Synchronous unfolding and locking mechanism for V-shaped empennage of small unmanned aerial vehicle

Abstract

The utility model relates to the technical field of unmanned aerial vehicles, and discloses a small unmanned aerial vehicle V-shaped empennage synchronous unfolding and locking mechanism which comprises a cabin body, a rotating assembly and a synchronous traction assembly, the cabin body comprises two installation walls, and the rotating assembly comprises a first rotating boss and a second rotating boss which are arranged on the two installation walls in a resettable rotating mode respectively. The left empennage and the right empennage are fixedly connected to the first rotating boss and the second rotating boss respectively, the synchronous traction assembly comprises a first synchronous rope and a second synchronous rope, and the two ends of the first synchronous rope are fixedly connected to the first rotating boss and the second rotating boss respectively. The first synchronous rope is sequentially wound on part of the circumferential surface of the first rotating boss clockwise and wound on part of the circumferential surface of the second rotating boss anticlockwise, and the two ends of the second synchronous rope are fixedly connected to the first rotating boss and the second rotating boss correspondingly; and the first rotating shaft and the second rotating shaft are sequentially and anticlockwise wound on partial circumferential surface of the first rotating boss and clockwise wound on partial circumferential surface of the second rotating boss. The cost is low, and the unfolding synchronism is good.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles (UAVs), in particular to a synchronous unfolding and locking mechanism for a V-shaped tail of a small UAV. Background Art

[0002] Small drones are currently widely used in various fields. Traditional drones have fixed tails, which take up a large space and are not easy to carry. Drones with detachable tails need to be disassembled and assembled on site when in use, which is time-consuming and labor-intensive. Existing drone tails generally adopt a combination of horizontal and vertical tails, which need to be folded at the same time, resulting in a complex structure. However, with a V-shaped tail layout, only a pair of V-tails need to be folded, which has a simple structure. Therefore, folding the V-shaped tail can reduce the loading volume of the drone, making it easier to transport and store, and convenient to use. However, due to the existence of the upper dihedral angle of the V-shaped tail, the rotation axes of the tails on both sides are not coaxial, so it is difficult to ensure the synchronization of the tail deployment. The asynchronous deployment process of the two tails will bring certain challenges to the stability control of the drone and reduce the flight reliability of the drone. In the existing technology, the tail is deployed synchronously using a servo / motor, but this will increase the cost and increase the complexity of the electrical system.

[0003] Therefore, there is an urgent need for a small UAV V-shaped tail synchronous deployment locking mechanism to solve the above problems. Utility Model Content

[0004] Based on the above, the purpose of the present invention is to provide a small UAV V-shaped tail synchronous deployment locking mechanism with a mechanical structure, low cost and better deployment synchronization.

[0005] In order to achieve the above purpose, the utility model adopts the following technical solutions:

[0006] A small UAV V-shaped tail synchronous deployment and locking mechanism, comprising:

[0007] A cabin body, the cabin body comprising two mounting walls arranged at an angle;

[0008] The rotating assembly includes a first rotating boss and a second rotating boss, the first rotating boss and the second rotating boss are respectively resettable and rotatable on the two mounting walls, the left tail and the right tail are respectively fixedly connected to the first rotating boss and the second rotating boss, the first rotating boss and the second rotating boss both have a stowed position and an deployed position, when the left tail and the right tail are constrained in the launch tube, the first rotating boss and the second rotating boss are both located in the stowed position, when the left tail and the right tail are separated from the launch tube, the first rotating boss and the second rotating boss rotate in opposite directions to reset and rotate to the deployed position, and drive the left tail and the right tail to deploy;

[0009] The synchronous pulling assembly includes a first synchronous rope and a second synchronous rope, the two ends of the first synchronous rope are respectively fixedly connected to the first rotating boss and the second rotating boss, and along one end to the other end of the first synchronous rope, the first synchronous rope is successively wound clockwise around a part of the circumference of the first rotating boss and counterclockwise around a part of the circumference of the second rotating boss, and the two ends of the second synchronous rope are respectively fixedly connected to the first rotating boss and the second rotating boss, and along one end to the other end of the second synchronous rope, the second synchronous rope is successively wound counterclockwise around a part of the circumference of the first rotating boss and clockwise around a part of the circumference of the second rotating boss.

[0010] As a preferred solution for the synchronous deployment and locking mechanism of the V-shaped tail of a small UAV, the synchronous pulling assembly further includes:

[0011] A sleeve is provided on the cabin body and is located between the two mounting walls, and the first synchronization rope and the second synchronization rope are both passed through the sleeve.

[0012] As a preferred solution for the synchronous deployment and locking mechanism of the V-shaped tail of a small UAV, the rotating assembly further includes:

[0013] A first base boss and a second base boss are respectively provided on the two mounting walls, the first rotating boss is rotatably connected to the first base boss, and the second rotating boss is rotatably connected to the second base boss;

[0014] Two torsion springs, one end of one torsion spring is connected to the first rotating base, and the other end is connected to the first base boss, and one end of the other torsion spring is connected to the second rotating base, and the other end is connected to the second base boss. When the first rotating boss and the second rotating boss are in the retracted position, the two torsion springs are in a force storage state. When the left tail wing and the right tail wing are separated from the envelope device, under the elastic force of the two torsion springs, the first rotating boss and the second rotating boss respectively rotate to the deployed position, and the rotation directions of the first rotating boss and the second rotating boss are opposite, driving the left tail wing and the right tail wing to deploy.

[0015] As a preferred solution of a synchronous deployment locking mechanism for a small UAV V-shaped tail, a first upper arc-shaped limit plate is convexly provided on a side of the first rotating boss facing the first base boss, and a first lower arc-shaped limit plate is convexly provided on a side of the first base boss facing the first rotating boss surface, the first upper arc-shaped limit plate and the first lower arc-shaped limit plate form a non-closed ring, when the first rotating boss is in the retracted position, one side of the first upper arc-shaped limit plate abuts against one side of the first lower arc-shaped limit plate, and when the first rotating boss is in the deployed position, the other side of the first upper arc-shaped limit plate abuts against the other side of the first lower arc-shaped limit plate;

[0016] The second rotating boss is provided with a second upper arc-shaped limit plate on a side facing the second base boss, and the second base boss is provided with a second lower arc-shaped limit plate on a side facing the second rotating boss. The second upper arc-shaped limit plate and the second lower arc-shaped limit plate form a non-closed ring. When the second rotating boss is in the retracted position, one side of the second upper arc-shaped limit plate abuts against one side of the second lower arc-shaped limit plate. When the second rotating boss is in the deployed position, the other side of the second upper arc-shaped limit plate abuts against the other side of the second lower arc-shaped limit plate.

