A marine deployment and recovery device and method of use thereof

Abstract

This invention relates to the field of marine deployment and recovery technology, and in particular to a marine deployment and recovery device and its method of use. The marine deployment and recovery device includes a lift, a vehicle, and a connecting assembly. The lift is mounted on the vehicle, and the tail of the vehicle has a connecting portion. The lift is connected to the connecting assembly. The lift can drive the connecting assembly to move vertically to the connecting portion, and the connecting assembly can clamp onto the connecting portion. The connecting portion is retractable, and the lift can drive the connecting assembly to move vertically between the vehicle and the connecting portion, so that the vehicle and the connecting portion are clamped onto the connecting assembly. In summary, the marine deployment and recovery device of this invention has the advantages of simple and compact structure, small footprint, and light weight. It can improve the structural compactness of the vehicle on which the deployment and recovery device is mounted and effectively reduce the load pressure on the vehicle.

Description

Technical Field

[0001] This invention relates to the field of marine deployment and recovery technology, and in particular to a marine deployment and recovery device and its usage method. Background Technology

[0002] Currently, in fields such as marine resource exploration, maritime search and rescue, and marine environmental monitoring, it is often necessary to use vehicles (such as aircraft and ships) to carry underwater vehicles to target sea areas to complete the deployment and recovery operations. Generally, the vehicle is equipped with multiple components to realize the deployment and recovery functions. For example, the invention patent with publication number CN108146581B, entitled "A Deployment and Recovery Device for Underwater Equipment," uses a structure composed of hydraulic cylinders, winches, wire ropes, supports, springs, fixed pulleys, and remote-controlled release hooks to realize the deployment function, and a structure composed of pneumatic net guns, net ropes, throwing nets, and net sinkers to realize the recovery function. This kind of device is highly complex, relies on the coordination of multiple components, resulting in the device occupying a lot of space and being heavy, which in turn makes the vehicle structure bulky and under heavy load. Summary of the Invention

[0003] The purpose of this invention is to provide a marine deployment and recovery device and its usage method, in order to solve the technical problem that deployment and recovery devices installed on general vehicles used for deploying and recovering ships include many components, resulting in a bulky vehicle structure and high load pressure.

[0004] To achieve the above objectives, the present invention provides a marine deployment and recovery device, comprising a lift, a vehicle, and a connecting assembly. The lift is disposed on a vehicle, and the tail of the vehicle is provided with a connecting portion. The lift is connected to the connecting assembly. The lift can drive the connecting assembly to move vertically to the connecting portion. The connecting assembly can clamp and connect to the connecting portion. The connecting portion is retractable. The lift can also drive the connecting assembly to move vertically between the vehicle and the connecting portion, so that the vehicle and the connecting portion are clamped and connected to the connecting assembly.

[0005] Optionally, the connecting part includes a tail pin located at the tail of the vehicle. The connecting assembly includes a connecting block, a clamping electromagnet, and multiple clamping blocks. The bottom surface of the connecting block has a clamping hole. The clamping electromagnet and multiple clamping blocks are located within the clamping hole. The clamping hole has an inclined section. Each clamping block is located below the clamping electromagnet and is positioned corresponding to the inclined section. Each clamping block is arranged around the axis of the clamping hole, and a clamping channel is formed between each clamping block. The clamping electromagnet can be magnetically connected to each clamping block. The clamping electromagnet can apply a force in the vertical direction to each clamping block to clamp or release the connecting part. The lifter is connected to the connecting block.

[0006] Optionally, the connecting part includes a connector and a telescopic member. The tail of the aircraft is provided with a connecting hole, the telescopic member is disposed in the connecting hole, the connector is connected to the tail end of the telescopic member, the aircraft is provided with a telescopic actuator, the telescopic actuator is connected to the telescopic member, the telescopic actuator can drive the telescopic member to extend and retract along the axial direction of the connecting hole, thereby driving the connector to move along the axial direction of the connecting hole, and the connector can move to a first position and a second position.

[0007] When the connector is in the first position, the connecting component can be moved between the connector and the vehicle;

[0008] When the connector is in the second position, the connector and the vehicle can clamp the connection assembly.

[0009] Optionally, the telescopic actuator is an air pump, the telescopic component is a telescopic airbag, and the telescopic component is provided with a corrugated structure.

[0010] Optionally, the connecting assembly includes a connecting block, a connecting wire, an abutment block, and a retrieval driver. The lifter is connected to the connecting block. The connecting block has a wire cavity inside. The bottom surface of the connecting block has a wire hole that extends through the wire cavity. Both the connecting wire and the wire cavity are spiral-shaped, and the connecting wire is located in the wire cavity. The abutment block is located at the bottom end of the connecting wire. The retrieval driver can drive the connecting wire to move to a third position and a fourth position.

[0011] When the connecting line is in the third position, the connecting line is completely retracted into the wire cavity;

[0012] When the connecting line is in the fourth position, the connecting line extends downward through the wire hole and then moves between the connecting part and the aircraft.

[0013] Optionally, if a clamping hole is provided on the bottom surface of the connecting block, the connecting wire and the wire cavity are arranged around the clamping hole.

[0014] Optionally, the system further includes a first driver, a second driver, a first guide rail, a second guide rail, and multiple storage compartments. Each storage compartment is mounted on a vehicle and has a through-hole in the vertical direction for storing the vehicle. The multiple storage compartments are arranged horizontally. The first guide rail extends along a first direction and is mounted on the vehicle. The second guide rail is slidably connected to the first guide rail along the first direction and extends along a second direction. The elevator is slidably connected to the second guide rail along the second direction. The first driver is connected to the second guide rail, and the second driver is connected to the elevator. The first driver can drive the second guide rail to move along the first direction, and the second driver can drive the elevator to move along the second direction, so that the elevator moves horizontally, thereby enabling the connecting assembly to move horizontally above the through-hole of each storage compartment. The first and second directions have an angle greater than 0°.

[0015] Optionally, it also includes a storage compartment and a locking structure. The outer side wall of the vehicle is provided with a wing. The storage compartment is located on the vehicle and has a receiving hole that runs vertically through the storage compartment. The receiving hole is used to receive the vehicle. The bottom surface of the storage compartment has a wing hole that communicates with the receiving hole. The wing hole is used to receive the wing. The wall of the wing hole has a locking groove. The locking structure includes a locking device and a locking tongue. The locking tongue is located in the locking groove. The locking device is connected to the locking tongue. The locking device can drive the locking tongue to move to a fifth position and a sixth position.

