A coaxial wing synchronous deployment mechanism for unmanned aerial vehicles

Abstract

This invention discloses a coaxial wing synchronous deployment mechanism for unmanned aerial vehicles (UAVs), comprising: a support base, a motor, a reduction gearbox, a deployment mechanism assembly, and a wing connector; the output shaft of the motor is connected to the input gear of the reduction gearbox, and the lead screw of the ball screw assembly in the reduction gearbox is connected to the rack of the deployment mechanism assembly; the rack of the deployment mechanism assembly meshes with two sets of gears inside it, and the two sets of gears mesh one-to-one with two nested drive housings in the deployment mechanism assembly; the wing connector is installed at the ends of the two drive housings. The technical solution provided by this invention solves the problems of poor synchronization, poor reliability, slow response speed, large volume, and long-term storage in existing UAV wing deployment mechanisms.

Description

Technical Field

[0001] This invention relates to, but is not limited to, the field of unmanned aerial vehicle (UAV) technology, and particularly to a coaxial wing synchronous deployment mechanism for UAVs. Background Technology

[0002] Barrel-shaped or box-shaped folding-wing drones are characterized by their small size, ease of carrying and transportation, and flexible deployment. Among them, the wing deployment mechanism is the key actuation device.

[0003] However, most existing UAV wing deployment mechanisms use torsion springs, linkages, and other mechanisms to drive deployment, but these mechanisms often suffer from poor synchronization, low reliability, slow response speed, and large size. Summary of the Invention

[0004] The purpose of this invention is to provide a coaxial wing synchronous deployment mechanism for unmanned aerial vehicles (UAVs) to solve the problems of poor synchronization, poor reliability, slow response speed, large volume, and long-term storage in existing UAV wing deployment mechanisms.

[0005] The technical solution of this invention is as follows:

[0006] This invention provides a coaxial wing synchronous deployment mechanism for a drone, comprising: a support base 1, a motor 2, a reduction gearbox 3, a deployment mechanism assembly 4, and a wing connector 5;

[0007] The output shaft of the motor 2 is connected to the input gear 3-5 of the reduction gearbox 3, and the ball screw assembly 3-2 in the reduction gearbox 3 is connected to the rack 4-6 of the unfolding mechanism assembly 4.

[0008] The racks 4-6 of the deployment mechanism assembly 4 mesh with the two sets of gears inside them, and the two sets of gears mesh with the two nested drive housings in the deployment mechanism assembly 4 one-to-one; the wing connectors 5 are installed at the ends of the two drive housings.

[0009] Optionally, in the coaxial wing synchronous deployment mechanism of the UAV as described above,

[0010] The coaxial wing synchronous deployment mechanism of the UAV is used to convert the rotation output by the motor 2 into linear motion transmitted to the rack 4-6 of the deployment mechanism assembly 4 through the reduction gearbox 3. The linear motion of the rack 4-6 drives the two sets of gears inside to rotate, thereby driving the two drive housings to drive the wing connectors 5 connected to them to rotate, thus driving the two sets of wings to rotate and deploy synchronously.

[0011] Optionally, in the coaxial wing synchronous deployment mechanism of the UAV as described above,

[0012] The reduction gearbox 3 includes: gear housing I 3-1, ball screw assembly 3-2, intermediate gear 3-3, gear housing II 3-4, and input gear 3-5; wherein, gear housing I 3-1 and gear housing II 3-4 are mounted together to form a gear cavity for mounting each gear, one end of the ball screw assembly 3-2 is mounted on the upper part of the gear cavity, one end of the multiple intermediate gears 3-3 located in the gear cavity meshes with the input gear 3-5, and the other end meshes with the ball screw assembly 3-2, and the extended screw of the ball screw assembly 3-2 is connected to the rack 4-6 of the unfolding mechanism assembly 4.

[0013] Optionally, in the coaxial wing synchronous deployment mechanism of the UAV as described above,

[0014] The output shaft of the motor 2 is connected to the input gear 3-5 of the reduction gearbox 3. The rotation of the motor 2 will transmit the rotation to the input gear 3-5. The rotation is converted into linear motion of the screw in the ball screw assembly 3-2 through the meshing connection structure of the intermediate gear 3-3 and transmitted to the rack 4-6 of the unfolding mechanism assembly 4.

