An Aerodynamic Catapult Recovery Device for Unmanned Aerial Vehicles

Abstract

The present invention relates to the technical field of UAV take-off and landing support systems, and particularly relates to a pneumatic ejection recovery device for UAVs, which includes a frame body. Both ends of the frame body are slidably connected with sliding frames, and the sliding frames slide along the length direction of the frame body. At least one set of enlarged pulley groups are arranged at both ends of the frame body. Each set of enlarged pulley groups includes a fixed pulley rotatably connected to the frame body and a movable pulley rotatably connected to the sliding frame. The frame body is connected with a power assembly for driving the two sliding frames to move synchronously, and reversing pulley groups are arranged at both ends of the frame body; the two sliding frames are commonly fixedly connected with a traction cable, and the traction cable is wound around each movable pulley, fixed pulley and guiding pulley. The number of turns of the traction cable wound on the movable pulley and the fixed pulley at both ends of the frame body is the same. A traction assembly is connected to the traction cable. This application can enable the ejection device to meet the take-off conditions of the UAV on the premise of low cost and low space occupation by magnifying the moving distance of the traction cable driven by the power assembly.

Description

Technical Field

[0001] The present invention relates to the technical field of UAV take-off and landing support systems, and particularly relates to an aerodynamic catapult recovery device for UAVs. Background Art

[0002] Currently, in the field of UAV applications, take-off and recovery are two important links in the application process of fixed-wing UAVs.

[0003] Take-off:

[0004] The take-off methods of fixed-wing UAVs mainly include runway take-off, rocket-boosted take-off, catapult take-off, manual throw-and-release take-off, etc.

[0005] Large UAVs generally adopt runway take-off or catapult take-off due to their large body size, large take-off weight, relatively low fuselage structural strength, and low anti-overload ability;

[0006] Medium and small fixed-wing UAVs have relatively small bodies, relatively high fuselage structural strength, and high anti-overload ability, and can adopt runway take-off, rocket-boosted take-off or catapult take-off;

[0007] Manual throw-and-release take-off is mainly applied to small and lightweight UAVs that are lightweight and sturdy.

[0008] Recovery:

[0009] The recovery methods of fixed-wing UAVs mainly include runway landing, drag chute, parachute descent, arresting, hanging rope, and belly landing, etc.

[0010] Large UAVs generally adopt runway landing recovery, and can also be assisted by arresting cables and drag chutes to shorten the runway length requirements for aircraft landing;

[0011] The existing recovery methods for medium and small UAVs mainly include runway landing, parachute descent, hanging rope recovery, net collision recovery, etc.;

[0012] Small and lightweight UAVs mostly adopt parachute descent or belly landing methods;

[0013] Currently, the catapult take-off of large UAVs mainly has two schemes: steam catapult and electromagnetic catapult, and the recovery mainly has three schemes: drag chute, arresting cable, and net collision. Generally, a towing rod and a tail hook are provided on the UAV. The towing rod is generally used to be connected with the catapult device during the take-off process of the UAV to let the catapult device drive the UAV, and the tail hook is generally used to be connected with devices such as the arresting cable during the landing process of the UAV to provide buffering for the UAV.

[0014] During the catapult takeoff process of large unmanned aerial vehicles (UAVs), whether it is steam catapult or electromagnetic catapult, a large amount of high-density energy release is required, and a powerful power system and energy reserve are needed. Therefore, the use of steam catapult and electromagnetic catapult has great limitations. It can only be supported by large ships or permanent large facilities, and it is difficult to achieve land mobility. Moreover, the establishment of the system requires a large amount of long-term investment.

[0015] Therefore, the pneumatic catapult device currently has unique advantages in catapulting UAVs and will be applied in many scenarios.

