Deployment and recovery apparatus and method for a vehicle

Abstract

The application discloses a launching and recovering device and method of a vehicle, which is applied to small and medium-sized ships and comprises a bearing base, a guide frame body, a transport assembly, a hoop assembly and an auxiliary compensation assembly. The bearing base is fixed to a deck of the ship, the guide frame body is arranged outside a shipboard and is installed on a side plate, the transport assembly is slidably connected with the guide frame body and reciprocates along the guide frame body between a high-position recovering position and a low-position operating position. The transport assembly is provided with a mounting position, the hoop assembly is installed on the mounting position and cooperatively surrounds the mounting position to form a mounting cavity, so that the vehicle entering the mounting cavity can be clamped and released. One end of the auxiliary compensation assembly is installed on the ship, and the other end is connected with the transport assembly through a traction member, so as to compensate the angle and position of the transport assembly and / or the vehicle. The device enables the vehicle to be launched and recovered outside the ship body, reduces the occupation of the deck space, and reduces the risk of deviation, swing and collision of the vehicle under dynamic sea conditions.

Description

Technical Field

[0001] This invention relates to the technical field of aircraft, and more specifically to a deployment and recovery device and method for an aircraft. Background Technology

[0002] Unmanned aerial vehicles (UAVs) are commonly used for marine surveys, near-shore patrols, underwater exploration, and environmental monitoring. After completing surface or underwater operations, the UAV needs to be deployed and retrieved by a vessel to allow it to move between the water and the vessel.

[0003] Current deployment and recovery operations for aircraft mostly rely on dedicated vessel platforms. The relevant equipment is usually located on the deck area and works with cranes, skids, or deployment and recovery mechanisms to lower and lift the aircraft. For small and medium-sized vessels with limited deck area and side installation space, large deployment and recovery equipment occupies a lot of space and can easily interfere with deck operation facilities, bulwarks, or personnel passage areas after installation. This makes it difficult for small and medium-sized vessels to directly adapt to the deployment and recovery operations of medium-sized aircraft.

[0004] During the recovery of a vehicle, it typically needs to approach the hull first before the recovery equipment guides, supports, clamps, and lifts it. When the vehicle is near the water surface or partially above water, its stress state gradually shifts from being supported by buoyancy to being supported by the recovery equipment. The hull's heave, roll, crosswinds, waves, and currents simultaneously alter the relative position between the vehicle and the recovery equipment. If the vehicle lacks stable guidance and restraint before entering the recovery position, it is prone to lateral drift, attitude deflection, or end-end swaying, potentially leading to a collision with the hull or recovery equipment.

[0005] Meanwhile, small and medium-sized vessels have limited anti-rolling capabilities, and the additional load generated after the vessel leaves the water will be concentrated on the hull side and recovery equipment. If the recovery equipment lacks constraints on the position and attitude of the vessel during the lifting and lowering process, the vessel is prone to swaying, tilting, or unstable clamping during the lifting phase, affecting the continuity of the recovery operation and increasing the risk of damage to the vessel's outer shell, sensors, or hull structure. Summary of the Invention

[0006] The present invention provides a deployment and recovery device for a spacecraft to solve the above-mentioned technical problems.

[0007] To achieve the above objectives, the present invention provides a deployment and recovery device for a vessel, applicable to small and medium-sized ships, comprising: Support base, fixed to the deck of the ship; The guide frame is located on the outside of the ship's hull and is installed on the outer plating of the side of the hull; The transport component is slidably connected to the guide frame and reciprocates between a high-level recovery position and a low-level working position along the guide frame. The transport component has an installation position. A clamp assembly is installed on the mounting position and together with the mounting position forms a mounting cavity to clamp and release the aircraft located in the mounting cavity; An auxiliary compensation component is mounted on the vessel at one end and connected to the transport component via a towing device at the other end to compensate for the angle and position of the transport component and / or the vehicle.

[0008] Preferably, the guide frame includes: The bracket is fixed to the outer side plating of the vessel and extends outward from the hull. The guide rail is mounted on the bracket and extends vertically. The transport component is slidably connected to the guide rail and reciprocates between the high-level recovery position and the low-level operation position along the guide rail.

[0009] Preferably, the transport component includes: The cage is slidably connected to the guide frame on one side and has the mounting position on the other side; A support section, located at the bottom of the cage, is used to support and limit the movement of the aircraft entering the mounting cavity; A guide structure is provided at the entrance of the mounting position to guide the aircraft entering the mounting cavity.

[0010] Preferably, the guide structure includes: The guide surface gradually expands towards the entrance of the mounting position; Guide rollers and / or elastic guide blocks are disposed on both sides of the guide surface to guide the vehicle when it enters the mounting cavity.

