A tail-type launching and recovering UAV device

Abstract

The present invention relates to a tail-type launch and recovery UAV device, belonging to the technical field of UAVs. It comprises a left vertical mounting surface, a right vertical mounting surface, a launch and recovery track, a sliding block, a traction rope, a traction motor, a recovery chain, a UAV and a UAV tail hook; a launch and recovery track is respectively provided on the upper end surface of the left vertical mounting surface and the right vertical mounting surface arranged in parallel in the device; a sliding block is provided on the launch and recovery track; the sliding block is connected to the traction motor through a traction rope; a recovery chain is provided between the sliding blocks on the launch and recovery tracks on both sides; and a UAV tail hook is provided under the UAV. The main equipment of the device of the present invention occupies a small volume and can be arranged and installed in a small space; it can provide additional torque, effectively reduce the head-up height of the ship at high speed, and improve navigation safety.

Description

Technical Field

[0001] The invention relates to a tail-type launching and recovering unmanned aerial vehicle (UAV) device, belonging to the technical field of UAVs. Background Art

[0002] Small fixed-wing drones are widely used, enabling aerial reconnaissance and the search for suspicious targets, as well as terrain surveying and mapping. With the expansion of platforms and the demand for use in diverse scenarios, vehicle- and ship-mounted drones have emerged. However, the primary challenge is how to launch and recover drones from confined spaces.

[0003] Currently, the main methods for assisted takeoff of small fixed-wing UAVs include rubber band catapults, hydraulic catapults, liquid-gas hybrid catapults, and rocket-assisted launch. Rubber band catapults have a simple structure and are primarily designed for small and micro fixed-wing UAVs used for model aircraft or demonstration purposes. However, the rubber bands have a short lifespan, a limited stretch range, and insufficient launch force, making them unsuitable for engineering applications. Hydraulic and liquid-gas hybrid catapults, while requiring high power, often require a long rigid catapult chute to achieve the required breakaway speed and relatively low acceleration for UAV takeoff. This long catapult chute complicates the folding structure, making the entire system heavy and bulky. The operator's operation process is complex and time-consuming, making it unsuitable for small vehicles and small ships. Rocket-assisted launch methods require high operator requirements, involve cumbersome procedures, and pose certain safety risks. They are single-use, non-recyclable, and lack the ability to be reused. They often target a single UAV, requiring different rockets for different configurations, resulting in poor compatibility.

[0004] Currently, the main methods for drone recovery include cable and net recovery, parachute-assisted landing, runway landing, and water landing and salvage recovery. While cable and net recovery is a viable option for ship-based recovery of fixed-wing drones, the additional recovery equipment and its associated power and control systems make operation, operation, maintenance, and repair of the equipment cumbersome and complex, while also increasing the burden of transportation. Sea landing and salvage recovery methods place stringent demands on the fixed-wing drone's watertightness and heat dissipation design, resulting in a reduction in payload capacity. Furthermore, the constraints of the marine environment, such as sea conditions and weather conditions, and the level of salvage operations, add to the burden on the vessel.

[0005] In short, current fixed-wing UAV launch and recovery systems can only be installed as a payload on ships and vehicles, with a single function and unable to perform other functions. This technical field urgently needs to address the shortcomings of existing technologies and develop a UAV with a short takeoff distance, low recovery risk, and adaptable to a variety of takeoff weights and landing speeds. Summary of the Invention

[0006] The purpose of the present invention is to solve the technical problems of long taxiing distance required for UAV take-off and complicated recovery method.

[0007] In order to achieve the purpose of solving the above problems, the technical solution adopted by the present invention is to provide a tail-type launch and recovery UAV device, including a left vertical mounting surface, a right vertical mounting surface, a launch and recovery track, a sliding block, a traction rope, a traction motor, a recovery chain, a UAV and a UAV tail hook; a launch and recovery track is respectively provided on the upper end surface of the left vertical mounting surface and the right vertical mounting surface arranged in parallel; a sliding block is provided on the launch and recovery track; the sliding block is connected to the traction motor through a traction rope; a recovery chain is provided between the sliding blocks on the launch and recovery tracks on both sides; and a UAV tail hook is provided under the UAV.

[0008] Preferably, an angle is provided between the launch and recovery track and the horizontal plane so as to lift the head of the UAV.

