Automatic folding device for the rear wing of a drone
Patent Information
- Application Number
- CN202522671915.1
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-12-17
- Publication Date
- 2026-10-23
- Estimated Expiration
- 2035-12-17
AI Technical Summary
由于翼面结构相对脆弱，且撞击力集中，极易导致后翼折断或蒙皮损伤，严重影响无人机的使用寿命和可靠性
1.本实用新型的无人机的后翼自动收拢装置包括安装基座和触发机构，安装基座的上表面安装有翼根转轴，翼根转轴的上表面依次转动安装有第一后翼和第二后翼；翼根转轴外侧安装有驱动装置，驱动装置与第一后翼和第二后翼均传动连接；触发机构设置在基座的外表面；触发机构包括传感器和限位装置，限位装置与第一后翼和第二后翼均卡接。在撞网瞬间传感器（碰撞传感器）立即驱动限位装置抽离第一后翼和第二后翼，回收扭簧对第一后翼和第二后翼的驱动，进而实现了第一后翼和第二后翼收拢，实现了对后翼的主动保护，而非被动承受撞击。
Smart Images
Figure CN224882291U_ABST
Abstract
Description
Technical Field
[0001] This application belongs to the field of unmanned aerial vehicle (UAV) technology, and specifically relates to an automatic folding device for the rear wing of an UAV. Background Technology
[0002] Folding-wing drones are widely used due to their portability and are typically recovered by colliding with a net. However, at the moment of impact, the drone continues to move forward due to inertia, and its rear wings (especially those that extend backward) violently collide with the recovery net. Because the wing structure is relatively fragile and the impact force is concentrated, the rear wings are very likely to break or the skin is damaged, seriously affecting the drone's service life and reliability.
[0003] Therefore, there is an urgent need for a folding mechanism that can be triggered instantly, operate reliably, and automatically protect the rear wing at the moment of impact with the net. Utility Model Content
[0004] To address the aforementioned issues, this application proposes an automatic rear wing folding device for an unmanned aerial vehicle (UAV), comprising a mounting base and a triggering mechanism. A wing root pivot is mounted on the upper surface of the mounting base, and a first rear wing and a second rear wing are rotatably mounted on the upper surface of the wing root pivot in sequence. A drive device is mounted on the outer side of the wing root pivot, and the drive device is connected to both the first and second rear wings in a transmission manner. The triggering mechanism is located on the outer surface of the base; the triggering mechanism includes a sensor and a limiting device, which are electrically connected, and the limiting device is engaged with both the first rear wing and the second rear wing.
[0005] Furthermore, the automatic retraction device for the rear wing includes a spring-loaded torsion spring, which is installed on the outside of the wing root pivot and located between the first and second rear wings. The spring-loaded torsion spring is connected to both the second and first rear wings in a transmission manner.
[0006] Furthermore, the automatic folding device for the rear wing of the UAV also includes a first recovery pusher and a second recovery pusher; both the first recovery pusher and the second recovery pusher are rotatably mounted on the outer surface of the wing root shaft, and the first recovery pusher and the second recovery pusher are respectively mounted on opposite sides of the first rear wing and the second rear wing; the first recovery pusher is engaged with the first rear wing, and the second recovery pusher is engaged with the second rear wing.
[0007] Furthermore, the edge of the first recovery pusher is provided with a first retaining plate, which abuts against the side of the first rear wing; the edge of the second recovery pusher is provided with a second retaining plate, which abuts against the side of the second rear wing. Furthermore, the drive device includes a recovery torsion spring, which is fitted onto the outside of the wing root pivot; the recovery torsion spring is drively connected to both the first and second recovery pushers.
[0008] Furthermore, the drive device includes two recovery torsion springs, which are respectively mounted on opposite sides of the first recovery push plate and the second recovery push plate; the two recovery torsion springs are driven connected to the first recovery push plate and the second recovery push plate respectively.
[0009] Furthermore, the torque of the recovery torsion spring is greater than that of the mainspring torsion spring.
[0010] Furthermore, the torque of the recovery torsion spring is 1.5-2.5 times that of the mainspring torsion spring.
[0011] Furthermore, the limiting device includes an electromagnetic locking pin and a locking pin, wherein the electromagnetic locking pin is engaged with a locking pin, and the end of the locking pin away from the electromagnetic locking pin is engaged between the first rear wing and the second rear wing.
