A UAV aileron and a towing mounting structure thereof

Abstract

This invention discloses an aileron and its towing mounting structure for a UAV, relating to the field of UAV technology. It includes an aileron body, an aileron pivot, a mounting connector, a retractable traction force transmission assembly, a quick-release mechanism, a release linkage assembly, and a status indicator pin. The aileron body is a box-type closed-cell load-bearing structure, with a main beam extending longitudinally and multiple ribs fixedly installed inside. The aileron pivot is located longitudinally at the leading edge of the aileron body and hinged to the trailing edge of the wing. The mounting connector is fixedly installed inside the aileron body, with its lower protruding end extending through the lower skin of the aileron and having a mounting ring groove. One end of the retractable traction force transmission assembly is hinged to the mounting connector, and the other end is hinged to a load-bearing joint inside the wing, used to transmit the towing load to the main load-bearing structure of the wing and adapt to the displacement changes caused by aileron deflection. This solves the problems of motion interference and poor force transmission adaptability in aileron mounting.

Description

Technical Field

[0001] This invention belongs to the field of unmanned aerial vehicle (UAV) technology, specifically relating to an UAV aileron and its towing and mounting structure. Background Technology

[0002] Currently, drones with mounting and delivery capabilities are widely used in reconnaissance, material delivery, and operational tasks. Existing small drone mounting structures are mostly concentrated on fixed sections of the fuselage or wings, rarely integrating mounting and delivery functions with aileron structures. This results in low space utilization and makes it difficult to meet the assembly and operational requirements of lightweight, compact drones. Traditional external mounting structures are mostly independent, fixed locking mechanisms with a rigid overall structure. When ailerons deflect for aerodynamic control, motion interference easily occurs, limiting aileron control travel, affecting flight attitude control accuracy, generating additional loads, and reducing flight stability and structural reliability.

[0003] Meanwhile, conventional payload release structures mostly employ independent electrically driven release schemes, requiring additional drive components, control circuits, and detection elements. This results in complex structures, a significant weight contribution, and increased overall power consumption and failure risks for the UAV. Furthermore, most lack intuitive payload status identification structures, making it impossible to quickly visually determine the payload locking and release status, leading to insufficient ease of maintenance and operational safety. In addition, existing payload force transmission structures have poor adaptability and cannot adaptively adjust to aileron deflection displacement. Traction loads are easily applied directly to the aileron control structure, causing localized stress concentration, component wear, and significantly reducing the service life of the aileron and payload structure. This makes it difficult to simultaneously meet the UAV's aerodynamic control performance, payload load-bearing capacity, and reliable release requirements. Summary of the Invention

[0004] The purpose of this invention is to provide an aileron for an unmanned aerial vehicle and its towing mounting structure to solve the problems mentioned in the background art.

[0005] To solve the above-mentioned technical problems, the present invention provides the following technical solution: an aileron of a UAV and its towing and mounting structure, including an aileron body, an aileron pivot, a mounting connection seat, a retractable traction force transmission component, a quick release mechanism, a release linkage component, and a status indicator pin. The aileron body is a box-type closed-cell load-bearing structure, with a main beam extending along the span and multiple ribs fixedly installed inside; the aileron pivot is located along the span at the leading edge of the aileron body and is hinged to the trailing edge of the wing. The mounting connector is fixedly installed inside the aileron body, with its lower protruding end extending through the lower aileron skin and having a mounting ring groove. One end of the retractable traction force transmission component is hinged to the mounting connection seat, and the other end is hinged to the load-bearing joint inside the wing. It is used to transmit the mounting traction load to the main load-bearing structure of the wing and adapt to the displacement changes caused by the aileron deflection. The quick-release mechanism is integrated inside the mounting connection seat and includes a first hook and a second hook arranged symmetrically. The two hooks remain closed to lock the mounting ring when there is no external force, and open to release the mounting ring when driven by an external force. The release linkage component is used to transmit the additional release angle of the aileron control system to the quick-release mechanism to trigger the release; The status indicator pin is slidably mounted on the upper surface of the aileron body, with its lower end extending into the mounting connection seat and its upper end having a marking part. The pin extends to different positions in the locked and released states by the pushing force of the mounting ring, indicating the mounting status in a purely mechanical way.

[0006] The present invention further illustrates that a rotating shaft drive arm is fixedly connected to the axial center of the aileron rotating shaft, and a drive pin is provided at the free end of the rotating shaft drive arm; the servo motor inside the wing drives the aileron through the servo motor output arm; an arc-shaped elongated hole is provided at the outer end of the servo motor output arm, and the drive pin is slidably engaged in the arc-shaped elongated hole. The two ends of the arc-shaped elongated hole are the normal operation limit end and the release travel limit end, respectively. During normal operation, the drive pin abuts against the normal operation limit end to drive the aileron to deflect synchronously. When the servo output arm rotates in the release direction beyond the normal operation angle, the aileron is stopped by the mechanical stop block, and the drive pin slides in the arc-shaped elongated hole to form an idle travel. This idle travel provides an additional rotation angle for driving the release linkage component.