[0016] When the latch is in the fifth position, the latch protrudes into the wing hole;

[0017] When the bolt is in the sixth position, the bolt is fully retracted into the lock groove.

[0018] Optionally, it also includes a connecting frame, a fixed pulley, an outer sleeve, an inner sleeve, and a lifting driver. The outer sleeve and the lifting device are fixedly mounted on the connecting frame. The connecting frame is slidably connected to the second guide rail in a second direction. The outer sleeve has a first cylindrical hole that extends vertically. The inner sleeve is slidably mounted in the first cylindrical hole in a vertical direction. The inner sleeve has a second cylindrical hole that extends vertically. The lifting driver is connected to the inner sleeve and can drive the inner sleeve to move vertically. The lifting device is a winch. The fixed pulley is located on the top surface of the outer sleeve. The winch rope of the lifting device is wound around the fixed pulley and passes through the first cylindrical hole and the second cylindrical hole. The winch rope of the lifting device is connected to the connecting assembly.

[0019] The present invention also relates to a method of using the aforementioned marine deployment and recovery device, the deployment method comprising the following steps:

[0020] S1. The elevator drive connection assembly moves downward to the gap between the connection part and the aircraft;

[0021] S2, The connecting component clamps the connecting part;

[0022] S3. The elevator drive connection assembly moves downward, thus moving the aircraft downward.

[0023] S4. The connecting component releases the connecting part;

[0024] The recycling method includes the following steps:

[0025] S5. The lifting device drive connection assembly moves downward to the connection part;

[0026] S6, Connector and vehicle clamping connection assembly;

[0027] S7. The elevator drive connection assembly moves upward, thereby moving the aircraft upward.

[0028] S8, Release the vehicle from the connecting section.

[0029] Compared with existing technologies, the advantages of the marine deployment and recovery device and its usage method implemented in this invention are as follows:

[0030] In the deployment and retrieval device of this invention, a lift is mounted on a carrier and connected to a connecting assembly. The lift can drive the connecting assembly to move vertically. Furthermore, when a vehicle needs to be deployed, the vehicle is positioned vertically on the carrier with the connecting part facing upwards. The lift drives the connecting assembly to move to the connecting part at the tail of the vehicle. The connecting assembly actively clamps the connecting part, fixing the connecting assembly to the connecting part. Then, the lift drives the connecting assembly and the vehicle downwards until the vehicle is a certain distance from the sea surface or the vehicle touches the seawater. The connecting assembly releases the connecting part, causing the vehicle to fall into the seawater, thus completing the deployment operation. When the vehicle needs to be retrieved, the vehicle is positioned horizontally in the seawater with the connecting part extended, forming a certain gap between the connecting part and the vehicle. The lift drives the connecting assembly... The component moves into the sea and into the gap between the connector and the vehicle. The connector retracts, clamping the vehicle and the connector together from both sides to secure them to the connector. Then, the elevator drives the connector and the vehicle upward into the vehicle. The connector extends, releasing the connector to achieve the recovery of the vehicle. In summary, the present invention, a marine deployment and recovery device and its method, achieves the deployment and recovery of a vehicle by using an elevator to drive the connector to rise and fall, the connector clamping the connector, and the connector and the vehicle clamping the connector. It has the advantages of simple structure, compact structure, small space occupation, and light weight. It can improve the structural compactness of the vehicle on which the deployment and recovery device is installed and effectively reduce the load pressure on the vehicle. Attached Figure Description

[0031] Figure 1 This is a schematic diagram of the structure of the marine deployment and recovery device of the present invention.

[0032] Figure 2 This is a front view of the marine deployment and recovery device of the present invention.

[0033] Figure 3 This is a top view of the marine deployment and recovery device of the present invention.

[0034] Figure 4 for Figure 3 Sectional view of AA.

[0035] Figure 5 for Figure 4 A magnified view of part B in the middle.

[0036] Figure 6 A cross-sectional view of the clamping connection part of the connecting component.

[0037] Figure 7 Release the cross-sectional view of the connecting part for the connecting component.

[0038] Figure 8 for Figure 4 A magnified view of part C in the middle.

[0039] Figure 9 This is a schematic diagram of the structure where the connecting line extends into the gap between the aircraft and the connector.

[0040] Figure 10 A schematic diagram of the structure for suspending the connecting part and the aircraft by the connecting line.

[0041] Figure 11 This is a schematic diagram of the structure of the marine deployment and recovery device of the present invention mounted on a vehicle.

[0042] Figure 12 This is a flowchart illustrating a method for deploying marine deployment and recovery devices using the present invention.

[0043] Figure 13 This is a flowchart of a method for recovery using the marine deployment and recovery device of the present invention.

[0044] Reference numerals: 1. Connecting assembly; 11. Connecting block; 111. Clamping hole; 112. Inclined hole section; 113. Wire cavity; 114. Wire hole; 12. Clamping electromagnet; 13. Clamping block; 14. Clamping channel; 15. Spring; 16. Baffle; 17. Connecting wire; 18. Abutting block; 2. Aircraft; 21. Connecting hole; 3. Connecting part; 31. Tail pin; 32. Connecting head; 33. Telescopic component; 4. Wing; 5. Elevator; 6. First guide rail; 7. Second guide rail; 8. Storage compartment; 81. Receiving hole; 82. Wing hole; 83. Locking groove; 9. Locking structure; 91. Locking tongue; 10. Connecting frame; 20. Fixed pulley; 30. Outer sleeve; 301. First cylinder hole; 40. Inner sleeve; 401. Second cylinder hole; 50. Carrier. Detailed Implementation

[0045] The specific embodiments of the present invention will be described in further detail below with reference to the accompanying drawings and examples. The following examples are for illustrative purposes only and are not intended to limit the scope of the invention.

[0046] In the description of this invention, it should be understood that the terms "top", "bottom", "inner", "outer", "circumferential", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this invention.

[0047] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this invention, "a plurality of" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0048] Furthermore, in this invention, vehicle 50 refers to a means of transportation that can navigate on the sea or in the air, including but not limited to airplanes and ships.

[0049] like Figures 1 to 11 As shown, a marine deployment and recovery device of the present invention includes a lift 5, a vehicle 2, and a connecting assembly 1. The lift 5 is disposed on a carrier 50. The tail of the vehicle 2 is provided with a connecting part 3. The lift 5 is connected to the connecting assembly 1. The lift 5 can drive the connecting assembly 1 to move in the vertical direction to the connecting part 3. The connecting assembly 1 can clamp and connect to the connecting part 3. The connecting part 3 is retractable. The lift 5 can drive the connecting assembly 1 to move in the vertical direction between the vehicle 2 and the connecting part 3, so that the vehicle 2 and the connecting part 3 are clamped and connected to the connecting assembly 1.

