A flapping wing structure and a flapping wing aircraft
By installing guide fins and transmission components on the flapping-wing aircraft, the airflow distribution and angle are adjusted, solving the flight stability problem of the flapping-wing aircraft and achieving more stable and flexible flight control.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- YANGZHOU UNIV
- Filing Date
- 2025-07-31
- Publication Date
- 2026-06-16
AI Technical Summary
Existing flapping-wing aircraft have poor flight stability and are easily affected by external airflow, leading to loss of attitude control and swaying, which limits their further promotion and application.
A guide fin and transmission assembly are installed on the flapping wing body. The guide fins are used to organize the airflow. Combined with the self-locking design of the worm gear and worm wheel, the tilt angle between the guide fins and the flapping wing body is adjusted to improve flight stability and control precision.
It improves the flight attitude stability of flapping-wing aircraft, reduces the probability of swaying and rolling, and achieves more sensitive and precise steering control, making it suitable for complex flight missions.
Smart Images
Figure CN224361375U_ABST
Abstract
Description
Technical Field
[0001] This utility model relates to the field of aircraft technology, and in particular to a flapping wing structure and a flapping wing aircraft. Background Technology
[0002] Flapping-wing aircraft, with their unique biomimetic flight mechanism, have demonstrated potential application value in numerous fields. A search reveals Chinese Patent Publication No. CN222329997U, which discloses a flapping-wing structure for a flapping-wing aircraft. This structure achieves wing shape changes through the hinged connection of several flapping-wing units, making it suitable for attitude adjustments under different flight conditions. It can instantly change shape to maintain flight stability; the use of several repeating unit structures makes manufacturing more convenient and cost-effective.
[0003] The existing technology has the following drawbacks: existing flapping-wing aircraft generally suffer from poor flight stability. The aerodynamic forces generated by the flapping-wing structure during flight are unsteady and easily affected by external airflow, which can lead to loss of attitude control, swaying, and other issues, thus limiting the further promotion and application of flapping-wing aircraft. This utility model aims to overcome the shortcomings of the existing flapping-wing structure in terms of flight stability by improving the stability of flapping-wing aircraft through innovative structural design. Utility Model Content
[0004] The purpose of this invention is to provide a flapping wing structure and a flapping wing aircraft. By incorporating guide fins on the flapping wing body, the airflow around the flapping wing body can be effectively channeled, thereby overcoming the shortcomings of insufficient flight stability in existing flapping wing aircraft. This invention is achieved through the following technical solution.
[0005] In a first aspect, this utility model provides a flapping wing structure, including: a flapping wing body with a cavity, a guide fin, and a transmission component;
[0006] The cross-section of the guide fin is arc-shaped, with part of it located inside the cavity and part of it located outside the cavity. Its bottom is fitted onto the outer ring of the rotating shaft located inside the cavity.
[0007] The two ends of the rotating shaft are fitted with a first connecting frame, and the ends of the first connecting frame are connected to the inner wall of the flapping wing body cavity.
[0008] The transmission component is located inside the cavity, and the power end of the transmission component is sleeved on the outer ring of the rotating shaft to provide power to the rotating shaft, so that the guide fin rotates to a predetermined angle and restricts the automatic reverse rotation of the rotating shaft.
[0009] In practical applications, the power source is a turbine fitted around the outer ring of the shaft.
[0010] Optionally, a bearing is provided between the rotating shaft and the first connecting frame, and the bearing is sleeved on the outer ring of the rotating shaft.
[0011] The bearing reduces the friction between the shaft and the first connecting frame, thereby improving the smoothness of the guide fin's rotation.
[0012] Optionally, the extension direction of the rotating shaft is perpendicular to the length direction of the flapping wing body.
[0013] Optionally, a plurality of reinforcing ribs are uniformly arranged in the cavity, and the plurality of reinforcing ribs are fixedly connected to the flapping wing body.
