rod; the end of the driving rod away from the support rod is hinged in the open through groove of the end of the wing root frame close to the support rod.

[0011] Furthermore, the second connecting rod includes: a second connecting rod A and a second connecting rod B; the second connecting rod A and the second connecting rod B are arranged in parallel up and down; the second connecting rod and the flange hinge, the second connecting rod A and the second connecting rod B are respectively located above and below the flange; the second connecting rod A and the second connecting rod B are respectively located on the upper and lower sides of the third connecting rod.

[0012] Furthermore, a first pin hole is provided at one end of the wing root frame; an open through slot is provided at the other end of the wing root frame; symmetrical long holes are provided on the upper wall and the lower wall of the open through slot; one end of the first connecting rod is placed in the first pin hole of the wing root frame; a Teflon bushing is provided in the first pin hole; the wing root frame, the wing root edge and the first connecting rod are hinged by plug bolts; a driving rod is hinged in the open through slot; and a third connecting rod is hinged at the end of the open through slot of the wing root frame.

[0013] Furthermore, the connecting end of the third connecting rod and the wing root frame is a long end; the connecting end of the third connecting rod and the first wing trailing edge is a short end.

[0014] Furthermore, the connecting end of the second connecting rod and the first connecting rod is a short end; the connecting end of the second connecting rod and the flange is a long end.

[0015] Furthermore, the driven rod is hinged to the long end of the second connecting rod.

[0016] Furthermore, the middle portion of the second connecting rod and the middle portion of the third connecting rod are hinged by a plug bolt.

[0017] Furthermore, the wing root edge is located below the wing root frame; the support rod is located above the wing root frame; the driving rod is located below the driven rod; the first wing trailing edge is located below the fourth connecting rod; and the second wing trailing edge is located below the first connecting rod.

[0018] Furthermore, the elongated through slot is used to accommodate the fourth connecting rod.

[0019] Compared with the prior art, the pneumatic flapping wing with a double quadrilateral contraction structure provided by the utility model has the following advantages:

[0020] 1. Compared with the wings of traditional flapping-wing aircraft, the wings of the present invention can be retracted during the flapping-wing aircraft dive, thereby reducing air resistance and increasing the dive speed.

[0021] 2. The wing retractable structure of the present invention is based on a double quadrilateral structure. The wing area changes greatly before and after retraction, the drag reduction effect is significant, and more supports are provided to ensure the rigidity requirements of the wing during normal flapping.

[0022] 3. The flapping wing edge of the present invention is slightly tilted, which can reduce the induced drag during gliding, increase the gliding distance, and improve the flight efficiency.

[0023] 4. The overall design of the flapping wing structure of the present invention is that the front middle part is raised and the rear part is sunken. After coating, it is closer to the shape of a bird's wing. During flight, the air velocity difference between the upper and lower surfaces is used to provide lift and improve flight efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 This is the pneumatic flapping state 1 of the double quadrilateral contraction structure of the utility model;

[0025] Figure 2 This is the second aerodynamic flapping state of the double quadrilateral contraction structure of the utility model;

[0026] Figure 3 This is the third aerodynamic flapping state of the double quadrilateral contraction structure of the utility model;

[0027] Figure 4 It is the pneumatic flapping state four of the double quadrilateral contraction structure of the utility model;

[0028] Figure 5 It is the pneumatic flapping state five of the double quadrilateral contraction structure of the utility model;

[0029] Figure 6 It is the pneumatic flapping state six of the double quadrilateral contraction structure of the utility model;

[0030] Figure 7 It is the pneumatic flapping state seven of the double quadrilateral contraction structure of the utility model;

[0031] Figure 8 It is the pneumatic flapping state eight of the double quadrilateral contraction structure of the utility model;

[0032] Fig. 9 It is the pneumatic flapping state nine of the double quadrilateral contraction structure of the utility model;

[0033] Fig.10 It is the pneumatic flapping state of the double quadrilateral contraction structure of the utility model;

[0034] Fig.11 It is the pneumatic flapping state eleven of the double quadrilateral contraction structure of the utility model;

[0035] Fig.12 It is the pneumatic flapping state twelve of the double quadrilateral contraction structure of the utility model;

[0036] Fig.13 It is the pneumatic flapping state thirteen of the double quadrilateral contraction structure of the utility model;

[0037] Fig.14 This is a schematic diagram of the pneumatic flapping wing mechanism of the double quadrilateral contraction structure of the utility model. Figure 1 ;

[0038] Fig.15 This is a schematic diagram of the pneumatic flapping wing mechanism of the double quadrilateral contraction structure of the utility model. Figure 2 ;

