Flight-oriented fan blade trailing edge adjustment device

Abstract

The application discloses a fan wing trailing edge adjusting device for flight and relates to the technical field of aircrafts, which comprises a trailing edge angle adjusting mechanism, a fairing angle adjusting mechanism, a circular end plate and a fairing plate, the trailing edge angle adjusting mechanism comprises a steering engine, a first connecting rod mechanism, a trailing edge plate and a rotating shaft, the steering engine is fixedly installed on the circular end plate, the steering engine controls the trailing edge plate to move through the first connecting rod mechanism, the rotating shaft is arranged on one side of the trailing edge plate, and the trailing edge plate is hinged to the fairing plate through the rotating shaft, the size of the trailing edge angle and the fairing angle is freely adjusted, the aerodynamic force of the fan wing aircraft changes, the lift and thrust distribution is improved, the aerodynamic effect is enhanced, the energy consumption is reduced, and the flight efficiency is improved. The fan wing trailing edge adjusting device is applied to a tandem fan wing, the size of the trailing edge angle and the fairing angle is changed, the positive coupling gain between the two wings is realized, different flight conditions are met, various flight requirements are flexibly coped with, and the load performance and the endurance are optimized.

Description

Technical Field

[0001] This invention relates to the field of aircraft technology, and more particularly to a trailing edge adjustment device for a flight-oriented fan wing. Background Technology

[0002] Fan-wing aircraft are flying devices that utilize the rotation of a cross-flow fan to draw in incoming airflow, accelerate it, and form an eccentric vortex, thereby generating lift and thrust. Due to their characteristics of short takeoff distance and high load at low speed, they have received increasing attention in the field of aircraft research in recent years.

[0003] The distribution of lift and thrust in a fan-wing aircraft is influenced by its airfoil structure, with the main structural parameters being the trailing edge angle and the rectification angle. An increased trailing edge angle increases lift, while a decreased rectification angle increases thrust. In fan-wing aircraft, such as the crossflow fan wing device proposed in CN107826245A, the airfoil's bottom slot is fixed. In actual flight, aerodynamic forces can only be changed by rotational speed, and lift and thrust cannot be freely altered, making it difficult to adapt to different flight conditions.

[0004] In a tandem fan-wing configuration, airflow coupling exists between the front and rear wings, primarily affecting the formation and stability of the eccentric vortex on the rear wing, leading to variations in trailing edge lift and thrust. Patent CN 104276284 A only studies vertical takeoff and landing in its tandem configuration, with limited attention to lift and thrust distribution. Applying a trailing edge adjustment device to a tandem fan-wing configuration can better adapt to various flight conditions. Summary of the Invention

[0005] This invention provides a flight-oriented trailing edge adjustment device for fan-wing aircraft, which can effectively improve the lift and thrust distribution of fan-wing aircraft, adapt to multiple flight modes, save energy, and improve flight efficiency.

[0006] To achieve the above objectives, the present invention provides a flight-oriented fan-shaped trailing edge adjustment device, comprising a trailing edge angle adjustment mechanism, a rectification angle adjustment mechanism, a circular endplate, and a rectification plate. The trailing edge angle adjustment mechanism includes a servo, a first linkage mechanism, a trailing edge plate, and a rotating shaft. The servo is fixedly mounted on the circular endplate and controls the movement of the trailing edge plate through the first linkage mechanism. The rotating shaft is located on one side of the trailing edge plate, and the trailing edge plate is hinged to the rectification plate through the rotating shaft. The rectification angle adjustment mechanism includes an electric push rod and a second linkage mechanism. The electric push rod is fixedly connected to the trailing edge plate, and controls the adjustment angle of the rectification plate through the second linkage mechanism.

