Cylinder shooting unmanned aerial vehicle unfolding mechanism with connecting rods driven by springs and unmanned aerial vehicle

Abstract

The invention relates to the technical field of foldable unmanned aerial vehicles, and provides a cylinder-launched unmanned aerial vehicle unfolding mechanism with spring-driven connecting rods and an unmanned aerial vehicle. The cylinder-launched unmanned aerial vehicle unfolding mechanism comprises a base, a spring-driven assembly and two connecting rod assemblies which are the same in structure and are arranged in a spatial staggered mode; a limiting long hole is formed in the base; each connecting rod assembly comprises a first connecting rod and a special-shaped connecting rod, and one end of the first connecting rod is rotationally connected with one end of the special-shaped connecting rod. The other ends of the two first connecting rods are connected through a first connecting column, and the first connecting column is slidably arranged in a limiting long hole in the base. The second ends of the two special-shaped connecting rods are jointly hinged to the base. The third ends of the two special-shaped connecting rods are respectively connected with the two wings; the first connecting columns of the two first connecting rods are connected to the spring driving assembly so that the first connecting columns can move in the limiting long holes to complete the unfolding action of the wings. One-time unfolding of the wings is achieved, complex limiting and locking structures are omitted, and the response speed and stability of the unfolding mechanism are improved.

Description

Technical Field

[0001] The present invention relates to the technical field related to foldable UAVs, and in particular to a spring-driven connecting rod tube-launched UAV deployment mechanism and a UAV. Background Art

[0002] The statements in this section merely provide background information related to the present invention and do not necessarily constitute prior art.

[0003] The existing tube-launched UAV platform has put forward higher requirements for structural compactness, deployment reliability and cost control for the deployment mechanism. In order to achieve efficient folding and stable deployment of the wings in a limited cabin space, the deployment mechanism must be lightweight, fast response and simple in structure. The deployment mechanism not only affects the storage efficiency and movement stability of the UAV platform, but its design also determines the deployment reliability of the wing under size-constrained conditions. Therefore, how to achieve efficient, stable and synchronous deployment in a limited space is a key technical problem that needs to be solved in the design process of the deployment structure, which has significant engineering value and research significance.

[0004] At present, the common deployment mechanism mostly adopts a torsion spring with a ratchet limit structure to achieve a single deployment. The structure is complex, the mass is too large, and the structure is too thick, resulting in a large space occupation; in order to increase the torque of the deployment, a heavier and larger torsion spring has to be selected, which also leads to a larger mass of the limit mechanism. In addition, the deployment mechanism using a torsion spring with a ratchet limit structure also has the following problems: First, the deployment structure using a torsion spring with a ratchet limit structure causes creep, tooth cutting or meshing surface damage of the ratchet structure after repeated use, resulting in jamming or insufficient meshing of the deployment structure. The ratchet mechanism needs to be precisely meshed in place during the release of the torsion spring, otherwise jamming or insufficient meshing may occur, causing the deployment action to lag or fail, affecting the stability and reusability of the deployment function of the deployment mechanism. Secondly, the torsion spring itself is prone to elastic fatigue in the long-term compressed energy storage state, which affects the consistency of energy release, resulting in differences in each deployment action, reducing the reliability and reusability of the deployment mechanism. In addition, due to the mechanical complexity of the ratchet limit structure, it is highly sensitive to processing accuracy and assembly errors, further increasing the uncertainty and failure risk in practical applications. Summary of the invention

[0005] In order to solve the above problems, the present invention proposes a spring-driven connecting rod barrel-launched UAV deployment mechanism and a UAV. Through the symmetrically arranged connecting rod structure combined with spring drive, efficient, stable and synchronous deployment action can be achieved in a limited space, and one-time deployment of the wings is realized, eliminating complex limiting and locking structures. The interaction between the connecting rods improves the response speed and stability of the deployment mechanism, and reduces the deviation or blockage of the wings during the deployment process, which is beneficial to improving the flight stability of the UAV; moreover, the deployment mechanism is easy to scale in size, has low processing cost, low precision requirements and light mechanism weight, and can be widely promoted and applied.

