Unmanned aerial vehicle ejection device

Abstract

The invention provides an unmanned aerial vehicle ejection device, and belongs to the technical field of unmanned aerial vehicle ejection. The device aims at solving the problems that in the prior art, an unmanned aerial vehicle ejection device locking mechanism is complex in structure, needs an independent unlocking power source and is slow in response. The unmanned aerial vehicle ejection device comprises a cylinder body, a piston and an initiating explosive device, and is characterized by further comprising a locking assembly fixed in the cylinder body and provided with a locking unit capable of elastically deforming in the radial direction; the locked assembly is fixedly connected with the piston and is provided with a locked structure matched with the locking unit, and in the locking state, the locking unit clamps the locked structure so as to fix the piston; and the unlocking triggering assembly can axially move independent of the piston, and one end of the unlocking triggering assembly is provided with a conical surface. The unlocking triggering assembly is configured to be driven by high-pressure gas generated by the initiating explosive device preferentially to move in the axial direction before the piston, the conical face of the unlocking triggering assembly acts on the locking unit, and therefore the locking unit expands in the radial direction, and locking on the locked assembly is relieved. According to the invention, unlocking and launching are realized through a single power source, the structure is compact, the response is quick, and the reliability is high.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of unmanned aerial vehicle launching, and particularly relates to an unmanned aerial vehicle launching device with a mechanical locking and releasing mechanism. BACKGROUND

[0002] The vertical launching of a folding-wing unmanned aerial vehicle from a cylinder is a common way of rapid deployment. In order to ensure the safety of the unmanned aerial vehicle before launching, especially during transportation and handling, the unmanned aerial vehicle in the launching cylinder needs to be effectively fixed to resist vibration and impact. In the prior art, some launching devices fix the unmanned aerial vehicle or its bearing piston by setting a locking mechanism in the launching cylinder. For example, some schemes use a separate rotary drive unit (such as a motor) to drive the rotation of a rotating sleeve, and a locking steel ball cooperating with the rotating sleeve is used to lock or unlock the piston. However, such schemes have some inherent defects: first, the structure is relatively complex, and a separate unlocking drive unit and its control system need to be set, which increases the volume, weight and failure points of the device; second, the unlocking action depends on the rotation of the motor, and the response speed is relatively slow, which may affect the instantaneousness of launching; and finally, the locking and launching actions are performed by different power sources and control systems, and the integration of the system is not high, and the reliability needs to be improved. SUMMARY

[0003] The present application aims to provide an unmanned aerial vehicle launching device with a mechanical locking and releasing mechanism, and aims to solve the technical problems of the prior art, such as the complex structure of the locking mechanism, the need for a separate unlocking power source, slow response speed, and low system integration.

[0004] To achieve the above-mentioned purpose, the present application provides an unmanned aerial vehicle launching device, comprising: a cylinder body; a piston arranged in the cylinder body; and a pyrotechnic device for generating high-pressure gas to drive the movement of the piston. The device further comprises: a locking assembly fixedly arranged in the cylinder body, the locking assembly having at least one radially elastically deformable locking unit, which is inwardly folded in a locked state; a locked assembly fixedly connected with the piston, the locked assembly having a locked structure cooperating with the locking unit, and in the locked state, the locking unit holds the locked structure to fix the piston at a predetermined position in the cylinder body; and an unlocking trigger assembly adapted to move axially independently of the piston, one end of the unlocking trigger assembly having a conical surface, the unlocking trigger assembly being configured to be driven by the high-pressure gas generated by the pyrotechnic device to move axially in front of the piston, so that the conical surface acts on the locking unit, thereby causing the locking unit to radially expand and release the locking of the locked assembly.

[0005] Optionally, the locking assembly is a flange claw; the locked component is a connecting upper rod; and the unlocking trigger assembly is a piston top rod.

[0006] Optionally, the locking unit is a claw provided on the flange claw; the locked structure is a protrusion provided on the connecting upper rod; and in the locked state, the claw and the protrusion are clamped with each other.