[0007] In some embodiments, the first linkage mechanism includes a driving gear, a driven gear, a gear shaft, a driving rod, a transmission rod, a driven rod, and a fixed shaft. The fixed shaft is fixedly mounted on a circular end plate. One end of the driven rod is rotatably mounted on the fixed shaft. The driving gear is fixedly mounted on the output end of the servo motor. The gear shaft is fixedly mounted on the circular end plate. The driven gear is fixedly fitted onto the gear shaft and meshes with the driving gear. One end of the driving rod is fixedly connected to the gear shaft, and the other end of the driving rod is hinged to the transmission rod. One end of the transmission rod is hinged to the driven rod. One end of the driven rod is rotatably mounted on one end of the fixed shaft, and the other end of the driven rod is fixedly connected to the rear edge plate.

[0008] In some embodiments, the fixed shaft is fixed at the center of the circular end plate, the driven rod drives the rear edge plate to rotate around the fixed shaft, the center of the rear edge plate and the center of the circular end plate are on the same axis, and the rear edge plate swings below the arc-shaped concave surface of the fixed bottom groove.

[0009] In some embodiments, the trailing edge angle adjustment mechanism further includes a roller, which is rotatably mounted on the edge of a circular end plate, and the surface of the roller is in contact with the inner wall of the trailing edge plate.

[0010] In some embodiments, the trailing edge plate has a fan-shaped cross-section with a central angle of 60° and an axial extension length greater than the blade length. The rectifier plate is a square flat plate with an axial extension length the same as that of the trailing edge plate.

[0011] In some embodiments, the second linkage mechanism includes a bolt bracket, a moving rod, a rotary link, a support shaft, a ball joint link, and a ball joint support. The bolt bracket is fixedly mounted on the rear edge plate, the electric push rod is fixedly mounted on the rear edge plate via the bolt bracket, one end of the moving rod is fixedly mounted on the output end of the electric push rod, the support shaft is fixedly mounted on the surface of the rear edge plate, the rotary link is rotatably connected to the support shaft, one end of the rotary link is hinged to the moving rod, the other end of the rotary link is connected to the ball joint link via a ball joint bearing, one end of the ball joint link is connected to the ball joint support via a ball joint bearing, and the ball joint support is fixedly mounted on the rectifier plate.

[0012] In some embodiments, the number of support shafts is at least two, the straight line of the two support shafts is parallel to both the moving rod and the rectifier plate, and the slewing link is L-shaped.

[0013] In some embodiments, the angle between the line connecting the trailing edge point of the trailing edge plate to the center point of the arc and the horizontal line passing through the center of the arc is the trailing edge angle β, and the angle between the rectifier plate and the horizontal plane is the rectification angle γ. The trailing edge angle β is 0 to 60°, and the rectification angle γ is 0 to 90°.

[0014] In some embodiments, when the trailing edge angle β = 0°, the highest point of the trailing edge plate is on a horizontal line passing through the center of the circular end plate, and when the trailing edge angle β = 60°, the trailing edge point of the trailing edge plate is on a vertical line passing through the center of the circular end plate.

[0015] In some embodiments, the rectification angle γ is 0 to 90°. When the rectification angle γ = 0°, the rectifier plate is perpendicular to the horizontal line, and when the rectification angle γ = 90°, the rectifier plate is parallel to the horizontal line.

[0016] Compared with related technologies, the trailing edge adjustment device for a flight-oriented fan wing provided by the present invention has the following beneficial effects:

[0017] This invention provides a flight-oriented trailing edge adjustment device for fan-wing aircraft. It features a simple structure, good stability, high reliability, and long service life. This device allows for the free adjustment of the trailing edge angle and the rectification angle, thereby altering the aerodynamic forces of the fan-wing aircraft, improving lift and thrust distribution, enhancing aerodynamic performance, reducing energy consumption, and increasing flight efficiency. Applying this device to tandem fan-wing aircraft, by changing the trailing edge angle and rectification angle, achieves positive coupling gain between the two wings, meeting different flight conditions and flexibly responding to various flight requirements, thus optimizing payload performance and range. Attached Figure Description

[0018] Figure 1 This is an isometric view of the structure of the fan trailing edge adjustment device of the present invention;

[0019] Figure 2 This is a schematic diagram of the trailing edge angle adjustment mechanism of the present invention;

[0020] Figure 3 This is a schematic diagram of the rectification angle adjustment mechanism of the present invention;

[0021] Figure 4 This is a schematic diagram of the coupling effect between the front and rear wings of a tandem twin-wing aircraft.

