Aleron control structure suitable for telescopic wing
By integrating the control components inside the wing and employing a servo mechanism and lever design, the problem of aileron control interference in existing telescopic wings has been solved, achieving seamless integration and improved flight performance.
Patent Information
- Application Number
- CN202422884607.2
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-11-25
- Publication Date
- 2025-11-14
- Estimated Expiration
- 2034-11-25
AI Technical Summary
The existing retractable wing control structure has failed to effectively optimize aileron control, resulting in external control mechanisms interfering with wing retraction and affecting flight performance.
The control components are integrated inside the wing, and a combination design of servo mechanism, rocker arm and lever is adopted to ensure that the rocker arm is inside the wing when the aileron is in neutral position, so as to avoid interference with wing retraction. Vibration is reduced by elastic fasteners and the structural life is improved.
Seamless integration of aileron control was achieved, improving the maneuverability and flight performance of the retractable wing, reducing air resistance, and enhancing the tightness and stability of the structure.
Smart Images
Figure CN223546499U_ABST
Abstract
Description
Technical Field
[0001] This utility model relates to the field of aircraft control technology, specifically to an aileron control structure suitable for telescopic wings. Background Technology
[0002] With the rapid development of drone and model aircraft technology, aircraft design has seen significant improvements in performance, operability, and structural complexity. Especially in the pursuit of more efficient space utilization and flight efficiency, retractable wing technology has gradually gained attention. Retractable wings allow aircraft to adjust their wingspan under different flight conditions, maintaining a compact structure during takeoff and landing while expanding their wingspan during cruise to achieve higher lift efficiency. This flexibility makes retractable wings a promising area for application in small drones and model aircraft.
[0003] However, despite overall progress in retractable wing technology, existing control structures largely focus only on the retraction and strength design of the airframe, neglecting the optimization of the aileron control system. As a crucial component for aircraft attitude control, the aileron directly impacts flight stability and maneuverability. Therefore, aileron control is paramount in retractable wings.
[0004] Because retractable wings require the outer wing to be tightly inserted into the inner wing, external control mechanisms can interfere with the smooth retraction of the two wings, resulting in insufficient coordination between the wings and even affecting flight performance. Utility Model Content
[0005] I. Technical problems to be solved
[0006] This invention addresses the shortcomings of existing technologies by proposing an aileron control structure suitable for telescopic wings. This structure integrates control components inside the wing, ensuring that the rocker arm is inside the wing when the aileron is in the neutral position, thus guaranteeing that the outer wing can smoothly insert into the inner wing.
[0007] II. Specific Technical Solutions
[0008] Aileron control structure suitable for telescopic wings includes a frame (1) and an aileron (2), the aileron (2) being hinged to the side of the frame (1). A wing beam (3) is distributed along the length direction of the frame (1), and wing ribs (4) are distributed along the width direction. The structure is characterized in that a servo mechanism (5) is provided on the side of one of the wing ribs (4). The output end of the servo mechanism (5) is connected to a rocker arm (6), and the output end of the rocker arm (6) is connected to a pull rod (7). The other end of the pull rod (7) is bent downward and hinged to the side of the aileron (2).
[0009] During use, the output shaft of the servo mechanism (5) rotates, driving the rocker arm (6) to rotate, and the lever (7) pulls the aileron (2) to rotate, thereby controlling the aileron (2). Because the connection end of the lever (7) and the aileron (2) bends downward, the swing height of the rocker arm (6) decreases during the rotation of the lever (7), so that it is always inside the frame (1) during operation.
[0010] Preferably, the tie rod (7) passes through the upper surface of the wing spar (3), and an elastic fastener (8) is provided at the intersection of the tie rod (7) and the wing spar (3). The elastic connection with the elastic fastener (8) not only provides flexibility but also effectively reduces vibration and improves the service life of the aileron control structure.
[0011] Preferably, the elastic fastener (8) is a rubber ring. Rubber rings have a simple structure, low cost, and high elasticity.
[0012] Preferably, the connection end of the lever (7) to the aileron (2) is close to a wing spar (3), and the connection end of the lever (7) maintains an angle of 15° to 30° with the wing spar (3). This ensures that when the aileron (2) is in the neutral position, the rocker arm (6) is located inside the fuselage, thereby preventing the rocker arm from protruding outside the wing and affecting the retraction and deployment process of the telescopic wing.
[0013] Preferably, when the connecting surfaces of the aileron (2) and the frame (1) are in a parallel position, the highest point of the rocker arm (6) is lower than the highest point of the wing rib (4).
[0014] Preferably, the wing spar (3) passes through the wing rib (4). The wing spar (3) and the wing rib (4) are connected to each other to form a whole, which improves the mechanical strength of the structure.