[0050] In the above technical solution, the lifting device 5 is located on the carrier 50 and connected to the connecting assembly 1. The lifting device 5 can drive the connecting assembly 1 to move vertically. Furthermore, when the vehicle 2 needs to be deployed, the vehicle 2 is positioned vertically on the carrier 50 with the connecting part 3 facing upwards. The lifting device 5 drives the connecting assembly 1 to move to the connecting part 3 at the tail of the vehicle 2. The connecting assembly 1 actively clamps the connecting part 3, fixing the connecting assembly 1 to the connecting part 3. Then, the lifting device 5 drives the connecting assembly 1 and the vehicle 2 downwards until the vehicle 2 is a certain distance from the sea surface or the vehicle 2 touches the seawater. The connecting assembly 1 releases the connecting part 3, causing the vehicle 2 to fall into the seawater, thus achieving the deployment of the vehicle 2. When the vehicle 2 needs to be retrieved, the vehicle 2 is positioned horizontally in the seawater, and the connecting part 3 is in an extended state, forming a certain gap between the connecting part 3 and the vehicle 2. The lifting device 5 drives the connecting assembly 1 to move downwards. Component 1 moves to the sea and into the gap between connecting part 3 and vehicle 2. Connecting part 3 retracts, clamping vehicle 2 and connecting part 3 from both sides to connect component 1, thus fixing vehicle 2 and connecting part 3 to connecting component 1. Then, elevator 5 drives connecting component 1 and vehicle 2 upward into carrier 50. Connecting part 3 extends, releasing connecting component 1 to achieve the recovery operation of vehicle 2. In summary, the present invention's marine deployment and recovery device and its method of use, through elevator 5 driving connecting component 1 to rise and fall, connecting component 1 clamping connecting part 3, and connecting part 3 and vehicle 2 clamping connecting component 1, achieves the functions of deploying and recovering vehicle 2. It has the advantages of simple structure, compact structure, small space occupation, and light weight, which can improve the compactness of the structure of carrier 50 where the deployment and recovery device is installed, and effectively reduce the load pressure of carrier 50.

[0051] In addition, the deployment notch and the recovery notch on the vehicle 50 can be the same, or a separate notch can be set up specifically for recovery to facilitate recovery.

[0052] Furthermore, such as Figure 6 and 7As shown, the connecting part 3 includes a tail pin 31, which is located at the tail of the vehicle 2. The connecting assembly 1 includes a connecting block 11, a clamping electromagnet 12, and a plurality of clamping blocks 13. The bottom surface of the connecting block 11 is provided with a clamping hole 111. The clamping electromagnet 12 and the plurality of clamping blocks 13 are located in the clamping hole 111. The clamping hole 111 is provided with an inclined hole section 112. Each clamping block 13 is located below the clamping electromagnet 12 and is arranged corresponding to the inclined hole section 112. Each clamping block 13 is arranged around the axis of the clamping hole 111, and a clamping channel 14 is formed between each clamping block 13. The clamping electromagnet 12 can be magnetically connected to each clamping block 13. The clamping electromagnet 12 can apply a force in the vertical direction to each clamping block 13 to clamp or release the connecting part 3. The lifter 5 is connected to the connecting block 11.

[0053] When the clamping electromagnet 12 is energized, it can attract the clamping block 13, causing it to move upward, or repel the clamping block 13, causing it to move downward. Furthermore, when the clamping block 13 moves towards the side with the smaller diameter of the inclined hole section 112, it moves along the hole wall of the inclined hole section 112 while moving vertically. The clamping blocks 13 move closer to each other, causing the horizontal cross-section of the clamping channel 14 to decrease. If at this time, the tail pin 31 is inserted into the clamping channel 14... The clamping blocks 13, which are close to each other, clamp the tail pin 31, connecting the connecting assembly 1 and the aircraft 2. With each clamping block 13 clamping the tail pin 31, when the clamping block 13 moves towards the side with the larger diameter of the inclined hole section 112, the clamping block 13 moves vertically, releasing the tail pin 31. The clamping blocks 13 move slightly apart, slightly increasing the horizontal cross-section of the clamping channel 14 to release the aircraft 2. Furthermore, the clamping electromagnet 12 exerts force on the clamping blocks 13... When the clamping block 13 clamps the tail needle 31, and the clamping electromagnet 12 stops exerting force on the clamping block 13, the clamping block 13 releases the tail needle 31 through the opposite force generated by the elastic element (spring 15) or gravity. Furthermore, the lifting device 5 is connected to the connecting block 11, and the lifting device 5 drives the connecting block 11 to move vertically, so that the connecting assembly 1 connected to the vehicle 2 can move to a position a certain distance from the water surface or into the seawater to prevent damage to the vehicle 2. In summary, the marine deployment device of the present invention does not occupy a large space and does not require additional drives or transmission mechanisms to assist in the operation. Therefore, the marine deployment device occupies little space, is lightweight, and has good compactness.

[0054] In addition, if it is necessary to apply a repulsive force to the clamping block 13 after the clamping electromagnet 12 is energized, the magnetic poles at the lower end of the clamping electromagnet 12 and the magnetic poles at the upper end of the clamping block 13 shall be of the same polarity.

[0055] In some embodiments, the horizontal distance between the axes of the inclined hole segment 112 and the clamping hole 111 gradually increases from top to bottom, so that the inclined hole segment 112 has a structure that is narrow at the top and wide at the bottom.

[0056] In these embodiments, when the clamping electromagnet 12 or the elastic element applies an upward force to the clamping block 13, each clamping block 13 moves along the inclined hole section 112, causing the clamping blocks 13 to move closer to each other, thereby reducing the area of ​​the horizontal cross-section of the clamping channel 14 to clamp the tail needle 31. Gravity or the clamping electromagnet 12 applies a downward force to the clamping block 13, causing the clamping block 13 to release the tail needle 31. The scheme of the clamping electromagnet 12 applying an upward force corresponds to the scheme of gravity applying a downward force to the clamping block 13, and the scheme of the elastic element applying an upward force corresponds to the scheme of the clamping electromagnet 12 applying a downward force.