[0022] Figure 5 A simulation diagram showing the change in lift as the trailing edge angle β varies from 30° to 70°.

[0023] Figure 6 A simulation diagram showing the thrust variation as the trailing edge angle β changes from 30° to 70°.

[0024] Figure 7 This is a simulation diagram of the lift change when the trailing edge angle β varies from 30° to 70°, with a leading edge opening angle of 40°.

[0025] Figure 8 This is a simulation diagram of thrust variation when the trailing edge angle β changes from 30° to 70° with a leading edge opening angle of 40°.

[0026] Figure 9 This is a simulation diagram of the aerodynamic changes as the rectification angle γ varies from 10° to 75°.

[0027] The following are the labeling elements in the diagram: 1. Trailing edge angle adjustment mechanism; 2. Rectifying angle adjustment mechanism; 3. Servo motor; 4. Drive gear; 5. Driven gear; 6. Gear shaft; 7. Drive rod; 8. Transmission rod; 9. Driven rod; 10. Fixed shaft; 11. Trailing edge plate; 12. Rotating shaft; 13. Rectifying plate; 14. Roller; 15. Electric push rod; 16. Bolt bracket; 17. Moving rod; 18. Rotating connecting rod; 19. Support shaft; 20. Ball joint connecting rod; 21. Ball joint support; 22. Circular end plate; 23. Fixed bottom groove; 31. Forewing; 32. Rearwing. Detailed Implementation

[0028] Example 1

[0029] This embodiment provides a flight-oriented trailing edge adjustment device for a fan wing, such as... Figure 1-4 As shown, the present invention includes a trailing edge angle adjustment mechanism 1, a rectification angle adjustment mechanism 2, a circular end plate 22, and a rectification plate 13. The trailing edge angle adjustment mechanism 1 includes a servo motor 3, a first linkage mechanism, a trailing edge plate 11, and a rotating shaft 12. The servo motor 3 is fixedly mounted on the circular end plate 22. The servo motor 3 controls the movement of the trailing edge plate 11 through the first linkage mechanism. The rotating shaft 12 is located on one side of the trailing edge plate 11, and the trailing edge plate 11 is hinged to the rectification plate 13 through the rotating shaft 12. The rectification angle adjustment mechanism 2 includes an electric push rod 15 and a second linkage mechanism. The electric push rod 15 is fixedly connected to the trailing edge plate 11, and the electric push rod 15 controls the adjustment angle of the rectification plate 13 through the second linkage mechanism.

[0030] In this embodiment, the servo motor 3 in the trailing edge angle adjustment mechanism 1 drives the trailing edge plate 11 to rotate through the first linkage mechanism, thereby adjusting the size of the trailing edge angle; the electric push rod 15 in the rectification angle adjustment mechanism 2 extends and retracts, drives the rectification plate 13 to rotate through the second linkage mechanism, thereby adjusting the size of the rectification angle. By changing the size of the trailing edge angle and the rectification angle, positive coupling gain between the two wings is achieved, which can meet different flight conditions, flexibly respond to various flight requirements, and optimize the load performance and endurance.