[0007] The present invention further illustrates that the retractable traction force transmission assembly includes a front connecting seat, a rear connecting seat, an inner rod, a sleeve, and a preload spring; The front connecting seat is hinged to the mounting connecting seat, and the rear connecting seat is hinged to the load-bearing joint; the front end of the inner rod is fixedly connected to the front connecting seat, and the rear end is inserted into the sleeve and slides axially; the rear end of the sleeve is fixedly connected to the rear connecting seat. The preloaded spring is sleeved on the outside of the inner rod, with one end abutting the shoulder of the inner rod shaft and the other end abutting the front end of the sleeve. When there is no external traction force, it drives the assembly to retract to the shortest length and maintain tension. When the load is attached and towed for takeoff, it is further compressed to buffer the impact and transfer the load.

[0008] The present invention further illustrates that the first hook and the second hook are rotatably mounted in the release hook mounting cavity of the mounting connector via a hook shaft; the drive arm ends of the two hooks are provided with mutually meshing sector-shaped synchronous gears. The quick-release mechanism also includes a release spring and a release fork; the release spring is a double torsion spring that applies a torque to the two hooks to keep them closed; the release fork is slidably installed in the guide groove of the mounting connection seat, with its rear end finger abutting against the outside of the drive arm and its front end connected to the release linkage assembly; when the release fork is pulled backward, it pushes the two hooks to open to release the mounting ring.

[0009] The present invention further illustrates that the release linkage assembly includes a release lever, a servo linkage lever, and a return spring; The release lever is arranged along the aileron chord, with its rear end connected to the release fork of the quick-release mechanism, and its front end having a pullable part that extends into the wing interior; The servo linkage lever is fixedly connected to the outer end of the servo output arm; during normal operation, the servo linkage lever maintains a safe gap with the pulled part; during the release triggering phase, the servo linkage lever hooks the pulled part to drive the release lever to slide backward, thereby driving the pawl to open. The reset spring is used to pull the release lever forward and reset it.

[0010] The present invention further illustrates that the status indicator pin has a shoulder in the middle, and an indicator spring is provided between the shoulder and the mounting base, which always applies a downward elastic force to the status indicator pin; When the load sheath is locked, the sheath pushes the status indicator pin upwards so that it extends out of the upper surface of the aileron; when the load is released or the sheath is not present, the status indicator pin retracts under the action of the indicator spring.

[0011] The present invention further explains that the aileron body is provided with a reinforcing rib corresponding to the mounting connection seat inside. The thickness of the reinforcing rib is greater than that of ordinary ribs, which is used to distribute the concentrated load of the mounting.

[0012] The present invention further explains that the aileron shaft is a hollow shaft with a grease channel extending longitudinally inside. The grease channel has radial through holes corresponding to the positions of each hinge bearing. One end is provided with an oil injection nozzle and the other end is provided with an exhaust hole, which is used to achieve lubrication maintenance without disassembly.

[0013] The present invention further includes the following steps: Insert the mounting ring into the lower protruding end of the mounting connector. The quick release mechanism will automatically close and lock the ring. At the same time, the ring push status indicator pin will pop up to indicate the locked status. During takeoff, the traction load is transferred to the main load-bearing structure of the wing through the retractable traction force transmission component. The component adapts to extend and retract to absorb the aileron deflection displacement. During normal flight, the servo drives the aileron to deflect within the normal control angle range, releasing the linkage component to maintain a non-triggered state; When release is required, the servo motor rotates beyond the normal operating angle in the release direction, using the extra angle generated by the free stroke to drive the release linkage component, pulling the hook of the quick release mechanism to open, causing the hanging ring to fall off. After the load is released, the status indicator pin retracts to indicate that the release is complete. After the servo motor returns, the pawl automatically closes and resets, waiting for the next load.

[0014] Compared with existing technologies, this invention, through the design of an inner rod, sleeve, and preloaded spring structure in a retractable traction force transmission component, can adapt to the aileron deflection displacement by relying on the axial relative sliding of the inner rod and sleeve. Combined with the adaptive extension and retraction characteristics of the preloaded spring, it completely eliminates motion interference between the mounting structure and the aileron deflection control, ensuring precise and jam-free aileron aerodynamic control throughout the entire process. Simultaneously, a complete force transmission path is formed through the front connecting seat, rear connecting seat, and wing load-bearing joint, stably transferring the mounted traction load from the mounting connecting seat to the wing's main load-bearing structure. Combined with the thickened and reinforced ribs inside the aileron and the reinforcement structure of the main beam, it effectively disperses the concentrated load of the mounted load, avoids local stress concentration, significantly improves the overall structural load-bearing strength and fatigue service life, and balances the high-precision flight control performance and large-payload operation capabilities of the UAV.