[0012] Furthermore, the electromagnetic locking pin is installed on the outside of the mounting base.
[0013] The beneficial effects of this utility model are: 1. The automatic rear wing retraction device for a UAV of this utility model includes a mounting base and a triggering mechanism. A wing root pivot is mounted on the upper surface of the mounting base, and a first rear wing and a second rear wing are rotatably mounted on the upper surface of the wing root pivot. A drive device is mounted on the outer side of the wing root pivot, and the drive device is connected to both the first and second rear wings. The triggering mechanism is located on the outer surface of the base. The triggering mechanism includes a sensor and a limiting device, and the limiting device is engaged with both the first and second rear wings. At the moment of impact with the net, the sensor (collision sensor) immediately drives the limiting device to pull away the first and second rear wings, recovering the torsion spring's drive on the first and second rear wings, thereby realizing the retraction of the first and second rear wings and achieving active protection of the rear wings, rather than passively bearing the impact.
[0014] 2. In the automatic wing retraction device of the UAV of this utility model, the torque of the recovery torsion spring is greater than the torque of the spring-loaded torsion spring. When the triggering mechanism is activated, the locking pin no longer engages the first and second recovery push plates, thus the torque of the recovery torsion spring is greater than the torque of the spring-loaded torsion spring, thereby driving the first and second rear wings to retract. By setting the recovery torque of the recovery torsion spring to be greater than the deployment torque of the spring-loaded torsion spring, it is ensured that after activation, the recovery torsion spring can reliably overcome the force of the spring-loaded torsion spring and quickly complete the retraction action, avoiding mechanism jamming or incomplete action.
[0015] 3. The automatic wing folding device of the UAV of this utility model mainly adopts common mechanical components such as torsion springs, push plates, and locking pins. It has a simple and reliable structure, is easy to process, manufacture and maintain, and meets the design goal of low-cost UAVs.
[0016] Other features and advantages of this application will be set forth in the following description and will be apparent in part from the description or may be learned by practicing the application. The objectives and other advantages of this application may be realized and obtained by means of the structures pointed out in the description and the accompanying drawings. Attached Figure Description
[0017] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.
[0018] Figure 1 An exploded schematic diagram of the automatic rear wing folding device of the UAV in an embodiment of this application is shown.
[0019] Figure 2 The diagram shows the first and second rear wings of the automatic rear wing retraction device of the UAV in an embodiment of this application, in the position of the locking pin engagement.
[0020] Figure 3 An exploded side view of the automatic rear wing folding device of the UAV in an embodiment of this application is shown.
[0021] In the diagram, 1 is the mounting base; 2 is the first rear wing; 3 is the second rear wing; 4 is the wing root pivot; 5 is the spring-loaded torsion spring; 6 is the recovery torsion spring; 71 is the first recovery pusher; 72 is the second recovery pusher; and 8 is the locking pin. Detailed Implementation
[0022] To make the objectives, technical solutions, and advantages of the embodiments of this application clearer, the technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, not all embodiments. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.
[0023] Example 1 refer to Figure 3 An automatic rear wing folding device for recovering a folding-wing UAV after it crashes into a net includes: a mounting base 1, a first rear wing 2, a second rear wing 3, a triggering mechanism, a recovery mechanism, and a deployment mechanism. The first rear wing 2 and the second rear wing 3 are rotatably connected to the upper surface of the mounting base 1 via a wing root pivot 4.
[0024] The deployment mechanism includes a spring-loaded torsion spring 5 disposed between the first rear wing 2 and the second rear wing 3, the spring-loaded torsion spring 5 providing a torque that causes the first rear wing 2 and the second rear wing 3 to rotate in the deployment direction.
[0025] The recovery mechanism includes a recovery torsion spring 6 and a recovery pusher driven by the recovery torsion spring 6, the torque provided by the recovery torsion spring 6 being greater than the torque of the spring-loaded torsion spring 5; the initial position of the recovery pusher is locked by a releasable latch 8.
[0026] Trigger mechanism, used to trigger and release pin 8 when the drone comes into contact with the recovery net.