[0016] In the above technical solution, when the pneumatic catapult device catapults UAVs, especially large UAVs, due to the need for a certain catapult acceleration and stroke, the space occupied by the catapult device is usually relatively large, but it is difficult to provide sufficient space for the catapult device in actual applications. Summary of the Invention

[0017] To solve the deficiencies of the existing technology, the present invention provides a pneumatic catapult recovery device for UAVs.

[0018] The technical solution of the present invention is as follows:

[0019] The present invention provides a pneumatic catapult recovery device for UAVs, which includes a frame body. Both ends of the frame body are slidably connected with sliding frames. The sliding frames slide along the length direction of the frame body. At least one set of magnification pulley groups are arranged at both ends of the frame body. The number of magnification pulley groups at both ends of the frame body is the same. Each set of magnification pulley groups includes a fixed pulley rotatably connected to the frame body and a movable pulley rotatably connected to the sliding frame. The frame body is connected with a power component for driving the two sliding frames to move synchronously. Commutation pulley groups are arranged at both ends of the frame body. Each set of commutation pulley groups includes at least one guiding pulley;

[0020] The two sliding frames are commonly fixedly connected with a traction cable. The traction cable is wound around each movable pulley, fixed pulley and guiding pulley. The number of turns of the traction cable wound on the movable pulley and fixed pulley at both ends of the frame body is the same. A traction component capable of driving the UAV to take off is connected to the traction cable.

[0021] The beneficial effects achieved by the present invention are as follows: During use, when the ejection device is installed, the power component drives the sliding frame to move, the sliding frame drives the moving pulley to move, and the moving pulley drives the traction cable to move together during the movement. Due to the magnifying pulley group, the moving distance of the traction cable is several times that of the moving pulley, enabling the power component to provide several times the moving distance for the traction component in a limited space, allowing the traction component to provide sufficient takeoff acceleration for the aircraft. The ejection device of the present application has the characteristics of simple structure, perfect function, practical reliability, low cost, easy manufacturing, easy operation, rapid erection, flexibility, etc. Any road surface or site with a certain levelness, length, and width can be quickly erected and quickly put into the operation of ensuring the takeoff and landing of large unmanned aerial vehicles, and it has excellent concealment. The traction cable can be laid at any position through the guiding pulley, and the frame, traction cable, and reversing pulley group can all be laid below the plane, facilitating the movement of the unmanned aerial vehicle on the site.

[0022] Further, the power component includes the cylinder body of a driving cylinder fixedly connected to the frame. The piston rod of the driving cylinder passes through the cylinder body of the driving cylinder, and both ends of the piston rod of the driving cylinder are fixedly connected to two sliding frames respectively.

[0023] Through the above solution, with the cylinder body of the driving cylinder fixed, the movement of the piston rod can drive the sliding frame to move. The power component is simple and has low cost.

[0024] Further, the power component includes the cylinder body of a power cylinder fixedly connected to two sliding frames, and the piston rod of the power cylinder is fixedly connected to the frame.

[0025] Through the above solution, with the piston rod of the driving cylinder fixed, the movement of the cylinder body can drive the sliding frame to move. The power component is simple and has low cost.

[0026] Further, the traction component includes a traction shuttle fixedly connected to the traction cable, and the traction shuttle is provided with a traction groove.

[0027] Through the above solution, when the unmanned aerial vehicle needs to take off, it only needs to move the unmanned aerial vehicle to the traction shuttle, let the traction pull rod be stuck in the traction groove, the movement of the traction cable will drive the traction shuttle to move together, the traction pull rod is driven by the traction shuttle to drive the unmanned aerial vehicle to move. When the acceleration of the unmanned aerial vehicle is sufficient to take off or after the traction shuttle has moved, the traction pull rod will be pulled by the unmanned aerial vehicle and separated from the traction shuttle. The operation is simple, and even large unmanned aerial vehicles can take off easily. The traction pull rod can be hung at any position of the unmanned aerial vehicle, adapting to various types of unmanned aerial vehicles.