[0007] Optionally, the flange claw is an integral structure.

[0008] Optionally, the device further comprises a base, and the base and the unlocking trigger assembly jointly enclose a high-pressure chamber for accommodating the initiating explosive in the initial state.

[0009] Optionally, axial movement of the unlocking trigger assembly is used to connect the high-pressure chamber with a low-pressure chamber provided below the piston, so as to drive the piston to move by using the high-pressure gas.

[0010] Optionally, a movable hook for hooking the unmanned aerial vehicle is provided on the piston.

[0011] Optionally, the movable hook is configured to change the posture due to the structural relationship with the barrel body when the unmanned aerial vehicle flies out of the barrel mouth of the barrel body, so as to be separated from the unmanned aerial vehicle.

[0012] Optionally, a roller for reducing friction with the inner wall of the barrel body is provided on the movable hook.

[0013] Optionally, the device further comprises a supporting barrel provided on the piston, and the supporting barrel is used to support the unmanned aerial vehicle.

[0014] Compared with the prior art, the unmanned aerial vehicle launching device provided by the application has the following beneficial effects: high reliability and good safety, reliable axial fixation of the piston and the unmanned aerial vehicle is realized through mechanical locking of the locking assembly and the locked component, damage of the device caused by internal movement during transportation, falling, vibration and the like is effectively prevented, and the reliability and safety of the system are significantly improved; compact structure and high integration, locking, unlocking and launching functions are highly integrated, a single initiating explosive power source is used, unlocking and launching are sequentially completed according to the timing sequence through structural design, an additional unlocking power source and control system are not needed, and the overall structure is more compact and simple; fast response and reliable action, the unlocking action is directly driven by the initiating explosive, the response speed is extremely fast, the instantaneity of launching is ensured, and the mechanical timing sequence of unlocking first and then launching is inherent in the structural design, timing errors caused by control delay or failure are avoided, and the action process is reliable. BRIEF DESCRIPTION OF DRAWINGS

[0015] In order to more clearly illustrate the technical solutions of the embodiments of the present application or the prior art, the following will briefly introduce the drawings needed to be used in the embodiments or prior art description. Obviously, the drawings in the following description are only some embodiments of the present application, and for those skilled in the art, other drawings can also be obtained without creative labor based on these drawings.

[0016] Figure 1 A schematic diagram of the overall structure of a UAV catapult device provided by the embodiments of the present application is shown in the figure.

[0017] Figure 2 A schematic diagram of the cross section of the locking and releasing mechanism in the locked state provided by the embodiments of the present application is shown in the figure.

[0018] Figure 3 A schematic diagram of the three-dimensional structure of the flange claw provided by the embodiments of the present application is shown in the figure.

[0019] Figure 4 A schematic diagram of the three-dimensional structure of the piston top rod provided by the embodiments of the present application is shown in the figure.

[0020] Figure 5 A schematic diagram of the three-dimensional structure of the connecting upper rod provided by the embodiments of the present application is shown in the figure.

[0021] Figure 6 A schematic diagram of the structure of the piston and the movable hook provided by the embodiments of the present application is shown in the figure.

[0022] Legend: 1 - Launching barrel module; 10 - barrel body; 20 - piston; 21 - lug; 30 - explosive; 40 - flange claw (locking component); 41 - claw (locking unit); 50 - connecting upper rod (locked component); 51 - locked structure (protrusion); 60 - piston top rod (unlocking trigger component); 61 - conical surface; 70 - base; 80 - movable hook DETAILED DESCRIPTION

[0023] In order to make the purpose, technical solutions and advantages of the present application more clear, the following will further describe the present application in combination with the drawings and specific embodiments. It should be noted that the specific embodiments described here are only used to explain the present application, and not to limit the protection scope of the present application.