[0017] As a preferred solution for the synchronous deployment and locking mechanism of the V-shaped tail of a small UAV, a limit assembly is also included. The limit assembly includes:

[0018] A first limiting pin and a second limiting pin are respectively arranged on the outer periphery of the first rotating boss and the outer periphery of the second rotating boss;

[0019] The first limit member and the second limit member are respectively arranged on the cabin body, the first limit member and the first rotating boss are arranged relative to each other, and the second limit member and the second rotating boss are arranged relative to each other. When the first rotating boss rotates from the stowed position to the deployed position, the first limit pin is limitedly connected to the first limit member, and the first limit member is used to limit the rotation of the first limit pin to limit the rotation of the first rotating boss. When the second rotating boss rotates from the stowed position to the deployed position, the second limit pin is limitedly connected to the second limit member, and the second limit member is used to limit the rotation of the second limit pin to limit the rotation of the second rotating boss.

[0020] As a preferred solution of the synchronous deployment locking mechanism of the V-shaped tail of a small unmanned aerial vehicle, the first limiting member is a first stopper elastically resetably arranged on the cabin and spaced apart from the first rotating boss, the first stopper has a first guide surface and a first locking surface arranged opposite to each other, the first guide surface is a first convex arc surface, when the first rotating boss rotates from the stowed position to the deployed position, the first limiting pin contacts and presses the first convex arc surface, the first stopper is forced to move in a direction away from the first rotating boss, after the first limiting pin slides over the first convex arc surface, the first stopper is elastically reset in a direction close to the first rotating boss, and the first limiting pin abuts the first locking surface;

[0021] The second limit member is a second stop block that is elastically reset and is arranged on the cabin body and is spaced relative to the second rotating boss. The second stop block has a second guide surface and a second locking surface that are relatively arranged. The second guide surface is a second convex arc surface. When the second rotating boss rotates from the retracted position to the deployed position, the second limit pin contacts and presses against the second convex arc surface. The second stop block is forced to move in the direction away from the second rotating boss. After the second limit pin slides over the second convex arc surface, the second stop block is elastically reset in the direction close to the second rotating boss, and the second limit pin abuts against the second locking surface.

[0022] As a preferred solution for the synchronous deployment locking mechanism of the V-shaped tail of a small unmanned aerial vehicle, the first limiting member is a first limiting block elastically resetably provided on the cabin and spaced apart from the first rotating boss; a first limiting groove is provided on a side of the first limiting block facing the first rotating boss; when the first rotating boss rotates from the stowed position to the deployed position, the first limiting pin contacts and presses the first limiting block, and the first limiting block is forced to move in a direction away from the first rotating boss;

[0023] The second limiting member is a second limiting block that is elastically reset and is arranged on the cabin body and is spaced relative to the second rotating boss. A second limiting groove is provided on the side of the second limiting block facing the second rotating boss. When the second rotating boss rotates from the retracted position to the deployed position, the second limiting pin contacts and presses the second limiting block, and the second limiting block is forced to move in a direction away from the second rotating boss.

[0024] As a preferred solution for the synchronous deployment locking mechanism of the V-shaped tail of a small unmanned aerial vehicle, a first mounting through-hole is provided on the first rotating boss along the radial direction of the first rotating boss, the connecting pin shaft of the left tail wing is inserted into the first rotating boss along the axial direction of the first rotating boss, a first fixing hole is provided on the connecting pin shaft of the left tail wing, the first fixing hole is communicated with the first mounting through-hole, the first limiting pin is inserted into the first mounting through-hole and the first fixing hole, and one end of the first limiting pin protrudes from one end of the first mounting through-hole;

[0025] A second mounting through hole is provided on the second rotating boss along the radial direction of the second rotating boss, the connecting pin shaft of the right tail wing is inserted into the second rotating boss along the axial direction of the second rotating boss, a second fixing hole is provided on the connecting pin shaft of the right tail wing, the second fixing hole is communicated with the second mounting through hole, the second limiting pin is inserted into the second mounting through hole and the second fixing hole, and one end of the second limiting pin protrudes from one end of the second mounting through hole.

[0026] As a preferred solution for the synchronous deployment and locking mechanism of the V-shaped tail of a small unmanned aerial vehicle, one end of the first synchronization rope is fixed to the first limit pin, and the other end is fixed to the second limit pin; one end of the second synchronization rope is fixed to the first limit pin, and the other end is fixed to the second limit pin.

[0027] As a preferred solution for the synchronous deployment and locking mechanism of the V-shaped tail of a small unmanned aerial vehicle, the outer ring of the first rotating boss is provided with a first anti-slip groove, and part of the first synchronization rope and part of the second synchronization rope are both wound and located in the first anti-slip groove; the outer ring of the second rotating boss is provided with a second anti-slip groove, and part of the first synchronization rope and part of the second synchronization rope are both wound and located in the second anti-slip groove.

[0028] The beneficial effects of the utility model are:

[0029] The utility model provides a V-shaped tail synchronous deployment locking mechanism for a small unmanned aerial vehicle (UAV). When the UAV is released from an envelope device, the left and right tail wings are released, thereby releasing the external force restraining the first and second rotating bosses. The first and second rotating bosses return to rotation, driving the left and right tail wings to deploy, thus achieving automatic deployment of the left and right tail wings. Simultaneously, when the first rotating boss rotates faster than the second rotating boss, the first synchronization rope applies a pulling force to the second rotating boss, causing the second rotating boss to remain synchronized with the first rotating boss. Similarly, when the second rotating boss rotates faster than the first rotating boss, the second synchronization rope applies a pulling force to the first rotating boss, causing the first rotating boss to remain synchronized with the second rotating boss. That is, during the return rotation process of the first and second rotating bosses, due to the pulling action of the first and second synchronization ropes, the first and second rotating bosses rotate in unison, i.e., the synchronization is improved, ensuring the synchronous deployment of the left and right tail wings, thereby making the UAV control more stable and improving the flight reliability of the UAV. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the following is a brief introduction to the drawings required for use in the description of the embodiments of the present invention. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the contents of the embodiments of the present invention and these drawings without paying any creative work.

