Unmanned aerial vehicle recycling square cabin and operation vehicle system

Abstract

The invention relates to an unmanned aerial vehicle recycling square cabin and an operation vehicle system.The unmanned aerial vehicle recycling square cabin comprises a recycling square cabin body which has a closed state and an unfolded state, and a containing cabin is formed when the recycling square cabin body is closed; an expanded recovery platform is provided during unfolding; the blocking mechanism is arranged in the recovery square cabin; when being closed, the container is folded and accommodated in the accommodating cabin; and when the blocking net is unfolded, the blocking rods are erected on the recovery platform, and the plurality of blocking rods are unfolded to form the blocking net. According to the recycling square cabin for the folding-wing unmanned aerial vehicle, a stopping system of the folding-wing unmanned aerial vehicle is integrally designed into an expandable square cabin structure, the overall structure size is reduced through the highly-integrated design, the recycling square cabin can be assembled through a universal vehicle-mounted chassis, and the recycling operation of the unmanned aerial vehicle can be rapidly deployed; and due to the structural design of the square cabin, the recycling vehicle has better task concealment in the deployment process.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned equipment recovery, and in particular to an unmanned aerial vehicle recovery cabin and an operating vehicle system. Background Art

[0002] In recent years, folding-wing drones have been increasingly used in military reconnaissance and surveillance fields due to their portability, flexibility, and ability to be quickly deployed. Folding-wing drones are generally small in size and lack landing gear, making them difficult to recover. The current practice of ground-cleaning recovery, which is often used in actual applications, requires pre-selection or construction of a flat landing location, and it is difficult for drones to maintain balance during gliding, which may damage components such as wings or sensors.

[0003] For example, the invention patent "A parachute device for folding-wing drones dropped from the air" with patent application number "202110620165.9" proposes a parachute device for folding-wing drones, which allows drones to land smoothly. This method is targeted at specific drone equipment, increases the complexity of the structural design of folding-wing drones, and cannot be recovered quickly. Therefore, it is necessary to develop a safe, reliable, and fast and maneuverable folding-wing drone recovery system. Summary of the invention

[0004] In order to realize the batch rapid recovery of drones, especially drone clusters, the present invention provides a folding-wing drone recovery cabin and an operating vehicle system.

[0005] The present application provides a UAV recovery cabin, comprising: The recovery cabin has two forms: closed and expanded. When closed, it forms a containment cabin; when expanded, it has an expanded recovery platform. The arresting mechanism is arranged in the recovery cabin; when closed, it is folded and accommodated in the accommodation cabin; when unfolded, it has an arresting rod upright on the recovery platform, and a plurality of arresting rods are stretched out to form an arresting net.

[0006] Preferably, the four corners of the barrier net are elastically connected to the tops and roots of the two groups of barrier rods respectively.

[0007] Preferably, the blocking mechanism further includes a plurality of dampers, which are used to provide working damping when the blocking net is blocking; the dampers are respectively connected to the four corners of the blocking net via the top and bottom of the blocking rod.

[0008] Preferably, each of the dampers comprises a coaxially relatively fixed drum and an electromagnetic damper, wherein the drum is wound around a flexible rope connected to a corner of the barrier net.

[0009] Preferably, the recovery cabin comprises a fixed bottom cabin plate and front and rear cabin plates; Movable side decks, which can be moved to the plane where the bottom deck is located when unfolded; A movable top deck, which can move into the plane of the bottom deck when deployed; In the storage state, the side panels and the top panel are in the storage position to form a closed storage cabin.

[0010] Preferably, the side cabin panels are in two groups, which are disposed on both sides of the bottom cabin panel, and the side edges of the bottom cabin panel are rotationally connected to the side edges of the side cabin panels; when the side cabin panels are unfolded, they are rotated to the outside of the storage cabin and opened until they are in the same plane with the bottom cabin panel.

[0011] Preferably, the top deck has two groups of movably arranged half decks; when stored, the two groups of half decks are butted together to form a complete top deck; the side edges of the half decks are rotationally connected to the side edges of the side decks; when unfolded, the half decks are rotated around the side edges of the side decks to open.