[0031] Example 2

[0032] Based on Example 1, such as Figure 2As shown, the first linkage mechanism in this embodiment includes a driving gear 4, a driven gear 5, a gear shaft 6, a driving rod 7, a transmission rod 8, a driven rod 9, and a fixed shaft 10. The fixed shaft 10 is fixedly mounted on a circular end plate 22. One end of the driven rod 9 is rotatably mounted on the fixed shaft 10. The driving gear 4 is fixedly mounted on the output end of the servo motor 3. The gear shaft 6 is fixedly mounted on the circular end plate 22. The driven gear 5 is fixedly mounted on the gear shaft 6 and meshes with the driving gear 4. One end of the driving rod 7 is fixedly connected to the gear shaft 6, and the other end of the driving rod 7 is hinged to the transmission rod 8. One end of the transmission rod 8 is hinged to the driven rod 9. One end of the driven rod 9 is rotatably mounted on one end of the fixed shaft 10, and the other end of the driven rod 9 is fixedly connected to the rear edge plate 11.

[0033] In this embodiment, utilizing the precise angle control capability of the servo motor 3, and combining it with the interconnection and fixed mounting of the drive rod 7, transmission rod 8, driven rod 9, and fixed shaft 10 on the circular end plate 22, a relatively stable mechanical structure system is formed. Through the transmission ratios and geometric relationships between the components, the position of the trailing edge plate 11 can be precisely controlled. The components mutually constrain and cooperate, sharing the forces during motion. Compared to a single transmission structure, it can better handle forces in different directions, reducing the risk of structural damage due to uneven force distribution, vibration, and other factors, ensuring the reliability of the entire device during long-term operation. During flight, the aircraft is affected by various complex external forces such as airflow. This linkage mechanism can stably convert the control signals of the servo motor 3 into corresponding actions of the wing trailing edge plate 11, ensuring that the structure will not easily malfunction due to vibrations or airflow impacts during flight, maintaining the aircraft's stable flight attitude.

[0034] Example 3

[0035] Based on Example 2, such as Figure 2 As shown, in this embodiment, the fixed shaft 10 is fixed at the center of the circular end plate 22, and the driven rod 9 drives the rear edge plate 11 to rotate around the fixed shaft 10. The center of the rear edge plate 11 and the center of the circular end plate 22 are on the same axis, and the rear edge plate 11 swings below the arc-shaped concave surface of the fixed bottom groove 23.

[0036] In this embodiment, the trailing edge plate 11 is concentrically arranged with the arc-shaped concave surface of the fixed bottom groove 23, and swings below the arc-shaped concave surface of the fixed bottom groove 23. During the swinging process, the trailing edge plate 11 can maintain a cooperative relationship with the circular end plate 22. The arc-shaped concave surface can guide the airflow to flow more smoothly over the trailing edge plate 11, reduce airflow turbulence and fluctuations, and improve airflow stability. This is of great significance for improving the performance of the fan blade and reducing noise.

[0037] Example 4

[0038] Based on Example 1, such as Figure 2 As shown, the trailing edge angle adjustment mechanism 1 of this embodiment also includes a roller 14, which is rotatably mounted on the edge of the circular end plate 22, and the surface of the roller 14 is in contact with the inner wall of the trailing edge plate 11.

[0039] In this embodiment, when the trailing edge plate 11 moves, especially when it rotates and oscillates around the fixed axis 10, it comes into contact with the roller 14. Since the roller 14 can rotate, the friction between the trailing edge plate 11 and the roller 14 changes from sliding friction to rolling friction. The frictional force of rolling friction is much smaller than that of sliding friction, which significantly reduces the resistance experienced by the trailing edge plate 11 during movement. Furthermore, during the operation of the fan blade, the trailing edge plate 11 may be subject to external forces such as airflow, leading to displacement or deformation. The roller 14 can limit the movement of the trailing edge plate 11 within a certain range, acting as a guide and ensuring that the trailing edge plate 11 moves along a predetermined trajectory. In addition, since the roller 14 bears most of the frictional force during the movement of the trailing edge plate 11, it reduces the wear caused by direct contact between the trailing edge plate 11 and the circular end plate 22. This helps extend the service life of both the trailing edge plate 11 and the circular end plate 22.

[0040] Example 5

[0041] Based on Example 1, such as Figure 2 As shown, the trailing edge plate 11 in this embodiment has a fan-shaped cross-section with a central angle of 60° and an axial extension length greater than the blade length. The rectifier plate 13 is a square flat plate with an axial extension length the same as that of the trailing edge plate 11.