[0027] The triggering mechanism is an electronically controlled triggering mechanism, including a collision sensor and an electromagnetic locking pin; after the collision sensor detects a collision signal, it controls the electromagnetic locking pin to release the locking pin 8. There are two recovery pushers, respectively located on the lower surface of the first rear wing 2 and the upper surface of the second rear wing 3. The torque of the recovery torsion spring 6 is greater than 1.5 times the torque of the spring-loaded torsion spring 5.
[0028] Furthermore, during normal drone flight, the latch 8 engages the two recovery pushers under the action of the recovery torsion spring 6. Once the two recovery pushers are released, the powerful torque of the recovery torsion spring 6 immediately drives the two recovery pushers to swing rapidly. The recovery pushers contact the side surfaces of the first rear wing 2 and the second rear wing 3, thereby forcibly pushing the first rear wing 2 and the second rear wing 3 to rotate inward around the wing root pivot 4, quickly folding the first rear wing 2 and the second rear wing 3 to the folded position, so that the wing surfaces of the first rear wing 2 and the second rear wing 3 avoid direct impact with the recovery net.
[0029] Example 2 An automatic rear wing folding device for recovering a folding-wing UAV after it crashes into a net includes a mounting base 1, a first rear wing 2, a second rear wing 3, a deployment mechanism, a recovery mechanism, and a triggering mechanism. The first rear wing 2 and the second rear wing 3 are rotatably connected to the mounting base 1 via a wing root pivot 4, and can rotate between the deployed position and the folded position.
[0030] The deployment mechanism includes a spring-loaded torsion spring 5 disposed between the first rear wing 2 and the second rear wing 3. The spring-loaded torsion spring 5 is pre-loaded with a torque that causes the first rear wing 2 and the second rear wing 3 to rotate in the deployment direction.
[0031] The recovery mechanism includes at least one pair of recovery torsion springs 6 and recovery pushers connected to the recovery torsion springs 6; the pre-applied torque of the recovery torsion springs 6 is greater than the torque of the spring-loaded torsion springs 5; the initial position of the recovery pushers is locked by a locking pin 8; when the locking pin 8 is released, the recovery torsion springs 6 drive the recovery pushers to move, thereby pushing the first rear wing 2 and the second rear wing 3 to rotate in the retraction direction. A triggering mechanism is used to generate a signal from a collision sensor and release the locking pin 8 the instant the UAV contacts the recovery net.
[0032] Preferably, the triggering mechanism is an electronically controlled triggering mechanism, including a collision sensor and an electromagnetic locking pin; after the collision sensor detects a collision signal, the control pin 8 is de-energized and released, thereby releasing the lock on the recovery pusher.
[0033] Preferably, the recovery pusher consists of two pieces, located on the lower surface of the first rear wing 2 and the upper surface of the second rear wing 3, respectively.
[0034] Preferably, the torque of the recovery torsion spring 6 is significantly greater than that of the spring torsion spring 5, to ensure that the deployment torque can be overcome and the rear wings (first rear wing 2 and second rear wing 3) can be quickly retracted.
[0035] Example 3 refer to Figure 1 An automatic wing folding device for a drone includes a mounting base 1 and a triggering mechanism. A wing root shaft 4 is mounted on the upper surface of the mounting base 1, and a first rear wing 2 and a second rear wing 3 are rotatably mounted on the upper surface of the wing root shaft 4. A drive device is mounted on the outer side of the wing root shaft 4, and the drive device is connected to both the first rear wing 2 and the second rear wing 3 in a transmission connection. Further, the drive device drives the first rear wing 2 and the second rear wing 3 to move in the folding direction, and the two drive devices drive the first folding pusher 71 and the second folding pusher 72 respectively, thereby driving the first rear wing 2 and the second rear wing 3 to move in the folding direction.
[0036] The triggering mechanism is located on the outer surface of the base 1. The triggering mechanism includes a sensor and a limiting device, which are electrically connected. The limiting device is engaged with both the first rear wing 2 and the second rear wing 3. At the moment of impact with the net, the sensor (collision sensor) immediately drives the limiting device to pull away from the first rear wing 2 and the second rear wing 3, recovering the drive of the torsion spring 6 on the first rear wing 2 and the second rear wing 3, thereby realizing the retraction of the first rear wing 2 and the second rear wing 3, achieving active protection of the rear wings rather than passively bearing the impact.