[0024] Embodiment 1

[0025] The embodiments of the present application provide a UAV catapult device with a mechanical locking and releasing mechanism. Please refer to Figure 1Figure 1 shows the overall structure of the unmanned aerial vehicle launching device in the embodiment. Overall, the device can constitute a launching cylinder module 1, which is generally cylindrical in shape, thereby facilitating storage, transportation and deployment. The inside of the launching cylinder module 1 integrates all the key components for achieving safe locking, quick unlocking and efficient launching of the unmanned aerial vehicle.

[0026] Please refer to Figure 2 Figure 2 is a cross-sectional view of the internal core structure of the unmanned aerial vehicle launching device in the embodiment, which shows the locking state of the device before launching. The device mainly includes a cylinder body 10, a piston 20 arranged in the cylinder body 10, a pyrotechnic device 30 for generating high-pressure gas, and a set of locking and releasing mechanism. Among them, the locking and releasing mechanism constitutes the core technical solution of the application embodiment, which is composed of a locking assembly, a locked assembly and an unlocking trigger assembly, to ensure the absolute safety of the unmanned aerial vehicle before launching and the instantaneous response during launching.

[0027] Specifically, the cylinder body 10 serves as the main structure of the entire device, providing a guiding and sealing environment for the movement of the unmanned aerial vehicle and the piston 20. In an embodiment of the application, the cylinder body 10 can be made of a composite material with high strength and good transparency to electromagnetic waves, such as wave-transparent glass fiber composite material, to reduce interference with the communication signals of the unmanned aerial vehicle. As a specific implementation, the main size of the cylinder body 10 can be designed as an outer diameter of 242 mm, a total length of 888 mm, and an inner diameter of 220 mm. In order to reduce the frictional resistance of the piston 20 during movement and ensure air tightness, the inner wall surface of the cylinder body 10 is precisely machined, and the surface roughness can reach Ra6.3 or better.

[0028] The piston 20 is arranged inside the cylinder body 10 and can slide along the axial direction of the cylinder body 10. The piston 20 is a key component for transmitting force, with its lower surface constituting the action surface of high-pressure gas, and its upper part being used to carry and push the unmanned aerial vehicle. The outer periphery of the piston 20 is usually provided with a sealing ring to prevent high-pressure gas from leaking from the gap between the piston 20 and the inner wall of the cylinder body 10, thereby ensuring the efficient use of launching energy.

[0029] The pyrotechnic device 30 is the only power source of the device, which can instantly generate a large amount of high-pressure gas after ignition. In the embodiment, about 3 grams of black powder or other suitable fast-burning propellant can be selected for the pyrotechnic device 30, which is prearranged in a specific chamber at the bottom of the device, waiting for the ignition instruction.

[0030] The core part of the embodiment, i.e. the locking and releasing mechanism, will be described in detail below. The mechanism includes a flange claw 40 as a locking assembly, a connecting upper rod 50 as a locked assembly, and a piston top rod 60 as an unlocking trigger assembly.

[0031] Please refer to Figure 2 andFigure 3 wherein Figure 3 is a schematic view of the three-dimensional structure of the flange claw 40. The flange claw 40 is a key executive component for realizing mechanical locking, which is fixedly installed on the internal support structure of the barrel 10, and the axial position is fixed. In the embodiment, the flange claw 40 is preferably an integrally formed structure, which can be made of a metal material with rigidity and elasticity such as high-strength spring steel or titanium alloy, by machining or precision casting, and the integrally formed structure ensures the structural strength and reliability of the action. The lower part of the flange claw 40 is an annular flange, which is used to reliably fix itself on the support structure inside the barrel 10; the upper part is designed with at least one locking unit, which is eight claws 41 uniformly distributed in the circumferential direction in the embodiment. The claws 41 are cantilever beam structures, the root is connected with the flange, and the end can be elastically deformed in the radial direction. In the natural state or the preset locking state, the ends of all the claws 41 are inwardly closed, and together form an inner hole, the diameter of which is smaller than the outer diameter of a specific part of the connecting upper rod 50.