[0011] Preferably, the clamp assembly includes: An arc-shaped fastener is installed at the mounting position; Two sets of clamping components are symmetrically arranged at both ends of the arc-shaped fixing member, and one set of clamping components has a locking position, while the other set of clamping components has a locking member; The two sets of clamping assemblies are brought close to each other so that the locking member locks with the locking position and together with the mounting position forms the mounting cavity; the two sets of clamping assemblies are moved away from each other so that the locking position and the locking member disengage to release the vehicle.

[0012] Preferably, the deployment and retrieval device further includes: The buoyancy adjustment assembly is partially installed on the vessel and partially installed on the transport assembly; The buoyancy adjustment component includes an air supply unit installed on the vessel and airbags installed on the bottom, side walls and top of the transport component. The air supply unit includes multiple independent air supply and exhaust circuits that are respectively connected to each of the airbags. Each air supply and exhaust circuit is provided with a control valve so that each of the airbags can be inflated and deflated independently.

[0013] Preferably, the auxiliary compensation component includes: A longitudinally compensating winch is fixed to the vessel and connected to the top of the transport assembly via a traction member; An auxiliary winch is fixed to the vessel and connected to the lower middle part of the transport assembly via a traction component; A lateral compensating winch is fixed to the vessel and connected to the side of the transport assembly via a traction member; The longitudinal compensation winch, the auxiliary winch, and the lateral compensation winch are used to compensate for the vertical displacement, lateral offset, and attitude deflection of the transport component, respectively.

[0014] Preferably, the deployment and recovery device for the aircraft further includes: A traction winch, fixed to the ship; A traction guide is provided on the transport assembly; The traction winch's traction cable extends into the mounting cavity via the traction guide, and the traction direction of the traction cable within the mounting cavity is consistent with the guide direction of the mounting position. The traction winch is used to assist the vehicle in entering and exiting the mounting cavity.

[0015] Preferably, each set of the clamping components includes: An arc-shaped clamping arm, one end of which is rotatably connected to the arc-shaped fixing member, and the other end of which has a locking position or locking member; The drive telescopic component has one end rotatably connected to the arc-shaped fixing component and the other end rotatably connected to the arc-shaped clamping arm, so as to drive the arc-shaped clamping arm to rotate. A cushioning pad is disposed on the side of the arc-shaped fixing member and / or the arc-shaped clamping arm facing the mounting cavity.

[0016] A method for deploying and recovering a spacecraft, comprising using the spacecraft deployment and recovery device described in any one of the above claims to deploy and recover the spacecraft, including: When recovering the vehicle, the transport components are lowered to a low working position along the guide frame, and the clamp assembly is kept in the open position. The vehicle is guided into the mounting position via the transport assembly, and the clamp assembly is controlled to close to clamp the vehicle located in the mounting position. Control the transport components to rise along the guide frame to the high recovery position for the recovery of the vehicle; When deploying the aircraft, the transport component clamping the aircraft is lowered along the guide frame to a low working position, and the clamping assembly is opened to release the aircraft.

[0017] The deployment and recovery device and method for the aircraft proposed in this invention have the following beneficial effects: The deployment and recovery device and method for a vessel proposed in this invention uses a support base fixed to the ship's deck. A guide frame is positioned outside the ship's hull and installed on the outer side plating. The transport component reciprocates along the guide frame between a high recovery position and a low working position. The lifting path of the transport component is located outside the hull, reducing the occupation of deck space on small and medium-sized vessels and minimizing interference with deck equipment, bulwarks, and personnel passage areas.

[0018] The transport component has a mounting position, and the clamp assembly is installed on the mounting position, together with the mounting position to form a mounting cavity. After the vehicle enters the mounting cavity, the clamp assembly clamps the vehicle, keeping it within the mounting position during the lifting and recovery process; when deployment is required, the clamp assembly opens, allowing the vehicle to be released from the mounting cavity, thus providing a clear clamping position and release path for the recovery and deployment of the vehicle.

[0019] One end of the auxiliary compensation component is installed on the vessel, and the other end is connected to the transport component via a towing device. Under the influence of hull heave, roll, or waves, the auxiliary compensation component compensates for the relative position and attitude of the transport component and the vehicle, reducing the offset, swaying, and collisions caused during the approach, clamping, and lifting of the vehicle, enabling small and medium-sized vessels to complete the deployment and recovery of the vehicle in dynamic sea conditions. Attached Figure Description

[0020] Figure 1 This is a reference diagram showing the usage status of the deployment and recovery device for the aircraft of the present invention; Figure 2 For the present invention Figure 1 A schematic diagram of the middle section structure; Figure 3 This is a schematic diagram showing the layout of the airbags distributed around the outer perimeter of the cage; Figure 4 This is another structural view of the deployment and recovery device for the aircraft of the present invention; Figure 5 This is a schematic diagram of the hoisting cage.