[0014] When flapping wings undergo complex movements such as flapping and twisting, they are subjected to forces from various sources, including aerodynamics, their own inertia, and their connection to the transmission mechanism. These forces can easily cause deformation, twisting, or even damage to the flapping wing body. Reinforcing ribs can alter the force distribution of the flapping wing body, enabling it to better withstand various stresses, dispersing external forces over a wider area, and preventing excessive local stress concentration.
[0015] Optionally, the transmission assembly includes a drive shaft, a worm gear, and a worm wheel.
[0016] The drive shaft passes through multiple second connecting frames and connects to the bottom surface of the multiple reinforcing ribs. The worm gear is sleeved on the outer ring of the drive shaft, and the worm wheel is sleeved on the outer ring of the rotating shaft. The worm gear meshes with the worm wheel.
[0017] The self-locking mechanism between the worm and the worm wheel prevents the guide fins from automatically rotating in the opposite direction.
[0018] Optionally, one end of the drive shaft is connected to a motor, and the motor is fixedly connected to the bottom surface of the reinforcing rib.
[0019] Optionally, one end of the flapping wing body is configured as an arc-shaped tail, and the other end is connected to the aircraft.
[0020] In actual operation, the motor is controlled to operate, which drives the drive shaft to rotate. The drive shaft drives the worm gear to rotate, which in turn drives the worm wheel to rotate. The worm wheel then drives the guide fin to rotate, thus achieving the tilting setting of the guide fin. The specific tilting setting is as follows:
[0021] When the guide fin is tilted at a small angle to the flapping wing body, within the angle range of 0°-15°, the guide fin mainly plays a role in fine-tuning the airflow on the surface of the flapping wing body. It can make the airflow passing through the flapping wing body more regular, reduce the generation of turbulence and vortices, and thus reduce air resistance.
[0022] When the tilt angle is in the range of 15°-30°, the effect of the guide fin 3 on changing the airflow is more significant, which can more effectively increase the pressure difference between the upper and lower surfaces of the flapping fin body 1, thereby significantly improving the lift generation efficiency.
[0023] By adjusting the angle of the flapping fins between 30° and 45°, the aerodynamic distribution around the flapping fins can be rapidly changed, generating a large lateral force, enabling the aircraft to perform complex and rapid maneuvers such as sharp turns.
[0024] Secondly, this utility model provides a flapping-wing aircraft that uses the flapping-wing structure described in the first aspect.
[0025] Compared with the prior art, the beneficial effects of this utility model are as follows:
[0026] (1) By setting the guide fin component, this utility model can sort out the airflow around the flapping wing body. When the flapping wing body makes flapping motion, the airflow flowing over the surface of the flapping wing body can be more regular and reduce the generation of unstable airflow phenomena such as turbulence and vortex. This improves the stability of the flapping wing aircraft during flight, effectively reduces the probability of the aircraft shaking, rolling and other unstable situations, and makes the flight state more stable and reliable.
[0027] (2) This utility model can adjust the tilt angle between the guide fin and the flapping wing body by cooperating with the drive shaft, worm and worm wheel. For example, when the installation angle of the guide fin on the left flapping wing body is set slightly larger and the right side slightly smaller, the aerodynamic difference caused by the difference in the angle of the guide fin will cause the aircraft to turn to the left during flight. Through this asymmetrical design, more sensitive and precise steering control can be achieved, so that the aircraft can change its flight direction more easily when performing complex flight tasks, such as bypassing obstacles or flying in a narrow space. Attached Figure Description
[0028] Figure 1 This is a schematic diagram of the overall structure of the flapping wing structure of this utility model;
[0029] Figure 2 This is a cross-sectional view of the flapping wing structure of this utility model;
[0030] Figure 3 This is a partial structural diagram of the flapping wing structure of this utility model;
[0031] Figure 4 This is a top view of the flapping wing structure of this utility model;
[0032] In the diagram: 1-flapping wing body, 2-arc tail edge, 3-guide fin, 4-rotating shaft, 5-first connecting frame, 6-bearing, 7-drive shaft, 8-second connecting frame, 9-worm gear, 10-worm wheel, 11-reinforcing rib, 12-motor. Detailed Implementation
[0033] The following description, in conjunction with the accompanying drawings and specific embodiments, provides further details. In the description of this utility model, it should be understood that the terms "first," "second," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Therefore, a feature defined with "first," "second," etc., may explicitly or implicitly include one or more of that feature.