[0031] Figure 1 This is a schematic diagram of the structure of the synchronous deployment and locking mechanism of the V-shaped tail of a small UAV provided by an embodiment of the utility model;

[0032] Figure 2 It is a side view of the first rotating boss provided in an embodiment of the present utility model;

[0033] Figure 3 This is a schematic structural diagram of the first rotating boss provided in an embodiment of the present utility model;

[0034] Figure 4 This is a schematic structural diagram of the first base boss provided in an embodiment of the present utility model;

[0035] Figure 5 It is a side view of the second rotating boss provided in an embodiment of the present utility model;

[0036] Figure 6 It is a structural schematic diagram of the second rotating boss provided in an embodiment of the utility model;

[0037] Figure 7 It is a structural schematic diagram of the second base boss provided in an embodiment of the utility model;

[0038] Figure 8 This is a schematic structural diagram of a first limiting pin provided in an embodiment of the present utility model;

[0039] Figure 9 This is a schematic structural diagram of a second limiting pin provided in an embodiment of the present utility model;

[0040] Figure 10 This is a schematic structural diagram of a first stopper provided in an embodiment of the present utility model;

[0041] Figure 11 This is a schematic structural diagram of a second stopper provided in an embodiment of the present utility model;

[0042] Figure 12 It is a partial structural diagram of the synchronous deployment and locking mechanism of the V-shaped tail of a small UAV provided by an embodiment of the utility model.

[0043] In the picture:

[0044] 100, left tail wing; 200, right tail wing;

[0045] 1. Cabin; 11. Mounting wall;

[0046] 2. Rotating assembly; 21. First rotating boss; 210. First anti-slip groove; 211. First upper arc-shaped limit plate; 22. Second rotating boss; 220. Second anti-slip groove; 221. Second upper arc-shaped limit plate; 23. First base boss; 231. First lower arc-shaped limit plate; 24. Second base boss; 241. Second lower arc-shaped limit plate;

[0047] 3. Synchronous pulling assembly; 31. First synchronization rope; 32. Second synchronization rope; 33. Sleeve;

[0048] 4. Limiting assembly; 41. First limiting pin; 411. First limiting head; 42. Second limiting pin; 421. Second limiting head; 43. First stopper; 431. First convex arc surface; 432. First locking surface; 44. Second stopper; 441. Second convex arc surface; 442. Second locking surface; 45. First base; 46. Second base. DETAILED DESCRIPTION

[0049] The present invention will be further described in detail below with reference to the accompanying drawings and examples. It should be understood that the specific embodiments described herein are intended only to illustrate the present invention and are not intended to limit the present invention. It should also be noted that, for ease of description, the accompanying drawings only illustrate portions relevant to the present invention, not all of its components.

[0050] In the description of this utility model, unless otherwise specified or limited, the terms "connected," "connect," and "fixed" should be understood in a broad sense. For example, they can refer to fixed connection, detachable connection, or integration; mechanical connection or electrical connection; direct connection or indirect connection through an intermediate medium; internal communication between two components or interaction between two components. Those skilled in the art will understand the specific meanings of the above terms in this utility model based on the specific circumstances.

[0051] In the present invention, unless otherwise expressly specified or limited, a first feature being "above" or "below" a second feature may include the first and second features being in direct contact, or may include the first and second features being in contact not directly but through another feature between them. Moreover, a first feature being "above," "above," and "above" a second feature may include the first feature being directly above or obliquely above the second feature, or may simply mean that the first feature is higher in level than the second feature. A first feature being "below," "below," and "below" a second feature may include the first feature being directly below or obliquely below the second feature, or may simply mean that the first feature is lower in level than the second feature.

[0052] In the description of this embodiment, terms such as "upper," "lower," "left," and "right" are based on the orientations or positional relationships shown in the accompanying drawings and are intended solely for ease of description and simplified operation. They are not intended to indicate or imply that the devices or components referred to must have, be constructed, or operate in a specific orientation. Therefore, they should not be construed as limitations on the present invention. In the description of this utility model, unless otherwise specified, "plurality" means two or more. Furthermore, the terms "first" and "second" are used solely for descriptive purposes and do not have any special meaning.

[0053] like Figures 1 to 12As shown, this embodiment provides a small UAV V-shaped tail synchronous deployment locking mechanism, the small UAV V-shaped tail synchronous deployment locking mechanism includes a cabin 1, the cabin 1 is located at the tail of the UAV, the cabin 1 has a storage space, the cabin 1 includes two mounting walls 11 arranged at an angle, the angle between the two mounting walls 11 is consistent with the angle between the left tail 100 and the right tail 200 of the UAV, the left tail 100 and the right tail 200 of the UAV are respectively rotated and arranged outside the two mounting walls 11, the left tail 100 and the right tail 200 are respectively rotated and arranged outside the two mounting walls 11, When the tail 200 is in the stowed state, that is, when the left tail 100 and the right tail 200 are constrained within the enveloping device, the left tail 100 and the right tail 200 are respectively located below the two mounting walls 11. When the left tail 100 and the right tail 200 are released from the enveloping device, the left tail 100 rotates relative to one mounting wall 11, and the right tail 200 rotates relative to the other mounting wall 11, and the left tail 100 and the right tail 200 rotate in opposite directions, indicating that the left tail 100 and the right tail 200 of the drone are fully deployed. The enveloping device is, for example, a launch tube.