[0015] Optionally, in the coaxial wing synchronous deployment mechanism of the UAV as described above,

[0016] The unfolding mechanism assembly 4 includes: mounting frame 4-1, internal gear ring drive housing I 4-2, cover plate 4-3, internal gear ring drive housing II 4-4, pinion I 4-5, rack 4-6, and pinion II 4-7;

[0017] The internal gear ring drive housing I4-2 and the internal gear ring drive housing II4-4 are both configured as sleeve structures with a boss on the outer side of the top end. The inner gear ring drive housing II4-4 is provided with a limiting protrusion on the outer side of the middle part and a mounting protrusion on the inner side of the middle part. The internal gear ring drive housing I4-2 is sleeved on the outside of the internal gear ring drive housing II4-4 from the bottom, and the top end position of the internal gear ring drive housing I4-2 is restricted by the limiting protrusion in the middle of the internal gear ring drive housing II4-4.

[0018] The mounting bracket 4-1 is installed inside the housing via the mounting protrusion in the middle of the internal gear ring drive housing II 4-4 and is fixed by the cover plate 4-3. The rack 4-6, pinion I 4-5 and pinion II 4-7 are all installed inside the mounting bracket 4-1. The rack 4-6 meshes with pinion I 4-5 and pinion II 4-7 respectively. The pinion I 4-5 meshes with the inner wall of the bottom end of the internal gear ring drive housing I 4-2 located on the outer side, and the pinion II 4-7 meshes with the inner wall of the internal gear ring drive housing II 4-4 located on the inner side.

[0019] Optionally, in the coaxial wing synchronous deployment mechanism of the UAV as described above,

[0020] The coaxial wing synchronous deployment mechanism of the UAV is specifically used to convert the rotation of the motor 2 into the linear motion of the rack 4-6 through the connection between the ball screw assembly 3-2 and the rack 4-6. The rack 4-6 meshes with pinion I 4-5 and pinion II 4-7 respectively, converting the linear motion of the rack 4-6 into the gear rotation of pinion I 4-5 and pinion II 4-7. Through the meshing of pinion I 4-5 with the internal gear ring drive housing I 4-2 and pinion II 4-7 with the internal gear ring drive housing II 4-4, the internal gear ring drive housing I 4-2 and internal gear ring drive housing II 4-4 are driven to move synchronously and symmetrically.

[0021] Optionally, in the coaxial wing synchronous deployment mechanism of the UAV as described above,

[0022] The internal gear ring drive housing I4-2 and the internal gear ring drive housing II4-4 rotate relative to each other on the same axis.

[0023] Optionally, in the coaxial wing synchronous deployment mechanism of the UAV as described above,

[0024] The wing connector 5 includes wing connector I and wing connector II, which are fixed to the internal gear ring drive housing I4-2 and internal gear ring drive housing II4-4 respectively, and rotate synchronously with the rotation of the internal gear ring drive housing I4-2 and internal gear ring drive housing II4-4. Wing connector I and wing connector II are connected to the left and right wings of the wing respectively, and the left and right wings of the wing are UAV components.

[0025] The beneficial effects of this invention are as follows:

[0026] This invention provides a coaxial wing synchronous deployment mechanism for a drone. A motor 2 drives a lead screw nut to rotate via a reduction gearbox 3. The lead screw nut pushes a rack 4-6 in linear motion. The rack 4-6 drives two gears to rotate clockwise and counterclockwise respectively. These two gears, in turn, drive two internal gear rings to drive the housing (corresponding to the right and left wings) in symmetrical coaxial deflection. This invention provides a technical solution that uses a centralized motor drive and distributed coaxial actuation to drive the wing's synchronous rotation and deployment. It features high synchronization, reliability, fast response, and a small footprint after folding. Compared to passive drives such as torsion springs or springs, it offers smoother operation and more controllable process. The coaxial wing synchronous deployment mechanism for drones provided by this invention has the following advantages:

[0027] Beneficial effects:

[0028] 1) The left and right wings are driven by a centralized motor, which effectively ensures mechanical synchronization;

[0029] 2) The internal gear ring drives housing I and internal gear ring drives housing II to rotate coaxially, enabling the left and right wings to fold vertically and horizontally, resulting in a smaller volume;

[0030] 3) The rack and pinion drives the internal gear ring drive housing through the pinion, which synchronously converts linear motion into rotational motion. This can counteract the overturning torque transmitted by the lead screw, resulting in smooth transmission, high transmission efficiency, and ensuring transmission accuracy and reliability.