[0006] In order to achieve the above object, the present invention adopts the following technical solution: One or more embodiments provide a spring-driven connecting rod barrel-launched UAV deployment mechanism, comprising a base, a spring-driven assembly, and two sets of connecting rod assemblies with the same structure and spatially staggered arrangement; The base is fixed on the drone body, and a limiting long hole is arranged on the base; Each connecting rod assembly includes a first connecting rod and a special-shaped connecting rod, one end of the first connecting rod is rotatably connected to one end of the special-shaped connecting rod; the other ends of the two first connecting rods are connected through a first connecting column, and the first connecting column is slidably arranged in a limiting long hole; the second ends of the two special-shaped connecting rods are jointly hinged to the first fulcrum position on the base as the rotation center of the special-shaped connecting rod; the third ends of the two special-shaped connecting rods are respectively connected to the two wings; The first connecting column is connected to the spring driving assembly so that the first connecting column moves in the limiting long hole to complete the unfolding action of the wing.

[0007] One or more embodiments provide a drone that uses the above-mentioned spring-driven connecting rod barrel-launched drone deployment mechanism to automatically deploy the wings of the drone.

[0008] Compared with the prior art, the present invention has the following beneficial effects: The deployment mechanism of this embodiment adopts a spring-driven mechanism to provide a one-time deployment capability, eliminating the complex limit and locking structure, and improving the response speed and stability of the deployment mechanism. The deployment mechanism of this embodiment adopts a four-bar mechanism composed of a connecting rod assembly and a sliding first connecting column. The component structure is simple, the structural mass accounts for a small proportion, and it is suitable for narrow spaces; the double-group connecting rod assembly arranged in a spatially staggered manner can also effectively improve the symmetry and balance during the deployment process, reduce the deviation or blockage of the wing during the deployment process, and is conducive to improving the reliability and stability of the drone wing deployment mechanism.

[0009] The advantages of the present invention and additional advantages will be described in detail in the following specific embodiments. BRIEF DESCRIPTION OF THE DRAWINGS

[0010] The accompanying drawings constituting a part of the present invention are used to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their description are used to explain the present invention but do not constitute a limitation of the present invention.

[0011] Figure 1 is a partial enlarged view of the deployment mechanism of Example 1 of the present invention disposed on a drone; Figure 2 is a schematic structural diagram of a base according to Embodiment 1 of the present invention; Figure 3 is a schematic structural diagram of the deployment mechanism of Embodiment 1 of the present invention when the wing is deployed; Figure 4 is a schematic structural diagram of the deployment mechanism of Example 1 of the present invention in a state of being at a large elevation angle during the launch of a UAV; Figure 5 is a schematic structural diagram of the deployment mechanism of Embodiment 1 of the present invention in a wing folded state; Figure 6 is a schematic structural diagram of the drone of Embodiment 1 of the present invention in a wing-folded state; Among them, 1. fuselage, 2. right wing, 3. left wing, 4. base, 5. spring, 6. straight connecting rod, 7. first connecting rod, 8. special-shaped connecting rod, 9. bolt, 10. stud, 11. rotation center, 12. limiting long hole, 13. positioning hole, 14. first connecting column, 15. second connecting column. DETAILED DESCRIPTION

[0012] The present invention will be further described below in conjunction with the accompanying drawings and embodiments.

[0013] It should be noted that the following detailed descriptions are exemplary and are intended to provide further explanation of the present invention. Unless otherwise specified, all technical and scientific terms used herein have the same meanings as those commonly understood by those skilled in the art to which the present invention belongs.

[0014] It should be noted that the terms used herein are only for describing specific embodiments and are not intended to limit exemplary embodiments according to the present invention. As used herein, unless the context clearly indicates otherwise, the singular form is also intended to include the plural form. In addition, it should be understood that when the terms "comprising" and / or "including" are used in this specification, it indicates the presence of features, steps, operations, devices, components and / or combinations thereof. It should be noted that, in the absence of conflict, the various embodiments of the present invention and the features in the embodiments can be combined with each other. The embodiments will be described in detail below in conjunction with the accompanying drawings.