[0032] Please refer to Figure 2 and Figure 5 wherein Figure 5 is a schematic view of the three-dimensional structure of the connecting upper rod 50. The connecting upper rod 50 constitutes a specific implementation of the locked assembly in the embodiment. It is an independent cylindrical part, and the upper end is fixedly connected with the piston 20 by a reliable way (using threaded connection and using lock nut fastening), to ensure that it and the piston 20 constitute a rigid whole in motion. The lower part of the connecting upper rod 50 is provided with a locked structure 51 matched with the claw 41. In the embodiment, the locked structure 51 is specifically an annular protrusion. The upper end face of the protrusion forms a bearing plane, and in the locked state, the inner side end of the plurality of claws 41 of the flange claw 40 is clamped above the protrusion and abuts against the bearing plane, thereby effectively preventing the connecting upper rod 50 and the piston 20 fixedly connected therewith from moving upward in the axial direction. And a screw rod is installed on the connecting upper rod 50, so as to realize the circumferential locking of the locking assembly and the locked assembly.

[0033] Please refer to Figure 2 and Figure 4 wherein Figure 4A schematic view of the three-dimensional structure of the piston top rod 60. The piston top rod 60 constitutes a specific implementation of the unlocking trigger assembly in this embodiment. The piston top rod 60 is located below the flange claw 40 and is designed to move axially independently of the piston assembly composed of the piston 20 and the connecting upper rod 50. Its key structural feature is that its upper end has a precise conical surface 61, the taper angle of which is optimized to ensure that the required axial driving force is not too large while providing sufficient radial expansion force. The lower end of the piston top rod 60 is in cooperation with the side of the flange claw 40 with holes, and the piston top rod 60 is exposed after being pushed by the propellant.

[0034] Please refer again to Figure 2 . The base 70 is fixed at the bottom of the barrel 10 to seal the launching barrel and carry all the internal components. In this embodiment, the upper surface of the base 70 is designed with a recess or chamber, in which the lower end of the piston top rod 60 is accommodated. Thus, in the initial state, the base 70 and the piston top rod 60 together enclose a sealed high-pressure chamber, in which the initiating explosive 30 is accommodated. This design allows the initial high-pressure gas generated by the initiating explosive 30 to be confined in a very small space, thereby being able to act preferentially and concentratedly on the piston top rod 60 with a smaller effective pressure area.

[0035] The working process of this embodiment clearly demonstrates how to achieve precise timing control of unlocking before launching using a single power source.

[0036] Before launching, whether during transportation, storage or service operation, the device is always in the locked state as shown in Figure 2 . At this time, the multiple claws 41 of the flange claw 40 are inwardly retracted due to their own elasticity, and the locking end surface on the inner side firmly holds above the locked structure 51 (i.e. the annular protrusion) of the connecting upper rod 50. Any force trying to move the piston 20 upwards (for example caused by vibration, impact or falling) will be transmitted to the locked structure 51 through the connecting upper rod 50 and finally borne by the claws 41 and the barrel 10 rigidly connected thereto. This purely mechanical rigid locking mode provides a very high locking force, which can effectively prevent the UAV and the piston assembly from moving axially in the barrel 10, thereby avoiding damage to critical components and ensuring the integrity and safety of the system.

[0037] When the firing command is received, the ignition system (not shown, usually integrated in the base 70) ignites the pyrotechnic charge 30 located in the high-pressure chamber, and the device enters the unlocking process. The pyrotechnic charge 30 burns in milliseconds and generates a large amount of high-temperature and high-pressure gas. Due to the airtightness and small volume of the high-pressure chamber, the internal pressure rises sharply. The high-pressure gas first acts on the lower surface of the piston top rod 60. Since the piston 20 is still firmly locked at this time, and the piston top rod 60 is designed to be independently movable, the initial thrust will be used to push the piston top rod 60 to move quickly upward in the axial direction. With the upward movement of the piston top rod 60, the conical surface 61 at its upper end is wedged between the inner sides of the plurality of claws 41 of the flange claw 40. According to the principle of force decomposition, the conical surface 61 decomposes the axial thrust on the piston top rod 60 into a plurality of powerful, radially outward expansion forces, and uniformly acts on each claw 41. When the bending moment generated by the radial expansion force exceeds the elastic bending moment of the claw 41 itself, it forces the claw 41 to elastically deform, and its end expands radially outward.