[0034] Example 1
[0035] This embodiment provides a flapping wing structure, including: a flapping wing body 1 with a cavity, a guide fin 3, and a transmission assembly;
[0036] The cross-section of the guide fin 3 is arc-shaped, with part located inside the cavity and part located outside the cavity, and its bottom is fitted onto the outer ring of the rotating shaft 4 located inside the cavity;
[0037] The two ends of the rotating shaft 4 are fitted with a first connecting frame 5, and the ends of the first connecting frame 5 are connected to the inner wall of the cavity of the flapping wing body 1.
[0038] The transmission component is located inside the cavity, and the power end of the transmission component is sleeved on the outer ring of the rotating shaft 4 to provide power to the rotating shaft 4, so that the guide fin 3 rotates to a predetermined angle and restricts the automatic reverse rotation of the rotating shaft 4.
[0039] In practical applications, the power end is a turbine fitted on the outer ring of the rotating shaft 4.
[0040] Example 2
[0041] Based on Example 1, this example describes a specific structure of a flapping wing structure, such as... Figures 1-4 As shown, it specifically includes the following:
[0042] In one specific embodiment of this example, combined with Figure 2 and Figure 3 A bearing 6 is provided between the rotating shaft 4 and the first connecting frame 5, and the bearing 6 is sleeved on the outer ring of the rotating shaft 4.
[0043] The bearing 6 reduces the friction between the rotating shaft 4 and the first connecting frame 5, thereby improving the smoothness of the rotation of the guide fin 3.
[0044] In one specific embodiment of this example, the extension direction of the rotating shaft 4 is perpendicular to the length direction of the flapping wing body 1.
[0045] In one specific embodiment of this example, a plurality of reinforcing ribs 11 are uniformly arranged in the cavity, and the plurality of reinforcing ribs 11 are fixedly connected to the flapping wing body 1.
[0046] When flapping wings undergo complex movements such as flapping and twisting, they are subjected to forces from various sources, including aerodynamics, their own inertia, and their connection to the transmission mechanism. These forces can easily cause deformation, twisting, or even damage to the flapping wing body. Reinforcing ribs can alter the force distribution of the flapping wing body, enabling it to better withstand various stresses, dispersing external forces over a wider area, and preventing excessive local stress concentration.
[0047] In one specific embodiment of this example, the transmission assembly includes a drive shaft 7, a worm 9, and a worm wheel 10. The drive shaft 7 passes through multiple second connecting frames 8 and is connected to the bottom surface of multiple reinforcing ribs 11. The worm 9 is sleeved on the outer ring of the drive shaft 7, and the worm wheel 10 is sleeved on the outer ring of the rotating shaft 4. The worm 9 and the worm wheel 10 mesh.
[0048] The self-locking mechanism between the worm 9 and the worm wheel 10 prevents the guide fin 3 from automatically rotating in the opposite direction.
[0049] In one specific embodiment of this example, one end of the drive shaft 7 is connected to the motor 12, and the motor 12 is fixedly connected to the bottom surface of the reinforcing rib 11.
[0050] In one specific implementation of this embodiment, such as Figure 2 As shown, one end of the flapping wing body 1 is set as an arc-shaped tail edge 2, and the other end is connected to the aircraft.