[0054] Specifically, if Figures 1 to 7 As shown, a rotating assembly 2 is provided in the cabin 1, and the rotating assembly 2 includes a first rotating boss 21 and a second rotating boss 22. The first rotating boss 21 and the second rotating boss 22 are respectively resettable and rotatable and are set on two mounting walls 11. The left tail 100 and the right tail 200 are respectively fixedly connected to the first rotating boss 21 and the second rotating boss 22. The first rotating boss 21 and the second rotating boss 22 both have a stowed position and a deployed position. When the left tail 100 and the right tail 200 are constrained in the envelope device, the first rotating boss 21 and the second rotating boss 22 are both in the stowed position. When the left tail 100 and the right tail 200 are separated from the envelope device, the first rotating boss 21 and the second rotating boss 22 rotate in opposite directions to reset and rotate to the deployed position, and drive the left tail 100 and the right tail 200 to deploy. When the drone leaves the envelope device, the left tail 100 and the right tail 200 are released, thereby releasing the external force on the first rotating boss 21 and the second rotating boss 22. The first rotating boss 21 and the second rotating boss 22 return to their original position and rotate, driving the left tail 100 and the right tail 200 to unfold, thereby realizing the automatic unfolding of the left tail 100 and the right tail 200.

[0055] More specifically, the rotating assembly 2 also includes a first base boss 23 and a second base boss 24, which are respectively arranged on two mounting walls 11, and the first rotating boss 21 is rotatably connected to the first base boss 23, for example, by a rotating shaft, and the second rotating boss 22 is rotatably connected to the second base boss 24, for example, by a rotating shaft. The roots of both the left and right tail wings 100 and 200 have vertically arranged connecting pins. The connecting pin of the left tail wing 100 passes through a mounting wall 11, a first base boss 23, and a first rotating boss 21. The connecting pin of the left tail wing 100 can rotate relative to the mounting wall 11 and the first base boss 23, while being fixed relative to the first rotating boss 21. The connecting pin of the right tail wing 200 passes through a mounting wall 11, a second base boss 24, and a second rotating boss 22. The connecting pin of the right tail wing 200 can rotate relative to the mounting wall 11 and the second base boss 24, while being fixed relative to the second rotating boss 22. The rotation of the first and second rotating bosses 21 and 22 drives the rotation of the left and right tail wings 100 and 200.

[0056] Preferably, the first base boss 23 and the second base boss 24 are symmetrically arranged on the two mounting walls 11 to further ensure the synchronization of the deployment and improve the uniformity of the force.

[0057] In this embodiment, the rotating assembly 2 also includes two torsion springs, one end of one torsion spring is connected to the first rotating base, and the other end is connected to the first base boss 23, and one end of the other torsion spring is connected to the second rotating base, and the other end is connected to the second base boss 24. When the first rotating boss 21 and the second rotating boss 22 are in the retracted position, the two torsion springs are in a force storage state. When the left tail 100 and the right tail 200 are separated from the envelope device, under the elastic force of the two torsion springs, the first rotating boss 21 and the second rotating boss 22 respectively rotate to the deployed position, and the rotation directions of the first rotating boss 21 and the second rotating boss 22 are opposite, driving the left tail 100 and the right tail 200 to deploy. The two torsion springs provide mechanical force storage, which is used as power to drive the first rotating boss 21 and the second rotating boss 22 to rotate, thereby driving the left tail 100 and the right tail 200 to automatically unfold. No additional driving mechanism is required, which saves power, simplifies the mechanical structure and electrical system, and at the same time reduces the probability of mechanical failure, ensures the deployment reliability of the left tail 100 and the right tail 200, and reduces costs.

[0058] Preferably, a first upper arc-shaped limit plate 211 is convexly provided on one side of the first rotating boss 21 facing the first base boss 23, and a first lower arc-shaped limit plate 231 is convexly provided on one side of the first base boss 23 facing the first rotating boss 21. The first upper arc-shaped limit plate 211 and the first lower arc-shaped limit plate 231 form a non-closed ring. When the first rotating boss 21 is in the retracted position, one side of the first upper arc-shaped limit plate 211 abuts against one side of the first lower arc-shaped limit plate 231. When the first rotating boss 21 is in the deployed position, the other side of the first upper arc-shaped limit plate 211 abuts against the other side of the first lower arc-shaped limit plate 231. Connect; a second upper arc-shaped limit plate 221 is convexly provided on the side of the second rotating boss 22 facing the second base boss 24, and a second lower arc-shaped limit plate 241 is convexly provided on the side of the second base boss 24 facing the second rotating boss 22. The second upper arc-shaped limit plate 221 and the second lower arc-shaped limit plate 241 form a non-closed ring. When the second rotating boss 22 is in the retracted position, one side of the second upper arc-shaped limit plate 221 abuts against one side of the second lower arc-shaped limit plate 241. When the second rotating boss 22 is in the expanded position, the other side of the second upper arc-shaped limit plate 221 abuts against the other side of the second lower arc-shaped limit plate 241. The setting of the first upper arc limit plate 211 and the first lower arc limit plate 231 and the setting of the second upper arc limit plate 241 ensure that the first rotating boss 21 has a rotation range when it rotates relative to the first base boss 23 and the second rotating boss 22 has a rotation range when it rotates relative to the second base boss 24, that is, the rotatable angle of the first rotating boss 21 and the second rotating boss 22 is less than 360°, and the rotatable angle is specifically set according to the deployment angle of the left tail wing 100 and the right tail wing 200. Through the limiting abutment of the first upper arc-shaped limiting plate 211 and the first lower arc-shaped limiting plate 231 and the limiting abutment of the second upper arc-shaped limiting plate 221 and the second lower arc-shaped limiting plate 241, the first rotating boss 21 and the second rotating boss 22 are relatively stable in the retracted position, avoiding the left tail 100 and the right tail wing 200 from having the space to move closer to each other, thereby ensuring the stability of the left tail wing 100 and the right tail wing 200 in the envelope device; and the first rotating boss 21 and the second rotating boss 22 are also relatively stable in the deployed position, avoiding the left tail wing 100 and the right tail wing 200 from having the space to continue to move away from each other, thereby ensuring the stability of the left tail wing 100 and the right tail wing 200 after deployment.