[0038] When the radial displacement of the claw 41 is sufficient to make the inner locking end surface completely pass over the annular protrusion of the locked structure 51 on the connecting upper rod 50, the locking of the connecting upper rod 50 is instantly released, and the device enters the launching process. At this time, the piston assembly composed of the piston 20 and the connecting upper rod 50 restores the freedom of upward movement. Almost at the same time, the continuous upward displacement of the piston top rod 60 forms a communication path between the high-pressure chamber originally sealed by it and the base 70 and the space below the piston 20 (which can be called a low-pressure chamber). For example, high-pressure gas can quickly flow into and act on the entire lower surface of the piston 20 through the through hole reserved on the flange claw 40, or the gap between the piston top rod 60 and the inner hole of the flange claw 40. Due to the fact that the area of the main acting surface of the piston 20 is much larger than the pressure receiving area of the piston top rod 60, the high-pressure gas will generate a huge and continuous thrust on the piston 20 at this time. Under the action of this thrust, the unlocked piston 20, together with the unmanned aerial vehicle it carries, moves upward along the inner wall of the barrel 10 at a very high acceleration until it flies out of the launch barrel mouth, completing the ejection. The entire process realizes the coherent action from ignition, unlocking to launching, and its timing is guaranteed by the mechanical structure itself, without the need for complex electronic control, thus having high reliability.

[0039] As a preferred solution, in order to better cooperate with the unmanned aerial vehicle, the embodiment also provides some preferred structures. Please refer to Figure 6Fig. 4 is a schematic view of the piston 20 and the movable hook 80. In a preferred embodiment of the present application, a movable hook 80 is provided on the upper portion of the piston 20 for hooking the UAV. Specifically, the top of the piston 20 can be integrally formed or fixedly connected with a plurality of lugs 21 (e.g. four), and each lug 21 is pivotally mounted with a S-shaped movable hook 80 via a pin. When inside the barrel 10, the root of the movable hook 80 is used to hook the matching structure on the UAV body, and the UAV is firmly connected with the piston 20 to jointly accelerate.

[0040] In addition, the configuration of the movable hook 80 enables it to automatically disengage from the UAV when the UAV flies out of the barrel 10. The implementation can be that when the movable hook 80 is inside the barrel 10, its shape is constrained by the inner wall of the barrel, so as to be forced to maintain the posture of hooking the UAV. When the piston 20 pushes the UAV to the barrel opening and flies out, the radial constraint on the movable hook 80 disappears instantaneously. The UAV continues to move under the action of inertia, pushing the movable hook 80 upward, and the piston 20 stops moving at the barrel opening under the action of the steel wire, pulling the movable hook 80 downward. After being stressed, the movable hook 80 overturns, i.e. the movable hook 80 quickly overturns outward and changes its posture due to the change of its structural relationship with the barrel 10 (i.e. the constraint is released), so as to automatically disengage from the UAV. This design realizes clean separation after launching, and avoids interference with the flight posture of the UAV.

[0041] As another improvement, in order to reduce the friction between the movable hook 80 and the inner wall of the barrel 10 during high-speed movement, a roller can be provided at the position (e.g. the head) of the movable hook 80 in contact with the barrel wall. The roller can convert sliding friction into rolling friction, thereby reducing energy loss and improving launching efficiency and device life.

[0042] In addition, the embodiment of the present application can also include a support barrel (not shown in the figure) provided on the piston 20. The support barrel is located between the piston 20 and the UAV, and its main function is to transmit the thrust of the piston 20 to the load-bearing frame of the UAV, and at the same time provide a safe accommodation space for the folded wings and other components of the UAV to avoid damage to the UAV under the huge launching overload.