[0031] 4) The ball screw assembly has a limiting function, which limits the unfolding angle to 90 degrees, effectively resisting the external force fluctuations transmitted by the pneumatic load and ensuring the smoothness of linear motion.

[0032] 5) By adjusting the forward and reverse rotation of the motor, bidirectional folding and unfolding can be achieved, which facilitates rapid recovery and deployment;

[0033] 6) The unfolding angle range is 0-90 degrees. The unfolding angle is adjustable and controllable, and is divided into 0 degrees, 45 degrees, 60 degrees and 90 degrees. It is controlled by the number of motor rotations in an open loop. Attached Figure Description

[0034] The accompanying drawings are provided to further understand the technical solutions of the present invention and constitute a part of the specification. They are used together with the embodiments of this application to explain the technical solutions of the present invention and do not constitute a limitation on the technical solutions of the present invention.

[0035] Figure 1 This is a schematic diagram of the overall structure of a coaxial wing synchronous deployment mechanism for a drone provided in an embodiment of the present invention;

[0036] Figure 2 for Figure 1 The schematic diagram of the reduction gearbox in the coaxial wing synchronous deployment mechanism of the UAV provided in the embodiment shown;

[0037] Figure 3 for Figure 1 The illustrated embodiment provides a schematic diagram of the deployment mechanism component in the coaxial wing synchronous deployment mechanism for unmanned aerial vehicles.

[0038] Figure 4 for Figure 1 The schematic diagram of the wing connector 5 in the coaxial wing synchronous deployment mechanism of the UAV provided in the embodiment shown.

[0039] 1 Support base, 2 Motor, 3 Reduction gearbox, 4 Deployment mechanism assembly, 5 Wing connector. The reduction gearbox 3 includes: 3-1 Gear housing I, 3-2 Ball screw assembly, 3-3 Intermediate gear, 3-4 Gear housing II, 3-5 Input gear. The deployment mechanism assembly includes: 4-1 Mounting bracket, 4-2 Internal gear ring drive housing I, 4-3 Cover plate, 4-4 Internal gear ring drive housing II, 4-5 Pinion I, 4-6 Rack, 4-7 Pinion II. Detailed Implementation

[0040] To make the objectives, technical solutions, and advantages of the present invention clearer, the embodiments of the present invention will be described in detail below with reference to the accompanying drawings. It should be noted that, unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

[0041] As explained in the background section, most existing UAV wing deployment mechanisms use torsion springs, linkages, and other mechanisms to drive deployment. However, these mechanisms often suffer from poor synchronization, low reliability, slow response speed, and large size. An example of an existing UAV wing deployment mechanism is shown below:

[0042] Patents CN209479954U and CN212500997U employ a gas-operated cylinder-driven linkage mechanism to achieve deployment, offering fast response. However, the wing and mechanism structure require significant strength to address the impact of the gas-operated cylinder, resulting in poor reliability and a heavy mechanism. Patent CN214648993U uses a crank-rocker mechanism for deployment, occupying considerable space and making storage and maintenance inconvenient. Patent CN110871886A uses a lead screw linear actuation to drive wing extension and retraction, while patent 206327561U uses a linear power mechanism to achieve both linear and rotational movement. While the motion is relatively smooth and reliable, its resistance to external load disturbances is poor. Patent CN112550666A uses a tension spring to drive the mechanism along the guide rail. However, the tension spring's lifespan and characteristics deteriorate under long-term tension and compression, resulting in poor reliability and making it unsuitable for long-term storage and transportation. Similarly, patents CN113148111A, CN211076312U, CN112849400A, CN207417122U, CN210707855U, and CN109367760A use a pre-compressed torsion spring or compression spring to drive the rotating shaft and deploy the wings. Patent CN207417115U uses a motor to drive the connecting rod to rotate, with double gears limiting the non-coaxial wings. However, this wing is non-coaxial, resulting in a large folded volume. Patent CN210526835U uses a motor-driven screw and nut mechanism to drive the connecting rod and deploy the wings.

