Unmanned aerial vehicle folding wing unfolding mechanism

Abstract

The utility model discloses an unmanned aerial vehicle folding wing unfolding mechanism which comprises a first wing, a second wing, a transmission assembly and a driving structure, the transmission assembly comprises a first connecting arm and a second connecting arm, one side of the first connecting arm is hinged to a first transmission plate, one side of the second connecting arm is hinged to a second transmission plate, and the first connecting arm is hinged to a second connecting arm. The top end of the first transmission plate is fixedly connected with a first transmission pipe, the second transmission plate is fixedly connected with a second transmission pipe, the driving structure is connected with the first connecting arm and the second connecting arm, and the driving structure can drive the first wing and the second wing to be unfolded or folded through the transmission assembly. Compared with the prior art, the folding wing unfolding mechanism of the unmanned aerial vehicle is simple and compact in structure, capable of saving the internal space of the vehicle body, suitable for various pipe launching unmanned aerial vehicles, high in response speed, reliable and high in transmission efficiency, and effectively solves the problems of a traditional folding wing unfolding mechanism.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) technology, and in particular to a UAV folding wing deployment mechanism. Background Technology

[0002] Modern drones have the advantage of folding into a tubular shape and being launched using traditional tubular launchers, which improves the versatility of drone launchers. Currently, tubular drones are widely used worldwide.

[0003] In the field of folding drone wings, the driving force for folding and unfolding is mostly provided by mechanisms such as tension springs, torsion springs, gas actuators, and motors. The existing methods for deploying folding wings include: 1) Using a tension spring drive structure, where the tension spring drives the folding wing's rotation axis via a rocker arm; 2) Using a torsion spring drive structure, where the torsion spring is embedded within the fuselage and connected to the fuselage and wing rotation axis at both ends; 3) Using a torsion spring drive structure, where the torsion spring only provides deployment torque to the wing root, resulting in insufficient torque for light, small UAVs; 4) Using a gas-actuated cylinder drive structure, which offers fast response but has a similar size to the tension spring structure, resulting in a large system size. The gas-actuated cylinder's output drives the folding wing's rotation axis via a rocker arm, and the system's reliability is limited by the mass of the gas-actuated cylinder; and 5) Using a motor drive structure, where a worm gear or gear set transmits power to the folding wing's rotation axis, resulting in slow response and requiring external power. Therefore, we propose a novel folding wing deployment mechanism for UAVs. Utility Model Content

[0004] The main purpose of this invention is to propose a folding wing deployment mechanism for unmanned aerial vehicles (UAVs), which can effectively solve the problems in the background art.

[0005] To achieve the above objectives, the technical solution adopted by this utility model is as follows: a folding wing deployment mechanism for unmanned aerial vehicles (UAVs), comprising a first wing and a second wing, wherein the first wing and the second wing are connected by a transmission component;

[0006] The transmission assembly includes a first connecting arm and a second connecting arm. A first transmission plate is hinged to one side of the first connecting arm, and a second transmission plate is hinged to one side of the second connecting arm. A first transmission pipe is fixedly connected to the top of the first transmission plate, and a second transmission pipe is fixedly connected to the second transmission plate.

[0007] A drive structure is connected to a first connecting arm and a second connecting arm. The drive structure can drive the first wing and the second wing to unfold or close via a transmission component.

[0008] As a further description of the above technical solution, the first transmission tube is sleeved on the lower end of the second transmission tube and is rotatably connected. The first wing is mounted on the first transmission tube, and the second wing is mounted on the second transmission tube. The first wing and the second wing are respectively provided with through holes adapted to the first transmission tube and the second transmission tube, and the inner wall of the through hole is provided with an integrally formed groove. Both the first transmission tube and the second transmission tube are provided with protrusions adapted to the grooves.

[0009] As a further description of the above technical solution, a partition tube is provided between the first wing and the second wing, the partition tube is sleeved on the second transmission tube, a partition plate is provided below the first wing, the partition plate is sleeved on the first transmission tube, and a limiting member is fixedly connected to the top end of the second transmission tube.

[0010] As a further description of the above technical solution, the drive structure includes a mounting plate, a servo motor is fixedly mounted on one side of the mounting plate, a moving component is provided at the top of the mounting plate, and a limiting component is provided at the bottom of the mounting plate.