[0057] In other embodiments, the horizontal distance between the axes of the inclined hole segment 112 and the clamping hole 111 gradually decreases from top to bottom, so that the inclined hole segment 112 has a structure that is wider at the top and narrower at the bottom.

[0058] In these embodiments, when the clamping electromagnet 12, the elastic element, or gravity applies a downward force to the clamping blocks 13, each clamping block 13 moves along the inclined hole section 112, causing the clamping blocks 13 to move closer to each other. This reduces the area of ​​the horizontal cross-section of the clamping channel 14, thus clamping the tail needle 31. The elastic element or the clamping electromagnet 12 applies an upward force to the clamping blocks 13, causing the clamping blocks 13 to release the tail needle 31. Specifically, the scheme of the clamping electromagnet 12 applying a downward force corresponds to the scheme of the elastic element applying a downward force to the clamping blocks 13, the scheme of the elastic element applying a downward force corresponds to the scheme of the clamping electromagnet 12 applying an upward force, and the scheme of gravity applying a downward force corresponds to the scheme of the clamping electromagnet 12 applying an upward force.

[0059] In addition, as the aforementioned distance gradually decreases, when each clamping block 13 moves along the inclined hole section 112 to the point where the horizontal cross-sectional area of ​​the clamping channel 14 is 0, each clamping block 13 abuts against each other, preventing each clamping block 13 from falling out of the clamping hole 111.

[0060] Furthermore, the connecting assembly 1 also includes a spring 15 disposed in the clamping hole 111, the spring 15 abutting against the clamping electromagnet 12 and the clamping block 13, the spring 15 being used to apply a force in the up-down direction to each of the clamping blocks 13.

[0061] The spring 15 continuously applies a force to the clamping block 13 in the opposite direction to the magnetic force applied by the clamping electromagnet 12 to the clamping block 13. The spring 15 continuously applies a force to the clamping block 13 less than the magnetic force applied by the clamping electromagnet 12 to the clamping block 13. Furthermore, the two ends of the spring 15 can respectively abut against the clamping electromagnet 12 and each clamping block 13, or they can be respectively fixedly connected to the clamping electromagnet 12 and each clamping block 13, depending on the specific situation.

[0062] Alternatively, one spring 15 can be provided along the axis of the clamping hole 111 and connected to each clamping block 13, or multiple springs can be provided and connected to each clamping block 13 respectively.

[0063] Furthermore, the connecting assembly 1 also includes a baffle 16 disposed in the clamping hole 111, the baffle 16 being disposed on the top surface of each clamping block 13, the spring 15 being connected to the top surface of the baffle 16, and the baffle 16 being connected to the top surface of each clamping block 13.

[0064] The baffle 16 is disposed on the top surface of each clamping block 13 so that the spring 15 can apply force evenly to each clamping block 13 through the baffle 16, avoiding uneven force on each clamping block 13 and thus different height positions between the clamping blocks 13; in addition, if the clamping electromagnet 12 needs to apply a repulsive force to the clamping block 13, the baffle 16 can be made into a magnet, with the magnetic poles on the top surface of the baffle 16 being the same as the magnetic poles on the bottom surface of the clamping electromagnet 12. The clamping electromagnet 12 applies a downward repulsive force to the baffle 16, thereby applying a downward force evenly to each clamping block 13; in addition, the baffle 16 can abut against the clamping block 13 or be magnetically connected to the clamping block 13.

[0065] Furthermore, the spring 15 is arranged along the axis of the clamping hole 111 so that the spring 15 can apply force to the baffle 16 along the axis of the clamping hole 111, thereby ensuring that the baffle 16 can apply force evenly to each clamping block 13 and avoid uneven force distribution.

[0066] Furthermore, such as Figures 8 to 10As shown, the connecting part 3 includes a connector 32 and a telescopic member 33. The tail of the aircraft 2 is provided with a connecting hole 21, the telescopic member 33 is disposed in the connecting hole 21, the connector 32 is connected to the tail end of the telescopic member 33, the aircraft 2 is provided with a telescopic actuator, the telescopic actuator is connected to the telescopic member 33, the telescopic actuator can drive the telescopic member 33 to extend and retract along the axial direction of the connecting hole 21, thereby driving the connector 32 to move along the axial direction of the connecting hole 21. The connector 32 can move to a first position and a second position. When the connector 32 is in the first position, the connecting assembly 1 can move between the connector 32 and the aircraft 2. When the connector 32 is in the second position, the connector 32 and the aircraft 2 can clamp the connecting assembly 1.

[0067] When the connector 32 is in the first position, there is a large gap between the connector 32 and the vehicle 2. The lift 5 can drive the connecting block 11 to move downward, thereby moving the connecting assembly 1 downward between the connector 32 and the vehicle 2. When the connector 32 moves from the first position to the second position, the gap between the connector 32 and the vehicle 2 narrows, and the connector 32 and the vehicle 2 abut against the connecting assembly 1 from both sides to clamp the connecting assembly 1. At this time, the lift 5 lifts the connecting assembly 1, the vehicle 2 and the connecting part 3 upward to continue the recovery operation.

[0068] In addition, the outer diameter of the connector 32 should be larger than the outer diameter of the telescopic member 33, so that when the telescopic member 33 extends along its axial direction, there can be a gap between the connector 32 and the aircraft 2 that can accommodate the connecting component 1, and when the telescopic member 33 shortens along its axial direction, the connector 32 and the aircraft 2 can abut against each other.

[0069] In some embodiments, the telescopic actuator is a motor or piston cylinder (pneumatic cylinder, hydraulic cylinder or electric cylinder) to drive the telescopic member 33 to extend or retract axially along the connecting hole 21.

[0070] In other embodiments, the telescopic actuator is an air pump, the telescopic member 33 is a telescopic airbag, and the telescopic member 33 is provided with a corrugated structure.

[0071] The telescopic component 33 is a telescopic airbag with a corrugated structure, similar to the structure on a bellows. When the air pump inflates the telescopic component 33, the amount of gas inside the telescopic component 33 increases, the corrugated structure expands, and the telescopic component 33 extends along its axial direction, so that the connecting part 3 and the tail end of the vehicle 2 face obliquely upward. This allows parts of the connecting head 32 and the telescopic component 33 to extend above the water surface, facilitating the movement of the connecting assembly 1 to the gap between the connecting head 32 and the vehicle 2. In addition, if the connecting head 32 and the telescopic component 33 are equipped with a signal transmitter and a signal receiver, since parts of the connecting head 32 and the telescopic component 33 are above the water surface, the signal transmitter and signal receiver can transmit and receive signals more effectively. When the air pump evacuates the air, the amount of gas inside the telescopic component 33 decreases, the corrugated structure folds up, and the telescopic component 33 shortens along its axial direction.