[0012] Preferably, it includes: A first telescopic assembly, two ends of which are respectively hinged to the side cabin plate and the bottom cabin plate; A second telescopic assembly, two ends of which are respectively hinged to the side cabin panel and the half cabin panel; Or, it includes a plurality of support rods, which are folded and arranged on the outer surface of the side deck and / or the top deck in the stowed state; and are unfolded to be perpendicular to the recovery platform and support the recovery platform in the unfolded state.

[0013] Preferably, the root of the arresting rod is fixed on a rotating support, and the rotating support is rotatably arranged on the inner surface of the side cabin plate; the arresting rod and the side cabin plate are connected via a third telescopic assembly; the third telescopic assembly is used to drive the rotational movement of the arresting rod from the retracted state to the deployed state; or, the arresting mechanism is further provided with a reinforcing rod, which hinges the arresting rod and the adjacent front and rear cabin plates in the deployed state.

[0014] The present application further provides a drone recovery operation vehicle system, comprising a carrier platform and any of the drone recovery cabins described above carried by the carrier platform.

[0015] Compared with the prior art, the present invention has the following beneficial effects: The present invention provides a recovery cabin for folding-wing UAVs, which integrates the arresting system of the folding-wing UAV into a deployable cabin structure. The highly integrated design reduces the overall structural size. The recovery cabin can be equipped on a general vehicle chassis, and the UAV recovery operation can be quickly deployed. In addition, the structural design of the cabin enables the recovery vehicle to have better mission concealment during the deployment process.

[0016] The present invention adds a double flexible blocking system, and the adjustable electromagnetic damping system cooperates with the recovery net to effectively buffer the force of different types of folding-wing UAVs hitting the net; at the same time, the folding-wing UAV can hit the net and land from either side, which effectively shortens the preparation time for the landing of the folding-wing UAV, improves the efficiency of the UAV recovery operation, and enhances its applicability to various tasks. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 It is a schematic diagram of the accommodation state of the drone recovery cabin of the present invention; Figure 2 It is a schematic diagram of a UAV recovery operation system with a recovery cabin 1 of the present invention; Figure 3 It is a schematic diagram of the drone recovery cabin of the present invention in an unfolded state; Figure 4 It is a schematic diagram of the inside of the recovery cabin 1 of the present invention, close to the side cabin board 13; Figure 5 It is a schematic diagram of the arresting mechanism 3 in the recovery shelter 1 of the present invention in the deployed state; Figure 6 It is a schematic diagram of the arresting mechanism 3 in the recovery cabin 1 of the present invention in the accommodation state; Figure 7 It is a schematic diagram of the damper 33 of the arresting mechanism 3 in the recovery shelter 1 of the present invention; Figure 8 It is a schematic diagram of the operation of the arresting mechanism 3 in the recovery cabin 1 of the present invention.

[0018] In the figure: 1: Recovery cabin; 11: Bottom cabin plate; 12: Front and rear cabin plates; 13: Side cabin plates; 14: Top cabin plate; 141: Half cabin plate; 15: Recovery platform; 151: Support rod; 152: First telescopic assembly; 153: Second telescopic assembly; 2: Carrying platform; 21: Cabin installation platform; 22: Cabin power auxiliary unit; 23: Vehicle chassis; 3: Arresting mechanism; 31: Arresting net; 32: Arresting rod; 321: Reset support seat; 322: Detection sensor; 323: Rotating support seat; 324: Third telescopic assembly; 325: Reinforcement rod; 33: Damper; 331: Roller; 332: Electromagnetic damper. DETAILED DESCRIPTION

[0019] The present invention is described in detail below in conjunction with the accompanying drawings and specific embodiments. In this specification, the size ratios in the drawings do not represent the actual size ratios, but are only used to reflect the relative position relationship and connection relationship between the components. Components with the same name or the same number represent similar or identical structures and are only for illustrative purposes.