[0043] To address the problems of poor synchronization, low reliability, slow response speed, large size, and long-term storage in existing UAV wing deployment mechanisms, this invention provides a coaxial wing synchronous deployment mechanism for UAVs. The basic principle is that a motor drives a lead screw nut to rotate through a spur gear reduction, the lead screw nut pushes a rack to move linearly, the rack drives two gears to rotate clockwise and counterclockwise respectively, and the two gears in turn drive two internal gear rings to drive the housing (corresponding to the right wing and the left wing respectively) to perform symmetrical coaxial deflection.

[0044] The present invention provides the following specific embodiments, which can be combined with each other. For the same or similar concepts or processes, they may not be described again in some embodiments.

[0045] Figure 1 This is a schematic diagram of the overall structure of a coaxial wing synchronous deployment mechanism for a drone provided in an embodiment of the present invention. Figure 2 for Figure 1 The schematic diagram of the reduction gearbox in the coaxial wing synchronous deployment mechanism of the UAV provided in the embodiment shown; Figure 3 for Figure 1 The illustrated embodiment provides a schematic diagram of the deployment mechanism component in the coaxial wing synchronous deployment mechanism for a UAV. The main structure of the coaxial wing synchronous deployment mechanism for a UAV provided in this embodiment includes: a support base 1, a motor 2, a reduction gearbox 3, a deployment mechanism component 4, and a wing connector 5.

[0046] Reference Figures 1 to 3 As shown, in the structure of the coaxial wing synchronous deployment mechanism of the UAV, the output shaft of the motor 2 is connected to the input gear 3-5 of the reduction gearbox 3, and the ball screw assembly 3-2 in the reduction gearbox 3 is connected to the rack 4-6 of the deployment mechanism assembly 4.

[0047] In this embodiment of the invention, the racks 4-6 of the deployment mechanism assembly 4 mesh with two sets of gears inside them respectively, and the two sets of gears mesh with the two nested drive housings in the deployment mechanism assembly 4 one-to-one; the wing connector 5 is installed at the ends of the two drive housings.

[0048] Based on the basic structure of the above-mentioned coaxial wing synchronous deployment mechanism for UAVs, the working principle of this mechanism is as follows:

[0049] The rotation output from motor 2 is converted into linear motion by reduction gearbox 3 and transmitted to rack 4-6 of deployment mechanism assembly 4. The linear motion of rack 4-6 drives the two sets of gears inside to rotate, thereby driving the two drive housings to drive the wing connectors 5 connected to them to rotate, thus driving the two sets of wings to rotate and deploy synchronously.

[0050] like Figure 2 The specific structure of the reduction gearbox 3 shown includes: gear housing I 3-1, ball screw assembly 3-2, intermediate gear 3-3, gear housing II 3-4, and input gear 3-5; wherein, gear housing I 3-1 and gear housing II 3-4 are mounted together to form a gear cavity for mounting each gear, one end of the ball screw assembly 3-2 is mounted on the upper part of the gear cavity, one end of the multiple intermediate gears 3-3 located in the gear cavity meshes with the input gear 3-5, and the other end meshes with the ball screw assembly 3-2, and the extended screw of the ball screw assembly 3-2 is connected to the rack 4-6 of the unfolding mechanism assembly 4.

[0051] Since the output shaft of motor 2 is connected to the input gear 3-5 of reduction gearbox 3, the rotation of motor 2 will be transmitted to the input gear 3-5. Through the meshing connection structure between intermediate gear 3-3 and ball screw assembly 3-2, the rotation will be converted into linear motion of the screw in ball screw assembly 3-2 and transmitted to the rack 4-6 of unfolding mechanism assembly 4.

[0052] like Figure 3 The specific structure of the unfolding mechanism component 4 shown includes: mounting bracket 4-1, internal gear ring drive housing I 4-2, cover plate 4-3, internal gear ring drive housing II 4-4, pinion I 4-5, rack 4-6, and pinion II 4-7.