[0015] This invention utilizes the idle stroke structure formed by the arc-shaped elongated hole of the servo motor output arm, combined with a mechanical linkage transmission link consisting of a servo motor linkage lever, a release lever, and a release fork. By using the servo motor's overtravel angle, the opening and closing of the first and second hooks can achieve loading and release, eliminating the need for additional electromagnetic, motor, or other electrical drive and detection components. This significantly simplifies the overall structure and reduces weight and power consumption. Furthermore, through a specially configured status indicator pin and indicator spring structure, the three working states—hook locking with loading, hook closed without loading, and loading and releasing—can be clearly distinguished mechanically, enabling rapid visual verification without external testing equipment. Attached Figure Description

[0016] The accompanying drawings are provided to further illustrate the invention and form part of the specification. They are used in conjunction with embodiments of the invention to explain the invention and do not constitute a limitation thereof. In the drawings: Figure 1 This is a schematic diagram of the overall structure of an embodiment of the present invention; Figure 2 This is a schematic diagram of the structure of the release linkage component according to an embodiment of the present invention; Figure 3 This is a schematic diagram of the aileron pivot structure according to an embodiment of the present invention; Figure 4 This is a side view of the overall structure of an embodiment of the present invention; Figure 5 This is a schematic diagram of the mounting connection seat structure according to an embodiment of the present invention; Figure 6 This is a schematic diagram of the quick-release mechanism structure in an embodiment of the present invention; Figure 7 This is a schematic diagram of the first hook structure according to an embodiment of the present invention; Figure 8 This is a schematic diagram of the release fork structure according to an embodiment of the present invention; Figure 9 This is a schematic diagram of the status indicator pin structure according to an embodiment of the present invention; Figure 10 This is a schematic diagram of the aileron body structure according to an embodiment of the present invention; Figure 11 This is a schematic diagram of the retractable traction force transmission component according to an embodiment of the present invention.

[0017] In the diagram: 1. Aileron body; 2. Aileron pivot; 3. Mounting connector; 4. Retractable traction transmission assembly; 5. Quick-release mechanism; 6. Release linkage assembly; 7. Status indicator pin; 11. Main beam; 12. Rib; 13. Pneumatic skin; 14. Reinforcing rib; 21. Grease channel; 22. Oil filler; 23. Exhaust port; 24. Pivot drive arm; 241. Drive pin; 31. Upper mounting flange; 32. Middle cavity; 321. Release hook mounting cavity; 322. Release fork guide groove; 33. Lower extension end; 331. Mounting ring groove; 34. Vibration damping pad; 41a. Front connector; 41b. Rear connector; 42. Inner rod; 43. Sleeve; 44. Preload spring ; 45. First joint bearing; 46. Second joint bearing; 47. Load-bearing joint; 48. Flexible dust cover; 51. First hook; 52. Second hook; 53. Release spring; 54. Release fork; 55. Hook shaft; 511. Drive arm; 512. Sector synchronous gear; 513. Hook; 514. Anti-slip texture; 541. Shift finger; 542. Connecting hole; 61. Release lever; 611. Pulled part; 62. Servo linkage lever; 63. Return spring; 64. Guide sleeve; 65. Servo output arm; 651. Arc-shaped elongated hole; 66. Servo; 67. Mechanical stop block; 71. Shoulder; 72. Mounting base; 73. Indicator spring; 75. Marking part; 76. Contact head. Detailed Implementation

[0018] The following detailed, non-limiting description of the technical solution of the present invention, in conjunction with preferred embodiments and accompanying drawings, is provided. Obviously, the described embodiments are merely some, not all, of the embodiments of the present invention. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without inventive effort are within the scope of protection of the present invention.

[0019] like Figures 1 to 11 As shown, this embodiment provides a drone aileron and its towing mounting structure, including an aileron body 1, an aileron pivot 2, a mounting connecting seat 3, a retractable traction force transmission component 4, a quick release mechanism 5, a release linkage component 6, and a status indicator pin 7.

[0020] For ease of description, the following orientation definitions are made in this embodiment: the direction of the leading edge of the wing is forward, and the direction of the trailing edge of the wing is backward; the side of the aileron span closer to the wing root is inward, and the side farther from the wing root is outward; and the upper and lower are defined based on the normal flight attitude of the UAV.

[0021] The aileron body 1 is a box-type closed-cell load-bearing structure. Its spanwise length is adapted to the aileron mounting slot on the trailing edge of the wing, and it can deflect around the aileron pivot 2 to achieve aerodynamic control. The aileron body 1 is internally fixed with a main beam 11 extending along the spanwise direction, and multiple ribs 12 arranged at intervals along the spanwise direction.

[0022] The main beam 11 is an I-beam made of carbon fiber composite material or aluminum alloy, located at a position 25%-30% of the leading edge along the chord of the aileron body 1, and behind the aileron pivot 2; the two ends of the main beam 11 are fixedly connected to the support seats of the aileron pivot 2 through end ribs, together forming the main load-bearing skeleton of the aileron.

[0023] The rib plate 12 is made of lightweight aluminum alloy or composite material, and the plate has weight-reducing holes to maintain the cross-sectional shape of the aileron and transfer local loads. The upper and lower surfaces of the aileron body 1 are aerodynamic skins 13, which are made of carbon fiber prepreg or aluminum alloy sheet, and are fixed to the main beam 11 and the rib plate 12 by adhesive bonding or riveting to form an integral box structure.