[0009] Preferably, the sliding block is provided with a drone fixing interface for mounting the drone.

[0010] Preferably, a first sliding block is provided on the launch and recovery track of the left vertical mounting surface; and a second sliding block is provided on the launch and recovery track of the right vertical mounting surface.

[0011] Preferably, traction motor 1 and traction motor 2 are provided inside the left vertical mounting surface; traction motor 1 is connected to sliding block 1 through traction rope 1, and traction motor 2 is connected to sliding block 1 through traction rope 2; traction motor 3 and traction motor 4 are provided inside the right vertical mounting surface; traction motor 3 is connected to sliding block 2 through traction rope 3, and traction motor 4 is connected to sliding block 2 through traction rope 4.

[0012] Preferably, electrical disconnect sensors are provided at both ends of the launch and recovery track.

[0013] Preferably, a recovery safety net for recovering the drone is provided between the left vertical mounting surface and the right vertical mounting surface.

[0014] Preferably, electric push rods for extending and retracting the recovery safety net are respectively provided between the bottom of the recovery safety net and the left vertical mounting surface and the right vertical mounting surface.

[0015] Preferably, a buffer block is provided at the end of the launch and recovery track to prevent the sliding block from sliding out of the track.

[0016] Preferably, the number of the recycling chain is at least one.

[0017] Compared with the prior art, the present invention has the following beneficial effects:

[0018] The device's key components are concentrated on the interior and exterior surfaces of two vertical mounting surfaces, resulting in a compact footprint and suitable for installation in confined spaces. This makes it particularly suitable for small vessels with limited space. When equipped with a drone, the device provides additional torque, effectively reducing the bow height of a vessel at high speeds and improving navigation safety. The drone's fixed wings can be attached to the catapult, acting as a lifting element and generating torque relative to the center of the vessel. This prevents the bow from rising too high, ensuring safe navigation. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 It is a schematic diagram of the overall structure of the present invention;

[0020] Figure 2 It is a front view of the overall structure of the present invention;

[0021] Figure 3 It is a side view of the overall structure of the present invention;

[0022] Figure 4 This is a schematic diagram of the launch and recovery orbit in the present invention;

[0023] Figure 5 Schematic diagram of the structure of the fixed-wing UAV in the present invention.

[0024] Figure 6 Schematic diagram of the drive system structure of the present invention.

[0025] Figure markings: 1. Left vertical mounting surface; 2. Right vertical mounting surface; 3. Sliding block 1; 4. Sliding block 2; 5. UAV fixing interface; 6. Launch and recovery track; 7. Traction motor 1; 8. Traction motor 2; 9. Traction motor 3; 10. Traction motor 4; 11. Traction rope 1; 12. Traction rope 2; 13. Traction rope 3; 14. Traction rope 4; 15. UAV; 16. Electrical disconnect sensor 1; 17. Electrical disconnect sensor 2; 18. Recovery safety net; 19. Electric push rod; 20. UAV tail hook; 21. First recovery chain; 22. Second recovery chain. DETAILED DESCRIPTION

[0026] In order to make the present invention more clearly understood, preferred embodiments are described in detail below with reference to the accompanying drawings:

[0027] like Figure 1-6As shown, the present invention provides a tail-type drone launch and recovery device, comprising a left vertical mounting surface 1, a right vertical mounting surface 2, a launch and recovery track 6, a sliding block, a towing rope, a towing motor, a recovery chain, a drone 15, and a drone tail hook 20. The upper end surfaces of the left and right vertical mounting surfaces 1 and 2 are each provided with a launch and recovery track 6. A sliding block is provided on the launch and recovery track 6, which is connected to the towing motor via a towing rope. A recovery chain is provided between the sliding blocks on the launch and recovery tracks 6 on both sides. A drone tail hook 20 is provided below the drone 15. The launch and recovery track 6 is angled with the horizontal plane to allow the drone's head to rise. The sliding block is provided with a drone fixing interface 5 for mounting the drone 15. Slider 1 3 is provided on the launch and recovery track 6 of the left vertical mounting surface 1, and slider 2 4 is provided on the launch and recovery track 6 of the right vertical mounting surface 2. Traction motor 1 7 and traction motor 2 8 are installed within the left vertical mounting surface 1. Traction motor 1 7 is connected to slider 1 3 via traction rope 1 11, while traction motor 2 8 is connected to slider 1 3 via traction rope 2 12. Traction motor 3 9 and traction motor 4 10 are installed within the right vertical mounting surface 2. Traction motor 3 9 is connected to slider 2 4 via traction rope 3 13, while traction motor 4 10 is connected to slider 2 4 via traction rope 4 14. An electrical disconnect sensor is installed on the launch and recovery track 6. A recovery safety net 18 for recovering the drone 15 is installed between the left and right vertical mounting surfaces 1 and 2. Electric push rods 19 are installed between the bottom of the recovery safety net 18 and the left and right vertical mounting surfaces 1 and 2, respectively, for extending and retracting the recovery safety net. A buffer block is installed at the end of the launch and recovery track 6 to prevent the slider from sliding off the track. The number of recovery chains is set to at least one.