[0042] In this embodiment, the cross-sectional shape of the trailing edge plate 11 is defined as a fan ring. This specific shape provides a basis for the installation and functional realization of the trailing edge plate 11 in the fan blade structure. The fan ring shape can better match the overall shape of the fan blade, making the adjustment of the trailing edge angle of the trailing edge plate 11 smoother and more efficient. The 60° central angle can limit the swing amplitude of the trailing edge plate 11 to a certain extent, and also provide a clear range for the adjustment of the trailing edge angle. The axial extension length of the trailing edge plate 11 is slightly greater than the blade length, which facilitates the connection between the trailing edge plate 11 and the first transmission mechanism. The square straight plate can better guide the airflow, reduce airflow turbulence and fluctuations, and improve airflow stability. The axial extension length of the rectifier plate 13 is the same as that of the trailing edge plate 11. This setting can ensure the coordination and consistency between the rectifier plate 13 and the trailing edge plate 11 during operation. When the trailing edge angle of the trailing edge plate 11 is adjusted, the rectifier plate 13 can adjust the rectification angle accordingly to achieve the best airflow rectification effect.

[0043] Example 6

[0044] Based on Example 1, such as Figure 3 As shown, the second linkage mechanism in this embodiment includes a bolt bracket 16, a moving rod 17, a rotating connecting rod 18, a support shaft 19, a ball joint connecting rod 20, and a ball joint support 21. The bolt bracket 16 is fixedly installed on the rear edge plate 11. The electric push rod 15 is fixedly installed on the rear edge plate 11 through the bolt bracket 16. One end of the moving rod 17 is fixedly installed on the output end of the electric push rod 15. The support shaft 19 is fixedly installed on the surface of the rear edge plate 11. The rotating connecting rod 18 is rotatably connected to the support shaft 19. One end of the rotating connecting rod 18 is hinged to the moving rod 17. The other end of the rotating connecting rod 18 is connected to the ball joint connecting rod 20 through a ball joint bearing. One end of the ball joint connecting rod 20 is connected to the ball joint support 21 through a ball joint bearing. The ball joint support 21 is fixedly installed on the rectifier plate 13.

[0045] In this embodiment, the output end of the electric push rod 15 extends and retracts to drive the moving rod 17 forward, causing the rotary connecting rod 18 to rotate around the support shaft 19. One end 20 of the ball joint connecting rod is connected to the rotary connecting rod 18 through a ball joint bearing, and the other end is fitted onto the ball joint support 21 on the rectifier plate 13, causing the rectifier plate 13 to rotate around the rotary shaft 12, thereby adjusting the rectification angle. The ball joint connection and the rotary connecting rod 18 enable the rectifier plate 13 to adapt to complex motion requirements. During flight, the fan blade is subjected to various external forces, such as airflow impact and vibration, which may cause changes in the direction and angle of motion of the rectifier plate 13. The ball joint connection allows the rectifier plate 13 to rotate freely in multiple directions, thereby adapting to these complex motion requirements, ensuring that the rectifier plate 13 can always effectively regulate the airflow, and improving the stability and reliability of the fan blade. The entire second linkage mechanism has a compact structure, occupies little space, and is suitable for installation in the limited space of the fan blade. Meanwhile, the connections between the various components are tight, using bolts, hinges, and ball joints to ensure the stability and reliability of the mechanism during operation.

[0046] Example 7

[0047] Based on Example 6, such as Figure 3 As shown, in this embodiment, the number of support shafts 19 is at least two, and the straight line of the two support shafts 19 is parallel to the moving rod 17 and the rectifier plate 13. The rotating connecting rod 18 is L-shaped.