[0011] As a further description of the above technical solution, the moving component includes two supports, a sliding rod is fixedly connected between the two supports, a sliding tube and a sliding sleeve are sleeved on the sliding rod, a vertical rod is fixedly connected to the top of the sliding sleeve, a limit hole is opened at the bottom of the sliding sleeve, and a compression spring is sleeved on the sliding tube.

[0012] As a further description of the above technical solution, the limiting component includes an electric slide rail and a limiting post. A sliding strip is fixedly connected to one side of the slider on the electric slide rail, and an inclined groove is formed on the side wall of the limiting post.

[0013] As a further description of the above technical solution, the two brackets are symmetrically fixedly connected to the top of the mounting plate, the compression spring is fixedly connected between the sliding sleeve and one of the brackets, the sliding tube and the sliding sleeve are integrally formed and are slidably connected to the sliding rod, the first connecting arm and the second connecting arm are hinged to the vertical rod, the limiting hole is adapted to the limiting post and is slidably connected, the limiting post is slidably connected to the mounting plate, and the sliding strip is inclined downward and is slidably connected to the inclined groove.

[0014] As a further description of the above technical solution, the electric slide rail is electrically connected to the motor controller in the servo motor.

[0015] Compared with the prior art, the present invention has the following beneficial effects:

[0016] 1. Compared to structures using tension springs or torsion springs, the drive structure of this invention does not require a large amount of internal space. Tension spring drives require rocker arm components, resulting in a large system size; torsion spring drives are mostly embedded in the fuselage, occupying space and having limited torque. In contrast, this device, through the setting of transmission components and drive structures, such as the connection method between the transmission tube and the wing and the layout of the drive structure, makes the overall structure more compact, effectively saving internal space and improving the utilization rate of the UAV's internal space.

[0017] 2. Existing torsion spring drives only apply deployment torque to the wing root, which is relatively small and not suitable for large drones. However, the drive structure of this invention drives the wings to unfold through a transmission component, which can provide a more reasonable torque output. It is not only suitable for light and small drones, but also for larger drones with heavier wings, and can reliably unfold the wings, thus expanding the applicability of drone folding wing unfolding mechanisms.

[0018] 3. Fast and reliable response: While gas-fired actuators offer fast response, their reliability is limited by their quality. This invention employs a drive system combining a servo motor and an electric slide rail, resulting in faster response, a stable and reliable structure, and improved overall reliability of the deployment mechanism.

[0019] 4. High transmission efficiency: Compared with motor drive that transmits power to the folding wing rotation shaft through worm gears, gear sets, etc., the transmission component of this utility model is directly connected to the wing. The drive structure controls the transmission component through simple moving components and limiting components. The transmission process is simple and efficient, avoiding energy loss and transmission delay caused by complex transmission methods, and improving transmission efficiency. Attached Figure Description

[0020] Figure 1 This is a schematic diagram of the overall structure of a folding wing deployment mechanism for a drone according to this utility model. Figure 1 ;

[0021] Figure 2 This is a schematic diagram of the overall structure of a folding wing deployment mechanism for a drone according to this utility model. Figure 2 ;

[0022] Figure 3 This is a partial structural diagram of a folding wing deployment mechanism for a drone according to this utility model. Figure 1 ;

[0023] Figure 4 This is a partial structural diagram of a folding wing deployment mechanism for a drone according to this utility model. Figure 2 ;

[0024] Figure 5 This is a schematic diagram of the transmission component structure of a folding wing deployment mechanism for a drone according to the present invention.

[0025] Figure 6 This is a schematic diagram of the drive structure of a folding wing deployment mechanism for a drone according to the present invention.

[0026] Figure 7 This is a cross-sectional view of the moving component structure of a folding wing deployment mechanism for a drone according to this utility model;

[0027] Figure 8 This is a schematic diagram of the limiting component structure of a folding wing deployment mechanism for a drone according to the present invention.