[0037] Furthermore, the automatic wing retraction device includes a spring-loaded torsion spring 5, which is mounted on the outside of the wing root pivot 4 and located between the first rear wing 2 and the second rear wing 3. The spring-loaded torsion spring 5 is connected to both the second rear wing 3 and the first rear wing 2. The torque generated by the spring-loaded torsion spring 5 causes the first rear wing 2 and the second rear wing 3 to unfold, thereby enabling the UAV to unfold during flight, facilitating UAV flight.
[0038] In the above embodiment, another optional implementation is that the two ends of the spring-loaded torsion spring 5 are respectively engaged with the first rear wing 2 and the second rear wing 3. The torque generated by the spring-loaded torsion spring 5 causes the first rear wing 2 and the second rear wing 3 to open.
[0039] Furthermore, the automatic folding device for the rear wing of the UAV also includes a first recovery pusher 71 and a second recovery pusher 72; both the first recovery pusher 71 and the second recovery pusher 72 are rotatably mounted on the outer surface of the wing root shaft 4, and the first recovery pusher 71 and the second recovery pusher 72 are respectively mounted on the opposite sides of the first rear wing 2 and the second rear wing 3; the first recovery pusher 71 is engaged with the first rear wing 2, and the second recovery pusher 72 is engaged with the second rear wing 3.
[0040] Furthermore, the edge of the first recovery pusher 71 is provided with a first retaining plate, which abuts against the side of the first rear wing 2; the edge of the second recovery pusher 72 is provided with a second retaining plate, which abuts against the side of the second rear wing 3.
[0041] In this embodiment of the invention, the driving device includes a recovery torsion spring 6, which is fitted onto the outer side of the wing root shaft 4. The recovery torsion spring 6 is connected to both the first recovery push plate 71 and the second recovery push plate 72. The two recovery torsion springs 6 drive the first recovery push plate 71 and the second recovery push plate 72 to rotate in a retraction direction, thereby causing the first rear wing 2 and the second rear wing 3 to rotate in the retraction direction, achieving the retraction of the first rear wing 2 and the second rear wing 3, preventing damage to the first rear wing 2 and the second rear wing 3, and facilitating the recovery of the UAV.
[0042] Furthermore, the drive device includes two recovery torsion springs 6, which are respectively mounted on opposite sides of the first recovery push plate 71 and the second recovery push plate 72; the two recovery torsion springs 6 are drivenly connected to the first recovery push plate 71 and the second recovery push plate 72. The two recovery torsion springs 6 drive the first recovery push plate 71 and the second recovery push plate 72 to rotate in the retraction direction, thereby causing the first rear wing 2 and the second rear wing 3 to rotate in the retraction direction, achieving the retraction of the first rear wing 2 and the second rear wing 3, preventing damage to the first rear wing 2 and the second rear wing 3, and thus facilitating the recovery of the UAV.
[0043] In this invention, the torque of the recovery torsion spring 6 is greater than the torque of the mainspring torsion spring 5. When the triggering mechanism is activated, the locking pin 8 no longer engages the first recovery push plate 71 and the second recovery push plate 72, thus the torque of the recovery torsion spring 6 is greater than the torque of the mainspring torsion spring 5, thereby driving the first rear wing 2 and the second rear wing 3 to retract. By setting the recovery torque of the recovery torsion spring 6 to be greater than the deployment torque of the mainspring torsion spring 5, it is ensured that after activation, the recovery torsion spring 6 can reliably overcome the force of the mainspring torsion spring 5 and quickly complete the retraction action, avoiding mechanism jamming or incomplete action.
[0044] Preferably, the torque of the recovery torsion spring 6 is 1.5-2.5 times the torque of the spring-loaded torsion spring 5. By setting the torque of the recovery torsion spring 6 to 1.5-2.5 times the torque of the spring-loaded torsion spring 5, the recovery torsion spring 6 can drive the first rear wing 2 and the second rear wing 3 to retract and prevent damage to the first rear wing 2 and the second rear wing 3.