[0015] Example 1 In the technical solutions disclosed in one or more embodiments, Figures 1 to 6As shown, a spring-driven connecting rod deployment mechanism for a barrel-launched UAV is installed on a barrel-launched UAV body 1 and connects a left wing 3 and a right wing 2; the deployment mechanism includes a base 4, a spring-driven assembly, and two sets of connecting rod assemblies with the same structure and spatially staggered arrangement; The base 4 is fixed on the UAV body 1, and a limiting long hole 12 is provided on the base 4; Each group of connecting rod assemblies includes a first connecting rod 7 and a special-shaped connecting rod 8, one end of the first connecting rod 7 in the same group is rotatably connected to one end of the special-shaped connecting rod 8; the other ends of the two first connecting rods 7 are connected by a first connecting column 14, and the first connecting column 14 is slidably set in the limiting long hole 12; the second ends of the two special-shaped connecting rods 8 are jointly hinged to the first fulcrum position on the base 4 as the rotation center 11 of the special-shaped connecting rod 8, and the third ends of the two special-shaped connecting rods 8 are respectively connected to the two wings, so that the two wings can be unfolded or folded; The first connecting column 14 is connected to the spring driving assembly so that the first connecting column 14 moves in the limiting slot 12 to complete the unfolding action of the wing.

[0016] The deployment mechanism of this embodiment uses a spring drive assembly as a power source to drive the first connecting column 14 to slide in the limiting long hole 12, thereby driving the two first connecting rods 7 to move synchronously. One end of the first connecting rod 7 is connected to the special-shaped connecting rod 8 through a hinge. During the sliding process of the first connecting column 14, power is transmitted to the special-shaped connecting rod 8, causing the special-shaped connecting rod 8 to rotate around the first fulcrum. The rotation of the special-shaped connecting rod 8 directly drives the wings to unfold, and the two wings achieve synchronous and balanced deployment actions. The two sets of connecting rod assemblies are arranged in a spatially staggered manner to avoid interference between the wings or the connecting rod mechanism and improve the compactness of the structure.

[0017] Compared with the traditional torsion spring and ratchet solution, the deployment mechanism of this embodiment adopts a four-bar linkage composed of a connecting rod assembly and a sliding first connecting column 14. The component structure is simple, the structural mass accounts for a small proportion, it is suitable for narrow spaces, and it is easy to standardize production and modular installation, which significantly reduces the difficulty of processing and assembly complexity. At the same time, the spring drive mechanism provides a one-time deployment capability, eliminating complex limit and locking structures, and improving the response speed and stability of the deployment mechanism. The double-group connecting rod assembly arranged in a spatially staggered manner can also effectively improve the symmetry and balance during the deployment process, reduce the offset or blockage of the wing during the deployment process, and is conducive to improving the reliability and stability of the drone wing deployment mechanism.

[0018] In a possible implementation, the base 4 may adopt a structure capable of realizing linkage of the connecting rod assembly, and a polygonal plate may be used to set the limiting long hole 12 at the corresponding position, or a straight-line structure may be used; Preferably, Figure 2As shown, the base 4 is a Y-shaped base; a limiting long hole 12 is provided on the symmetry axis of the Y-shaped base 4; and a positioning hole 13 is provided at the end of the base 4; In some embodiments, the spatial staggered arrangement of the two groups of connecting rod assemblies may be an up-down staggered arrangement, and the two wings connected by the connecting rod assemblies are in a folded state, with the left wing 3 and the right wing 2 stacked up and down; The staggered arrangement of the embodiment sets the installation positions of the two connecting rod assemblies in the vertical direction in the base 4 so that each set of connecting rod assemblies is located at different height planes, thereby avoiding interference caused by overlapping connecting rods when the unfolding mechanism is in the folded state. The stacked arrangement helps to improve the symmetry and balance during the unfolding process, reduce the asymmetric interference caused by gravity or connecting rod coupling during the wing unfolding process, and improve the stability and response consistency of the mechanism operation.