[0024] To bear the concentrated load, a reinforcing rib 14 is provided inside the aileron body 1 at the installation position corresponding to the mounting bracket 3. The thickness of the reinforcing rib 14 is greater than that of the ordinary rib 12. The plate is machined with mounting holes and bolt connection bosses that cooperate with the mounting bracket 3, which are used to distribute the concentrated load and avoid local stress concentration.

[0025] The aileron pivot 2 is located along the spanwise at the leading edge of the aileron body 1, and is hinged to the trailing edge of the wing via multiple hinge supports, forming the rotation center for aileron deflection. The aileron pivot 2 is a hollow shaft made of stainless steel or titanium alloy; its two ends are supported on the end ribs of the wing by bearings, allowing for free circumferential rotation.

[0026] The aileron shaft 2 has a grease channel 21 extending longitudinally inside. The grease channel 21 has radial through holes corresponding to the positions of each hinge bearing. Grease can be injected into the bearing raceway from inside the channel, achieving lubrication maintenance without disassembly. One end of the grease channel 21 is provided with an oil filling nozzle 22, and the other end is provided with an air vent 23 to expel air from the channel during oil filling.

[0027] A pivot drive arm 24 is fixedly connected to the axial center of the aileron pivot 2, and a drive pin 241 is provided at the free end of the pivot drive arm 24; a servo motor 66 is fixedly installed inside the wing, and a servo motor output arm 65 is fixedly connected to the output shaft of the servo motor 66.

[0028] The outer end of the servo output arm 65 is provided with an arc-shaped elongated hole 651, and the drive pin 241 is slidably fitted in the arc-shaped elongated hole 651. The circumferential arc length of the arc-shaped elongated hole 651 is greater than the diameter of the drive pin 241, and the drive pin 241 can slide circumferentially in the arc-shaped elongated hole 651. The rotation angle corresponding to the difference in arc length constitutes the idle travel of the servo output arm 65 relative to the aileron pivot 2.

[0029] The two ends of the arc-shaped elongated hole 651 are the normal control limit end and the release stroke limit end, respectively: the normal control limit end corresponds to the normal deflection working range of the aileron, and the arc segment between the release stroke limit end and the normal control limit end is the empty stroke area.

[0030] The wing structure is also fixedly equipped with a mechanical stop block 67 that cooperates with the aileron body 1 to limit the maximum deflection angle of the aileron; the limiting position of the mechanical stop block 67 is consistent with the aileron deflection angle when the drive pin 241 abuts against the arc-shaped elongated hole 651 during normal operation of the limiting end.

[0031] Based on the above structure, the aileron's actuation is divided into two stages, which is the prerequisite for realizing the control-release function: Normal operation phase: When the servo output arm 65 rotates within the normal operation angle range, the drive pin 241 abuts against the normal operation limit end of the arc-shaped long hole 651. The servo output torque is transmitted to the aileron pivot 2 through the drive pin 241 and the pivot drive arm 24, which drives the aileron body 1 to deflect synchronously, thus realizing conventional aerodynamic control. Release trigger phase: When the servo output arm 65 exceeds the normal operating angle and continues to rotate in the release direction, the aileron body 1 is stopped from deflecting by the mechanical stop block 67, and the drive pin 241 slides relative to the arc-shaped elongated hole 651 into the free travel area, so that the servo output arm 65 obtains an additional rotation angle independent of the aileron. This additional rotation angle is dedicated to driving the release linkage component 6 described below to provide power input for the load release.

[0032] The mounting bracket 3 is a precision casting of aluminum alloy or titanium alloy, fixedly installed at a predetermined spanwise position inside the aileron body 1. It serves as the input node for the mounted load and also integrates the installation space for the quick-release mechanism 5. The mounting bracket 3 includes an upper mounting flange 31, a middle cavity 32, and a lower protruding end 33. The upper mounting flange 31 is a rectangular flange, which is fixedly connected to the aileron main beam 11 and the reinforcing rib plate 14 by high-strength bolts; a vibration damping pad 34 is provided between the upper mounting flange 31 and the main beam 11 to buffer the impact vibration of the traction load; The central cavity 32 is a rectangular cavity, which is divided into a release hook mounting cavity 321 and a release fork guide groove 322. The bottom of the release hook mounting cavity 321 is an arc surface, which is adapted to the rotation trajectory of the hook claw. The release fork guide groove 322 is a straight groove extending along the chord of the aileron, which is used to provide straight guidance for the release action. The lower protruding end 33 extends downward through the lower skin of the aileron body 1, and its outer wall is machined with an annular mounting ring groove 331 for accommodating the traction rope or mounting ring; the lower end face of the lower protruding end 33 is chamfered to facilitate the quick mounting of the mounting ring; the interior of the lower protruding end 33 is interconnected with the middle cavity 32, allowing the hook of the quick release mechanism 5 to extend in and lock the ring.

[0033] The retractable traction force transmission assembly 4 is used to transfer the traction load borne by the mounting bracket 3 to the main load-bearing structure of the wing, while adapting to the displacement changes caused by the aileron deflection, thus avoiding motion interference with the aileron control. The retractable traction force transmission assembly 4 includes a front mounting bracket 41a, a rear mounting bracket 41b, an inner rod 42, a sleeve 43, and a preload spring 44.