[0048] In this embodiment, when the rotary link 18 rotates under the force transmitted from the moving rod 17 during operation, the multiple support shafts 19 can share the load, reducing the pressure on a single support shaft 19 and thus lowering the risk of damage to the support shaft 19 due to excessive force. The rotary link 18 is L-shaped, which can change the direction of force transmission, making it more suitable for converting the linear motion of the moving rod 17 into rotational motion suitable for adjusting the angle of the rectifier plate 13.

[0049] Example 8

[0050] like Figure 2 As shown, in this embodiment, the angle between the line connecting the trailing edge point of the trailing edge plate 11 to the center point of the arc and the horizontal line passing through the center of the arc is the trailing edge angle β. The angle between the rectifier plate 13 and the horizontal plane is the rectification angle γ. The trailing edge angle β ranges from 0 to 60°, and the rectification angle γ ranges from 0 to 90°. When the trailing edge angle β = 0°, the highest point of the trailing edge plate 11 is on the horizontal line passing through the center of the circular end plate 22. When the trailing edge angle β = 60°, the trailing edge point of the trailing edge plate 11 is on the vertical line passing through the center of the circular end plate 22. The rectification angle γ ranges from 0 to 90°. When the rectification angle γ = 0°, the rectifier plate 13 is parallel to the horizontal line, and when the rectification angle γ = 90°, the rectifier plate 13 is perpendicular to the horizontal line.

[0051] In this embodiment, during the design phase, appropriate ranges for the trailing edge angle β and the rectification angle γ can be determined based on different flight requirements and aerodynamic principles to optimize the fan blade performance. During manufacturing, precise machining and assembly ensure that the angles of the trailing edge plate 11 and the rectification plate 13 meet the design requirements. During use, operators can adjust these two angles using the adjustment mechanism according to actual flight conditions to achieve optimal flight performance.

[0052] Specific states of trailing edge angle β:

[0053] When the trailing edge angle β = 0°, the highest point of the trailing edge plate 11 is on the horizontal line passing through the center of the circular end plate 22. At this time, the high-speed airflow accelerated by the internal impeller rotation of the fan is discharged horizontally from above the trailing edge point, increasing the fan thrust and decreasing the lift. This state may be suitable for some situations requiring low drag and high-speed flight, or for situations where increased thrust or decreased lift is needed during landing. For example, during takeoff, in order to reach a safe altitude as quickly as possible, the trailing edge angle β can be adjusted to a smaller value to increase thrust and increase flight speed, allowing the aircraft to accelerate more quickly. During high-speed cruise, in order to increase thrust and improve fuel efficiency, the trailing edge angle β can also be kept at a smaller angle.

[0054] When the trailing edge angle β = 60°, the midpoint of the arc of the trailing edge plate 11 lies on the perpendicular line passing through the center of the circular end plate 22. The high-speed airflow discharged after the internal impeller of the fan increases, and the airflow is discharged obliquely downwards and backwards. Part of the thrust is converted into lift, resulting in decreased thrust and increased lift. This state may be suitable for situations requiring greater lift, such as during low-speed flight, takeoff, or certain special flight missions. For example, when the aircraft is under heavy load, to increase lift, the trailing edge angle β can be adjusted to a larger value. The reaction force of the high-speed airflow discharged obliquely downwards from the tail of the fan increases lift, thereby increasing the aircraft's load-bearing capacity.

[0055] Specific states of the rectification angle γ:

[0056] When the rectification angle γ = 0°, the rectifier plate 13 is perpendicular to the horizontal line, and at this time, the rectification effect of the rectifier plate 13 on the airflow is strongest. This state allows the airflow to flow more smoothly over the trailing edge of the fan, reducing airflow turbulence and energy loss, and improving the efficiency of the fan. For example, in some situations requiring high-efficiency flight, such as long-distance flight or performing important missions, the rectification angle γ can be adjusted to 0° to improve the aircraft's performance and stability.