[0028] In the diagram: 1. First wing; 2. Second wing; 3. Transmission assembly; 4. Drive structure; 5. Separator tube; 6. Separator plate; 7. Limiting component; 8. Protrusion; 31. First connecting arm; 32. Second connecting arm; 33. First transmission plate; 34. Second transmission plate; 35. First transmission tube; 36. Second transmission tube; 41. Mounting plate; 42. Servo; 43. Moving assembly; 45. Limiting assembly; 431. Bracket; 432. Slide rod; 433. Slide tube; 434. Slide sleeve; 435. Vertical rod; 436. Limiting hole; 437. Compression spring; 451. Electric slide rail; 452. Limiting post; 453. Sliding bar; 454. Inclined groove. Detailed Implementation

[0029] To make the technical means, creative features, and objectives of this utility model easier to understand, the following describes this utility model in conjunction with specific embodiments.

[0030] In the description of this utility model, it should be noted that the terms "upper," "lower," "inner," "outer," "front end," "rear end," "both ends," "one end," and "the other end," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this utility model and simplifying the description, 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. Therefore, they should not be construed as limitations on this utility model. In addition, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0031] In the description of this utility model, it should be noted that, unless otherwise explicitly specified and limited, the terms "installed," "equipped with," and "connected," etc., should be interpreted broadly. For example, "connected" can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium; it can be a connection within two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model based on the specific circumstances.

[0032] Please see Figure 1-8This utility model provides a technical solution: a folding wing deployment mechanism for a drone, including a first wing 1 and a second wing 2. The first wing 1 is located below the second wing 2. The first wing 1 and the second wing 2 are connected by a transmission assembly 3. The transmission assembly 3 includes a first connecting arm 31 and a second connecting arm 32. A first transmission plate 33 is hinged to one side of the first connecting arm 31, and a second transmission plate 34 is hinged to one side of the second connecting arm 32. A first transmission pipe 35 is sleeved on the lower end of the second transmission pipe 36 and is rotatably connected. A first transmission plate 34 is fixedly connected to the top of the first transmission plate 33. The transmission pipe 35 and the second transmission plate 34 are fixedly connected to the second transmission pipe 36. The first wing 1 is installed on the first transmission pipe 35 and the second wing 2 is installed on the second transmission pipe 36. The first wing 1 and the second wing 2 are respectively provided with through holes that are adapted to the first transmission pipe 35 and the second transmission pipe 36, and the inner wall of the through hole is provided with an integrally formed groove. The first transmission pipe 35 and the second transmission pipe 36 are both provided with protrusions 8 that are adapted to the grooves. When the first transmission pipe 35 rotates, it will drive the first wing 1 to rotate, and when the second transmission pipe 36 rotates, it will drive the second wing 2 to rotate. A partition tube 5 is provided between the first wing 1 and the second wing 2. The partition tube 5 is sleeved on the second transmission tube 36 to prevent the second wing 2 from sliding down on the second transmission tube 36 and contacting the first wing 1. A partition plate 6 is provided below the first wing 1. The partition plate 6 is sleeved on the first transmission tube 35 to prevent the first wing 1 from sliding down on the first transmission tube 35. A limiting member 7 is fixedly connected to the top of the second transmission tube 36 to prevent the second wing 2 from sliding up from the second transmission tube 36.

[0033] The drive structure 4 is connected to the first connecting arm 31 and the second connecting arm 32. The drive structure 4, through the transmission assembly 3, can drive the first wing 1 and the second wing 2 to unfold or close. The drive structure 4 includes a mounting plate 41, which is used to fix the device in a groove on the top of the UAV fuselage. A servo motor 42 is fixedly mounted on one side of the mounting plate 41. It should be noted that the UAV servo motor is a mature and publicly available technology, and is an important actuator in the UAV flight control system. It is typically small and lightweight to meet the UAV's lightweight requirements. Its internal structure generally includes a micro motor, a reduction gear set, a position sensor (such as a potentiometer), and a controller. The micro motor provides power, the reduction gear set converts the motor's high speed and low torque into low speed and high torque to drive the control surfaces; the position sensor provides real-time feedback on the control surface position information, and the controller adjusts the motor according to the received control signals.