[0039] Description of the drawings: 1. Wing root frame, 2. Wing root edge, 3. First connecting rod, 4. Second connecting rod; 5. Third connecting rod, 6. Fourth connecting rod, 7. Driving rod, 8. Support rod, 9. Follower rod, 10. Wing edge, 11. First wing trailing edge, 12. Second wing trailing edge, 13. Teflon bushing, 14. Plug bolt, 15. Servo quick adjustment. DETAILED DESCRIPTION

[0040] In order to make the technical problems solved by the present invention, the technical solutions adopted and the technical effects achieved clearer, the present invention is further described in detail below in conjunction with the accompanying drawings and embodiments. It is understood that the specific embodiments described herein are only used to explain the present invention, rather than to limit the present invention. It should also be noted that, for the sake of ease of description, only the parts related to the present invention are shown in the accompanying drawings, rather than all of the contents.

[0041] like Figure 1-15As shown, an aerodynamic flapping wing with a double quadrilateral contraction structure provided by an embodiment of the utility model includes: a wing root frame 1, a wing root edge 2, a first connecting rod 3, a second connecting rod 4, a third connecting rod 5, a fourth connecting rod 6, a driving rod 7, a supporting rod 8, a driven rod 9, a wing edge 10, a first wing trailing edge 11 and a second wing trailing edge 12; the wing root frame 1, the wing root edge 2 and one end of the first connecting rod 3 are hinged; the wing root edge 2 is located below the wing root frame 1; the wing root frame 1, the wing root edge 2 and one end of the first connecting rod 3 are hinged, and the through holes at the ends of the three are concentric, and the plug bolt 14 passes through the through holes of the wing root frame 1, the wing root edge 2 and the first connecting rod 3 to connect the three together. One end of the first connecting rod 3 away from the wing root frame 1 is hinged to the second connecting rod 4 and the second wing trailing edge 12, and the three are connected by a plug bolt 14; one end of the second connecting rod 4 away from the first connecting rod 3 is hinged to the end of the flange 10, and the second connecting rod 4 and the flange 10 are connected by a plug bolt 14;

[0042] The end of the wing root frame 1 away from the first connecting rod 3 is hinged to the third connecting rod 5 and the support rod 8, and the three are connected by a plug bolt 14; the end of the third connecting rod 5 away from the wing root frame 1 is hinged to the fourth connecting rod 6 and the first wing trailing edge 11, and the three are connected by a plug bolt 14; the end of the fourth connecting rod 6 away from the third connecting rod 5 is hinged in the long through groove of the flange 10 close to the end of the second connecting rod 4, and the fourth connecting rod 6 is connected to the flange 10 by a plug bolt 14;

[0043] The end of the support rod 8 away from the wing root frame 1 is hinged to the driven rod 9 and the driving rod 7, and the three are connected by a plug bolt 14; the driven rod 9 is hinged to the middle part of the second connecting rod 4 by a plug bolt 14; the end of the driving rod 7 away from the support rod 8 is hinged in the open through groove of the end of the wing root frame 1 close to the support rod 8 through a servo quick adjustment 15; long through holes are symmetrically arranged on the upper and lower side walls of the open through groove.

[0044] The second connecting rod 4 includes: a second connecting rod A and a second connecting rod B; the second connecting rod A and the second connecting rod B are arranged in parallel up and down; the second connecting rod 4 and the flange 10 are hinged at the upper and lower sides of the flange 10; the second connecting rod A and the second connecting rod B are respectively located at the upper and lower sides of the third connecting rod 5. The connecting end of the second connecting rod 4 and the first connecting rod 3 is a short section end; the connecting end of the second connecting rod 4 and the flange 10 is a long section end. The short section end of the second connecting rod 4 is concentric with the through hole in the middle of the third connecting rod 5, and the middle of the second connecting rod 4 and the middle of the third connecting rod 5 are hinged by a plug bolt 14.

[0045] A first pin hole is provided at one end of the wing root frame 1; an open through groove is provided at one end of the wing root frame 1; symmetrical long strip holes are provided on the upper wall and the lower wall of the open through groove; one end of the first connecting rod 3 is placed in the first pin hole of the wing root frame 1; Teflon bushings 13 are provided at the upper and lower ends of the first pin hole, so that one end of the first connecting rod 3 is placed in the first pin hole of the wing root frame 1; the upper and lower ends of the first pin hole are respectively provided with 3 and are tightly connected with the wing root frame 1; the wing root frame 1, the wing root edge 2 and the first connecting rod 3 are hinged by plug bolts 14; the drive rod 7 is hinged in the open through groove; the drive rod 7 is connected to the wing root frame 1 through a servo quick adjustment 15; the third connecting rod 5 is hinged at the end of the open through groove of the wing root frame 1.