[0034] The front connecting seat 41a is hinged to the upper mounting flange 31 of the mounting connecting seat 3 via the first joint bearing 45; the rear connecting seat 41b is hinged to the load-bearing joint 47 via the second joint bearing 46, and the load-bearing joint 47 is fixedly installed at the main load-bearing node of the main spar or wing rib inside the wing.

[0035] The inner rod 42 is a solid rod made of high-strength steel or titanium alloy. Its front end is fixedly connected to the front connecting seat 41a, and its rear end is inserted into the sleeve 43 and can slide freely along the axis. The sleeve 43 is a hollow tube with an inner diameter that matches the inner rod 42. Its rear end is fixedly connected to the rear connecting seat 41b.

[0036] The preload spring 44 is sleeved on the outside of the inner rod 42, with one end abutting against the shoulder of the front end of the inner rod 42 and the other end abutting against the front end face of the sleeve 43; after the assembly is completed, the preload spring 44 is in a pre-compressed state, providing axial preload force.

[0037] When there is no external traction, the elastic force of the preload spring 44 drives the inner rod 42 to extend forward and the sleeve 43 to retract backward, so that the component automatically retracts to the shortest length and remains taut, avoiding the component from shaking and making abnormal noise when the aileron deflects.

[0038] When the load is attached for takeoff, the external traction force acts on the load-bearing connecting seat 3 and is transmitted to the inner rod 42 through the front connecting seat 41a, causing the inner rod 42 to extend outward relative to the sleeve 43, and the preload spring 44 is further compressed; the traction force is transmitted through the continuous force transmission path formed by the inner rod 42, the preload spring 44, the sleeve 43, and the rear connecting seat 41b, and is finally transmitted to the load-bearing joint 47 of the wing, realizing the reliable transmission of load from the aileron to the wing.

[0039] When the aileron deflects, the mounting bracket 3 undergoes angular displacement around the aileron's axis of rotation. The inner rod 42 can slide adaptively within the sleeve 43, and the preload spring 44 extends and retracts synchronously, thereby absorbing the displacement difference and completely eliminating interference with the aileron's deflection motion.

[0040] To achieve a cross-cavity arrangement of components from the aileron interior to the wing interior, a clearance through-hole is provided on the root rib or corresponding rib plate 12 of the aileron body 1, through which the retractable traction force transmission component 4 passes. A flexible dust cover 48 is installed at the through-hole, with its two ends respectively clamped to the outer wall of the sleeve 43 and the edge of the through-hole. It can flexibly deform with the extension, contraction, and deflection of the component to prevent dust and debris from entering the aileron interior. A linear bearing or low-friction coating is provided between the inner rod 42 and the sleeve 43 to ensure smooth and unobstructed relative sliding between them.

[0041] The quick-release mechanism 5 is integrated into the central cavity 32 of the mounting connector 3, and is used to realize the automatic locking and active release of the mounting ring. The quick-release mechanism 5 includes a first hook 51, a second hook 52, a release spring 53, a release fork 54, and a hook shaft 55.

[0042] The first hook 51 and the second hook 52 are symmetrically arranged arc-shaped hooks, which are rotatably mounted in the release hook mounting cavity 321 via hook shaft 55. The upper ends of the two hooks extend in opposite directions to form drive arms 511. Each end of the two drive arms 511 is provided with a sector-shaped synchronous gear 512. The two sector-shaped synchronous gears 512 mesh with each other to ensure that the two hooks open and close synchronously, while improving the load-bearing capacity in the locked state.

[0043] The lower ends of the two hooks are hooks 513. The inner surface of the hooks 513 is machined with anti-slip textures 514 to increase the friction with the hanging ring and prevent accidental slippage.

[0044] The release spring 53 is a double torsion spring, which is sleeved on the hook pawl shaft 55. One end of it is fixed to the cavity wall of the mounting connection seat 3. The two torsion arms abut against the surfaces of the first hook pawl 51 and the second hook pawl 52 respectively, applying a torque to the two hook pawls to make the drive arm 511 rotate inward, so that the two hook pawls remain in a closed and locked state when no external force is applied.

[0045] When the two hooks close, the two hooks 513 form a closed locking ring, locking the hanging ring in the hanging ring groove 331 and preventing the hanging ring from coming out from the lower protruding end 33.

[0046] The release fork 54 is slidably mounted in the release fork guide groove 322 and can only slide forward and backward along the aileron chord. The rear end of the release fork 54 is provided with two fingers 541, which abut against the outer side of the drive arm 511 of the first pawl 51 and the second pawl 52, respectively; the front end of the release fork 54 is provided with a connecting hole 542 for connecting with the release linkage assembly 6.

[0047] When the release fork 54 is pulled backward, the finger 541 pushes the drive arm 511 of the two hooks to open outward, overcoming the elastic force of the release spring 53, so that the hook 513 at the lower end opens synchronously, and the hanging ring can be released from the lower extension end 33 without restraint, thus completing the release action.