[0015] The beneficial effects of this utility model are as follows: 1. The servo mechanism, rocker arm, and lever are all installed inside the wing. The lever and aileron are bent downwards to ensure that when the aileron is in the neutral position, the rocker arm is located inside the wing and does not interfere with the wing's retraction operation. This greatly improves the operability and close coordination of the telescopic wing, while reducing air resistance and improving flight performance.
[0016] 2. When the aileron is in the neutral position, all components in the control mechanism are located inside the wing, ensuring that the outer wing can be smoothly inserted into the inner wing to achieve seamless docking and ensure unobstructed extension and retraction.
[0017] 3. The overall design is simple and reliable, suitable for various types of retractable wing aircraft, and has high practicality and stability. Attached Figure Description
[0018] Figure 1 This is a schematic diagram of the structure of this utility model.
[0019] Figure 2 for Figure 1 The structural diagram of A in the middle.
[0020] Figure 3 This is a schematic diagram of the telescopic extension of this utility model. Detailed Implementation
[0021] The preferred embodiments of this utility model will now be described in detail with reference to the accompanying drawings, so that the advantages and features of this utility model can be more easily understood by those skilled in the art, thereby providing a clearer and more definite definition of the scope of protection of this utility model. All other embodiments obtained by those skilled in the art based on the embodiments of this utility model without inventive effort are within the scope of protection of this utility model.
[0022] like Figure 1 and Figure 2 As shown: An aileron control structure suitable for telescopic wings includes a rectangular frame 1 and an aileron 2. Three wing beams 3 are distributed along the length of the frame 1. The aileron 2 is hinged to the wing beam 3 near the side. Four wing ribs 4 are distributed along the width, with the wing beams 3 passing through the wing ribs 4 to form the frame 1. A servo mechanism 5 is fixedly installed on the side of the second wing rib 4 from the inside to the outside. The output end of the servo mechanism 5 is connected to a rocker arm 6. The output end of the rocker arm 6 is connected to a pull rod 7. The other end of the pull rod 7 is bent downward and hinged to the side of the aileron 2.
[0023] The tie rod 7 passes through the upper surface of the wing spar 3, and an elastic fastener 8, specifically a rubber band, passes through the intersection of the tie rod 7 and the wing spar 3 located in the middle. The connecting end of the tie rod 7 maintains an angle of 15° to 30° with the wing spar 3 to which the aileron 2 is hinged. When the connection surface between the aileron 2 and the frame 1 is in a parallel position, the highest point of the rocker arm 6 is lower than the highest point of the wing rib 4.
[0024] like Figure 3 As shown, during use, a small wing is formed by covering the surface of the frame 1. The entire small wing is telescopically connected to the large wing 9. The small wing and the large wing are connected by a telescopic mechanism. When the servo mechanism 5 is activated, the rocker arm 6 swings up or down, and the lever 7 is pulled down or up, thereby controlling the rotation of the aileron 2. This ensures precise control of the aileron and is particularly suitable for telescopic wings that require close coordination.
[0025] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims.
Claims
1. An aileron control structure suitable for a telescopic wing, comprising a frame (1) and an aileron (2), the aileron (2) being hinged to the side of the frame (1), a wing crossbeam (3) being distributed along the length direction of the frame (1), and wing ribs (4) being distributed along the width direction, characterized in that: A servo mechanism (5) is provided on the side of one of the wing ribs (4). The output end of the servo mechanism (5) is connected to a rocker arm (6). The output end of the rocker arm (6) is connected to a pull rod (7). The other end of the pull rod (7) is bent downward and hinged to the side of the aileron (2).
2. The aileron control structure for a telescopic wing according to claim 1, characterized in that: The tie rod (7) passes through the upper surface of the wing crossbeam (3), and an elastic fastener (8) is provided at the intersection of the tie rod (7) and the wing crossbeam (3).
3. The aileron control structure for telescopic wings according to claim 2, characterized in that: The elastic fastener (8) is a rubber ring.
4. The aileron control structure for a telescopic wing according to claim 1, characterized in that: The connection end of the tie rod (7) to the aileron (2) is close to a wing crossbeam (3), and the connection end of the tie rod (7) maintains an angle of 15° to 30° with the wing crossbeam (3).
5. The aileron control structure for a telescopic wing according to claim 1, characterized in that: When the connecting surfaces of the aileron (2) and the frame (1) are in a parallel position, the highest point of the rocker arm (6) is lower than the highest point of the wing rib (4).
6. The aileron control structure for a telescopic wing according to claim 1, characterized in that: The wing spar (3) is arranged through the wing rib (4).