[0043] Embodiment 2

[0044] This embodiment provides another alternative structure of the UAV launching device described in the present application. For the same or similar parts as in Embodiment 1, the same reference signs will be used, and the detailed structure and function will not be described again. The differences between this embodiment and Embodiment 1 will be mainly described below.

[0045] In this embodiment, the structure of the locked component is simplified. In Embodiment 1, the locked component is an independent connecting upper rod 50, which needs to be connected with the piston 20 by screwing or the like. In this embodiment, the locked component is integrated with the piston 20. Specifically, the lower part of the piston 20 directly extends an integral piston rod, which is equivalent in function to the connecting upper rod 50 in Embodiment 1. Correspondingly, the locked structure 51 is no longer a protrusion on the independent rod, but a ring-shaped groove directly machined on the specific position of the integral piston rod by turning or the like.

[0046] Correspondingly, the structure of the locking component flange claw 40 is also changed. The end of the locking unit claw 41 thereon is no longer a simple plane or hook, but has an inwardly protruding toothed structure, which is accurately matched in shape and size with the ring-shaped groove on the piston rod. In the locked state, the multiple claws 41 of the flange claw 40 are inwardly closed, and the toothed structure at the end thereof is embedded in the ring-shaped groove of the piston rod, limiting the axial movement of the piston 20 by shearing force. It can be understood that this "groove-tooth" engagement can also provide very reliable axial locking.

[0047] The unlocking and launching process of this embodiment is exactly the same as that of Embodiment 1. After the ignition of the initiating explosive 30, the high-pressure gas preferentially pushes the piston top rod 60 to move upward; the conical surface 61 of the piston top rod 60 wedges into the inside of the flange claw 40, forcibly opening the multiple claws 41 radially; when the toothed structure at the end of the claw 41 is completely withdrawn from the ring-shaped groove of the piston rod, the locking is released; then, the high-pressure gas is communicated to the low-pressure chamber below the piston 20, pushing the piston 20 to be launched at high speed.

[0048] Compared with Embodiment 1, the integrated design of the piston and the locked component in this embodiment reduces the number of parts and assembly steps, thereby reducing the production cost. At the same time, since the connecting interface is eliminated, the coaxiality and structural rigidity can be higher, thereby improving the reliability of the entire moving assembly. This change further illustrates that the "locked component" and "locked structure" protected by the present application are not limited to a specific form, but cover all implementation manners that can be fixed with the piston and provide a structure feature that can be clamped by the locking unit.

[0049] Furthermore, the present embodiment can also provide a more specific implementation of the gas passage. In Embodiment 1, the gas passage is only described in general. As an optional implementation, in the present embodiment, the structure of the flange claw 40 and the piston top rod 60 can be designed more precisely. For example, the flange portion of the flange claw 40 can be provided with a plurality of axially-through gas guide holes. In the initial locking state, the upper portion of the piston top rod 60 with a larger diameter completely blocks the lower end entrances of the gas guide holes. When the piston top rod 60 is pressed to move upward, its stroke is precisely designed: in the initial stage of its stroke, its conical surface 61 completes the expansion unlocking action on the claw 41, while the upper portion with a larger diameter still blocks the gas guide holes; when the unlocking action is completed, the piston top rod 60 continues to move upward for a small distance, and then the rod body portion with a smaller diameter is aligned with the gas guide holes on the flange claw 40, thereby instantaneously opening the passage for the high-pressure gas to the low-pressure chamber below the piston 20. This design realizes precise timing control of the unlocking action and the main gas passage opening through the displacement of the piston top rod 60, further ensuring the reliability of “unlocking first and then pressurizing”.