[0057] When the rectification angle γ = 90°, the fairing 13 is parallel to the horizontal line, and its impact on airflow is minimized. This state may be suitable for situations requiring less rectification, such as during special flight maneuvers or in certain specific flight environments. For example, during high-speed rolls or sharp turns, to reduce the impact of the fairing 13 on aircraft maneuverability, the rectification angle γ can be adjusted to 90° to minimize the interference of the fairing 13 on airflow.

[0058] like Figure 4 As shown, the trailing edge adjustment device of the fan wing is respectively installed on the fore wing 31 and the rear wing 32 of the tandem wing. The trailing edge adjustment device controls the deflection of the trailing edge plate 11 and the rectifier plate 13 through the servo motor 3 and the electric push rod 15, that is, controls the size of the fan wing trailing edge angle β and the rectification angle γ. The rotation of the impeller inside the fan wing generates a high-speed airflow, which flows out from the trailing edge and flows along the rectifier plate to the rear wing. When both the fore wing trailing edge angle β and the rectification angle γ decrease, the exhaust airflow of the fore wing increases and the outflow direction tends to be horizontal, which enhances the aerodynamic force of the trailing edge.

[0059] like Figure 5-6 As shown, the incoming flow is 4 m / s, the rotational speed is 1200 rpm, and the trailing edge angle β varies from 30° to 70°. The lift continuously increases and the thrust continuously decreases. Different colored curves represent different leading edge opening angles.

[0060] like Figure 7-8 As shown, with an incoming flow of 4 m / s, a rotational speed of 1200 rpm, and a leading edge opening angle of 40°, the trailing edge angle β changes from 30° to 70°, resulting in a continuous increase in lift and a continuous decrease in thrust.

[0061] like Figure 9 As shown, with an incoming flow rate of 4 m / s and a rotational speed of 1200 rpm, as the rectification angle γ increases from 15° to 75°, the lift continuously increases while the thrust continuously decreases.

[0062] Therefore, the aircraft attitude can be controlled based on the relationship between the changes in the trailing edge angle β and the rectification angle γ and the aerodynamic forces. Working principle: The servo motor 3 in the trailing edge angle adjustment mechanism 1 drives the drive gear 4 to mesh with the driven gear 5 and rotate, which drives the drive rod 7 to move. The drive rod 7 is connected to the transmission rod 8 through a rotary joint, causing the transmission rod 8 to rotate around the drive rod 7. At the same time, it drives the driven rod 9 to rotate around the fixed shaft 10. The trailing edge plate 11, which is fixed to the driven rod 9, rotates along the roller 14, thereby adjusting the size of the trailing edge angle. The electric push rod 15 in the rectification angle adjustment mechanism 2 extends and retracts, driving the moving rod 17 to move forward and drive the rotary connecting rod 18 to rotate around the support shaft 19. One end 20 of the ball joint connecting rod is connected to the rotary connecting rod 18 through a ball joint bearing. The other end is sleeved on the ball joint support 21 on the rectification plate 13 and drives the rectification plate 13 to rotate around the rotary shaft 12, thereby adjusting the size of the rectification angle. The flight-oriented fan trailing edge adjustment device achieves free adjustment of the fan trailing edge angle and the rectification angle through the trailing edge angle adjustment mechanism 1 and the rectification angle adjustment mechanism 2, thereby changing the aerodynamic force of the fan and improving the distribution of lift and thrust to adapt to different flight conditions.