[0028] Installation of the device:

[0029] Traction motor 1 7, traction motor 2 8, traction motor 3 9, traction motor 4 10 are installed in the vertical mounting surface, and components such as sliding block 1 3, sliding block 2 4, launch and recovery track 6 are installed on the upper end surface of the vertical mounting surface.

[0030] The process of loading a drone:

[0031] The drone 15 is placed on the sliding block, and the drone 15 is interfaced with the drone fixed end of the device of the present invention to realize the function of carrying the drone in daily life.

[0032] Launch recovery orbit:

[0033] Electrical disconnect sensors and buffer blocks are installed at each end of the launch and recovery track. Once the slider 3 slides to the launch and recovery track's electrical disconnect sensor 16, the traction motor 7 automatically shuts off, and the slider 3 continues sliding forward by inertia until it strikes the buffer block and stops. Once the slider 3 slides to the launch and recovery track's electrical disconnect sensor 2 17, the traction motor 2 8 automatically shuts off, and the slider 3 continues sliding backward by inertia until it strikes the buffer block and stops.

[0034] Once the second slider 4 reaches the launch / recovery track's electrical disconnect sensor 16, the traction motor 3 9 automatically shuts off, and the second slider 4 continues sliding forward by inertia until the impact buffer stops. Once the second slider 4 reaches the launch / recovery track's electrical disconnect sensor 2 17, the traction motor 4 10 automatically shuts off, and the second slider 4 continues sliding backward by inertia until the impact buffer stops.

[0035] Slider 1 3 and Slider 2 4 move forward:

[0036] The sliding block slides forward as traction motor 17 tightens and retracts traction rope 11, while traction motor 28 releases traction rope 2 12. The speed at which the traction motors retract and release traction rope 11 and 12 determines the speed at which the sliding block 3 moves forward.

[0037] The sliding block slides forward when the traction motor 3 9 tightens and retracts the traction rope 3 13 and the traction motor 4 10 releases the traction rope 4 14. The speed at which the traction motor retracts and releases the traction rope 3 13 and the traction rope 4 14 determines the forward movement speed of the sliding block 2 4.

[0038] By simultaneously controlling the speed and response of traction motor 1 7 , traction motor 2 8 , traction motor 3 9 , and traction motor 4 10 , the synchronous forward movement of sliding block 1 3 and sliding block 2 4 is achieved.

[0039] Slider 1 3 and Slider 2 4 move backward:

[0040] The slider slides backward as traction motor 1 (7) releases traction rope 1 (11) and traction motor 2 (8) tightens and retracts traction rope 2 (12). The speed at which traction motors 1 (7) and 2 (8) release and retract traction rope 1 (11) and 12 determines the speed at which slider 1 (3) moves backward.

[0041] The sliding block slides backwards when traction motor 3 9 releases traction rope 3 13 and traction motor 4 10 tightens and retracts traction rope 4 14. The speed at which traction motors 3 9 and 4 10 release and retract traction rope 3 13 and 4 14 determines the speed at which sliding block 2 4 moves backwards.

[0042] Launch process:

[0043] By simultaneously controlling the speed and response of traction motors 1 (7), 2 (8), 3 (9), and 4 (10), sliders 1 (3) and 2 (4) move forward synchronously. As sliders 1 (3) and 2 (4) accelerate, they drive the drone forward, increasing its initial takeoff speed. When sliders 1 (3) and 2 (4) pass the electrical disconnect sensor 1 (16), traction motors 1 (7) and 3 (9) lose power, causing sliders 1 (3) and 2 (4) to lose forward acceleration. At this point, the drone reaches the required takeoff speed, detaches from its fixed end, and successfully takes off. The sliders continue to slide forward, impacting the buffer block and then stopping.