[0050] Those skilled in the art can understand that the structure of the locking assembly, the locked assembly and the unlocking trigger assembly in the above embodiments can also have other variations. For example, the locking unit of the locking assembly is not limited to the claw of cantilever beam type, but can also be a flexible chuck structure similar to a collet; the locked structure is not limited to a protrusion or a groove, but can be any mechanical structure capable of effectively transmitting an axial locking force, such as a step or a pin hole; the conical surface of the unlocking trigger assembly can also be replaced by a curved surface or other wedge-shaped structure with the same function. These variations do not deviate from the core idea of the present application, i.e., using a single explosive power source to separate a flexible locking assembly through the initial displacement of an independently movable unlocking trigger assembly, thereby unlocking the piston and immediately connecting the main gas passage to drive the piston to launch.

[0051] In summary, the unmanned aerial vehicle launching device provided by the embodiments of the present application realizes reliable axial fixation of the piston and the unmanned aerial vehicle before launching by setting a mechanical locking and releasing mechanism composed of a flange claw, a connecting rod and a piston top rod, effectively prevents damage caused by internal movement during transportation, falling, vibration and other service processes, and significantly improves the reliability and safety of the system. At the same time, the design highly integrates the functions of locking, unlocking and launching, uses a single explosive power source, and completes the unlocking and launching actions in sequence through ingenious structural design, without the need for an additional unlocking power source and control system, so that the overall structure is more compact and simple. Moreover, the unlocking action is directly driven by the explosive, with fast response speed, ensuring the instantaneity of launching; the mechanical timing of unlocking first and then launching is inherent in the structural design, avoiding timing errors caused by control delay or failure, so that the entire action process has high reliability.

[0052] The above descriptions are only the preferred embodiment of the present application, but not for limiting the present application. For those skilled in the art, the present application can have various modifications and changes. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present application shall be included in the protection scope of the present application.

Claims

1.A UAV launching device, comprising: a barrel; a piston arranged in the barrel; a pyrotechnic device for generating high pressure gas to drive the piston to move; characterized in that further comprising: a locking assembly fixedly arranged in the barrel, the locking assembly having at least one radially elastically deformable locking unit which is inwardly retracted in a locking state; a locked assembly fixedly connected with the piston, the locked assembly having a locked structure matched with the locking unit, the locking unit clamping the locked structure to fix the piston at a predetermined position in the barrel in the locking state; an unlocking trigger assembly adapted to move axially independently of the piston, one end of the unlocking trigger assembly having a tapered surface, the unlocking trigger assembly being configured to move axially in advance of the piston and preferentially driven by the high pressure gas generated by the pyrotechnic device, so that the tapered surface acts on the locking unit to make the locking unit radially expand and release the locking of the locked assembly. 2.The UAV launching device according to claim 1, characterized in that: the locking assembly is a flange claw; the locked assembly is a connecting upper rod; the unlocking trigger assembly is a piston top rod. 3.The UAV launching device according to claim 2, characterized in that: the locking unit is a claw arranged on the flange claw; the locked structure is a protrusion arranged on the connecting upper rod; in the locking state, the claw and the protrusion are clamped with each other. 4.The UAV launching device according to claim 3, characterized in that: the flange claw is an integral structure. 5.The UAV launching device according to claim 1, characterized in that: further comprising a base, the base and the unlocking trigger assembly together enclosing a high pressure chamber for accommodating the pyrotechnic device in an initial state. 6.The UAV launching device according to claim 5, characterized in that: axial movement of the unlocking trigger assembly is used to make the high pressure chamber communicate with a low pressure chamber arranged below the piston, so as to drive the piston to move by the high pressure gas. 7.The UAV launching device according to claim 1, characterized in that: a movable hook for hooking a UAV is arranged on the piston. 8.The UAV launching device according to claim 7, characterized in that: the movable hook is configured to change its posture due to its structural relationship with the barrel when the UAV flies out of a barrel mouth of the barrel, so as to be detached from the UAV. 9.The UAV launching device according to claim 8, characterized in that: a roller for reducing friction with an inner wall of the barrel is arranged on the movable hook. 10.The UAV launching device according to claim 1, characterized in that: further comprising a support barrel arranged on the piston, the support barrel being used to support a UAV.

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