[0048] Four-way release linkage components: the transmission link between the servo motor's free travel and the release mechanism. The release linkage component 6 is used to transmit the additional release angle of the servo output arm 65 to the release fork 54 of the quick-release mechanism 5, realizing the core linkage logic that triggers release when the servo overtravels. The release linkage component 6 includes a release lever 61, a servo linkage lever 62, and a return spring 63.

[0049] The release lever 61 is a stainless steel rod arranged along the chord of the aileron; its rear end is fixedly connected to the connection hole 542 at the front end of the release fork 54, and its front end extends towards the forward edge. A guide sleeve 64 is fitted in the middle of the release lever 61, and the guide sleeve 64 is fixed to the rib plate 12 of the aileron body 1, which restricts the release lever 61 to slide only forward and backward along the chord.

[0050] The release lever 61 has a pullable part 611 at its front end, which is a ball joint structure. A clearance window is provided on the leading edge of the aileron body 1 corresponding to the position of the ball joint. The ball joint extends through this clearance window into the internal cavity of the trailing edge of the wing, so that the entire pullable part 611 is located within the cavity on one side of the wing. A flexible dust cover is installed at the clearance window. The ball joint of the release lever 61 can swing slightly within the cover as the aileron deflects. The elastic deformation of the dust cover can completely accommodate this swing, and its stiffness in the direction of lever movement is much less than the combined force of the return spring 63 and the release spring 53, thus not hindering the reliable triggering of the release action.

[0051] The servo linkage lever 62 is an arc-shaped lever, fixedly connected to the outer end of the servo output arm 65, and rotates synchronously with the servo output arm 65; the inner arc surface of the arc-shaped lever is located behind the movement trajectory of the released lever being pulled 611. The arc contour of the servo linkage lever 62 precisely matches the aforementioned idle travel phase. Normal operation phase: The servo output arm 65 rotates within the normal operation angle range, and the drive pin 241 abuts against the normal operation limit end of the arc-shaped long hole 651. The aileron deflects synchronously with the servo. At this time, a safe gap is always maintained between the servo linkage lever 62 and the ball head of the pulled part 611, and the release action will not be triggered, ensuring that the normal operation of the aileron is not affected. Release trigger phase: The servo output arm 65 exceeds the normal control angle and enters the free travel zone. The aileron is stopped from deflecting by the mechanical stop block 67. The servo output arm 65 drives the servo linkage lever 62 to continue rotating in the release direction. The arc surface of the servo linkage lever 62 gradually approaches and contacts the ball head of the pulled part 611. Through the gradual change of the arc surface contour, the ball head is hooked towards the trailing edge of the wing, thereby driving the release lever 61 to slide backward as a whole. The rear end of the release lever 61 pulls the release fork 54 to move backward, finally driving the pawl to open and completing the load release.

[0052] The reset spring 63 is a tension spring, with its rear end hooked to the hanging hole in the middle of the release rod 61 and its front end hooked to the guide sleeve 64 or the fixing post on the adjacent rib plate; the preload of the reset spring 63 will pull the release rod 61 forward to keep it in its initial position.

[0053] When the servo output arm 65 returns to the normal operating angle range, the servo linkage lever 62 disengages from the pulled part 611, the tension of the return spring 63 drives the release lever 61 to return forward, and the release fork 54 retracts forward simultaneously; the pawl automatically closes under the action of the release spring 53, restoring the locked state.

[0054] The status indicator pin 7 is used to visually indicate the locking and releasing status of the mount in a purely mechanical manner, without the need for electrical detection components. The status indicator pin 7 is slidably mounted in the mounting base 72 on the upper surface of the aileron body 1, and is located directly above the mount connection base 3.

[0055] The status indicator pin 7 is a slender rod with a red or fluorescent marking part 75 at its upper end for easy visual observation from the ground and air. A shoulder 71 is located in the middle of the status indicator pin 7, and an indicator spring 73 is positioned between the shoulder 71 and the mounting base 72. The indicator spring 73 is a compression spring that constantly applies a downward elastic force to the status indicator pin 7, keeping it in a retracted downward posture in its free state.

[0056] The lower end of the status indicator pin 7 extends into the middle cavity 32 of the mounting connector 3 and is located directly above the locking space formed by the closing of the first hook 51 and the second hook 52; the lower end surface of the status indicator pin 7 is a flat contact head 76.

[0057] When the mounting ring is locked in the mounting ring groove 331 by the hook, the upper end face of the ring abuts against the contact head 76, pushing the status indicator pin 7 upward, overcoming the elastic force of the indicator spring 73, causing the status indicator pin 7 to pop up upward, and the marking part 75 extends out of the upper surface of the aileron, visually indicating that the mounting is in place and locked.

[0058] When the release mechanism is activated, the hook opens, and the hanging ring falls off, the upward pushing force of the hanging ring on the contact head 76 disappears. Under the elastic force of the indicator spring 73, the status indicator pin 7 retracts downward into the mounting base 72, and the upper marking part 75 is hidden under the skin, visually indicating that the load has been released and there is no load.

[0059] If the hook automatically closes when no lifting ring is attached, the status indicator pin 7 remains retracted because there is no lifting ring pushing upwards. This directly distinguishes between the two states of hook closure with or without a lifting ring, eliminating ambiguity in the indication.