[0028] Further, a arresting cable is placed on the top of the traction shuttle, and the traction shuttle is connected with a connection component for allowing the arresting cable to slide on the top of the traction shuttle;

[0029] Arresting frames are arranged on both sides of the traction shuttle, and the arresting cable can be connected to the two arresting frames.

[0030] Through the above scheme, when the UAV needs to land, the ejection device can also be used for buffering. It is only necessary to pass the arresting cable through the through hole, connect the arresting cable head to tail and clamp it on the two arresting frames. The two arresting frames cooperate with the traction shuttle to stretch the arresting cable. When the UAV lands, the tail hook of the aircraft is hooked to the arresting cable. As the UAV moves, the arresting cable will be detached from the arresting frame and straightened. At the same time, the traction shuttle is pulled by the arresting cable to give a moving force to the traction cable. The traction cable applies a pulling force to the power assembly through the guide pulley and the amplifying pulley group. The power assembly will feedback a reverse resistance to the traction shuttle through the traction cable, so that the traction shuttle prevents the UAV from moving through the arresting cable. At the same time, because the power assembly is a pneumatic device, it can act as a damper to buffer the traction shuttle, and continue to block the movement of the UAV until the UAV stops moving, so as to avoid the arresting cable or the UAV being damaged due to excessive resistance to the UAV. At the same time, since the arresting cable is still connected to the traction shuttle, the UAV will be continuously adjusted in the moving direction of the traction shuttle during the movement of the UAV, thereby improving the landing accuracy of the UAV.

[0031] Furthermore, a plurality of supporting balls are fixedly connected to the arresting cable.

[0032] Through the above solution, the support ball can lift the arresting cable to prevent the part of the arresting cable located between the arresting frames from contacting the ground and affecting the drone's attachment to the arresting cable.

[0033] Furthermore, a track is arranged along the moving direction of the traction shuttle near the traction cable, and the traction shuttle is slidably connected to the track.

[0034] Through the above solution, the track can make the moving trajectory of the towing shuttle more stable, thereby making the moving trajectory of the drone straighter during the ejection process.

[0035] Furthermore, the traction assembly includes a tractor fixedly connected to the traction cable or the traction shuttle for lifting the drone.

[0036] Through the above solution, when the drone takes off, the staff can place the drone on a tractor, and the tractor will drive the drone to move, thereby providing acceleration to the drone.

[0037] Furthermore, the two sliding frames are fixedly connected with at least one traction cable, and each traction cable is wound around two sets of reversing pulley blocks.

[0038] Through the above solution, a catapult device can have multiple traction cables, which can drive multiple drones to take off at the same time.

[0039] Furthermore, support pulleys are provided at the positions between the traction cable and each guiding pulley and between every two adjacent guiding pulleys corresponding to the frame body, and the traction cable bypasses the support pulleys from the tops of the support pulleys.

[0040] Through the above solution, the support pulleys can lift the traction cable, reduce the part of the traction cable at the bottom of the device, make it more convenient for the installation and maintenance of the traction cable, and also save more space.

[0041] An unmanned aerial vehicle pneumatic ejection recovery device of the present invention has the following advantages:

[0042] 1. The ejection device of this application occupies a small space, has a simple structure, and low cost. The traction cable can be laid at any position through the guiding pulleys, and the frame body, the traction cable, and the commutation pulley group can all be laid below the plane, which is convenient for the unmanned aerial vehicle to move on the site. BRIEF DESCRIPTION OF THE DRAWINGS

[0043] Figure 1 is a schematic diagram of the overall structure of Embodiment 1 of the present invention;

[0044] Figure 2 is a schematic diagram of the frame body, the traction cable, and the commutation pulley group of Embodiment 1 of the present invention;

[0045] Figure 3 is a partial schematic diagram of the enlarged pulley group of Embodiment 1 of the present invention;

[0046] Figure 4 is Figure 1 an enlarged view of part A in

[0047] Figure 5 is a schematic diagram of the structure of Embodiment 2 of the present invention;