[0019] A feasible technical solution, the base 4 comprises an upper bracket and a lower bracket of the same structure, the upper bracket and the lower bracket are stacked and arranged up and down and spaced apart by a first spacing H, and the stacked upper bracket and the lower bracket are fixed on the body 1 of the UAV; the connecting rod assembly is arranged between the upper bracket and the lower bracket and spaced apart by a second height difference h; the second height difference h is not less than the thickness of the wing; In this embodiment, the stacked upper bracket and the lower bracket are fixed to the body 1 of the drone, and threaded connection can be adopted, and the upper bracket and the lower bracket are connected and fixed to the body 1 by bolts 9.

[0020] The above embodiment adopts a modular bracket structure, and an installation platform for the deployment mechanism is formed by stacking an upper bracket and a lower bracket inside the drone body 1. A space area for installing the connecting rod assembly is formed between the two layers of brackets, and the height difference of the connecting rod assembly is set to the second height difference h, ensuring that the area is sufficient to accommodate the connecting rod mechanism and the wing assembly connected thereto. The first spacing H between the upper bracket and the lower bracket is adjusted according to the structural space of the drone body 1, so as to provide sufficient space for the mechanism layout without affecting the folding and storage of the wings, so as to achieve vertical isolation and structural support for the connecting rod assembly.

[0021] Optionally, two groups of connecting rod assemblies, one group of connecting rod assemblies is attached to the lower surface of the upper bracket in the base 4, and the other group of connecting rod assemblies is attached to the upper surface of the lower bracket in the base 4; In the above embodiment, two connecting rod assemblies are respectively arranged on the inner surface areas of the upper and lower brackets, one connecting rod assembly is installed on the lower surface of the upper bracket, and the other connecting rod assembly is installed on the upper surface of the lower bracket, forming a symmetrically distributed layout structure. This arrangement improves space utilization, makes the structure more compact, and helps to reduce the overall volume of the deployment mechanism. The connecting rod assembly is installed close to the inner surface of the bracket, which not only improves the structural stability, but also facilitates assembly and subsequent maintenance. Symmetrical installation further improves the balance of the deployment action and reduces structural distortion or motion interference caused by eccentric loading or assembly errors.

[0022] A specific implementation scheme, the upper bracket and the lower bracket are provided with a relative position to set a limit long hole 12, the two limit long holes 12 are penetrated by a slidable first connecting column 14, one end of the two first connecting rods 7 is hinged on the first connecting column 14, and the elastic force output end of the spring drive component is fixedly connected to the first connecting column 14; In some embodiments, the spring drive assembly may include one or more springs 5, one end of the spring 5 is connected to the first connecting column 14, and the other end is fixed to a positioning position on the body 1; like Figure 1 As shown, corresponding to the Y-shaped base 4, three fixing columns can be set at the three ends of the Y-shape to stably fix the base 4 on the body 1; the fixing columns can all be bolts 9; Preferably, the upper bracket and the lower bracket are Figure 2 The spring drive assembly of the Y-shaped bracket shown in the figure includes two springs 5, which are transversely arranged between the upper bracket and the lower bracket; one end of the spring 5 is fixedly connected to the fixing column at the end of the Y-shaped bracket, and the other end is connected to the first connecting column 14 for hingedly connecting the two first connecting rods 7; Specifically, circular rings are provided at both ends of the spring 5, which are connected to the fixed columns at the ends of the Y-shaped bracket. The fixed columns can be bolts 9, and two bolts 9 can be passed through to form a rotating pair. After the spring 5 is stretched, it is sleeved on the bolts 9 and the first connecting column 14. The spring 5 is always in a stretched state to provide tension.

[0023] In this embodiment, the upper bracket and the lower bracket are respectively designed as a Y-shaped structure, and the two springs 5 ​​are arranged in a transverse direction, that is, parallel to the horizontal axis direction of the drone, with one end fixedly connected to the fixing column arranged at the end of the Y-shaped bracket, and the other end connected to the first connecting column 14 between the two first connecting rods 7. When the spring 5 is pre-stressed, energy is stored in its elastic deformation; at the moment of launch, the spring 5 releases the stored energy, driving the first connecting column 14 to slide along the limiting long hole 12, thereby driving the connecting rod mechanism to move, and realizing the automatic and synchronous deployment of the wings.