[0046] The connection end of the third connecting rod 5 and the wing root frame 1 is a long section end; the long section end of the third connecting rod 5 is inserted into the end of the open through slot of the wing root frame, the support rod 8 is located above the wing root frame 1, and the third connecting rod 5, the support rod 8 and the wing root frame 1 are connected by a plug bolt 14, and a Teflon bushing 13 is provided on the plug bolt 14. The connection end of the third connecting rod 5 and the first wing trailing edge 11 is a short section end.

[0047] The driven rod 9 is hinged to the long end of the second connecting rod 4 , and the driven rod 9 is located above the second connecting rod 4 .

[0048] The driving rod 7 is located below the driven rod 9; the first wing trailing edge 11 is located below the fourth connecting rod 6; the first wing trailing edge 11 is located horizontally below the wing 10. The second wing trailing edge 12 is located below the first connecting rod 3. The long through slot is used to accommodate the fourth connecting rod 6.

[0049] The working principle of this utility model: Fig.13 As shown,

[0050] Point a is the hinge point of the wing root frame 1, the third connecting rod 5 and the support rod 8;

[0051] Point b is the hinge point of the wing root frame 1, the first connecting rod 3 and the wing root edge 2;

[0052] Point c is the hinge point of the driving rod 7, the supporting rod 8 and the driven rod 9;

[0053] Point d is the hinge point of the first connecting rod 3, the second connecting rod 4 and the trailing edge of the second wing;

[0054] Point e is the hinge point of the second connecting rod 4 and the third connecting rod 5;

[0055] Point f is the hinge point of the second connecting rod 4 and the driven rod 9;

[0056] Point g is the hinge point of the third connecting rod 5, the fourth connecting rod 6 and the first wing trailing edge 11;

[0057] Point h is the hinge point between the fourth connecting rod 6 and the flange 10;

[0058] Point i is the hinge point between the flange 10 and the second connecting rod 4;

[0059] The utility model relies on the steering gear to connect the iron wire and then insert it into the hole at the lower end of the steering gear quick adjustment 15, tighten and fix it, and realize the movement along the open slot of the wing root frame 1 by pulling the steering gear. After the steering gear quick adjustment 15 moves along the open slot of the wing root frame 1, it drives the driving rod 7 to move, and the angle between the driving rod 7 and the support rod 8 increases. The end of the driving rod 7 close to the c point drives the end of the support rod 8 close to the c point to move upward, and the distance between the a point and the f point increases. The second connecting rod 4 rotates counterclockwise around the e point as a whole, driving the first connecting rod 3 to rotate clockwise around the d point, further pushing the ed part of the second connecting rod 4 to stretch, pushing the third connecting rod 5 to rotate clockwise around a, and pushing the fourth connecting rod 6 to move along the gh direction. In the quadrilateral abde, the angle abd decreases, the angle bde increases, the angle dea decreases, and the angle eab increases. When the wing root frame 1 is fixed, the quadrilateral gradually stretches to the side, and the height with ab as the base continues to increase, and the area becomes larger. Because point h rises and point i falls, in quadrilateral iegh, angle ieg decreases, angle egh increases, angle ghi decreases, angle hie increases, and the height with ie as the base increases continuously, and the area becomes larger. Under the staggered movement of the fourth link 6 and the second link 4, the flange 10 rotates clockwise around point h. Since the ih section of the flange 10 is extremely short relative to the whole, the movement of the flange 10 is very significant, the whole wing surface is rapidly unfolded, and the wing surface is rapidly increased.

[0060] The upper part of the wing after coating is convex, the air velocity is fast, the air pressure is low, while the lower part is relatively flat, the air velocity is slow, the air pressure is high, and the pressure difference between the upper and lower parts forms a force from the lower part of the wing to the upper part of the wing, providing lift for the whole flapping wing. This provides a source of lift during the gliding process, allowing the gliding distance to be longer and the flight efficiency to be higher.

[0061] The J end of the wing edge 10 is slightly upturned, blocking or reducing the wing tip vortex formed by the airflow on the lower surface of the flapping wing around the upper surface, thereby reducing the induced drag and improving the flight efficiency of the flapping wing aircraft. It can also generate a wing tip vortex, which is opposite to the flapping wing tip vortex in direction and very close to it. Under the action of viscous dissipation, the two vortices are entangled with each other, counteracting each other, and also achieving the purpose of reducing induced drag, significantly improving flight efficiency.