[0048] Figure 6 is a schematic diagram of the traction shuttle of Embodiment 2 of the present invention;

[0049] Figure 7 is a partial schematic diagram of the state where the arresting cable is disengaged from the arresting frame of Embodiment 2 of the present invention;

[0050] Figure 8 is a schematic diagram of the structure of Embodiment 3 of the present invention;

[0051] Figure 9 is a schematic diagram of the structure of Embodiment 4 of the present invention;

[0052] Figure 10 is a schematic diagram of the structure of Embodiment 5 of the present invention;

[0053] Figure 11 is a schematic diagram of the structure of Embodiment 6 of the present invention.

[0054] In the figure, 1 is the frame body; 11 is the sliding frame; 12 is the magnification pulley block; 121 is the movable pulley; 122 is the fixed pulley; 13 is the power assembly; 131 is the driving cylinder; 132 is the power cylinder; 2 is the reversing pulley block; 21 is the guiding pulley; 22 is the supporting pulley; 3 is the towing cable; 4 is the towing assembly; 41 is the towing shuttle; 411 is the connecting assembly; 4111 is the pressing block; 4112 is the bolt; 4113 is the through groove; 412 is the arresting cable; 4121 is the supporting ball; 42 is the towing groove; 43 is the arresting frame; 44 is the track; 45 is the towing vehicle; 5 is the ground; 6 is the unmanned aerial vehicle; 61 is the towing pull rod; 62 is the tail hook. Detailed implementation manners

[0055] For the convenience of those skilled in the art to understand the present invention, the following combines the accompanying drawings to illustrate the detailed implementation manners of the present invention.

[0056] In the description of the present application, it should be noted that the orientation or positional relationship indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. is based on the orientation or positional relationship shown in the accompanying drawings. It is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation of the present invention. In addition, the terms "first", "second", and "third" are only used for descriptive purposes and cannot be understood as indicating or implying relative importance.

[0057] In the description of the present application, it should be noted that unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium, and it can be the communication inside two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present application can be understood according to specific situations.

[0058] Embodiment 1. The present invention provides an unmanned aerial vehicle pneumatic ejection recovery device, as Figure 1 and Figure 2As shown in the figure, it includes a frame body 1 installed below the ground 5 (the ground 5 can be any plane such as the surface of a platform for the takeoff of the drone 6). At both ends inside the frame body 1, there are sliding frames 11 slidably connected, and the sliding frames 11 slide along the length direction of the frame body 1. At both ends of the frame body 1, there are at least one set of magnifying pulley groups 12, and the number of magnifying pulley groups 12 at both ends of the frame body 1 is the same. Each set of magnifying pulley groups 12 includes a fixed pulley 122 rotatably connected to the frame body 1 and a movable pulley 121 rotatably connected to the sliding frame 11. The frame body 1 is connected with a power assembly 13. The power assembly 13 includes the cylinder body of a driving cylinder 131 fixedly connected to the frame body 1. The piston rod of the driving cylinder 131 passes through the cylinder body of the driving cylinder 131, and both ends of the piston rod of the driving cylinder 131 are respectively fixedly connected to the two sliding frames 11. The cylinder body of the driving cylinder 131 is fixed, and the movement of the piston rod can drive the movement of the pulley 121 frame. The power assembly 13 is simple and has a low cost.

[0059] As Figure 2 and Figure 3 As shown in the figure, at both ends of the frame body 1, there are reversing pulley groups 2. Each set of reversing pulley groups 2 includes at least one guiding pulley 21 (in this embodiment, the number of guiding pulleys 21 in each set of reversing pulley groups 2 is two), and the guiding pulleys 21 are all rotatably connected to the ground 5. The two sliding frames 11 are fixedly connected together with a towing cable 3, and the towing cable 3 is buried under the ground 5. The towing cable 3 is wound around each movable pulley 121, fixed pulley 122, and guiding pulley 21, and the number of turns of the towing cable 3 wound on the movable pulley 121 and fixed pulley 122 at both ends of the frame body 1 is the same. The towing cable 3 bypasses the guiding pulley 21 to form an approximate quadrilateral.