[0020] The invention provides a folding-wing UAV recovery cabin. The UAV recovery cabin is designed to be deployable. Figure 1 This is a schematic diagram of the containment status of the drone recovery cabin of this application. Figure 2 The schematic diagram of the UAV recovery operation system with the recovery cabin 1. The recovery cabin 1 is in the storage state, and it becomes a box that can be carried by the carrier platform 2. The recovery cabin 1 can have a standard cargo box size or a container size to match the general carrier platform 2. The recovery cabin 1 can be relatively fixed with the carrier platform 2 to form a special UAV recovery operation vehicle system, and it can also be considered to be flexibly disassembled and combined with the carrier platform 2 to form a UAV recovery operation vehicle system that adapts to different terrains and traffic requirements.

[0021] The transport platform 2 includes a container installation platform 21, a container support seat, a container power auxiliary unit 22, a hydraulic jack and a vehicle chassis 23. The vehicle chassis 23 is modified from a special vehicle chassis, and four hydraulic jacks are installed at the bottom of the frame. The container power auxiliary unit 22 is installed on one side of the vehicle fuel tank of the vehicle chassis 23 to provide electrical energy for each electric hydraulic mechanism of the container. The container installation platform 21 is fixed to the frame of the vehicle chassis 23, and the container support seats are installed at the four corners of the upper platform for connecting and recovering the container 2.

[0022] The vehicle chassis is a general special vehicle chassis, which carries the recovery cabin, and the operator drives the recovery vehicle to the designated working position. Four sets of hydraulic jacks are installed on the main beam of the frame. When the deployment operation begins, the hydraulic jacks are manually loaded and touched to the ground to avoid the shaking of the suspension and tire elastic mechanism caused by uneven loading during the drone recovery operation. The cabin installation platform connects the vehicle chassis and the cabin, which is fixed on the frame. Cabin support seats are installed at the four corners of the upper platform to fix the entire recovery cabin. The power auxiliary unit of the recovery cabin is installed on the side of the frame. It contains a diesel generator inside to provide power for the electric hydraulic mechanisms of the cabin. The power auxiliary unit is independent of the vehicle's power unit. When the vehicle is in standby operation for a long time, the vehicle can be in a flameout state. The power auxiliary unit provides power for the electric mechanisms of the cabin.

[0023] Figure 3This is a schematic diagram of the drone recovery cabin of the present application in the unfolded state. The recovery cabin 1 has a fixed bottom cabin plate 11 and front and rear cabin plates 12, and also has a movable top cabin plate 14 and side cabin plates 13. In the accommodated state, the side cabin plates 13 and the top cabin plates 14 are in the accommodated position, forming a closed accommodation cabin that can be used for storing and transporting drones. In the unfolded state, the side cabin plates 13 and the top cabin plates 14 are unfolded. The overall area composed of the side cabin plates 13, the top cabin plates 14 and the bottom cabin plates 11 forms a significantly expanded recovery area, which improves the efficiency and success rate of drone recovery. An auxiliary ladder, an inspection door and an electrical control cabinet are installed on at least one of the front and rear cabin plates 12.

[0024] The front and rear cabins of the cabin assembly are directly fixed on the square cabin installation platform. The interior is reinforced with a steel tube truss structure and the exterior is covered with a metal skin. The side cabin panels are connected to the cabin floor through hinges and hydraulic push rods, and the upper hatch cover is also connected to the side cabin panels through hinges and hydraulic push rods. The expansion mode of the square cabin adopts a two-stage expansion operation scheme. When the operator opens the power auxiliary unit in the electrical control cabinet and manually unlocks the locking mechanism of the upper hatch cover, the side cabin hydraulic rod installed on the extended support of the steel tube truss pushes the side cabin panels to expand and to a horizontal state, and then the upper hatch cover hydraulic rod pushes the upper hatch cover to a horizontal state. After the expansion is completed, the side cabin support rods and the upper hatch cover support rods are adjusted to the ground to bear the weight of each plate.