[0024] A further technical solution is that a slidable second connecting column 15 is arranged through the limiting long hole 12, the first connecting column 14 and the second connecting column 15 are connected by a straight connecting rod 6, the spring 5 of the spring drive assembly is connected to the first connecting column 14 through the second connecting column 15 and the straight connecting rod 6, and the maximum deployment angle of the wing is adjusted by adjusting the length of the straight connecting rod 6; the straight connecting rod 6 passes through the first connecting column 14 and the second connecting column 15 to form a revolute pair.

[0025] In this embodiment, a slidable second connecting column 15 is provided in the limiting long hole 12 of the base 4, which can move smoothly in the direction of the limiting long hole 12 under the drive of the release of the spring 5. The first connecting column 14 is connected to the second connecting column 15 through the straight connecting rod 6, forming an indirect transmission path between the spring 5 and the first connecting rod 7. When the spring 5 releases the stored energy, its thrust acts on the first connecting column 14 through the second connecting column 15 and the straight connecting rod 6, driving the two first connecting rods 7 to slide in the direction of the limiting long hole 12, and at the same time driving the special-shaped connecting rod 8 to rotate, so that the wing connected to its end is synchronously unfolded. The length of the straight connecting rod 6 determines the maximum stroke of the first connecting column 14 in the limiting long hole 12, which in turn affects the rotation angle of the special-shaped connecting rod 8 and the maximum unfolding angle of the wing, thereby realizing adjustable control of the unfolding angle.

[0026] In addition, the base 4 is composed of an upper and lower bracket, and is provided with a limiting long hole 12 for constraining the motion path of the straight connecting rod 6 and the first connecting column 14. The limiting long hole 12 is arranged in a long strip shape, plays a guiding and limiting role, effectively controls the sliding trajectory of the straight connecting rod 6, so that it forms a stable linear motion path in the Y-shaped base, avoids lateral shaking or deviation, and ensures the stability and reliability of the mechanism operation.

[0027] The above structural design realizes the flexible distribution of the driving force path and the precise control of the deployment angle by setting the second connecting column 15 and the straight connecting rod 6. The length adjustment function of the straight connecting rod 6 makes the wing deployment angle highly adjustable to meet different flight requirements. The limiting long hole 12 not only provides a stable motion guide for the straight connecting rod 6, but also constrains the motion range of the first connecting column 14, further ensuring the consistency and accuracy of the structural movement. Through the design of this guiding structure, the risk of lateral interference, structural shaking or interference of the connecting rod mechanism is effectively reduced, thereby greatly improving the stability, symmetry and accuracy of the wing deployment process, and enhancing the flight reliability of the UAV and the overall adaptability of the deployment mechanism.

[0028] Furthermore, the second connecting column 15 connected to the straight connecting rod 6 moves to the edge of the hole of the limiting long hole 12 close to one end of the spring drive assembly, and the corresponding unfolding angle of the wing is 90 degrees.

[0029] This embodiment can effectively control the maximum wing deployment angle through the end position of the second connecting column 15, ensuring that the wing can stably reach a 90-degree angle after each ejection and deployment, thereby improving the consistency of each deployment action. This structure does not require an additional angle limit mechanism, and only relies on the structural arrangement to achieve precise control, simplifying the system structure and improving reliability.