[0060] As Figure 1 and Figure 4 As shown in the figure, at the position of the towing cable 3 corresponding to between the two reversing pulley groups 2, there is a towing assembly 4 connected. The towing assembly 4 includes a towing shuttle 41 fixedly connected to the towing cable 3. The towing shuttle 41 is provided with a towing groove 42, and a towing pull rod 61 fixedly connected to the bottom of the drone 6 can be clamped in the towing groove 42. When the drone 6 needs to take off, only need to move the drone 6 to the position of the towing shuttle 41, let the towing pull rod 61 be stuck in the towing groove 42. The movement of the towing cable 3 will drive the towing shuttle 41 to move together. The towing pull rod 61 is driven by the towing shuttle 41 to drive the drone 6 to move. When the acceleration of the drone 6 is sufficient to take off and the towing shuttle 41 has moved completely, the towing pull rod 61 will be pulled by the drone 6 to separate from the towing shuttle 41. The operation is simple. Even a large drone 6 can take off easily. The towing pull rod 61 can be hung at any position of the drone 6 to adapt to various types of drones 6.

[0061] As Figure 2As shown in the figure, a track 44 is arranged near the traction cable 3 and along the moving direction of the traction shuttle 41. The traction shuttle 41 is slidably connected to the track 44. The track 44 can make the moving track of the traction shuttle 41 more stable, so that the moving track of the drone 6 during the catapulting process is straighter.

[0062] Usage method: When in use, install the catapulting device. The driving cylinder 131 drives the sliding frame 11 to move, the sliding frame 11 drives the movable pulley 121 to move, and the movable pulley 121 drives the traction cable 3 to move together during the movement. Due to the magnifying pulley block 12, the moving distance of the traction cable 3 is several times that of the movable pulley 121, so that the power assembly 13 can also provide several times the moving distance for the traction assembly 4 in a limited space, enabling the traction assembly 4 to provide sufficient takeoff acceleration for the aircraft. The catapulting device of the present application has the characteristics of simple structure, perfect function, practical reliability, low cost, easy manufacturing, easy operation, rapid erection, flexibility, etc. It can be quickly erected on any road surface or site with a certain flatness, length, and width, and can quickly be put into the takeoff and landing support operation of large drones 6, and has excellent concealment. The traction cable 3 can be laid in any position through the guiding pulley 21, and the frame 1, the traction cable 3, and the reversing pulley group 2 can all be laid below the plane, facilitating the movement of the drone 6 on the site.

[0063] Embodiment 2: A pneumatic catapulting and recovery device for a drone, which is different from Embodiment 1 in that: as Figure 5 and Figure 6 shown in the figure, a arresting cable 412 is placed on the top of the traction shuttle 41. The traction shuttle 41 is connected with a connecting component 411. The connecting component 411 includes a pressing block 4111 hinged to the top of the traction shuttle 41. A through groove 4113 is jointly opened on the side of the pressing block 4111 and the traction shuttle 41 close to each other. The arresting cable 412 can pass through the through groove 4113. The pressing block 4111 is threadedly connected with a bolt 4112, and the bolt 4112 can be threadedly connected to the traction shuttle 41. Arresting frames 43 are arranged on both sides of the traction shuttle 41. The arresting frames 43 are installed on the ground 5, and the arresting cable 412 can be clamped on the two arresting frames 43.