[0025] Figure 3 As an embodiment, the side deck 13 and the top deck 14 can be unfolded to be in the same plane as the bottom deck 11 . Figure 3 The specific implementation of the unfolding structure of the recovery cabin 1 is given in the specification. The side cabin panels 13 are divided into two groups, which are respectively placed on both sides of the bottom cabin panel 11, and the side edges of the bottom cabin panel 11 are rotatably connected to the side edges of the side cabin panels 13. When the side cabin panels 13 are unfolded, the side cabin panels 13 are rotated and opened to the outside of the recovery cabin 1 until they are in the same plane as the bottom cabin panel 11. The top cabin panel 14 has two groups of half cabin panels 141 that are movably arranged. When accommodated, the two groups of half cabin panels 141 are docked to form a complete top cabin panel 14 to close the recovery cabin 1. When closed, the half cabin panels 141 can be locked by a locking mechanism. The side edges of the half cabin panels 141 are rotatably connected to the side edges of the side cabin panels 13, so that when unlocked, the half cabin panels 141 can be opened around the edges of the side cabin panels 13.

[0026] In the actual deployment process, the top deck 14 is first unlocked, that is, the mutual fixation between the two groups of half decks 141 is released. Then the half deck 141 is driven to rotate to the same plane as the side deck 13, and simultaneously or successively, the side deck 13 is driven to rotate to the same plane as the bottom deck 11 to form a deployed recovery platform 15 with an area of ​​substantially four times that of the bottom deck 11.

[0027] refer to Figure 1Schematic diagram of . In order to ensure the overall stability of the recovery platform 15 when it is unfolded into a recovery platform, a plurality of support rods 151 are folded and arranged on the outer surfaces of the side panels 13 and the top panels 14 in the stowed state. The support rods 151 are folded and attached to the outer surfaces of the side panels 13 and the top panels 14 when stowed; during the unfolding process, they are opened to be perpendicular to the surface of the recovery platform 15. The length of the support rods 151 is adjustable and can be maintained at any length to support and keep the recovery platform 15 relatively flat on irregular ground.

[0028] Figure 4 It is a schematic diagram of the direction of the side panel 13 on one side of the interior of the recovery cabin 1. The side panel 13 and the top panel 14 are unfolded by hydraulic drive. Specifically, it has a first telescopic component 152 whose two ends are respectively hinged or rotatably connected to the bottom panel 11 and the side panel 13. The first telescopic component 152 can be a hydraulic cylinder or other equivalent power-driven length telescopic device, and its length change drives the side panel 13 to rotate around the axis to open and rotate and close during recovery. Similarly, it also has a second telescopic component 153 whose two ends are respectively hinged or rotatably connected to the side panel 13 and the top panel 14. The second telescopic component 153 can be a hydraulic cylinder or other equivalent power-driven length telescopic device, and the controlled telescopic movement of the second telescopic component 153 drives the top panel 14 to rotate around the side panel 13 to open or close.

[0029] The arresting mechanism 3 is distributed in one group on the left and right sides of the recovery cabin 1, and each group includes two arresting bars installed on the inner side of the side cabin plate. A fixed pulley device is installed on the upper end of the arresting bar to connect the arresting net. In the closed storage and transportation state, the two arresting bars are displayed side by side on the reset support seat 321 and fixed by the support cover plate on the reset support seat 321; in the recovery cabin deployment task, after the cabin body deployment action is completed, the support cover plate is manually opened, and the arresting bar driving hydraulic rod is controlled in the electrical control cabinet to push each arresting bar to rise; then the reinforcing rod is used to connect the front / rear cabin of the arresting bar to enhance the arresting system The rigidity of the system is to protect the arresting bar when the UAV hits the net for recovery; the damping device is composed of four on each side, two of which are fixed to the side cabin plate and connected to the connecting line on the bottom side of the arresting net, and the other two are fixed to the bottom cabin plate and connected to the connecting line on the upper side of the arresting net. The roller of the damping device is wound around the connecting line of the arresting net. After the arresting bar is raised, the arresting net is finally raised by the rotating roller and the electromagnetic damper is used to keep it locked. According to the mass of the folding-wing UAV to be recovered and the landing speed before the mission setting, the damping size of the electromagnetic damper is adjusted to make the folding-wing UAV fall to the appropriate position for recovery. After completing the recovery mission, the unfolded square cabin is reset and stored. First, the reinforcement rod connected to the arresting bar is released. The arresting bar drives the hydraulic rod to pull the arresting bar back to the reset support. The support cover is fixed by bolts. The angle sensor under the cover detects that the arresting bar has been reset. Then the side cabin plate and the upper hatch cover are pulled back by their hydraulic rods in turn. After the cabin assembly is reset, the cabin is locked using the locking mechanism of the upper hatch cover. Finally, raise the hydraulic jack connected to the chassis frame, and you can drive the folding-wing drone recovery vehicle that has completed the mission away from the work area.