[0062] Finally, it should be noted that the above embodiments are only used to illustrate the technical solution of the utility model, rather than to limit it. Although the utility model has been described in detail with reference to the aforementioned embodiments, ordinary technicians in the field should understand that modifying the technical solutions recorded in the aforementioned embodiments, or replacing part or all of the technical features therein by equivalents, does not make the essence of the corresponding technical solution deviate from the scope of the technical solution of the embodiments of the utility model.

Claims

1. A pneumatic flapping wing with a double quadrilateral contraction structure, characterized in that: include: A wing root frame (1), a wing root edge (2), a first connecting rod (3), a second connecting rod (4), a third connecting rod (5), a fourth connecting rod (6), a driving rod (7), a supporting rod (8), a driven rod (9), a wing edge (10), a first wing trailing edge (11) and a second wing trailing edge (12); The wing root frame (1), the wing root edge (2) and one end of the first connecting rod (3) are hinged; the end of the first connecting rod (3) away from the wing root frame (1) is hinged to the second connecting rod (4) and the second wing trailing edge (12); the end of the second connecting rod (4) away from the first connecting rod (3) is hinged to the end of the wing edge (10); One end of the wing root frame (1) away from the first connecting rod (3) is hinged to the third connecting rod (5) and the support rod (8); one end of the third connecting rod (5) away from the wing root frame (1) is hinged to the fourth connecting rod (6) and the first wing trailing edge (11); one end of the fourth connecting rod (6) away from the third connecting rod (5) is hinged in a long through groove on the wing edge (10) close to the end of the second connecting rod (4); The end of the support rod (8) away from the wing root frame (1) is hinged to the driven rod (9) and the driving rod (7); the driven rod (9) is hinged to the middle part of the second connecting rod (4); the end of the driving rod (7) away from the support rod (8) is hinged in an open through groove at the end of the wing root frame (1) close to the support rod (8).

2. The pneumatic flapping wing of the double quadrilateral contraction structure according to claim 1, characterized in that: The second connecting rod (4) comprises: a second connecting rod A and a second connecting rod B; the second connecting rod A and the second connecting rod B are arranged in parallel up and down; the hinge between the second connecting rod (4) and the flange (10), the second connecting rod A and the second connecting rod B are respectively located above and below the flange (10); the second connecting rod A and the second connecting rod B are respectively located on the upper and lower sides of the third connecting rod (5).

3. The pneumatic flapping wing of the double quadrilateral contraction structure according to claim 1, characterized in that: A first pin hole is provided at one end of the wing root frame (1); an open through slot is provided at the other end of the wing root frame (1); symmetrical long strip holes are provided on the upper wall and the lower wall of the open through slot; one end of the first connecting rod (3) is placed in the first pin hole of the wing root frame (1); a Teflon bushing (13) is provided in the first pin hole; the wing root frame (1), the wing root edge (2) and the first connecting rod (3) are hinged by a plug bolt (14); a driving rod (7) is hinged in the open through slot; and a third connecting rod (5) is hinged at the end of the open through slot of the wing root frame (1).

4. The pneumatic flapping wing of the double quadrilateral contraction structure according to claim 3 is characterized in that: The connection end between the third connecting rod (5) and the wing root frame (1) is a long section end; the connection end between the third connecting rod (5) and the first wing trailing edge (11) is a short section end.

5. The pneumatic flapping wing of the double quadrilateral contraction structure according to claim 3, characterized in that: The connecting end of the second connecting rod (4) and the first connecting rod (3) is a short end; the connecting end of the second connecting rod (4) and the flange (10) is a long end.

6. The pneumatic flapping wing of the double quadrilateral contraction structure according to claim 5, characterized in that: The driven rod (9) is hinged to the long end of the second connecting rod (4).

7. The pneumatic flapping wing of the double quadrilateral contraction structure according to claim 1, characterized in that: The middle part of the second connecting rod (4) and the middle part of the third connecting rod (5) are hingedly connected by plug bolts.

8. The pneumatic flapping wing of the double quadrilateral contraction structure according to claim 2, characterized in that: The wing root edge (2) is located below the wing root frame (1); the support rod (8) is located above the wing root frame (1); the driving rod (7) is located below the driven rod (9); the first wing trailing edge (11) is located below the fourth connecting rod (6); and the second wing trailing edge (12) is located below the first connecting rod (3).

9. The pneumatic flapping wing of the double quadrilateral contraction structure according to claim 1, characterized in that: The long through groove is used to accommodate the fourth connecting rod (6).

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