[0072] Furthermore, such as Figures 5 to 10 As shown, the connecting assembly 1 includes a connecting block 11, a connecting line 17, an abutment block 18, and a retrieval driver. The elevator 5 is connected to the connecting block 11. The connecting block 11 has a wire cavity 113 inside, and the bottom surface of the connecting block 11 has a wire hole 114 that extends through the wire cavity 113. Both the connecting line 17 and the wire cavity 113 are spiral-shaped, and the connecting line 17 is located in the wire cavity 113. The abutment block 18 is located at the bottom end of the connecting line 17. The retrieval driver can drive the connecting line 17 to move to a third position and a fourth position. When the connecting line 17 is in the third position, the connecting line 17 is completely retracted into the wire cavity 113. When the connecting line 17 is in the fourth position, the connecting line 17 extends downward out of the wire hole 114 and then moves between the connecting part 3 and the aircraft 2.

[0073] When the connector 32 is in the first position, there is a large gap between the connector 32 and the vehicle 2. The elevator 5 can drive the connecting block 11 to move downward, thereby moving the connecting line 17 downward to the space between the connector 32 and the vehicle 2. When the connector 32 moves from the first position to the second position, the gap between the connector 32 and the vehicle 2 narrows, and the connector 32 and the vehicle 2 abut against the connecting line 17 from both sides to clamp the connecting line 17. At this time, the elevator 5 lifts the connecting block 11, the connecting line 17, the vehicle 2 and the connecting part 3 upward to continue the recovery operation. Furthermore, after the vehicle 2 and the connecting part 3 leave the water surface, since the connecting line 17 is connected to the tail of the vehicle 2, the vehicle 2 is lifted and recovered into the aircraft in a posture with the tail facing up or diagonally up and the head facing down or diagonally down (vertical posture or near-vertical tilted posture). In summary, the alignment operation can be achieved by moving the connecting line 17 between the connector 32 and the vehicle 2, which reduces the difficulty of recovery. Moreover, the vehicle 2 can be lifted in a vertical or near-vertical tilted position and recovered into the aircraft. During the recovery of the vehicle 2, the horizontal cross-sectional area of ​​the vehicle 2 is small, which allows the aircraft to use a smaller recovery port for recovery, thus having a smaller impact on the aircraft's aerodynamics, structural complexity, and structural strength.

[0074] When the connecting line 17 moves between the connector 32 and the vehicle 2, the spiral connecting line 17 is wrapped around the telescopic member 33. When the connector 32 and the vehicle 2 clamp the connecting line 17, it can clamp the connecting line 17 at more positions, which can effectively improve the stability and reliability of clamping.

[0075] When the connecting line 17 and the connecting part 3 slide relative to the vehicle 2, the abutment block 18 abuts against the connecting part 3 and the vehicle 2, which can prevent the connecting line 17 and the connecting part 3 from sliding further relative to the vehicle 2, so as to avoid the connecting line 17 from detaching from the connecting part 3 and the vehicle 2; in addition, the abutment block 18 can be a spherical component, and the diameter of the abutment block 18 is larger than the diameter of the connecting line 17.

[0076] The recovery drive can be a winch, which changes the position of the bottom end of the connecting line 17 by pushing and pulling along the axial direction of the connecting line 17. This structure can drive the connecting line 17 to move more directly and reduce redundant mechanisms and actions.

[0077] When not in operation, the connecting wire 17 is in the third position and is completely retracted into the wire cavity 113, which can prevent the connecting wire 17 from getting tangled with other components, reduce safety hazards, and the wire cavity 113 is integrated into the connecting block 11, reducing the overall space occupied by the connecting component 1.

[0078] The connecting wire 17 can be a stainless steel wire rope, which, after being pushed into the wire cavity 113, can be plastically deformed into a spiral shape along the spiral structure of the wire cavity 113, and maintains the spiral structure after extending out of the wire hole 114.

[0079] Furthermore, the telescopic member 33, the connector 32, and the tail pin 31 are connected in sequence.

[0080] Furthermore, the outer diameter of the connector 32 is greater than the outer diameter of the telescopic member 33, which is greater than the outer diameter of the tail pin 31.

[0081] Furthermore, if the area of ​​the horizontal cross-section of the clamping channel 14 is large enough, the connector 32 can be used as a tail pin 31.

[0082] Furthermore, such as Figures 5 to 7 As shown, when the bottom surface of the connecting block 11 is provided with a clamping hole 111, the connecting line 17 and the wire cavity 113 are arranged around the clamping hole 111, so that the components for deployment and the components for retrieval on the connecting assembly 1 can work along the same axis. This not only makes the connecting assembly 1 occupy less space, has higher space utilization and better compactness, but also simplifies the control logic and makes it convenient for the components for deployment and the components for retrieval to pass through the same hole to carry out operations.

[0083] Furthermore, such as Figures 1 to 4 As shown, it also includes a first driver, a second driver, a first guide rail 6, a second guide rail 7, and multiple storage compartments 8. The storage compartments 8 are disposed on the vehicle 50 and have a receiving hole 81 that runs vertically through the vehicle. The receiving hole 81 is used to store the vehicle 2. The multiple storage compartments 8 are arranged horizontally. The first guide rail 6 extends along a first direction and is disposed on the vehicle 50. The second guide rail 7 is slidably connected to the first guide rail 6 along the first direction and extends along a second direction. The elevator 5 is slidably connected to the second guide rail 7 along the second direction. The first driver is connected to the second guide rail 7 and the second driver is connected to the elevator 5. The first driver can drive the second guide rail 7 to move along the first direction, and the second driver can drive the elevator 5 to move along the second direction, so that the elevator 5 moves horizontally, thereby driving the connecting assembly 1 to move horizontally above the receiving hole 81 of each storage compartment 8. The first direction and the second direction have an angle greater than 0°.

[0084] The first guide rail 6 is fixedly installed on the carrier 50 and provides guidance for the second guide rail 7 in the first direction. The second guide rail 7 is slidably connected to the first guide rail 6 and provides guidance for the elevator 5 in the second direction, so that the elevator 5 can move above each storage compartment 8, thereby enabling the connecting component 1 to perform operations corresponding to each storage compartment 8.