[0030] The recovery cabin 1 is provided with an arresting mechanism 3 for recovering the drone. The arresting mechanism 3 adopts a collision net recovery solution and has an arresting net 31 that can be deployed in the height direction of the recovery platform 15. The arresting mechanism 3 also has a folding and unfolding design. The figure is a schematic diagram of the arresting mechanism 3 after it is unfolded. Figure 6 It is a schematic diagram of the arresting mechanism 3 in the receiving state.

[0031] like Figure 5As shown, the arresting mechanism 3 is deployed after the recovery cabin 1 is deployed or at the same time as the recovery cabin 1 is deployed. In the deployed state, there are at least two erected arresting bars 32 arranged at a certain distance. The arresting net 31 is arranged between the multiple arresting bars 32 to cover a certain area between the arresting bars 32 in the height direction. In order to adapt to the recovery of different types of drones, the arresting net 31 is movably arranged on the arresting bars 32 to achieve a certain degree of elastic expansion and contraction. Taking two groups of arresting bars 32 as an example, the arresting net 31 has four corners that are respectively movably connected to the ends of the arresting bars 32, and the four corners are connected to the corresponding ends of the arresting bars 32 through flexible ropes that can be extended and contracted. When the landing drone hits the net, the arresting net 31 itself absorbs part of the kinetic energy. In addition, the main kinetic energy is absorbed by the expansion and contraction of the flexible rope to achieve the purpose of non-destructive recovery of the arresting mechanism 3 and the drone. The flexible rope can be an elastic rope that absorbs kinetic energy through elastic deformation of the elastic rope, or it can be a flexible rope connected to mechanical or electromagnetic damping.

[0032] like Figure 6 As shown, the arresting bar 32 can be folded in the recovery cabin 1. In the storage state, the arresting bar 32 is folded from being perpendicular to the side cabin plate 13 when unfolded to being parallel to the surface of the side cabin plate 13, so as to achieve the function of being stored inside the recovery cabin 1. A reset support seat 321 is fixed in the side cabin plate 13, which is used to support and fix the arresting bar 32 when the arresting bar 32 is folded to be parallel to the surface of the side cabin plate 13. A detection sensor 322 for detecting whether the arresting bar 32 is accurately reset can also be set on the reset support seat 321.

[0033] like Figure 5 As shown, it is preferred to set a plurality of dampers 33, which are used to provide working damping when the blocking net 31 is blocking. Two sets of blocking rods 32 are provided, and four sets of dampers 33 are provided. Figure 7 As shown, the damper 33 is connected to the four corners of the arresting net 31 via the pulleys at the top and bottom of the arresting rod 32. The damper 33 has a coaxial relatively fixed roller 331 and an electromagnetic damper 332. When the folding wing UAV is recovered, the roller 331 winds the connecting line of the recovery net and pulls up the recovery net. The electromagnetic damper 332 provides damping calibrated according to the speed and mass of the UAV to tension the arresting net 31, and deforms the arresting net 31 to absorb energy during the arresting process.