[0030] Optionally, the first connecting column 14 and the second connecting column 15 may have the same structure, and may be a bare stud or a double-headed rivet; In some embodiments, the first connecting rod 7 is an L-shaped connecting rod including two ends; the special-shaped connecting rod 8 is an asymmetric T-shaped connecting rod including three ends; This embodiment optimizes the design of the connecting rod structure shape, wherein the first connecting rod 7 adopts an L-shaped structure, so that it can better adapt to the sliding path of the limiting long hole 12 during the installation process, and provide a favorable angle for the hinge with the special-shaped connecting rod 8. At the same time, the L-shaped configuration can produce a larger angle output in a smaller linear sliding stroke, thereby improving the driving efficiency. The special-shaped connecting rod 8 adopts an asymmetric T-shaped structure, one end of which is hinged to the first connecting rod 7, the second end is fixed to the base 4 as the rotation center 11, and the third end is used to connect the wing. The asymmetric T-shaped design allows nonlinear acceleration transmission during its rotation, which helps to optimize the deployment speed curve of the wing and avoid too fast initial deployment or too large impact at the end.

[0031] Optionally, the first connecting rod 7 and the special-shaped connecting rod 8 in the same connecting rod assembly are rotatably connected via a stud 10 to form a movable revolving pair; the second ends of the two special-shaped connecting rods 8 are hinged to the first fulcrum position on the base 4 via a bolt 9 to form a revolving pair, and the first fulcrum position is the rotation center 11 of the special-shaped connecting rod 8.

[0032] Optionally, the first connecting rod 7, the special-shaped connecting rod 8, the straight connecting rod 6 and the base 4 can use 45 steel material to ensure high structural strength, the spring 5 can use a manganese steel spring, and the bolts 9 and the studs 10 use standard metal material mother-and-child stud parts.

[0033] In the deployment mechanism of the above scheme, the connecting rod mechanism provides the required movement mode, the spring drive assembly provides the driving force, and the base 4 is used to connect the movement mechanism and the structure of the body 1. During the launch process, from the ejection of the launch tube of the drone to the stable flight of the drone, the action process of the deployment structure is as follows: 1) The UAV is in the launch tube, and the unfolded structure is as follows: Figure 5 As shown, the wings are in folded state; Figure 6 The drone is shown in a folded state, with the wings stacked close to the drone body 1. Figure 6 The middle A area is the deployment mechanism for the wing connection; 2) The whole drone is ejected from the launch tube. The left wing 3 and the right wing 2 are no longer restrained by the launch tube. The elastic force of the spring 5 pulls the straight connecting rod 6 through the second connecting column 15, and the straight connecting rod 6 pulls the first connecting column 14 to transmit the pulling force to the two sets of connecting rod assemblies. When the drone just comes out of the tube, the body 1 is in a large elevation angle state, and the gravity is always vertically downward, that is, the component of gravity in the body coordinate system will inhibit the wing from unfolding, such as Figure 4 As shown, the two special-shaped connecting rods 8 are unfolded at a certain angle, but cannot be fully unfolded; 3) The UAV body 1 changes from a high elevation angle to a level flight angle, and the gravity is perpendicular to the spring 5, so that the elastic force of the spring 5 is transmitted from the second connecting column 15, the straight connecting rod 6, and the first connecting column 14 to the first connecting rod 7. The first connecting rod 7 pulls the second end of the special-shaped connecting rod 8 through the stud 10, and the special-shaped connecting rod 8 rotates around the rotation center 11 as the axis, as shown in FIG. Figure 3 As shown, the unfolding device is set on the fuselage 1 without connecting the wing, and the special-shaped connecting rod 8 is transformed into a flattened state, driving the wing to quickly transform from a retracted state to an unfolded state.

[0034] 4) During the level flight phase of the UAV, the external forces acting on the wing are mainly lift, drag, aerodynamic torque and gravity; the driving force provided by the spring 5 passes through the second connecting column 15, the straight connecting rod 6, the first connecting column 14, the first connecting rod 7, the special-shaped connecting rod 8 and the wing in sequence, and finally offsets a small part of the aerodynamic force and most of the aerodynamic torque; all the gravity acting on the body 1 is almost offset by the lift provided by the wing; the base 4 is used to bear lift and gravity, and the force is complex; the base 4 also has a limiting function, which will offset part of the driving force to ensure the dynamic stability of the wing structure.

[0035] Example 2 Based on Example 1, a drone is provided in this embodiment, which adopts the barrel-launched drone deployment mechanism of a spring-driven connecting rod described in Example 1, and the deployment mechanism is connected to the wings of the drone for automatically deploying the wings of the drone.