[0021] In the picture: 100. Deployment and recovery equipment for aircraft; 10. Supporting base; 20. Guide frame; 21. Support; 22. Guide rail; 30. Transport component; 31. Cage; 31a. Mounting position; 32. Support; 33. Guide structure; 34. Flexible guide block; 40. Clamp assembly; 40a. Mounting cavity; 41. Arc-shaped fixing component; 42. Clamping assembly; 421. Locking position; 422. Locking component; 43. Arc-shaped clamping arm; 44. Drive telescopic component; 51. Longitudinal compensating winch; 52. Auxiliary winch; 53. Lateral compensating winch; 60. Buoyancy adjustment assembly; 61. Airbag; 70. Traction winch.

[0022] The realization of the objective, functional features and advantages of the present invention will be further explained in conjunction with the embodiments and with reference to the accompanying drawings. Detailed Implementation

[0023] It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.

[0024] It should be noted that in the description of this invention, the terms "lateral," "longitudinal," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used solely for the convenience of describing the invention and for 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. Therefore, they should not be construed as limitations on the invention. Furthermore, the terms "first," "second," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0025] In at least one embodiment of this application, a deployment and retrieval device 100 for a vehicle is provided. This deployment and retrieval device 100 is applied to small and medium-sized vessels and is used to deploy a vehicle from the vessel into the water or to retrieve a vehicle from the water to a high-level retrieval position near the vessel.

[0026] Please refer to Figures 1 to 5The deployment and recovery device 100 for the aircraft includes a support base 10, a guide frame 20, a transport component 30, a clamping assembly 40, and an auxiliary compensation assembly. The support base 10 is fixed to the deck of the vessel. The guide frame 20 is located on the outside of the hull and installed on the outer side plating. The transport component 30 is slidably connected to the guide frame 20 and reciprocates between a high recovery position and a low working position along the guide frame 20. The transport component 30 has a mounting position 31a, and the clamping assembly 40 is installed on the mounting position 31a, forming a mounting cavity 40a together with the mounting position 31a. One end of the auxiliary compensation assembly is installed on the vessel, and the other end is connected to the transport component 30 via a traction member. It compensates for the position and attitude of the transport component 30 and the aircraft during deployment and recovery. The high recovery position is when the transport component 30 is raised to a position close to the deck or above the upper edge of the hull, and the low working position is when the transport component 30 is lowered to a position close to the water surface or at least partially submerged in the water.

[0027] The load-bearing base 10 is a metal load-bearing component installed on the deck, formed by welding steel plates, reinforcing ribs, and connecting plates. The lower side of the load-bearing base 10 is welded or bolted to the ship's deck, and the side of the load-bearing base 10 near the hull side is connected to the bulwark or the hull side reinforcement area. The load-bearing base 10 bears the loads transmitted by the guide frame 20, auxiliary compensation assembly, buoyancy adjustment assembly 60, and traction winch 70 during operation, and distributes the loads to the deck and hull side structures.

[0028] The guide frame 20 includes a support 21 and a guide rail 22. The support 21 is a frame-type metal support, formed by welding together shaped steel, square tubing, or plate-shaped reinforcing members. One end of the support 21 is fixed to the outer side plating of the vessel, and the other end extends outward from the hull, placing the guide rail 22 on the outer side of the hull. The guide rail 22 is installed on the outer side of the support 21 and extends vertically. The guide rail 22 can be a straight guide rail, a grooved guide rail, or a vertical guide rail with roller mating surfaces. After the transport assembly 30 is engaged with the guide rail 22, the lifting path of the transport assembly 30 is located on the outer side of the hull, reducing the occupation of the deck area and minimizing interference between the transport assembly 30 and deck equipment, bulwarks, and personnel passage areas.

[0029] The transport assembly 30 includes a cage 31, a support 32, and a guide structure 33. The cage 31 is a frame-type load-bearing structure, formed by welding stainless steel pipes, aluminum alloy profiles, or corrosion-resistant steel components. A sliding engagement component is provided on the side of the cage 31 closest to the guide frame 20, and the sliding engagement component is slidably connected to the guide rail 22. The sliding engagement component is a slider, roller assembly, or guide sleeve, allowing the cage 31 to move up and down along the guide rail 22. An installation position 31a is formed on the side of the cage 31 away from the guide rail 22, and the installation position 31a is open towards the direction of vehicle entry, allowing the vehicle to enter and be fixed in place with the clamp assembly 40.

[0030] A support portion 32 is located at the bottom of the cage 31 and below the mounting position 31a. The support portion 32 is a support plate, beam, or arc-shaped support frame, with its upper surface facing the mounting cavity 40a. The support portion 32 is welded, bolted, or integrally formed with the cage 31. After the aircraft enters the mounting position 31a, the bottom of the aircraft contacts the support portion 32, which bears part or all of the aircraft's weight and restricts its downward movement. The contact surface of the support portion 32 is provided with rubber pads or a wear-resistant lining to reduce rigid contact between the aircraft's outer shell and the support portion 32.