[0060] Working principle: The operator inserts the mounting ring from bottom to top into the lower extension end 33. The upper end of the ring pushes open the closed pawl and enters the mounting ring groove 331. Subsequently, the pawl automatically closes under the action of the release spring 53, locking the ring. At the same time, the upper end of the ring pushes the status indicator pin 7 upward, causing it to pop up, and the marking part 75 extends out of the upper surface of the aileron, visually indicating that the mounting is locked in place.

[0061] During the takeoff of the UAV, the traction load acts on the mounting connection seat 3 through the mounting ring, and then is transmitted to the load-bearing joint 47 of the wing through the retractable traction force transmission assembly 4, and finally merges into the main load-bearing structure of the wing. During the force transmission process, the inner rod 42 of the retractable traction force transmission assembly 4 extends outward relative to the sleeve 43, and the preload spring 44 compresses adaptively to buffer the traction impact. When the aileron deflects, the inner rod 42 and the sleeve 43 can slide freely relative to each other without interfering with the aerodynamic control of the aileron.

[0062] Servo 66 drives the aileron to deflect within the normal control angle range to achieve flight attitude control. At this time, the drive pin 241 always abuts against the normal control limit end of the arc-shaped elongated hole 651, the servo linkage lever 62 and the ball joint of the release lever 61 maintain a safe clearance, and the quick release mechanism 5 remains locked; the maximum deflection angle of the aileron is limited by the mechanical stop block 67 to ensure control safety.

[0063] After the flight control system issues a release command, the servo output arm 65 rotates beyond the normal control angle in the release direction, entering the free travel zone. At this time, the aileron body 1 is stopped from deflecting by the mechanical stop block 67, and the drive pin 241 slides relative to each other in the arc-shaped elongated hole 651, giving the servo output arm 65 an additional release angle. The servo linkage lever 62, fixed on the servo output arm 65, pulls the ball head of the release lever 61 backward with the additional angle. After being transmitted through the release lever 61 and the release fork 54, it drives the two claws to open, and the mounting ring automatically falls off after losing its restraint. At the same time, after the mounting ring falls off, the upward pushing force at the lower end of the status indicator pin 7 disappears, and it retracts downward under the action of the indicator spring 73. The marking part 75 is hidden under the aileron skin, visually indicating that the release is complete.

[0064] After release, the servo output arm 65 returns to the normal operating angle range, and the servo linkage lever 62 disengages from the ball joint; the reset spring 63 drives the release lever 61 and the release fork 54 to return forward, and the pawl automatically closes under the action of the release spring 53. Since the unloaded lifting ring pushes upward, the status indicator pin 7 remains in the retracted state, waiting for the next loading; when the load is locked again, the lifting ring pushes the status indicator pin 7 upward again, completing the fully automatic mechanical indication cycle.

[0065] In the description of this invention, it should be understood that the terms "upper", "lower", "front", "rear", "left", "right", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing this invention, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this invention.

[0066] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features, and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A UAV aileron and its towing and mounting structure, characterized in that: It includes the aileron body (1), aileron pivot (2), mounting bracket (3), retractable traction transmission assembly (4), quick release mechanism (5), release linkage assembly (6), and status indicator pin (7). The aileron body (1) is a box-type closed-cell load-bearing structure, with a main beam (11) extending along the span and multiple ribs (12) fixedly installed inside; the aileron pivot (2) is located along the span at the leading edge of the aileron body (1) and is hinged to the trailing edge of the wing; The mounting connector (3) is fixedly installed inside the aileron body (1), and its lower protruding end (33) extends out of the aileron lower skin and is provided with a mounting ring groove (331). One end of the retractable traction force transmission component (4) is hinged to the mounting connection seat (3), and the other end is hinged to the load-bearing joint (47) inside the wing. It is used to transmit the mounting traction load to the main load-bearing structure of the wing and adapt to the displacement changes caused by the aileron deflection. The quick release mechanism (5) is integrated inside the mounting connection seat (3), including a first hook (51) and a second hook (52) arranged symmetrically. The two hooks remain closed to lock the mounting ring when there is no external force, and open to release the mounting ring when driven by an external force. The release linkage component (6) is used to transmit the additional release angle of the aileron control system to the quick release mechanism (5) to trigger the release; The status indicator pin (7) is slidably installed on the upper surface of the aileron body (1), with its lower end extending into the mounting connection seat (3) and its upper end having a marking part (75). The mounting status is indicated mechanically by the pushing force of the mounting ring in the locked and released states.

2. The UAV aileron and its towing mounting structure according to claim 1, characterized in that: The aileron pivot (2) is fixedly connected to the axial center of the pivot drive arm (24), and the free end of the pivot drive arm (24) is provided with a drive pin (241); the servo motor (66) inside the wing drives the aileron through the servo motor output arm (65); the outer end of the servo motor output arm (65) is provided with an arc-shaped long hole (651), and the drive pin (241) is slidably fitted in the arc-shaped long hole (651); The two ends of the arc-shaped elongated hole (651) are the normal operation limit end and the release stroke limit end, respectively; during normal operation, the drive pin (241) abuts against the normal operation limit end to drive the aileron to deflect synchronously. When the servo output arm (65) rotates in the release direction beyond the normal operating angle, the aileron is stopped by the mechanical stop block (67), and the drive pin (241) slides in the arc-shaped long hole (651) to form a free stroke, which provides an additional rotation angle for driving the release linkage assembly (6).