[0045] refer to Figure 2 The limiting device includes a collision sensor, an electromagnetic locking pin, and a locking pin 8. The electromagnetic locking pin is engaged with the locking pin 8, and the end of the locking pin 8 away from the electromagnetic locking pin is engaged between the first rear wing 2 and the second rear wing 3. Through an electrically controlled triggering mechanism, the locking pin 8 is immediately driven to disengage upon impact with the net, thereby enabling the recovery torsion spring 6 to drive the first rear wing 2 and the second rear wing 3, and thus achieving the retraction of the first rear wing 2 and the second rear wing 3, achieving active protection of the rear wings rather than passively withstanding the impact.
[0046] Furthermore, the electromagnetic locking pin is installed on the outside of the mounting base 1.
[0047] Preferably, the edge of the first recovery pusher 71 is provided with a first retaining plate, which abuts against the side of the first rear wing 2; the edge of the second recovery pusher 72 is provided with a second retaining plate, which abuts against the side of the second rear wing 3.
[0048] This utility model mainly uses common mechanical components such as torsion springs, push plates, and locking pins. It has a simple and reliable structure, is easy to process, manufacture, and maintain, and meets the design goal of low-cost drones.
[0049] Although this application 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 this application.
Claims
1. An automatic wing-folding device for a drone, characterized in that, It includes a mounting base (1) and a triggering mechanism. The upper surface of the mounting base (1) is equipped with a wing root shaft (4). The upper surface of the wing root shaft (4) is rotatably equipped with a first rear wing (2) and a second rear wing (3). A driving device is installed on the outer side of the wing root shaft (4). The driving device is connected to both the first rear wing (2) and the second rear wing (3) in a transmission manner. The triggering mechanism is located on the outer surface of the base (1); the triggering mechanism includes a sensor and a limiting device, which are electrically connected, and the limiting device is engaged with both the first rear wing (2) and the second rear wing (3).
2. The automatic wing folding device for a UAV according to claim 1, characterized in that, The automatic retraction device for the rear wing also includes a spring-loaded torsion spring (5), which is installed on the outside of the wing root pivot (4) and located between the first rear wing (2) and the second rear wing (3). The spring-loaded torsion spring (5) is connected to both the second rear wing (3) and the first rear wing (2) in a transmission manner.
3. The automatic wing folding device for a UAV according to claim 2, characterized in that, The automatic folding device for the rear wing of the UAV also includes a first recovery pusher (71) and a second recovery pusher (72); the first recovery pusher (71) and the second recovery pusher (72) are both rotatably mounted on the outer surface of the wing root pivot (4), and the first recovery pusher (71) and the second recovery pusher (72) are respectively mounted on opposite sides of the first rear wing (2) and the second rear wing (3); the first recovery pusher (71) is engaged with the first rear wing (2), and the second recovery pusher (72) is engaged with the second rear wing (3).
4. The automatic wing folding device for a drone according to claim 3, characterized in that, The first recovery pusher (71) has a first retaining plate on its edge, which abuts against the side of the first rear wing (2); the second recovery pusher (72) has a second retaining plate on its edge, which abuts against the side of the second rear wing (3).
5. An automatic wing-folding device for a UAV according to claim 3 or 4, characterized in that, The drive device includes a recovery torsion spring (6), which is fitted on the outside of the wing root shaft (4); the recovery torsion spring (6) is connected to the first recovery push plate (71) and the second recovery push plate (72) in a transmission connection.
6. The automatic wing retraction device for a UAV according to claim 5, characterized in that, The drive device includes two recovery torsion springs (6), which are respectively installed on opposite sides of the first recovery push plate (71) and the second recovery push plate (72); the two recovery torsion springs (6) are respectively driven connected to the first recovery push plate (71) and the second recovery push plate (72).
7. The automatic wing retraction device for a UAV according to claim 6, characterized in that, The torque of the recovery torsion spring (6) is greater than the torque of the spring torsion spring (5).
8. The automatic wing retraction device for a UAV according to claim 7, characterized in that, The torque of the recovery torsion spring (6) is 1.5-2.5 times that of the spring torsion spring (5).
9. The automatic wing folding device for a UAV according to claim 1, characterized in that, The limiting device includes an electromagnetic locking pin and a locking pin (8). The locking pin (8) is engaged in the electromagnetic locking pin. The end of the locking pin (8) away from the electromagnetic locking pin is engaged between the first rear wing (2) and the second rear wing (3).
10. The automatic wing retraction device for a UAV according to claim 9, characterized in that, The electromagnetic locking pin is installed on the outside of the mounting base (1).