[0059] Furthermore, if Figure 1 and Figure 12As shown, the small UAV V-shaped tail synchronous deployment locking mechanism also includes a synchronous pulling component 3, which includes a first synchronization rope 31 and a second synchronization rope 32. The two ends of the first synchronization rope 31 are respectively fixedly connected to the first rotating boss 21 and the second rotating boss 22. Along one end to the other end of the first synchronization rope 31, the first synchronization rope 31 is successively wound clockwise on a part of the circumference of the first rotating boss 21 and counterclockwise on a part of the circumference of the second rotating boss 22. The two ends of the second synchronization rope 32 are respectively fixedly connected to the first rotating boss 21 and the second rotating boss 22. Along one end to the other end of the second synchronization rope 32, the second synchronization rope 32 is successively wound counterclockwise on a part of the circumference of the first rotating boss 21 and clockwise on a part of the circumference of the second rotating boss 22. When the left tail 100 and the right tail 200 are deployed, Figure 12 In the middle view, the first rotating boss 21 rotates counterclockwise, while the second rotating boss 22 rotates clockwise. When the first rotating boss 21 rotates faster than the second rotating boss 22, the first rotating boss 21 applies force to the first synchronization rope 31, as the first synchronization rope 31 is wound clockwise around the first rotating boss 21. This causes the first synchronization rope 31 to apply a pulling force to the second rotating boss 22, driving the second rotating boss 22 to keep up with the rotation speed of the first rotating boss 21 and maintain synchronization with the first rotating boss 21. Similarly, when the second rotating boss 22 rotates faster than the first rotating boss 21, the second synchronization rope 32 applies a pulling force to the first rotating boss 21, keeping the first rotating boss 21 synchronized with the second rotating boss 22. That is, during the return rotation process, the first and second rotating bosses 21, 22 rotate in unison due to the pulling action of the first and second synchronization ropes 31, 32. This results in excellent synchronization, ensuring the simultaneous deployment of the left and right tail wings 100, 200. This ensures more stable drone control and improves drone flight reliability. The first and second synchronization ropes 31, 32 are flexible, inelastic ropes.

[0060] Preferably, if Figure 3 and Figure 6 As shown, the outer circumference of the first rotating boss 21 is provided with a first anti-slip groove 210, and portions of the first and second synchronous ropes 31 and 32 are both wound and located in the first anti-slip groove 210. The outer circumference of the second rotating boss 22 is provided with a second anti-slip groove 220, and portions of the first and second synchronous ropes 31 and 32 are both wound and located in the second anti-slip groove 220. The first and second anti-slip grooves 210 and 220 effectively prevent the first and second synchronous ropes 31 and 32 from slipping and falling off along the axial direction of the first and second rotating bosses 21 and 22 during operation, thereby ensuring the reliability and stability of the first and second synchronous ropes 31 and 32.

[0061] In this embodiment, if Figure 12 As shown, the synchronous pulling assembly 3 also includes a sleeve 33, which is disposed on the cabin 1 and located between the two mounting walls 11. The first synchronization rope 31 and the second synchronization rope 32 are both threaded through the sleeve 33. The length of the sleeve 33 is preferably arranged to extend along the connecting line between the two mounting walls 11. The sleeve 33 serves as a guide and limiter for the first and second synchronization ropes 31, 32, ensuring that the first and second synchronization ropes 31, 32 are positioned as close to the same plane as possible. This improves force transmission efficiency and enhances the rotational synchronization of the first and second rotating bosses 21, 22.

[0062] Furthermore, if Figure 1 、 Figures 7 to 11 As shown, the small UAV V-shaped tail synchronous deployment locking mechanism also includes a limit assembly 4, the limit assembly 4 includes a first limit pin 41, a second limit pin 42, a first limit member and a second limit member, the first limit pin 41 and the second limit pin 42 are respectively arranged on the periphery of the first rotating boss 21 and the periphery of the second rotating boss 22; the first limit member and the second limit member are respectively arranged on the cabin body 1, and the specific cabin body 1 also includes side walls arranged oppositely on both sides, and the two mounting walls 11 are the bottom walls of the cabin body 1, the first limit member and the second limit member are respectively arranged on the two side walls, and the first limit member and the first rotating boss 21 are arranged relative to each other, and the second limit member and the second rotating boss 22 are arranged relative to each other. When the first rotating boss 21 rotates from the stowed position to the deployed position, the first limiting pin 41 is connected to the first limiting member, and the first limiting member is used to limit the rotation of the first limiting pin 41, thereby limiting the rotation of the first rotating boss 21. When the second rotating boss 22 rotates from the stowed position to the deployed position, the second limiting pin 42 is connected to the second limiting member, and the second limiting member is used to limit the rotation of the second limiting pin 42, thereby limiting the rotation of the second rotating boss 22. Due to the limiting effects of the first limiting member and the second limiting member on the first limiting pin 41 and the second limiting pin 42, respectively, the first rotating boss 21 and the second rotating boss 22 can be stabilized in the deployed position after rotating to the deployed position, avoiding rotation caused by external forces, such as preventing the left tail 100 and the right tail 200 from rotating due to wind force, thereby ensuring the stability of the left tail 100 and the right tail 200 after deployment.

[0063] Among them, a first mounting through hole is provided on the first rotating boss 21 along the radial direction of the first rotating boss 21, and the connecting pin shaft of the left tail wing 100 is inserted into the first rotating boss 21 along the axial direction of the first rotating boss 21, and a first fixing hole is provided on the connecting pin shaft of the left tail wing 100, the first fixing hole is communicated with the first mounting through hole, the first limit pin 41 is inserted into the first mounting through hole and the first fixing hole, and one end of the first limit pin 41 protrudes from one end of the first mounting through hole; a second mounting through hole is provided on the second rotating boss 22 along the radial direction of the second rotating boss 22, and the connecting pin shaft of the right tail wing 200 is inserted into the second rotating boss 22 along the axial direction of the second rotating boss 22, and a second fixing hole is provided on the connecting pin shaft of the right tail wing 200, the second fixing hole is communicated with the second mounting through hole, the second limit pin 42 is inserted into the second mounting through hole and the second fixing hole, and one end of the second limit pin 42 protrudes from one end of the second mounting through hole. The first stop pin 41 connects the left wing 100 to the first rotating boss 21, while the second stop pin 42 connects the right wing 200 to the second rotating boss 22. Together with the first and second stop members, these pins provide a stable position after deployment, resulting in a compact structure and ease of assembly and disassembly. Of course, in other embodiments, the first and second stop pins 41, 42 may also be two stop rods protruding from the outer circumferences of the first and second rotating bosses 21, 22, respectively, depending on actual needs.