[0085] Furthermore, such as Figures 1 to 4 ,and Figure 8 As shown, the aircraft 2 has wings 4 on both sides, and the bottom surface of the storage compartment 8 has two wing holes 82 extending in the vertical direction. The wing holes 82 are used to accommodate the wings 4. The horizontal cross section of the storage compartment 8 is rhomboid. The two wing holes 82 are spaced apart along the long diagonal of the rhomboid of the storage compartment 8 and are located on both sides of the receiving hole 81. The wing holes 82 are connected to the receiving hole 81.

[0086] The storage compartment 8 is designed with a horizontal cross-section of rhombus, and two wing holes 82 are spaced apart on both sides of the receiving hole 81 along the long diagonal of the rhombus to adapt to the structure of the aircraft 2 with wings 4 on both sides. This reduces the area with greater thickness in the storage compartment 8, decreases the redundant space occupied by the storage compartment 8, and thus improves the space utilization of the storage compartment 8.

[0087] Furthermore, multiple storage compartments 8 arranged sequentially along the first direction form a storage combination. The long diagonals of the rhombuses of each storage compartment 8 in a storage combination are collinear. Multiple storage combinations are arranged sequentially along the second direction. The long diagonals of the rhombuses of the storage compartments 8 in different storage combinations are parallel. The storage compartments 8 in adjacent storage combinations are staggered. The side of a storage compartment 8 in one storage combination is attached to the side of a storage compartment 8 in another adjacent storage combination.

[0088] In this configuration, the long diagonals of the rhombuses of the storage compartments 8 in a group of storage combinations are collinear, and the long diagonals of the rhombuses of the storage compartments 8 in different storage combinations are parallel, so that each storage compartment 8 is set in the same orientation. Combined with the features that the storage compartments 8 in a group of storage combinations are arranged sequentially along a first direction, multiple groups of storage combinations are arranged sequentially along a second direction, the storage compartments 8 in adjacent storage combinations are staggered, and the side of the storage compartment 8 in one storage combination is attached to the side of the storage compartment 8 in another adjacent storage combination, the storage compartments 8 are arranged neatly, and the gaps between the storage compartments 8 are reduced, thereby improving the space utilization of the storage device.

[0089] Furthermore, it also includes a storage compartment 8 and a locking structure 9. The outer wall of the aircraft 2 is provided with a wing 4. The storage compartment 8 is located on the carrier 50. The storage compartment 8 is provided with a receiving hole 81 that runs vertically through the space. The receiving hole 81 is used to receive the aircraft 2. The bottom surface of the storage compartment 8 is provided with a wing hole 82 that communicates with the receiving hole 81. The wing hole 82 is used to receive the wing 4. The hole wall of the wing hole 82 is provided with a locking groove 83. The locking structure 9 includes a locking device and a locking tongue 91. The locking tongue 91 is located in the locking groove 83. The locking device is connected to the locking tongue 91. The locking device can drive the locking tongue 91 to move to a fifth position and a sixth position. When the locking tongue 91 is in the fifth position, the locking tongue 91 protrudes into the wing hole 82. When the locking tongue 91 is in the sixth position, the locking tongue 91 is completely retracted into the locking groove 83.

[0090] The locking structure 9 is used to prevent the vehicle 2 located in the storage compartment 8 from falling downwards. Specifically, when the locking tongue 91 is in the fifth position, the locking tongue 91 protrudes horizontally into the wing hole 82, and the locking tongue 91 abuts against the wing 4 to prevent the vehicle 2 from falling downwards. When deploying the vehicle 2, when the locking tongue 91 moves to the sixth position, the locking tongue 91 is located outside the wing hole 82, and there is no object below the vehicle 2 and the wing 4 to prevent them from falling downwards, so the vehicle 2 and the wing 4 can move downwards.

[0091] The locking device may include a locking electromagnet and a spring 15. The locking electromagnet is magnetically connected to the latch 91, and the two ends of the spring 15 are connected to the latch 91 and the storage compartment 8. Specifically, the locking electromagnet can attract or repel the latch 91 to move to a first position, and the spring 15 can reset the latch 91 to a second position. Alternatively, the locking electromagnet can attract or repel the latch 91 to move to a second position, and the spring 15 can reset the latch 91 to the first position.

[0092] Alternatively, the locking device can be a motor or a piston cylinder (pneumatic cylinder, electric cylinder, or hydraulic cylinder). The locking device is connected to the locking tongue 91 and can directly drive the locking tongue 91 to move in a straight line to the first position and the second position.

[0093] Furthermore, such as Figures 1 to 4As shown, it also includes a connecting frame 10, a fixed pulley 20, an outer sleeve 30, an inner sleeve 40, and a lifting driver. The outer sleeve 30 and the lifting device 5 are fixedly mounted on the connecting frame 10. The connecting frame 10 is slidably connected to the second guide rail 7 in a second direction. The outer sleeve 30 has a first cylindrical hole 301 that extends in the vertical direction. The inner sleeve 40 is slidably mounted in the first cylindrical hole 301 in the vertical direction. The inner sleeve 40 has a second cylindrical hole 401 that extends in the vertical direction. The lifting driver is connected to the inner sleeve 40 and can drive the inner sleeve 40 to move in the vertical direction. The lifting device 5 is a winch. The fixed pulley 20 is located on the top surface of the outer sleeve 30. The winch rope of the lifting device 5 is wound around the fixed pulley 20 and passes through the first cylindrical hole 301 and the second cylindrical hole 401. The winch rope of the lifting device 5 is connected to the connecting assembly 1.

[0094] The outer sleeve 30 is used to install the fixed pulley 20 and provide vertical guidance for the inner sleeve 40. The inner sleeve 40 can provide vertical guidance for the connecting block 11. The connecting block 11 can move vertically into the second cylindrical hole 401 and slide to the second cylindrical hole 401. When the inner sleeve 40 is slidably connected to the first cylindrical hole 301 and the connecting block 11 is slidably connected to the second cylindrical hole 401, the impact of the shaking generated by the carrier 50 on the connecting assembly 1 can be reduced, so that the connecting assembly 1 can be aligned with the target for operation. Furthermore, the inner sleeve 40 can also adjust the range of the connecting block 11's stable alignment with the target by sliding vertically in the first cylindrical hole 301. When not in operation, the inner sleeve 40 is retracted as much as possible into the first sleeve and the connecting block 11 is retracted as much as possible into the second cylindrical hole 401 to reduce the space occupied by the outer sleeve 30, the inner sleeve 40 and the connecting assembly 1, and to prevent the aforementioned components from colliding with other components.