[0036] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A spring-driven connecting rod tube-launched UAV deployment mechanism, characterized in that: It includes a base, a spring drive assembly, and two sets of connecting rod assemblies with the same structure and spatially staggered arrangement; The base is fixed on the drone body, and a limiting long hole is arranged on the base; Each connecting rod assembly includes a first connecting rod and a special-shaped connecting rod, one end of the first connecting rod is rotatably connected to one end of the special-shaped connecting rod; the other ends of the two first connecting rods are connected through a first connecting column, and the first connecting column is slidably arranged in a limiting long hole; the second ends of the two special-shaped connecting rods are jointly hinged to the first fulcrum position on the base as the rotation center of the special-shaped connecting rod; the third ends of the two special-shaped connecting rods are respectively connected to the two wings; The first connecting column is connected to the spring driving assembly so that the first connecting column moves in the limiting long hole to complete the unfolding action of the wing.

2. The spring-driven connecting rod barrel-launched UAV deployment mechanism according to claim 1, characterized in that: The two sets of connecting rod assemblies are spatially staggered, and an upper and lower staggered arrangement is adopted. When the two wings connected by the connecting rod assemblies are in a folded state, the left wing and the right wing are stacked up and down.

3. The spring-driven connecting rod barrel-launched UAV deployment mechanism according to claim 1, characterized in that: The base includes an upper bracket and a lower bracket with the same structure. The upper bracket and the lower bracket are stacked up and down and spaced apart by a first spacing H. The stacked upper bracket and the lower bracket are fixed on the body of the drone. Two sets of connecting rod assemblies are arranged between the upper bracket and the lower bracket, spaced apart by a second height difference h. The second height difference h is not less than the thickness of the wing.

4. The spring-driven connecting rod barrel-launched UAV deployment mechanism according to claim 3, characterized in that: Two groups of connecting rod assemblies, one group of connecting rod assemblies fits the lower surface of the upper bracket in the base, and the other group of connecting rod assemblies fits the upper surface of the lower bracket in the base.

5. The spring-driven connecting rod barrel-launched UAV deployment mechanism according to claim 3, characterized in that: The upper bracket and the lower bracket adopt Y-shaped brackets, and the spring drive assembly includes two springs, which are transversely arranged between the upper bracket and the lower bracket; one end of the spring is fixedly connected to the fixed column at the end of the Y-shaped bracket, and the other end is connected to the first connecting column used to hinge the two first connecting rods.

6. The spring-driven connecting rod barrel-launched UAV deployment mechanism according to claim 3, characterized in that: A second slidable connecting column is arranged through the limiting long hole, the first connecting column and the second connecting column are connected by a straight connecting rod, and the spring of the spring drive assembly is connected to the first connecting column through the second connecting column and the straight connecting rod; the maximum deployment angle of the wing is adjusted by adjusting the length of the straight connecting rod.

7. The spring-driven connecting rod barrel-launched UAV deployment mechanism according to claim 6, characterized in that: The second connecting column connected by the straight connecting rod moves to the edge of the hole of the limiting long hole close to one end of the spring drive assembly, and the corresponding unfolding angle of the wing is 90 degrees.

8. The spring-driven connecting rod barrel-launched UAV deployment mechanism according to claim 1, characterized in that: The first connecting rod adopts an L-shaped connecting rod; the special-shaped connecting rod adopts an asymmetric T-shaped connecting rod.

9. The spring-driven connecting rod barrel-launched UAV deployment mechanism according to claim 1, characterized in that: The first connecting rod and the special-shaped connecting rod in the same connecting rod assembly are rotatably connected through a stud to form a movable revolute pair; the second ends of the two special-shaped connecting rods are hinged to the first fulcrum position on the base through the stud to form a revolute pair.

10. A drone, characterized in that: A barrel-launched UAV deployment mechanism using a spring-driven connecting rod as described in any one of claims 1 to 9 is used to automatically deploy the wings of a UAV.

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