[0044] Recycling process:

[0045] The drone 15 has a tail hook 20 below its fuselage. When the drone 15 approaches the device of the present invention, the drone 15 reduces its flight speed and altitude.

[0046] When the drone's tail hook 20 hooks onto the first recovery chain 21 or the second recovery chain 22 of the present invention, the drone 15 drags the slider 1 3 and the slider 2 4 forward. Traction motor 2 8 then tightens the recovery traction rope 2 12, traction motor 1 7 releases the traction rope 1 11, traction motor 4 10 tightens the recovery traction rope 4 14, and traction motor 3 9 releases the traction rope 3 13. This creates backward resistance for the slider 1 3 and the slider 2 4, helping to decelerate the drone 15. When the sliders reach the buffer block position, the drone decelerates to the front of the recovery safety net 18, where it directly impacts the net and is recovered.

[0047] The above description is only a preferred embodiment of the present invention and does not limit the present invention in any form or substance. It should be pointed out that ordinary technicians in this technical field can make several improvements and supplements without departing from the present invention, and these improvements and supplements should also be regarded as the scope of protection of the present invention. Any equivalent changes, modifications and evolutions made by technicians familiar with this profession without departing from the spirit and scope of the present invention by using the technical content disclosed above are all equivalent embodiments of the present invention; at the same time, any equivalent changes, modifications and evolutions made to the above embodiments based on the essential technology of the present invention are still within the scope of the technical solution of the present invention.

Claims

1. A tail-type launch and recovery UAV device, characterized by: It includes a left vertical mounting surface, a right vertical mounting surface, a launch and recovery track, a sliding block, a towing rope, a traction motor, a recovery chain, a UAV and a UAV tail hook; the UAV can be fixed between the left vertical mounting surface and the right vertical mounting surface, generating a torque relative to the center of the ship, thereby reducing the height of the ship's head when sailing at high speed; a launch and recovery track is respectively provided on the upper end surface of the parallel left vertical mounting surface and the right vertical mounting surface; a sliding block is provided on the launch and recovery track; the sliding block is connected to the traction motor through a towing rope; a recovery chain is provided between the sliding blocks on the launch and recovery tracks on both sides; a UAV tail hook is provided under the UAV; an angle is provided between the launch and recovery track and the horizontal plane to lift the head of the UAV; a UAV fixing interface for installing the UAV is provided on the sliding block.

2. The tail-type launch and recovery UAV device according to claim 1, characterized in that: A first sliding block is provided on the launch and recovery track of the left vertical mounting surface; a second sliding block is provided on the launch and recovery track of the right vertical mounting surface.

3. The tail-type launch and recovery UAV device according to claim 2, characterized in that: A traction motor 1 and a traction motor 2 are provided inside the left vertical mounting surface; the traction motor 1 is connected to the sliding block 1 through the traction rope 1, and the traction motor 2 is connected to the sliding block 1 through the traction rope 2; a traction motor 3 and a traction motor 4 are provided inside the right vertical mounting surface; the traction motor 3 is connected to the sliding block 2 through the traction rope 3, and the traction motor 4 is connected to the sliding block 2 through the traction rope 4.

4. The tail-type launch and recovery UAV device according to claim 3, characterized in that: Electrical disconnect sensors are provided at both ends of the launch and recovery track.

5. The tail-type launch and recovery UAV device according to claim 4, characterized in that: A recovery safety net for recovering the drone is provided between the left vertical mounting surface and the right vertical mounting surface.

6. The tail-type launch and recovery UAV device according to claim 5, characterized in that: An electric push rod for extending and retracting the recovery safety net is respectively provided between the bottom of the recovery safety net and the left vertical mounting surface and the right vertical mounting surface.

7. The tail-type launch and recovery UAV device according to claim 6, characterized in that: A buffer block is provided at the end of the launch and recovery track for preventing the sliding block from sliding out of the track.

8. The tail-type launch and recovery UAV device according to claim 7, characterized in that: The number of the recycling chains is set to at least one.

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