[0095] like Figure 11 and 12 As shown, this embodiment also relates to a method of using the aforementioned marine deployment and recovery device, the deployment method comprising the following steps:

[0096] S1. The lifting device 5 drives the connecting assembly 1 to move downward to the connecting part 3, so that the tail pin 31 is inserted into the clamping channel 14.

[0097] S2. The clamping electromagnet 12 applies a force to each clamping block 13, causing each clamping block 13 to move closer to each other and reducing the area of ​​the horizontal cross section of the clamping channel 14, thereby causing the connecting assembly 1 to clamp the connecting part 3.

[0098] S3, the lifting device 5 pushes out the winch, drives the connecting assembly 1 to move downward, and moves the vehicle 2 downward until the vehicle 2 is a certain distance from the water surface or is in the seawater.

[0099] S4. The clamping electromagnet 12 stops applying force to each clamping block 13, causing each clamping block 13 to release the tail pin 31, and the connecting assembly 1 releases the connecting part 3, allowing the vehicle 2 to fall into the sea and complete the deployment operation.

[0100] Additionally, between steps S2 and S3, the locking device drives the bolt 91 to retract into the lock groove 83.

[0101] The recycling method includes the following steps:

[0102] S5, the elevator 5 pushes out the winch rope, driving the connecting assembly 1 to move downward, so that the connecting line 17 is located in the gap between the connecting part 3 and the aircraft 2.

[0103] S6, the connecting part 3 shortens, and the connecting part 3 and the aircraft 2 clamp the connecting line 17 from both sides;

[0104] S7. The lifting device 5 pulls the winch rope, driving the connecting component 1 to move upward, and causing the vehicle 2 to move upward. After the vehicle 2 leaves the water surface, it is in a vertical or nearly vertical tilted position.

[0105] S8. When the vehicle 2 is lifted into the carrier 50, the connecting part 3 extends to release the vehicle 2 and complete the recovery operation.

[0106] Before step S5, the connecting part 3 extends to create a larger gap between the connecting part 3 and the aircraft 2.

[0107] Additionally, in step S8, the aircraft 2 can be lifted into the receiving hole 81. At this time, after the wing 4 passes through the locking tongue 91, the locking device drives the locking tongue 91 to block the wing hole 82 to prevent the aircraft 2 from falling.

[0108] Furthermore, fixed setting and fixed connection refer to the fixed relative positional relationship of two components, including but not limited to fixing by connectors, fixing by welding, fixing by adhesive, fixing by integral molding, and fixing by snap-fit ​​connection.

[0109] Furthermore, sliding connection and sliding setting refer to the connection between two connected components, where one component can slide along a fixed trajectory on the other component, including but not limited to connection by sliding a slider into a groove, or connection by inserting a slider into a hole whose size and profile match the slider.

[0110] Furthermore, the connectors include, but are not limited to, fasteners, straps, ropes, pneumatic connectors, hydraulic connectors, flanges, Velcro, and buttons.

[0111] Furthermore, other actuators not explained in this embodiment may be motors, piston cylinders (pneumatic cylinders, electric cylinders, or hydraulic cylinders).

[0112] In summary, the embodiments of the present invention provide a marine deployment and recovery device and its usage method, the technical effects of which are as follows:

[0113] In the deployment and recovery device of this invention, a lift 5 is installed on a carrier 50 and connected to a connecting assembly 1. The lift 5 can drive the connecting assembly 1 to move vertically. Furthermore, when it is necessary to deploy the vehicle 2, the vehicle 2 is positioned vertically on the carrier 50 with the connecting part 3 facing upwards. The lift 5 drives the connecting assembly 1 to move to the connecting part 3 at the tail of the vehicle 2. The connecting assembly 1 actively clamps the connecting part 3, fixing the connecting assembly 1 to the connecting part 3. Then, the lift 5 drives the connecting assembly 1 and the vehicle 2 downwards until the vehicle 2 is a certain distance from the sea surface or touches the seawater. The connecting assembly 1 releases the connecting part 3, causing the vehicle 2 to fall into the seawater, thus achieving the deployment operation of the vehicle 2. When it is necessary to recover the vehicle 2, the vehicle 2 is positioned horizontally in the seawater, and the connecting part 3 is in an extended state, forming a certain gap between the connecting part 3 and the vehicle 2. The lift 5 then drives... The connecting component 1 moves into the sea and into the gap between the connecting part 3 and the vehicle 2. The connecting part 3 retracts, clamping the vehicle 2 and the connecting part 3 from both sides to the connecting component 1, thus fixing the vehicle 2 and the connecting part 3 to the connecting component 1. Then, the elevator 5 drives the connecting component 1 and the vehicle 2 upward into the carrier 50. The connecting part 3 extends, releasing the connecting component 1 to achieve the recovery operation of the vehicle 2. In summary, the marine deployment and recovery device and its usage method of the present invention, through the elevator 5 driving the connecting component 1 to rise and fall, the connecting component 1 clamping the connecting part 3, and the connecting part 3 and the vehicle 2 clamping the connecting component 1, achieve the functions of deploying and recovering the vehicle 2. It has the advantages of simple structure, compact structure, small space occupation, and light weight. It can improve the compactness of the structure of the carrier 50 where the deployment and recovery device is installed and effectively reduce the load pressure of the carrier 50.

[0114] The above description is only a preferred embodiment of the present invention. It should be noted that for those skilled in the art, several improvements and substitutions can be made without departing from the technical principles of the present invention, and these improvements and substitutions should also be considered within the scope of protection of the present invention.