[0064] When the UAV 6 needs to land, the ejection device can also be used for buffering. It only needs to pass the arresting cable 412 through the through hole, connect the arresting cable 412 head to tail and clamp it on the two arresting frames 43. The two arresting frames 43 cooperate with the traction shuttle 41 to stretch the arresting cable 412. When the UAV 6 lands, the tail hook 62 of the aircraft is hooked to the arresting cable 412. As the UAV 6 moves, the arresting cable 412 will be disengaged from the arresting frame 43 and straightened. At the same time, the traction shuttle 41 is pulled by the arresting cable 412 to give the traction cable 3 a moving force. The traction cable 3 applies a pulling force to the power component 13 through the guide pulley 21 and the amplifying pulley group 12. The power component 13 will A reverse resistance is fed back to the traction shuttle 41 through the traction cable 3, so that the traction shuttle 41 can prevent the movement of the UAV 6 through the arresting cable 412. At the same time, because the power component 13 is a pneumatic device, it can act as a damper to the traction shuttle 41 and continue to block the movement of the UAV 6 until the UAV 6 stops moving, thereby avoiding the situation where the arresting cable 412 gives too much resistance to the UAV 6 and the arresting cable 412 or the UAV 6 is damaged. At the same time, since the arresting cable 412 is still connected to the traction shuttle 41, the UAV 6 will be continuously adjusted in the moving direction of the traction shuttle 41 during the movement of the UAV 6, thereby improving the landing accuracy of the UAV 6.

[0065] like Figure 6 and Figure 7 As shown, a plurality of support balls 4121 are fixedly connected to the arresting cable 412. The support balls 4121 can lift the arresting cable 412 to prevent the portion of the arresting cable 412 between the arresting frames 43 from contacting the ground 5, which would affect the drone 6 from hooking the arresting cable 412.

[0066] Embodiment 3: A pneumatic ejection recovery device for a drone, which is different from Embodiment 1 in that: Figure 8 As shown, the traction assembly 4 includes a tractor 45 fixedly connected to the traction cable 3 for lifting the drone 6. The traction cable 3 is provided with two tracks 44 arranged along the moving direction of the tractor 45 near the tractor 45, and the tractor 45 is slidably connected to the two tracks 44. When the drone 6 takes off, the staff can put the drone 6 on the tractor 45, and the tractor 45 drives the drone 6 to move, thereby providing acceleration to the drone 6.

[0067] Embodiment 4: A pneumatic ejection recovery device for a drone, which is different from Embodiment 1 in that: Figure 9 As shown, two sliding frames 11 are fixedly connected with two traction cables 3, and the guide pulleys 21 of each set of reversing pulley sets 2 are symmetrically arranged on both sides of the frame, and the two traction cables 3 are respectively wound around the guide pulleys 21 on one side of the frame. One ejection device can have two traction cables 3, which can drive two drones 6 to take off at the same time.

[0068] Embodiment 5. A pneumatic catapult recovery device for an unmanned aerial vehicle, which is different from Embodiment 1 in that: as Figure 10 shown, support pulleys 22 are provided at the positions corresponding to each guiding pulley 21 between the support frame 1 and at the positions between every two adjacent guiding pulleys 21. The towing cable 3 bypasses the support pulleys 22 from the top of the support pulleys 22. The support pulleys 22 can lift the towing cable 3, reducing the part of the towing cable 3 at the bottom of the device, making it more convenient for the installation and maintenance of the towing cable 3 and also saving more space.

[0069] Embodiment 6. A pneumatic catapult recovery device for an unmanned aerial vehicle, which is different from Embodiment 1 in that: as Figure 11 shown, the power assembly 13 includes the cylinder body of a power cylinder 132 fixedly connected between two sliding frames 11, and the piston rod of the power cylinder 132 is fixedly connected to the support frame 1. The piston rod of the driving cylinder 131 is fixed, and the movement of the cylinder body can drive the movement of the pulley 121 frame. The power assembly 13 is simple and has a low cost.

[0070] The above-described embodiments of the present invention do not constitute a limitation to the protection scope of the present invention. Any modifications, equivalent replacements, and improvements made within the spirit and principle of the present invention shall be included within the protection scope of the claims of the present invention.