[0053] Figure 3 In the structure of the unfolding mechanism assembly 4 shown, both the internal gear ring drive housing I4-2 and the internal gear ring drive housing II4-4 are configured as sleeve structures with a boss on the outer side of the top end. The inner gear ring drive housing II4-4 has a limiting protrusion ring on the outer side of the middle part and an installation protrusion ring on the inner side of the middle part. The internal gear ring drive housing I4-2 is sleeved on the outside of the internal gear ring drive housing II4-4 from the bottom, and the top end position of the internal gear ring drive housing I4-2 is restricted by the limiting protrusion ring in the middle of the internal gear ring drive housing II4-4.

[0054] In the unfolding mechanism assembly 4, the mounting frame 4-1 is installed inside the housing via the mounting protrusion in the middle of the internal gear ring drive housing II 4-4 and is fixed by the cover plate 4-3. The rack 4-6, pinion I 4-5 and pinion II 4-7 are all installed inside the mounting frame 4-1. The rack 4-6 meshes with pinion I 4-5 and pinion II 4-7 respectively. The pinion I 4-5 meshes with the inner wall of the bottom end of the internal gear ring drive housing I 4-2 located on the outer side, and the pinion II 4-7 meshes with the inner wall of the internal gear ring drive housing II 4-4 located on the inner side.

[0055] Based on the specific structure of the aforementioned deployment mechanism component 4, the coaxial wing synchronous deployment mechanism of the UAV converts the rotation of the motor 2 into the linear motion of the rack 4-6 through the connection between the ball screw component 3-2 and the rack 4-6. The rack 4-6 meshes with pinion I 4-5 and pinion II 4-7 respectively, converting the linear motion of the rack 4-6 into the gear rotation of pinion I 4-5 and pinion II 4-7. Through the meshing of pinion I 4-5 with the internal gear ring drive housing I 4-2 and pinion II 4-7 with the internal gear ring drive housing II 4-4, the internal gear ring drive housing I 4-2 and internal gear ring drive housing II 4-4 are driven to move synchronously and symmetrically.

[0056] It should be noted that, based on the structural configuration of the unfolding mechanism component 4, the internal gear ring drive housing I4-2 and the internal gear ring drive housing II4-4 rotate coaxially relative to each other.

[0057] like Figure 4The specific structure of the wing connector 5 shown includes wing connector I and wing connector II, which are fixed to the internal gear ring drive housing I4-2 and internal gear ring drive housing II4-4 respectively, and rotate synchronously with the rotation of the internal gear ring drive housing I4-2 and internal gear ring drive housing II4-4. Wing connector I and wing connector II are connected to the left and right wings of the wing respectively, and the left and right wings of the wing are UAV components.

[0058] Additionally, it should be noted that in this embodiment of the invention, the support base 1 is used for fixing and supporting the reduction gearbox 3 and the unfolding mechanism assembly 4, ensuring the positional relationship between the reduction gearbox 3, the unfolding mechanism assembly 4, and the internal components, effectively guaranteeing transmission accuracy and stability. Motor 2 is an active drive device.

[0059] The coaxial wing synchronous deployment mechanism for UAVs provided in this embodiment of the invention uses a motor 2 to drive a lead screw nut to rotate via a reduction gearbox 3. The lead screw nut drives a rack 4-6 to move linearly. The rack 4-6 drives two gears to rotate clockwise and counterclockwise respectively. These two gears, in turn, drive two internal gear rings to drive the housing (corresponding to the right and left wings) to perform symmetrical coaxial deflection. This embodiment of the invention provides a technical solution that uses a centralized motor drive and distributed coaxial actuation to drive the wing to rotate and deploy synchronously. This method features high synchronization, reliability, fast response speed, and small footprint after folding. Compared to passive drives such as torsion springs or springs, it offers smoother operation and more controllable process. The coaxial wing synchronous deployment mechanism for UAVs provided in this embodiment of the invention has the following characteristics:

[0060] Beneficial effects:

[0061] 1) The left and right wings are driven by a centralized motor, which effectively ensures mechanical synchronization;

[0062] 2) The internal gear ring drives housing I and internal gear ring drives housing II to rotate coaxially, enabling the left and right wings to fold vertically and horizontally, resulting in a smaller volume;

[0063] 3) The rack and pinion drives the internal gear ring drive housing through the pinion, which synchronously converts linear motion into rotational motion. This can counteract the overturning torque transmitted by the lead screw, resulting in smooth transmission, high transmission efficiency, and ensuring transmission accuracy and reliability.