[0034] The arresting mechanism 3 is preferably provided in two groups, which are respectively provided on the inner surface of the two groups of side panels 13. The two groups of arresting mechanisms 3 provide recovery operations for the UAV that lands in the left and right directions defined by the two front and rear panels 12. Figure 5As shown, the root of the arresting bar 32 is fixed on the rotating support 323, and the rotating support 323 is rotatably arranged on the inner surface of the side cabin plate 13. The arresting bar 32 and the side cabin plate 13 are connected via the third telescopic assembly 324, and the third telescopic assembly 324 can be a hydraulic cylinder or other linear telescopic assembly. The third telescopic assembly 324 drives the arresting bar 32 to complete the rotation switching between the folded state and the unfolded state. In the unfolded state, the arresting bar 32 stands upright on the surface of the side cabin plate 13. In order to ensure the stability of the arresting bar 32, a reinforcing rod 325 is also provided. The reinforcing rod 325 is hinged to the arresting bar 32 and the adjacent front and rear cabin plates 12 to provide stable support in the left and right directions.

[0035] Figure 8 It is a schematic diagram of the recovery process. During the recovery process, the damping size of the damper 33 is calibrated according to the mass and speed of the recovered drone. During the drone collision process, the drone is controlled to be recovered from the outer collision net with the half cabin plate 141 of the arresting net 31, so that the drone decelerates above the bottom cabin plate 11 and finally stops after hitting the net. Preferably, in order to ensure the stability and recovery efficiency during the recovery process and reduce additional recovery work, when calibrating the damping size of the damper 33, the constraint condition is the arresting distance. First, the arresting distance is satisfied not to exceed the center line of the front-to-back direction of the bottom cabin plate 11, so as to avoid the entanglement of the arresting net 31 and the collision of the drone when the left and right arresting nets 31 are recovered at the same time. Secondly, the arresting distance can be no less than half of the side deck 13, so as to ensure that the drone can fall into the predetermined area on the bottom deck 11 or the side deck 13 after being arrested and recovered. The advantage is that as long as the drone falls on the bottom deck 11 or the side deck 13 close to the bottom deck 11, the collection operation of the recovery cabin 1 can be quickly started without re-positioning the drone, and the drone can be loaded into the recovery cabin 1 at the same time. If the arresting distance is too small, the drone may be located on the half deck 141 or on the side deck 13 close to the arresting net 3, which will interfere with the collection operation process of the recovery cabin 1.

[0036] During the recovery process, in order to avoid rebounding from hitting the net during the arresting process, the damping size of the damper 33 is guaranteed to be gradually reduced from the set value to zero from the time the arresting net 31 contacts the drone to the maximum arresting distance. The damping of the damper 33 can be optionally maintained at zero for a period of time. The purpose of maintaining is to extend the free time of the arresting net 31 so that the drone has the opportunity to land on the surface of the bottom deck 11 almost unaffected by the arresting net 31. Preferably, during the arresting process, the damping of the dampers 33 controlling the two bottom corners of the arresting net 31 should be lower than that of the dampers controlling the two upper corners of the arresting net 31. The purpose is to make the bottom edge of the arresting net 31 be pushed toward the top of the bottom deck 11 more quickly than the top edge during the arresting process, so as to achieve the following effect: Figure 8As shown, a space is left below to expose the bottom deck 11, so that the UAV can fall onto the surface of the bottom deck 11 through this space, and avoid being interfered by the arresting net 31 and sliding onto the half deck 141 outside the arresting net 31. The specific control of the damping of the damper 33 controlling the bottom of the arresting net 31 compared with the damping of the damper controlling the top of the arresting net 31 can be determined according to the height of the arresting net 31 with a difference of 1 / 3-1 / 2 in the rolling distance of its roller 331, so that there is enough landing space and a lower landing height when the UAV finally stops.

[0037] The above content only describes the preferred implementation mode of the present invention, and does not limit the scope of the present invention. Without departing from the design spirit of the present invention, various modifications and improvements made to the technical solution of the present invention by ordinary technicians in this field should fall within the protection scope determined by the claims of the present invention.