Claims

1. A trailing edge adjustment device for a flight-oriented fan wing, comprising a trailing edge angle adjustment mechanism, a rectification angle adjustment mechanism, a circular endplate, and a rectification plate, characterized in that: The trailing edge angle adjustment mechanism includes a servo motor, a first linkage mechanism, a trailing edge plate, and a rotating shaft; The servo is fixedly mounted on the circular end plate. The servo controls the movement of the trailing edge plate through the first linkage mechanism. The rotating shaft is located on one side of the trailing edge plate. The trailing edge plate is hinged to the rectifier plate through the rotating shaft. The rectification angle adjustment mechanism includes an electric push rod and a second linkage mechanism; The electric push rod is fixedly connected to the rear edge plate, and the electric push rod controls the adjustment angle of the rectifier plate through the second linkage structure. The first linkage mechanism includes a driving gear, a driven gear, a gear shaft, a driving rod, a transmission rod, a driven rod, and a fixed shaft. The fixed shaft is fixedly mounted on a circular end plate. One end of the driven rod is rotatably mounted on the fixed shaft. The driving gear is fixedly mounted on the output end of the servo motor. The gear shaft is fixedly mounted on the circular end plate. The driven gear is fixedly fitted onto the gear shaft and meshes with the driving gear. One end of the driving rod is fixedly connected to the gear shaft, and the other end of the driving rod is hinged to the transmission rod. One end of the transmission rod is hinged to the driven rod. One end of the driven rod is rotatably mounted on one end of the fixed shaft, and the other end of the driven rod is fixedly connected to the rear edge plate. The fixed shaft is fixed at the center of the circular end plate, and the driven rod drives the rear edge plate to rotate around the fixed shaft. The center of the rear edge plate and the center of the circular end plate are on the same axis, and the rear edge plate swings below the arc-shaped concave surface of the fixed bottom groove.

2. The trailing edge adjustment device for a flight-oriented fan wing according to claim 1, characterized in that, The trailing edge angle adjustment mechanism also includes a roller, which is rotatably mounted on the edge of the circular end plate, and the surface of the roller is in contact with the inner wall of the trailing edge plate.

3. The trailing edge adjustment device for a flight-oriented fan wing according to claim 1, characterized in that, The trailing edge plate has a fan-shaped cross-section with a central angle of 60° and an axial extension length greater than the blade length. The rectifier plate is a square flat plate with an axial extension length the same as the trailing edge plate.

4. The trailing edge adjustment device for a flight-oriented fan wing according to claim 1, characterized in that, The second linkage mechanism includes a bolt bracket, a moving rod, a rotating linkage, a support shaft, a ball joint linkage, and a ball joint support. The bolt bracket is fixedly mounted on the rear edge plate. The electric push rod is fixedly mounted on the rear edge plate via the bolt bracket. One end of the moving rod is fixedly mounted on the output end of the electric push rod. The support shaft is fixedly mounted on the surface of the rear edge plate. The rotating linkage is rotatably connected to the support shaft. One end of the rotating linkage is hinged to the moving rod. The other end of the rotating linkage is connected to the ball joint linkage via a ball joint bearing. One end of the ball joint linkage is connected to the ball joint support via a ball joint bearing. The ball joint support is fixedly mounted on the rectifier plate.

5. A flight-oriented trailing edge adjustment device for a fan-shaped wing according to claim 4, characterized in that, The number of support shafts is at least two, and the straight line of the two support shafts is parallel to the moving rod and the rectifier plate. The slewing link is L-shaped.

6. A flight-oriented trailing edge adjustment device for a fan-shaped wing according to any one of claims 1-5, characterized in that, The angle between the line connecting the trailing edge point of the trailing edge plate to the center point of the arc and the horizontal line passing through the center of the arc is the trailing edge angle β. The angle between the rectifier plate and the horizontal plane is the rectification angle γ. The trailing edge angle β is 0~60° and the rectification angle γ is 0~90°.

7. A flight-oriented trailing edge adjustment device for a fan-shaped wing according to claim 6, characterized in that, When the trailing edge angle β = 0°, the highest point of the trailing edge plate is on the horizontal line passing through the center of the circular end plate; when the trailing edge angle β = 60°, the trailing edge point of the trailing edge plate is on the vertical line passing through the center of the circular end plate.

8. A flight-oriented trailing edge adjustment device for a fan-shaped wing according to claim 6, characterized in that, The rectification angle γ is 0~90°. When the rectification angle γ=0°, the rectifier plate is perpendicular to the horizontal line, and when the rectification angle γ=90°, the rectifier plate is parallel to the horizontal line.

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