[0064] Specifically, a first limiting head 411 is provided at one end of the first limiting pin 41, and a second limiting head 421 is provided at one end of the second limiting pin 42. After the first limiting pin 41 is inserted into the first mounting through-hole and the first fixing hole, the first limiting head 411 abuts against the outer peripheral wall of the first rotating boss 21, and the end of the first limiting pin 41 facing away from the first limiting head 411 protrudes from the first mounting through-hole. After the second limiting pin 42 is inserted into the second mounting through-hole and the second fixing hole, the second limiting head 421 abuts against the outer peripheral wall of the second rotating boss 22, and the end of the second limiting pin 42 facing away from the second limiting head 421 protrudes from the second mounting through-hole. The first limiting head 411 and the second limiting head 421 prevent the first limiting pin 41 and the second limiting pin 42 from disengaging from the first rotating boss 21 and the second rotating boss 22.

[0065] Preferably, if Figure 12As shown, one end of the first synchronization cord 31 is fixed to the first stop pin 41, and the other end is fixed to the second stop pin 42. The second synchronization cord 32 is also fixed to the first stop pin 41, and the other end is fixed to the second stop pin 42. Specifically, a first connection hole is provided on the portion of the first stop pin 41 that protrudes from the first rotating boss 21, and a second connection hole is provided on the portion of the second stop pin 42 that protrudes from the second rotating boss 22. One end of the first synchronization cord 31 is fixedly connected to the first connection hole, and the other end is fixedly connected to the second connection hole. The first and second stop pins 41, 42 not only provide mounting locations for the first and second synchronization cords 31, 32, but also prevent the first and second stop pins 41, 42 from disengaging from the first and second rotating bosses 21, 22, resulting in a compact and reliable structure.

[0066] In one embodiment, Figure 1 As shown, the first stopper is a first stopper 43 elastically resettable on the housing 1 and spaced apart from the first rotating boss 21. The first stopper 43 has a first guide surface and a first locking surface 432 disposed opposite each other. The first guide surface is a first convex arc surface 431. When the first rotating boss 21 rotates from the stowed position to the deployed position, the first stopper 41 contacts and presses against the first convex arc surface 431, causing the first stopper 43 to move away from the first rotating boss 21 under force. After the first stopper 41 slides over the first convex arc surface 431, the first stopper 43 elastically resets toward the first rotating boss 21, abutting against the first locking surface 432. A first base 45 is provided on a side wall of the housing 1. The first stopper 43 is elastically resettable and connected to the first base 45. For example, the first stopper 43 is elastically connected to the first base 45 via a first compression spring, the length of which is radially aligned with the first rotating boss 21. When the first rotating boss 21 rotates from the stowed position to the deployed position, the first stop pin 41 contacts and presses against the first convex curved surface 431. The first convex curved surface 431 serves as a good guide, allowing the first stop pin 41 to smoothly squeeze the first stop 43, causing the first compression spring to contract. When the first stop pin 41 slides over the first convex curved surface 431, the first compression spring automatically extends, driving the first stop 43 to move closer to the first rotating boss 21. At this time, the first stop pin 41 abuts the first locking surface 432. The first stop 43 can effectively prevent the first stop pin 41 from rotating, that is, preventing the first rotating boss 21 from rotating, thereby preventing the left tail wing 100 from rotating, ensuring stability after deployment. The first locking surface 432 is preferably a plane, and the first stop pin 41 is aligned with the plane, effectively preventing the first stop pin 41 from passing over the first stop 43.

[0067] Similarly, the second stopper is a second stopper 44 elastically resettable on the housing 1 and spaced apart from the second rotating boss 22. The second stopper 44 has a second guide surface and a second locking surface 442 disposed opposite each other. The second guide surface is a second convex arc surface 441. When the second rotating boss 22 rotates from the stowed position to the deployed position, the second stopper pin 42 contacts and presses against the second convex arc surface 441, causing the second stopper 44 to be forced away from the second rotating boss 22. After the second stopper pin 42 slides over the second convex arc surface 441, the second stopper 44 elastically resets toward the second rotating boss 22, where it abuts the second locking surface 442. A second base 46 is provided on the other sidewall of the housing 1. The second stopper 44 is elastically resettable and connected to the second base 46. For example, the second stopper 44 is elastically connected to the second base 46 via a second compression spring, the length of which is aligned with the radial direction of the second rotating boss 22. When the second rotating boss 22 rotates from the stowed position to the deployed position, the second stop pin 42 contacts and presses against the second convex curved surface 441. The second convex curved surface 441 serves as a good guide, allowing the second stop pin 42 to smoothly squeeze the second stopper 44, causing the second compression spring to contract. When the second stop pin 42 slides over the second convex curved surface 441, the second compression spring automatically extends, driving the second stopper 44 to move closer to the second rotating boss 22. At this time, the second stop pin 42 abuts the second locking surface 442. The second stopper 44 can effectively prevent the second stop pin 42 from rotating, that is, preventing the second rotating boss 22 from rotating, thereby preventing the right tail wing 200 from rotating, ensuring stability after deployment. The second locking surface 442 is preferably a plane, and the second stop pin 42 is aligned with the plane, effectively preventing the second stop pin 42 from passing over the second stopper 44.