[0064] 4) The ball screw assembly has a limiting function, which limits the unfolding angle to 90 degrees, effectively resisting the external force fluctuations transmitted by the pneumatic load and ensuring the smoothness of linear motion.

[0065] 5) By adjusting the forward and reverse rotation of the motor, bidirectional folding and unfolding can be achieved, which facilitates rapid recovery and deployment;

[0066] 6) The unfolding angle range is 0-90 degrees. The unfolding angle is adjustable and controllable, and is divided into 0 degrees, 45 degrees, 60 degrees and 90 degrees. It is controlled by the number of motor rotations in an open loop.

[0067] The working principle of the coaxial wing synchronous deployment mechanism for UAVs provided in the above embodiments of the present invention is described as follows:

[0068] (a) Collapse function:

[0069] The coaxial wing synchronous deployment mechanism of the UAV transitions from the deployed state to the folded state. Motor 2 rotates counterclockwise, transmitting the rotational motion to ball screw assembly 3-2 via input gear 3-5 and intermediate gear 3-3. Ball screw assembly 3-2 converts the rotational motion into linear motion, which drives rack 4-6 to move linearly. Rack 4-6 meshes with pinion I 4-5 and pinion II 4-7, respectively, driving pinion I 4-5 and pinion II 4-7 to rotate counterclockwise and clockwise, respectively. Pinion I 4-5 and pinion II 4-7 then drive internal gear ring drive housing I 4-2 and internal gear ring drive housing II 4-4 to perform symmetrical coaxial deflection, thus achieving the folding function.

[0070] (II) Expand function:

[0071] The coaxial wing synchronous deployment mechanism of the UAV transitions from a folded state to a fully deployed state. Motor 2 rotates clockwise, transmitting the rotational motion to ball screw assembly 3-2 via input gear 3-5 and intermediate gear 3-3. Ball screw assembly 3-2 converts the rotational motion into linear motion, which in turn drives rack 4-6 to move linearly. Rack 4-6 meshes with pinion I 4-5 and pinion II 4-7, driving pinion I 4-5 and pinion II 4-7 to rotate clockwise and counterclockwise, respectively. Pinion I 4-5 and pinion II 4-7 then drive internal gear ring drive housing I 4-2 and internal gear ring drive housing II 4-4 to perform symmetrical coaxial deflection, thus achieving the deployment function.

[0072] While the embodiments disclosed in this invention are as described above, the content is merely for the purpose of facilitating understanding of the invention and is not intended to limit the invention. Any person skilled in the art to which this invention pertains may make any modifications and changes to the form and details of the implementation without departing from the spirit and scope disclosed herein; however, the scope of patent protection of this invention shall still be determined by the scope defined in the appended claims.

Claims

1. A coaxial wing synchronous deployment mechanism for a drone, characterized in that, include: Support base (1), motor (2), reduction gearbox (3), deployment mechanism assembly (4) and wing connector (5); The output shaft of the motor (2) is connected to the input gear (3-5) of the reduction gearbox (3), and the ball screw assembly (3-2) in the reduction gearbox (3) is connected to the rack (4-6) of the unfolding mechanism assembly (4). The rack (4-6) of the deployment mechanism assembly (4) meshes with two sets of gears inside it, and the two sets of gears mesh with two nested drive housings in the deployment mechanism assembly (4) in a one-to-one correspondence; the wing connector (5) is installed at the ends of the two drive housings; The unfolding mechanism assembly (4) includes: a mounting frame (4-1), an internal gear ring drive housing I (4-2), a cover plate (4-3), an internal gear ring drive housing II (4-4), a pinion I (4-5), a rack (4-6), and a pinion II (4-7). The internal gear ring drive housing I (4-2) and the internal gear ring drive housing II (4-4) are both configured as sleeve structures with a boss on the outer side of the top end. The inner gear ring drive housing II (4-4) is provided with a limiting protrusion ring on the outer side of the middle part and an installation protrusion ring on the inner side of the middle part. The internal gear ring drive housing I (4-2) is sleeved on the outside of the internal gear ring drive housing II (4-4) from the bottom, and the top end position of the internal gear ring drive housing I (4-2) is restricted by the limiting protrusion ring in the middle of the internal gear ring drive housing II (4-4). The mounting bracket (4-1) is installed inside the housing via the mounting protrusion in the middle of the internal gear ring drive housing II (4-4) and fixed by the cover plate (4-3). The rack (4-6), pinion I (4-5) and pinion II (4-7) are all installed inside the mounting bracket (4-1). The rack (4-6) meshes with pinion I (4-5) and pinion II (4-7) respectively. Pinion I (4-5) meshes with the inner wall of the bottom end of the internal gear ring drive housing I (4-2) located on the outer side, and pinion II (4-7) meshes with the inner wall of the internal gear ring drive housing II (4-4) located on the inner side. The internal gear ring drive housing I (4-2) and the internal gear ring drive housing II (4-4) rotate coaxially relative to each other.