3. The UAV aileron and its towing mounting structure according to claim 1, characterized in that: The retractable traction transmission assembly (4) includes a front connecting seat (41a), a rear connecting seat (41b), an inner rod (42), a sleeve (43), and a preload spring (44). The front connecting seat (41a) is hinged to the mounting connecting seat (3), and the rear connecting seat (41b) is hinged to the load-bearing joint (47); the front end of the inner rod (42) is fixedly connected to the front connecting seat (41a), and the rear end is inserted into the sleeve (43) and slides axially; the rear end of the sleeve (43) is fixedly connected to the rear connecting seat (41b). The preload spring (44) is sleeved on the outside of the inner rod (42), with one end abutting the shoulder of the inner rod (42) and the other end abutting the front end of the sleeve (43). When there is no external traction force, it drives the assembly to retract to the shortest length and maintain tension. When the load is towed and taken off, it is further compressed to buffer the impact and transfer the load.

4. The UAV aileron and its towing mounting structure according to claim 1, characterized in that: The first hook (51) and the second hook (52) are rotatably mounted in the release hook mounting cavity (321) of the mounting connector (3) via the hook shaft (55); the upper ends of the drive arms (511) of the two hooks are provided with mutually meshing sector synchronous gears (512). The quick-release mechanism (5) also includes a release spring (53) and a release fork (54); the release spring (53) is a double torsion spring that applies a torque to the two hooks to keep them closed; the release fork (54) is slidably installed in the guide groove of the mounting connection seat (3), with its rear end finger (541) abutting against the outside of the drive arm (511) and its front end connected to the release linkage assembly (6); when the release fork (54) is pulled backward, it pushes the two hooks to open to release the mounting ring.

5. The UAV aileron and its towing mounting structure according to claim 2, characterized in that: The release linkage assembly (6) includes a release lever (61), a servo linkage paddle (62), and a reset spring (63). The release lever (61) is arranged along the aileron chord, and its rear end is connected to the release fork (54) of the quick release mechanism (5). Its front end is provided with a pull part (611) that extends into the wing. The servo linkage lever (62) is fixedly connected to the outer end of the servo output arm (65); during normal operation, the servo linkage lever (62) and the pulled part (611) maintain a safe gap; during the release triggering stage, the servo linkage lever (62) hooks the pulled part (611) to drive the release lever (61) to slide backward, thereby driving the pawl to open. The reset spring (63) is used to pull the release lever (61) forward to reset it.

6. The UAV aileron and its towing mounting structure according to claim 1, characterized in that: The status indicator pin (7) has a shoulder (71) in the middle, and an indicator spring (73) is provided between the shoulder (71) and the mounting base (72) to always apply a downward elastic force to the status indicator pin (7); When the load-bearing ring is locked, the ring pushes the status indicator pin (7) upward to extend it out of the upper surface of the aileron; when the load is released or the load-bearing ring is not present, the status indicator pin (7) retracts under the action of the indicator spring (73).

7. The UAV aileron and its towing mounting structure according to claim 1, characterized in that: The aileron body (1) has a reinforcing rib (14) inside the corresponding mounting connection seat (3). The thickness of the reinforcing rib (14) is greater than that of the ordinary rib (12), which is used to distribute the concentrated load.

8. The UAV aileron and its towing mounting structure according to claim 1, characterized in that: The aileron shaft (2) is a hollow shaft with a grease channel (21) extending along the span direction inside. The grease channel (21) has radial through holes corresponding to the positions of each hinge bearing. One end is provided with an oil injection nozzle (22), and the other end is provided with an exhaust hole (23) to achieve lubrication maintenance without disassembly.

9. A method for releasing a UAV aileron towing mounting structure based on any one of claims 1 to 8, characterized in that, Includes the following steps: When the mounting ring is inserted into the lower protruding end (33) of the mounting connector (3), the quick release mechanism (5) automatically closes and locks the ring, and at the same time the ring push status indicator pin (7) pops up to indicate the locked status. During takeoff, the traction load is transmitted to the main load-bearing structure of the wing via the retractable traction force transmission component (4). The component adapts to extend and retract to absorb the aileron deflection displacement. During normal flight, the servo (66) drives the aileron to deflect within the normal control angle range and releases the linkage component (6) to maintain a non-triggered state; When release is required, the servo motor (66) rotates beyond the normal operating angle in the release direction, using the extra angle generated by the free stroke to drive the release linkage component (6), pulling the hook of the quick release mechanism (5) to open, causing the hanging ring to fall off; After the load is removed, the status indicator pin (7) retracts to indicate that the release is complete. After the servo motor (66) returns, the pawl automatically closes and resets, waiting for the next load.

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