[0068] In another embodiment, the first limiting member is a first limiting block that is elastically resettable and disposed on the cabin body 1 and spaced apart from the first rotating boss 21. A first limiting groove is disposed on a side of the first limiting block that faces the first rotating boss 21. When the first rotating boss 21 rotates from the stowed position to the deployed position, the first limiting pin 41 contacts and presses against the first limiting block. The first limiting block is forced to move in a direction away from the first rotating boss 21 until the first limiting pin 41 is inserted into the first limiting groove. The first limiting block then elastically resets in a direction toward the first rotating boss 21. A first base 45 is disposed on a side wall of the cabin body 1. The first limiting block is elastically resettable and connected to the first base 45. For example, the first limiting block is elastically connected to the first base 45 via a first compression spring, the length of which is consistent with the radial direction of the first rotating boss 21. When the first rotating boss 21 rotates from the stowed position to the deployed position, the first limiting pin 41 contacts the first limiting block to press the first limiting block, causing the first compression spring to contract under force. As the first limiting pin 41 continues to follow the rotation of the first rotating boss 21, when the first limiting pin 41 is directly opposite the first limiting groove, the pressure of the first limiting pin 41 on the first limiting block is released, and the first compression spring automatically extends, driving the first limiting block to move in a direction closer to the first rotating boss 21. At this time, the first limiting pin 41 is inserted into the first limiting groove, limiting the further rotation of the first rotating boss 21, that is, the left tail wing 100 is deployed in place and the deployed position is stable. Preferably, the top of the first limiting block is arc-shaped, so that the first limiting pin 41 can press the first limiting block back after contacting the first limiting block.

[0069] Similarly, the second limiting member is a second limiting block that is elastically resettable and disposed on the cabin body 1 and spaced apart from the second rotating boss 22. A second limiting groove is disposed on the side of the second limiting block that faces the second rotating boss 22. When the second rotating boss 22 rotates from the stowed position to the deployed position, the second limiting pin 42 contacts and presses against the second limiting block, and the second stopper 44 is forced to move in a direction away from the second rotating boss 22 until the second limiting pin 42 is inserted into the second limiting groove. The second limiting block then elastically resets toward the second rotating boss 22. A second base 46 is disposed on the other side wall of the cabin body 1. The second limiting block is elastically resettable and connected to the second base 46. For example, the second limiting block is elastically connected to the second base 46 via a second compression spring, the length of which is consistent with the radial direction of the second rotating boss 22. When the second rotating boss 22 rotates from the stowed position to the deployed position, the second limiting pin 42 contacts the second limiting block to press the second limiting block, causing the second compression spring to contract under force. As the second limiting pin 42 continues to follow the rotation of the second rotating boss 22, when the second limiting pin 42 is directly opposite the second limiting groove, the pressure of the second limiting pin 42 on the second limiting block is released, and the second compression spring automatically extends, driving the second limiting block to move in a direction closer to the second rotating boss 22. At this time, the second limiting pin 42 is inserted into the second limiting groove, limiting the further rotation of the second rotating boss 22, that is, the left tail wing 100 is fully deployed and the deployed position is stable. Preferably, the top of the second limiting block is arc-shaped, so that the second limiting pin 42 can press the second limiting block back after contacting the second limiting block.

[0070] The V-shaped tail wing synchronous deployment and locking mechanism for a small drone provided in this embodiment enables the left tail wing 100 and the right tail wing 200 to automatically deploy without external power, requiring no manual operation, and with excellent deployment synchronization. It has the advantages of a simple structure, no electrical system, good compactness, and low cost.

[0071] Note that the above are merely preferred embodiments of the present invention and the technical principles employed. Those skilled in the art will appreciate that the present invention is not limited to the specific embodiments described herein, and that various obvious changes, readjustments, and substitutions are possible for those skilled in the art without departing from the scope of protection of the present invention. Therefore, while the present invention has been described in detail through the above embodiments, the present invention is not limited to the above embodiments and may include many other equivalent embodiments without departing from the scope of the present invention. The scope of the present invention is determined by the scope of the appended claims.

Claims

1. A small UAV V-shaped tail synchronous deployment locking mechanism, characterized by: include: A cabin body, the cabin body comprising two mounting walls arranged at an angle; The rotating assembly includes a first rotating boss and a second rotating boss, the first rotating boss and the second rotating boss are respectively resettable and rotatable on the two mounting walls, the left tail wing and the right tail wing are respectively fixedly connected to the first rotating boss and the second rotating boss, the first rotating boss and the second rotating boss both have a stowed position and an deployed position, when the left tail wing and the right tail wing are constrained in the envelope device, the first rotating boss and the second rotating boss are both located in the stowed position, when the left tail wing and the right tail wing are separated from the envelope device, the first rotating boss and the second rotating boss rotate in opposite directions to reset and rotate to the deployed position, and drive the left tail wing and the right tail wing to be deployed; The synchronous pulling assembly includes a first synchronous rope and a second synchronous rope, the two ends of the first synchronous rope are respectively fixedly connected to the first rotating boss and the second rotating boss, and along one end to the other end of the first synchronous rope, the first synchronous rope is successively wound clockwise around a part of the circumference of the first rotating boss and counterclockwise around a part of the circumference of the second rotating boss, and the two ends of the second synchronous rope are respectively fixedly connected to the first rotating boss and the second rotating boss, and along one end to the other end of the second synchronous rope, the second synchronous rope is successively wound counterclockwise around a part of the circumference of the first rotating boss and clockwise around a part of the circumference of the second rotating boss.

2. The V-shaped tail synchronous deployment locking mechanism for a small UAV according to claim 1, characterized in that: The synchronous pulling assembly further includes: A sleeve is provided on the cabin body and is located between the two mounting walls, and the first synchronization rope and the second synchronization rope are both passed through the sleeve.

3. The V-shaped tail synchronous deployment locking mechanism for a small UAV according to claim 1, characterized in that: The rotating assembly further comprises: A first base boss and a second base boss are respectively provided on the two mounting walls, the first rotating boss is rotatably connected to the first base boss, and the second rotating boss is rotatably connected to the second base boss; Two torsion springs, one end of one torsion spring is connected to the first rotating boss, and the other end is connected to the first base boss, and one end of the other torsion spring is connected to the second rotating boss, and the other end is connected to the second base boss. When the first rotating boss and the second rotating boss are in the retracted position, the two torsion springs are in a force storage state. When the left tail wing and the right tail wing are separated from the envelope device, under the elastic force of the two torsion springs, the first rotating boss and the second rotating boss respectively rotate to the deployed position, and the rotation directions of the first rotating boss and the second rotating boss are opposite, driving the left tail wing and the right tail wing to deploy.