Claims

1. A marine deployment and recovery device, characterized in that, The system includes an elevator (5), a vehicle (2), and a connecting assembly (1). The elevator (5) is mounted on a vehicle (50). The tail of the vehicle (2) has a connecting part (3). The elevator (5) is connected to the connecting assembly (1). The elevator (5) can drive the connecting assembly (1) to move vertically to the connecting part (3). The connecting assembly (1) can clamp onto the connecting part (3). The connecting part (3) is retractable. The elevator (5) can drive the connecting assembly (1) to move vertically between the vehicle (2) and the connecting part (3) so that the vehicle (2) and the connecting part (3) are clamped onto the connecting assembly (1). The connecting part (3) includes a tail pin (31) located at the tail of the vehicle (2). The connecting assembly (1) includes a connecting block (11). A clamping electromagnet (12) and a plurality of clamping blocks (13) are provided. The bottom surface of the connecting block (11) is provided with a clamping hole (111). The clamping electromagnet (12) and the plurality of clamping blocks (13) are provided in the clamping hole (111). The clamping hole (111) is provided with an inclined hole section (112). Each clamping block (13) is located below the clamping electromagnet (12) and is provided corresponding to the inclined hole section (112). Each clamping block (13) is arranged around the axis of the clamping hole (111), and a clamping channel (14) is formed between each clamping block (13). The clamping electromagnet (12) can be magnetically connected to each clamping block (13). The clamping electromagnet (12) can apply a force in the up and down direction to each clamping block (13) to clamp or release the connecting part (3). The lifting device (5) is connected to the connecting block (11). The connecting assembly (1) further includes a connecting line (17), an abutment block (18), and a retrieval driver. The connecting block (11) has a wire cavity (113) inside. The bottom surface of the connecting block (11) has a wire hole (114) that extends through the wire cavity (113). The connecting line (17) and the wire cavity (113) are both spiral-shaped. The connecting line (17) is located in the wire cavity (113). The abutment block (18) is located at the bottom end of the connecting line (17). The retrieval driver can drive the connecting line (17) to move to the third position and the fourth position. When the connecting line (17) is in the third position, the connecting line (17) is completely retracted into the wire cavity (113); When the connecting line (17) is in the fourth position, the connecting line (17) extends downward through the wire hole (114) and moves between the connecting part (3) and the aircraft (2).

2. The marine deployment and recovery device according to claim 1, characterized in that, The connecting part (3) includes a connector (32) and a telescopic member (33). The tail of the aircraft (2) is provided with a connecting hole (21). The telescopic member (33) is located in the connecting hole (21). The connector (32) is connected to the tail end of the telescopic member (33). The aircraft (2) is provided with a telescopic driver. The telescopic driver is connected to the telescopic member (33). The telescopic driver can drive the telescopic member (33) to extend and retract along the axial direction of the connecting hole (21), thereby driving the connector (32) to move along the axial direction of the connecting hole (21). The connector (32) can move to a first position and a second position. When the connector (32) is in the first position, the connecting component (1) can move between the connector (32) and the vehicle (2); When the connector (32) is in the second position, the connector (32) and the vehicle (2) are able to clamp the connecting assembly (1).

3. A marine deployment and recovery device according to claim 2, characterised in that, The telescopic actuator is an air pump, the telescopic component (33) is a telescopic airbag, and the telescopic component (33) is provided with a corrugated structure.

4. The offshore launch and recovery apparatus of claim 1, wherein, When the bottom surface of the connecting block (11) is provided with a clamping hole (111), the connecting line (17) and the wire cavity (113) are arranged around the clamping hole (111).

5. The offshore launch and recovery apparatus of claim 1, wherein, It also includes a first drive, a second drive, a first guide rail (6), a second guide rail (7), and multiple storage compartments (8). The storage compartments (8) are located on the vehicle (50). Each storage compartment (8) has a through-hole (81) in the vertical direction for storing the aircraft (2). The multiple storage compartments (8) are arranged horizontally. The first guide rail (6) extends along a first direction and is located on the vehicle (50). The second guide rail (7) is slidably connected to the first guide rail (6) in the first direction and extends along a second direction. The elevator (5) extends along the first direction. The first driver is connected to the second guide rail (7) in two directions, and the second driver is connected to the elevator (5). The first driver can drive the second guide rail (7) to move in a first direction, and the second driver can drive the elevator (5) to move in a second direction, so that the elevator (5) moves in a horizontal direction, thereby driving the connecting assembly (1) to move in a horizontal direction above the receiving hole (81) of each of the storage compartments (8), wherein the first direction and the second direction have an angle greater than 0°.

6. An offshore launch and recovery arrangement according to claim 1 or 5, characterised in that, It also includes a storage compartment (8) and a locking structure (9). The outer side wall of the aircraft (2) is provided with a wing (4). The storage compartment (8) is located on the vehicle (50). The storage compartment (8) is provided with a receiving hole (81) that runs through the vertical direction. The receiving hole (81) is used to receive the aircraft (2). The bottom surface of the storage compartment (8) is provided with a wing hole (82) that communicates with the receiving hole (81). The wing hole (82) is used to receive the wing (4). The hole wall of the wing hole (82) is provided with a locking groove (83). The locking structure (9) includes a locking device and a locking tongue (91). The locking tongue (91) is located in the locking groove (83). The locking device is connected to the locking tongue (91). The locking device can drive the locking tongue (91) to move to the fifth position and the sixth position. When the latch (91) is in the fifth position, the latch (91) protrudes into the wing hole (82); When the latch (91) is in the sixth position, the latch (91) is fully retracted into the lock groove (83).

7. The marine deployment and recovery device according to claim 5, characterized in that, It also includes a connecting frame (10), a fixed pulley (20), an outer sleeve (30), an inner sleeve (40), and a lifting drive. The outer sleeve (30) and the lifting device (5) are fixedly mounted on the connecting frame (10). The connecting frame (10) is slidably connected to the second guide rail (7) along the second direction. The outer sleeve (30) has a first cylindrical hole (301) that extends in the vertical direction. The inner sleeve (40) is slidably mounted in the first cylindrical hole (301) in the vertical direction. The inner sleeve (40) has a vertically extending... The second cylindrical hole (401) is penetrating downwards. The lifting drive is connected to the inner sleeve (40). The lifting drive can drive the inner sleeve (40) to move in the vertical direction. The lifting device (5) is a winch. The fixed pulley (20) is located on the top surface of the outer sleeve (30). The winch rope of the lifting device (5) is wound around the fixed pulley (20) and passes through the first cylindrical hole (301) and the second cylindrical hole (401). The winch rope of the lifting device (5) is connected to the connecting assembly (1).

8. A method of using a marine deployment and recovery device as described in any one of claims 1 to 5 and 7, characterized in that, The deployment method includes the following steps: S1, the elevator (5) drives the connecting assembly (1) to move downward to the gap between the connecting part (3) and the aircraft (2); S2, Connecting component (1) clamps the connecting part (3); S3, the elevator (5) drives the connecting assembly (1) to move downward, and drives the aircraft (2) to move downward; S4, Connecting component (1) releases connecting part (3); The recycling method includes the following steps: S5, the lifting device (5) drives the connecting assembly (1) to move downward to the connecting part (3); S6, the connecting part (3) and the aircraft (2) clamp the connecting assembly (1); S7. The elevator (5) drives the connecting assembly (1) to move upward, and drives the aircraft (2) to move upward. S8, Connector (3) Releases the vehicle (2).

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