2. The coaxial wing synchronous deployment mechanism for unmanned aerial vehicles according to claim 1, characterized in that, The coaxial wing synchronous deployment mechanism of the UAV is used to convert the rotation output by the motor (2) into linear motion transmitted to the rack (4-6) of the deployment mechanism assembly (4) through the reduction gearbox (3). The linear motion of the rack (4-6) drives the two sets of gears inside to rotate, thereby driving the two drive housings to drive the wing connectors (5) connected to them to rotate, thus driving the two sets of wings to rotate synchronously and deploy.

3. The coaxial wing synchronous deployment mechanism for unmanned aerial vehicles according to claim 1, characterized in that, The reduction gearbox (3) includes: gear housing I (3-1), ball screw assembly (3-2), intermediate gear (3-3), gear housing II (3-4), and input gear (3-5); wherein, gear housing I (3-1) and gear housing II (3-4) are mounted together to form a gear cavity for mounting each gear, one end of the ball screw assembly (3-2) is mounted on the upper part of the gear cavity, one end of the multiple intermediate gears (3-3) located in the gear cavity meshes with the input gear (3-5) and the other end meshes with the ball screw assembly (3-2), and the screw extending from the ball screw assembly (3-2) is connected to the rack (4-6) of the unfolding mechanism assembly (4).

4. The coaxial wing synchronous deployment mechanism for unmanned aerial vehicles according to claim 3, characterized in that, The output shaft of the motor (2) is connected to the input gear (3-5) of the reduction gearbox (3), which transmits the rotation of the motor (2) to the input gear (3-5). Through the meshing connection structure between the intermediate gear (3-3) and the ball screw assembly (3-2), the rotation is converted into the linear motion of the screw in the ball screw assembly (3-2) and transmitted to the rack (4-6) of the unfolding mechanism assembly (4).

5. The coaxial wing synchronous deployment mechanism for unmanned aerial vehicles according to claim 1, characterized in that, The coaxial wing synchronous deployment mechanism of the UAV is specifically used to convert the rotation of the motor (2) into the linear motion of the rack (4-6) through the connection between the ball screw assembly (3-2) and the rack (4-6). The rack (4-6) meshes with pinion I (4-5) and pinion II (4-7) respectively, converting the linear motion of the rack (4-6) into the gear rotation of pinion I (4-5) and pinion II (4-7). Through the meshing of pinion I (4-5) with the internal gear ring drive housing I (4-2) and pinion II (4-7) with the internal gear ring drive housing II (4-4), the internal gear ring drive housing I (4-2) and internal gear ring drive housing II (4-4) are driven to move synchronously and symmetrically.

6. The coaxial wing synchronous deployment mechanism for unmanned aerial vehicles according to claim 1, characterized in that, The wing connector (5) includes wing connector I and wing connector II, which are fixed to the internal gear ring drive housing I (4-2) and internal gear ring drive housing II (4-4) respectively, and rotate synchronously with the rotation of the internal gear ring drive housing I (4-2) and internal gear ring drive housing II (4-4). Wing connector I and wing connector II are connected to the left and right wings of the wing respectively, and the left and right wings of the wing are UAV components.

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