[0034] A movable component 43 is provided at the top of the mounting plate 41. The movable component 43 includes two brackets 431, which are symmetrically and fixedly connected to the top of the mounting plate 41. A slide rod 432 is fixedly connected between the two brackets 431. A slide tube 433 and a slide sleeve 434 are fitted on the slide rod 432. The slide tube 433 and the slide sleeve 434 are integrally formed and are slidably connected to the slide rod 432. A compression spring 437 is fitted on the slide tube 433 and is fixedly connected between the slide sleeve 434 and one of the brackets 431. A vertical rod 435 is fixedly connected to the top of the slide sleeve 434. The first connecting arm 31 and the second connecting arm 32 are both hinged to the vertical rod 435. A limit hole 436 is provided at the bottom of the slide sleeve 434. A limiting component 45 is provided at the bottom of the plate 41. The limiting component 45 includes an electric slide rail 451 and a limiting post 452. The electric slide rail 451 is existing technology, so its specific structure and working principle will not be described here. The electric slide rail 451 is electrically connected to the motor controller in the servo motor 42. The servo motor 42 can control the slider on the electric slide rail 451 to slide on the guide rail. The limiting post 452 is slidably connected to the mounting plate 41. A sliding strip 453 is fixedly connected to one side of the slider on the electric slide rail 451. An inclined groove 454 is opened on the side wall of the limiting post 452. The sliding strip 453 is inclined downward and slidably connected to the inclined groove 454. The limiting hole 436 is adapted to the limiting post 452 and is slidably connected.

[0035] like Figure 1 , Figure 2 and Figure 3 As shown, the first wing 1 and the second wing 2 are in a closed state at this time. The UAV is inside the tube-type launch device. The compression spring 437 on the moving component 43 is in a compressed state. At this time, the limiting post 452 on the limiting component 45 is inserted into the limiting hole 436 on the sliding sleeve 434 to limit the sliding sleeve 434 and prevent it from sliding on the sliding rod 432.

[0036] It should be noted that this utility model is a folding wing deployment mechanism for a drone. The wing deployment process is as follows: When the drone needs to deploy its wings, the servo motor 42 receives the deployment command and controls the slider on the electric slide rail 451 to start sliding through its internal motor controller. Since the sliding bar 453 is fixed to one side of the slider and is set at an angle downward, it is slidably connected to the inclined groove 454 on the side wall of the limiting post 452. Therefore, when the slider slides, it will push the limiting post 452 to move downward. When the limiting post 452 moves downward from the bottom of the sliding sleeve 434... After the sliding sleeve 434 is removed from the hole 436, it is no longer restricted in its position. At this time, the compression spring 437, which was in a compressed state, restores its elastic deformation and pushes the sliding sleeve 434 to slide along the sliding rod 432. The vertical rod 435, which is fixedly connected to the top of the sliding sleeve 434, moves accordingly. Since the first connecting arm 31 and the second connecting arm 32 are both hinged to the vertical rod 435, the movement of the vertical rod 435 will cause the first connecting arm 31 and the second connecting arm 32 to rotate around the hinge point. When the first connecting arm 31 rotates, it drives the first transmission plate 33, which is hinged to it, to move. The first transmission tube 35 at the top of the first transmission plate 33 rotates; similarly, the second connecting arm 32 drives the second transmission plate 34 and the second transmission tube 36 to rotate, and the first transmission tube 35 and the second transmission tube 36 respectively drive the first wing 1 and the second wing 2 mounted on them to rotate around their own axes to realize the deployment of the wings; wing closing process: when the UAV needs to close its wings, the external force overcomes the elastic force of the compression spring 437, pushing the sliding sleeve 434 to slide in the opposite direction along the sliding rod 432, and the vertical rod 435 also moves in the opposite direction, driving the first connecting arm 31 and the second connecting arm 32 to rotate in the opposite direction, thereby causing the first transmission tube 35 and the second transmission tube 36 to rotate in the opposite direction, and finally driving the first wing 1 and the second wing 2 to rotate in the opposite direction around their own axes to realize the wing closing. After the wings are closed, the motor controller in the servo motor 42 will control the slider on the electric slide rail 451 to slide in the opposite direction, and the slider drives the sliding bar 453 to move in the opposite direction, causing the limiting post 452 to move upward and insert into the limiting hole 436 of the sliding sleeve 434 to limit the sliding sleeve 434. Compared with existing drone folding wing deployment mechanisms, this utility model has a simple and compact structure, saves internal space, is suitable for various tube-launched drones, has a fast and reliable response speed, and high transmission efficiency, effectively solving the problems existing in traditional folding wing deployment mechanisms.