[0051] In actual operation, by controlling the operation of motor 12, motor 12 drives drive shaft 7 to rotate, drive shaft 7 drives worm 9 to rotate, worm 9 drives worm wheel 10 to rotate, and worm wheel 10 drives guide fin 3 to rotate, thereby achieving the tilt setting of guide fin 3. The specific tilt setting is as follows:
[0052] When the guide fin 3 is tilted at a small angle to the flapping wing body 1, within the angle range of 0°-15°, the guide fin 3 mainly plays the role of fine adjustment of the airflow on the surface of the flapping wing body 1. It can make the airflow passing through the flapping wing body 1 more regular, reduce the generation of turbulence and vortex, and thus reduce air resistance.
[0053] When the tilt angle is in the range of 15°-30°, the effect of the guide fin 3 on changing the airflow is more significant, which can more effectively increase the pressure difference between the upper and lower surfaces of the flapping fin body 1, thereby significantly improving the lift generation efficiency.
[0054] By adjusting the angle of the flapping fins to 30°-45°, the aerodynamic distribution around the flapping fins can be rapidly changed, generating a large lateral force, enabling the aircraft to perform complex and rapid maneuvers such as sharp turns.
[0055] Example 3
[0056] This embodiment describes a flapping-wing aircraft that uses the flapping-wing structure as described in Embodiment 1 or 2.
[0057] The embodiments of the present utility model have been described above with reference to the accompanying drawings. However, the present utility model is not limited to the specific embodiments described above. The specific embodiments described above are merely illustrative and not restrictive. Those skilled in the art can make many other forms under the guidance of the present utility model without departing from the spirit and scope of the claims. All of these forms are within the protection scope of the present utility model.
Claims
1. A flapping wing structure, characterized in that, include: The flapping fin body (1) with a cavity, the guide fin (3) and the transmission assembly; The cross-section of the guide fin (3) is arc-shaped, with part located inside the cavity and part located outside the cavity. Its bottom is fitted around the outer ring of the rotating shaft (4) located inside the cavity. The two ends of the rotating shaft (4) are fitted with a first connecting frame (5), and the end of the first connecting frame (5) is connected to the inner wall of the cavity of the flapping wing body (1); The transmission assembly is located inside the cavity. The power end of the transmission assembly is sleeved on the outer ring of the rotating shaft (4) to provide power to the rotating shaft (4), so that the guide fin (3) rotates to a predetermined angle and restricts the automatic reverse rotation of the rotating shaft (4).
2. The flapping wing structure according to claim 1, characterized in that, A bearing (6) is provided between the rotating shaft (4) and the first connecting frame (5), and the bearing (6) is sleeved on the outer ring of the rotating shaft (4).
3. The flapping wing structure according to claim 2, characterized in that, The extension direction of the pivot (4) is perpendicular to the length direction of the flapping wing body (1).
4. The flapping wing structure according to claim 1, characterized in that, Multiple reinforcing ribs (11) are uniformly arranged inside the cavity, and the multiple reinforcing ribs (11) are fixedly connected to the flapping wing body (1).
5. The flapping wing structure according to claim 4, characterized in that, The transmission assembly includes a drive shaft (7), a worm (9), and a worm wheel (10). The drive shaft (7) passes through multiple second connecting frames (8) and connects to the bottom surface of multiple reinforcing ribs (11). The worm (9) is sleeved on the outer ring of the drive shaft (7), and the worm wheel (10) is sleeved on the outer ring of the rotating shaft (4). The worm (9) meshes with the worm wheel (10).
6. The flapping wing structure according to claim 5, characterized in that, One end of the drive shaft (7) is connected to the motor (12), and the motor (12) is fixedly connected to the bottom surface of the reinforcing rib (11).
7. The flapping wing structure according to claim 1, characterized in that, One end of the flapping wing body (1) is set as an arc-shaped tail edge (2), and the other end is connected to the aircraft.
8. A flapping-wing aircraft, characterized in that, The flapping wing structure as described in any one of claims 1-7 is applied.