Claims

1. An unmanned aerial vehicle pneumatic ejection recovery device, characterized in that: The invention comprises a frame (1), both ends of the frame (1) are slidably connected with a sliding frame (11), the sliding frame (11) slides along the length direction of the frame (1), both ends of the frame (1) are provided with at least one set of amplifying pulley groups (12), the number of amplifying pulley groups (12) at both ends of the frame (1) is the same, each set of amplifying pulley groups (12) comprises a fixed pulley (122) rotatably connected to the frame (1) and a movable pulley (121) rotatably connected to the sliding frame (11), the frame (1) is connected with a power component (13) for driving the two sliding frames (11) to move synchronously, both ends of the frame (1) are provided with a reversing pulley group (2), each set of reversing pulley group (2) comprises at least one guide pulley (21); The two sliding frames (11) are fixedly connected to a traction cable (3), the traction cable (3) is wound around each movable pulley (121), a fixed pulley (122) and a guide pulley (21), the number of turns of the traction cable (3) wound around the movable pulley (121) and the fixed pulley (122) at both ends of the frame (1) is the same, and the traction cable (3) is connected to a traction component (4) capable of driving a drone (6) to take off; The two sliding frames (11) are fixedly connected with at least one traction cable (3), and each traction cable (3) is wound around two sets of reversing pulley blocks (2); The traction assembly (4) comprises a traction shuttle (41) fixedly connected to the traction cable (3), and the traction shuttle (41) is provided with a traction groove (42); a blocking cable (412) is placed on the top of the traction shuttle (41), and the traction shuttle (41) is connected to a connecting assembly (411) for allowing the blocking cable (412) to slide on the top of the traction shuttle (41); blocking frames (43) are arranged on both sides of the traction shuttle (41), and the blocking cable (412) can be clamped on the two blocking frames (43); a track (44) is arranged along the moving direction of the traction shuttle (41) near the traction cable (3) near the traction shuttle (41), and the traction shuttle (41) is slidably connected in the track (44); the connecting assembly (411) comprises a pressing block (4111) hinged to the top of the traction shuttle (41), and a through groove (4113) is commonly provided on the side where the pressing block (4111) and the traction shuttle (41) are close to each other; When the UAV is landing, the arresting cable (412) is passed through the through slot (4113), the arresting cable (412) is connected end to end and clamped on the two arresting frames (43), and the two arresting frames (43) cooperate with the traction shuttle (41) to open the arresting cable (412), and the tail hook of the aircraft is hooked to the arresting cable (412) when the UAV is landing.

2. The unmanned aerial vehicle pneumatic ejection recovery device according to claim 1, characterized in that: The power assembly (13) comprises a cylinder body of a driving cylinder (131) fixedly connected to the frame body (1); a piston rod of the driving cylinder (131) passes through the cylinder body of the driving cylinder (131); and two ends of the piston rod of the driving cylinder (131) are respectively fixedly connected to the two sliding frames (11).

3. The unmanned aerial vehicle pneumatic ejection recovery device according to claim 1, characterized in that: The power assembly (13) comprises a cylinder body of a power cylinder (132) fixedly connected to two sliding frames (11), and a piston rod of the power cylinder (132) is fixedly connected to the frame body (1).

4. The unmanned aerial vehicle pneumatic ejection recovery device according to claim 1, characterized in that: A plurality of support balls (4121) are fixedly connected to the arresting cable (412).

5. The unmanned aerial vehicle pneumatic ejection recovery device according to claim 1, characterized in that: The traction assembly (4) includes a tractor (45) fixedly connected to the traction cable (3) for lifting the UAV (6).

6. The unmanned aerial vehicle pneumatic ejection recovery device according to claim 1, characterized in that: Support pulleys (22) are provided at positions between the traction cable (3) corresponding to each guiding pulley (21) and the frame body (1) and at positions between every two adjacent guiding pulleys (21), and the traction cable (3) bypasses the support pulley (22) from the top of the support pulley (22).

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