[0037] The foregoing has shown and described the basic principles, main features, and advantages of this utility model. Those skilled in the art should understand that this utility model is not limited to the above embodiments. The embodiments and descriptions in the specification are merely illustrative of the principles of this utility model. Various changes and modifications can be made to this utility model without departing from its spirit and scope, and all such changes and modifications fall within the scope of the claims. The scope of protection of this utility model is defined by the appended claims and their equivalents.

Claims

1. A UAV folding wing deployment mechanism, characterized by, Including first wing (1) and second wing (2), the first wing (1) and the second wing (2) are connected by being provided with transmission assembly (3); The transmission assembly (3) includes first connecting arm (31) and second connecting arm (32), one side of the first connecting arm (31) is hinged with first transmission plate (33), one side of the second connecting arm (32) is hinged with second transmission plate (34), the top end of the first transmission plate (33) is fixedly connected with first transmission pipe (35), and the second transmission plate (34) is fixedly connected with second transmission pipe (36); Drive structure (4), the drive structure (4) is connected with first connecting arm (31), second connecting arm (32), and the drive structure (4) can drive the unfolding or closing of first wing (1) and second wing (2) through transmission assembly (3).

2. The folding wing deployment mechanism of claim 1, wherein, The first transmission pipe (35) is sleeved on the lower end of the second transmission pipe (36) and is rotatably connected, the first wing (1) is installed on the first transmission pipe (35), the second wing (2) is installed on the second transmission pipe (36), the first wing (1) and the second wing (2) are respectively provided with through holes matched with the first transmission pipe (35) and the second transmission pipe (36), and a clamping groove is formed in the inner wall of the through hole, and the first transmission pipe (35) and the second transmission pipe (36) are provided with protrusions (8) matched with the clamping groove.

3. The folding wing deployment mechanism of claim 1, wherein, The first wing (1) and the second wing (2) are provided with a partition pipe (5), the partition pipe (5) is sleeved on the second transmission pipe (36), a partition plate (6) is arranged below the first wing (1), the partition plate (6) is sleeved on the first transmission pipe (35), and the top end of the second transmission pipe (36) is fixedly connected with a limiting piece (7).

4. The folding wing deployment mechanism of claim 1, wherein, The drive structure (4) includes a mounting plate (41), one side of the mounting plate (41) is fixedly provided with a steering gear (42), the top end of the mounting plate (41) is provided with a moving assembly (43), and the bottom end of the mounting plate (41) is provided with a limiting assembly (45).

5. The folding wing deployment mechanism of claim 4, wherein, The moving assembly (43) includes two supports (431), two supports (431) are fixedly connected with a sliding rod (432), a sliding pipe (433) and a sliding sleeve (434) are sleeved on the sliding rod (432), the top end of the sliding sleeve (434) is fixedly connected with a vertical rod (435), the bottom end of the sliding sleeve (434) is provided with a limiting hole (436), and a compression spring (437) is sleeved on the sliding pipe (433).

6. The folding wing deployment mechanism of claim 5, wherein, The limiting assembly (45) includes an electric sliding rail (451) and a limiting column (452), one side of the sliding block on the electric sliding rail (451) is fixedly connected with a sliding bar (453), and the side wall of the limiting column (452) is provided with an inclined groove (454).

7. The folding wing deployment mechanism of claim 6, wherein, Two said supports (431) are symmetrically fixedly connected at the top end of the mounting plate (41), the compression spring (437) is fixedly connected between the sliding sleeve (434) and one of the supports (431), the sliding pipe (433) and the sliding sleeve (434) are integrally formed and are both in sliding connection with the sliding rod (432), the first connecting arm (31) and the second connecting arm (32) are both hinged to the vertical rod (435), the limiting hole (436) is matched with the limiting column (452) and is in sliding connection, the limiting column (452) is in sliding connection with the mounting plate (41), and the sliding bar (453) is arranged in an inclined downward manner and is in sliding connection with the inclined groove (454).

8. The folding wing deployment mechanism of claim 7, wherein, The electric sliding rail (451) is electrically connected with the motor controller in the steering wheel (42).

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