4. The small UAV V-shaped tail synchronous deployment locking mechanism according to claim 3 is characterized in that: A first upper arc-shaped limit plate is convexly provided on a side of the first rotating boss facing the first base boss, and a first lower arc-shaped limit plate is convexly provided on a side of the first base boss facing the first rotating boss surface, the first upper arc-shaped limit plate and the first lower arc-shaped limit plate form a non-closed ring, when the first rotating boss is in the retracted position, one side of the first upper arc-shaped limit plate abuts against one side of the first lower arc-shaped limit plate, and when the first rotating boss is in the deployed position, the other side of the first upper arc-shaped limit plate abuts against the other side of the first lower arc-shaped limit plate; The second rotating boss is provided with a second upper arc-shaped limit plate on a side facing the second base boss, and the second base boss is provided with a second lower arc-shaped limit plate on a side facing the second rotating boss. The second upper arc-shaped limit plate and the second lower arc-shaped limit plate form a non-closed ring. When the second rotating boss is in the retracted position, one side of the second upper arc-shaped limit plate abuts against one side of the second lower arc-shaped limit plate. When the second rotating boss is in the deployed position, the other side of the second upper arc-shaped limit plate abuts against the other side of the second lower arc-shaped limit plate.

5. The small UAV V-shaped tail synchronous deployment locking mechanism according to claim 1, characterized in that: It also includes a limiting component, which includes: A first limiting pin and a second limiting pin are respectively arranged on the outer periphery of the first rotating boss and the outer periphery of the second rotating boss; The first limit member and the second limit member are respectively arranged on the cabin body, the first limit member and the first rotating boss are arranged relative to each other, and the second limit member and the second rotating boss are arranged relative to each other. When the first rotating boss rotates from the stowed position to the deployed position, the first limit pin is limitedly connected to the first limit member, and the first limit member is used to limit the rotation of the first limit pin to limit the rotation of the first rotating boss. When the second rotating boss rotates from the stowed position to the deployed position, the second limit pin is limitedly connected to the second limit member, and the second limit member is used to limit the rotation of the second limit pin to limit the rotation of the second rotating boss.

6. The small UAV V-shaped tail synchronous deployment locking mechanism according to claim 5, characterized in that: The first stopper is elastically reset and is provided on the cabin body and is spaced apart from the first rotating boss. The first stopper has a first guide surface and a first locking surface which are relatively arranged. The first guide surface is a first convex arc surface. When the first rotating boss is rotated from the stowed position to the deployed position, the first limit pin contacts and presses against the first convex arc surface. The first stopper is forced to move in a direction away from the first rotating boss. After the first limit pin slides over the first convex arc surface, the first stopper is elastically reset in a direction close to the first rotating boss, and the first limit pin abuts against the first locking surface. The second limit member is a second stop block that is elastically reset and is arranged on the cabin body and is spaced relative to the second rotating boss. The second stop block has a second guide surface and a second locking surface that are relatively arranged. The second guide surface is a second convex arc surface. When the second rotating boss rotates from the retracted position to the deployed position, the second limit pin contacts and presses against the second convex arc surface. The second stop block is forced to move in the direction away from the second rotating boss. After the second limit pin slides over the second convex arc surface, the second stop block is elastically reset in the direction close to the second rotating boss, and the second limit pin abuts against the second locking surface.

7. The small UAV V-shaped tail synchronous deployment locking mechanism according to claim 5, characterized in that: The first limiting member is a first limiting block elastically resetably provided on the cabin body and spaced apart from the first rotating boss, a first limiting groove being provided on a side of the first limiting block facing the first rotating boss, and when the first rotating boss rotates from the stowed position to the deployed position, the first limiting pin contacts and presses the first limiting block, and the first limiting block is forced to move in a direction away from the first rotating boss until the first limiting pin is inserted into the first limiting groove, and the first limiting block is elastically reset toward a direction close to the first rotating boss; The second limit member is a second limit block that is elastically reset and is arranged on the cabin body and is spaced relative to the second rotating boss. A second limit groove is provided on the side of the second limit block facing the second rotating boss. When the second rotating boss rotates from the retracted position to the deployed position, the second limit pin contacts and presses the second limit block. The second limit block is forced to move in the direction away from the second rotating boss until the second limit pin is inserted into the second limit groove, and the second limit block is elastically reset in the direction close to the second rotating boss.

8. The small UAV V-shaped tail synchronous deployment locking mechanism according to claim 5, characterized in that: A first mounting through-hole is provided on the first rotating boss along a radial direction of the first rotating boss, the connecting pin shaft of the left tail wing is inserted into the first rotating boss along an axial direction of the first rotating boss, a first fixing hole is provided on the connecting pin shaft of the left tail wing, the first fixing hole is communicated with the first mounting through-hole, the first limiting pin is inserted into the first mounting through-hole and the first fixing hole, and one end of the first limiting pin protrudes from one end of the first mounting through-hole; A second mounting through hole is provided on the second rotating boss along the radial direction of the second rotating boss, the connecting pin shaft of the right tail wing is inserted into the second rotating boss along the axial direction of the second rotating boss, a second fixing hole is provided on the connecting pin shaft of the right tail wing, the second fixing hole is communicated with the second mounting through hole, the second limiting pin is inserted into the second mounting through hole and the second fixing hole, and one end of the second limiting pin protrudes from one end of the second mounting through hole.

9. The small UAV V-shaped tail synchronous deployment locking mechanism according to claim 5, characterized in that: One end of the first synchronization rope is fixed to the first limit pin, and the other end is fixed to the second limit pin; one end of the second synchronization rope is fixed to the first limit pin, and the other end is fixed to the second limit pin.

10. The small UAV V-tail synchronous deployment locking mechanism according to any one of claims 1 to 9, characterized in that: The outer ring of the first rotating boss is provided with a first anti-slip groove, and parts of the first synchronization rope and parts of the second synchronization rope are both wound and located in the first anti-slip groove. The outer ring of the second rotating boss is provided with a second anti-slip groove, and parts of the first synchronization rope and parts of the second synchronization rope are both wound and located in the second anti-slip groove.

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