Claims

1. A UAV recovery cabin, characterized in that: include: The recovery cabin (1) has two forms: closed and expanded, and forms a containment cabin when closed; When deployed, it has an enlarged recovery platform (15); The arresting mechanism (3) is arranged in the recovery cabin (1); when closed, it is folded and accommodated in the accommodation cabin; when unfolded, it has an arresting rod (32) standing upright on the recovery platform (15), and a plurality of arresting rods (32) are stretched to form an arresting net (31).

2. The UAV recovery shelter according to claim 1, characterized in that: The four corners of the barrier net (31) are elastically connected to the top and the root of the two groups of barrier bars (32).

3. The UAV recovery shelter according to claim 1, characterized in that: The blocking mechanism (3) further comprises a plurality of dampers (33), the dampers (33) being used to provide working damping when the blocking net (31) is blocking; the dampers (33) are respectively connected to the four corners of the blocking net (31) via the top and bottom of the blocking rod (32).

4. The UAV recovery shelter according to claim 3, characterized in that: Each of the dampers (33) comprises a coaxially relatively fixed roller (331) and an electromagnetic damper (332), wherein the roller (331) is wound around a flexible rope connected to a corner of the barrier net (31).

5. The UAV recovery cabin according to claim 1, characterized in that: The recovery cabin (1) comprises a fixed bottom cabin plate (11) and front and rear cabin plates (12); A movable side deck (13), which can be moved to the plane where the bottom deck (11) is located when unfolded; A movable top deck (14), which can move to the plane where the bottom deck (11) is located when unfolded; In the storage state, the side cabin panels (13) and the top cabin panels (14) are in the storage positions, forming a closed storage cabin.

6. The UAV recovery shelter according to claim 5, characterized in that: The side cabin panels (13) are divided into two groups and are disposed on both sides of the bottom cabin panel (11). The side edges of the bottom cabin panel (11) are rotatably connected to the side edges of the side cabin panels (13). When the side cabin panels (13) are unfolded, they are rotated toward the outside of the storage cabin and opened until they are in the same plane as the bottom cabin panel (11).

7. The UAV recovery shelter according to claim 6, characterized in that: The top deck (14) has two groups of movably arranged half decks (141); when folded, the two groups of half decks (141) are butted together to form a complete top deck (14); the side edges of the half decks (141) are rotationally connected to the side edges of the side decks (13); when unfolded, the half decks (141) are rotated around the side edges of the side decks (13) to open.

8. The UAV recovery shelter according to claim 7, characterized in that: include: A first telescopic assembly (152), two ends of the first telescopic assembly (152) being respectively hinged to the side cabin plate (13) and the bottom cabin plate (11); A second telescopic assembly (153), two ends of the second telescopic assembly (153) are respectively hinged to the side cabin panel (13) and the half cabin panel (141); Or, it comprises a plurality of support rods (151), wherein in the storage state, the support rods (151) are folded and arranged on the outer surface of the side deck (13) and / or the top deck (14); In the unfolded state, the support rod (151) is unfolded to be perpendicular to the recovery platform (15) and supports the recovery platform (15).

9. The UAV recovery shelter according to claim 8, characterized in that: The root of the arresting rod (32) is fixed on a rotating support (323), and the rotating support (323) is rotatably arranged on the inner surface of the side cabin plate (13); the arresting rod (32) and the side cabin plate (13) are connected via a third telescopic assembly (324); the third telescopic assembly (324) is used to drive the arresting rod (32) to rotate from the retracted state to the deployed state; or, the arresting mechanism (3) is also provided with a reinforcing rod (325), and the reinforcing rod (325) is hinged to the arresting rod (32) and the adjacent front and rear cabin plates (12) in the deployed state.

10. A drone recovery vehicle system, characterized in that: It comprises a carrier platform (2) and a UAV recovery cabin as described in any one of claims 1 to 9 carried by the carrier platform (2).

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