[0031] A guide structure 33 is disposed at the entrance of the installation position 31a. The guide structure 33 includes a guide surface, guide rollers, and / or elastic guide blocks 34. The guide surface gradually expands towards the entrance of the installation position 31a, forming an inlet area that gradually narrows from the outside to the inside at the entrance of the installation position 31a. The guide surface is formed by two relatively inclined guide plates, or by arc-shaped traction guides disposed on both sides of the entrance of the cage 31. The guide rollers are rotatably mounted on the side of the guide surface, and the elastic guide blocks 34 are fixed on both sides of the guide surface. The elastic guide blocks 34 are made of rubber, polyurethane, or other seawater-resistant elastic materials. When the vehicle approaches the installation position 31a, if there is a lateral deviation between the vehicle and the installation position 31a, the vehicle will first contact the guide surface, guide rollers, or elastic guide blocks 34, and gradually enter the installation position 31a under the guiding action of the guide structure 33.

[0032] The clamp assembly 40 is installed on the mounting position 31a. The clamp assembly 40 includes an arc-shaped fixing member 41 and two sets of clamping assemblies 42. The arc-shaped fixing member 41 is fixed at the mounting position 31a of the cage 31, and the inner contour of the arc-shaped fixing member 41 is adapted to the outer periphery of the aircraft. The arc-shaped fixing member 41 is an arc-shaped metal plate, an arc-shaped frame, or an arc-shaped clamp seat. The two sets of clamping assemblies 42 are respectively disposed at both ends of the arc-shaped fixing member 41. One set of clamping assemblies 42 has a locking position 421, and the other set of clamping assemblies 42 has a locking member 422. The locking position 421 is a lock hole, a slot, or a lock seat, and the locking member 422 is a locking pin, a locking hook, or a locking tongue.

[0033] In this embodiment, when the two sets of clamping assemblies 42 approach each other, the locking member 422 locks with the locking position 421, and the arc-shaped fixing member 41, the two sets of clamping assemblies 42, and the mounting position 31a together form the mounting cavity 40a. When the aircraft is located in the mounting cavity 40a, the support part 32 supports the aircraft from below, and the clamping assembly 40 clamps the aircraft from the outer periphery, keeping the aircraft in the mounting position 31a during the lifting and lowering of the transport assembly 30. When the two sets of clamping assemblies 42 move away from each other, the locking member 422 disengages from the locking position 421, the mounting cavity 40a opens, and the aircraft can be released from the mounting position 31a.

[0034] Each clamping assembly 42 includes an arc-shaped clamping arm 43, a drive telescopic member 44, and a buffer pad. One end of the arc-shaped clamping arm 43 is rotatably connected to the arc-shaped fixing member 41, and the other end has a locking position 421 or a locking member 422. One end of the drive telescopic member 44 is rotatably connected to the arc-shaped fixing member 41, and the other end is rotatably connected to the arc-shaped clamping arm 43. The drive telescopic member 44 is a hydraulic cylinder, an electric push rod, or a pneumatic cylinder. When the drive telescopic member 44 extends, it drives the arc-shaped clamping arm 43 to rotate toward the mounting cavity 40a; when the drive telescopic member 44 retracts, it drives the arc-shaped clamping arm 43 to rotate away from the mounting cavity 40a. The buffer pad is disposed on the side of the arc-shaped fixing member 41 and / or the arc-shaped clamping arm 43 facing the mounting cavity 40a. The buffer pad is made of rubber, polyurethane, or soft wear-resistant material, conforming to the outer shell of the aircraft when clamping it and reducing local impact during the clamping process.

[0035] In at least one embodiment of this application, the deployment and recovery device 100 of the vessel further includes a buoyancy adjustment assembly 60, a portion of which is mounted on the vessel and another portion on the transport assembly 30. The buoyancy adjustment assembly 60 includes an air supply unit and multiple airbags 61. The air supply unit is installed near the vessel's deck, compartment, or support base 10, and includes an air compressor, an air tank, air supply lines, and exhaust lines. Multiple airbags 61 are respectively installed on the bottom, sidewalls, and top of the transport assembly 30. The airbags 61 are made of seawater-resistant rubber or flexible composite materials and are secured to the outside of the cage 31 by fixing straps, pressure plates, or mounting brackets.

[0036] The air supply system includes multiple independent air supply and exhaust circuits connected to each airbag 61, with a control valve on each circuit. Airbags 61 at different locations correspond to independent air supply and exhaust circuits; the bottom airbag 61, side airbags 61, and top airbag 61 can be inflated or deflated independently. When the transport assembly 30 descends to its low-level operating position and approaches the water surface, the bottom airbag 61 provides upward buoyancy support to the transport assembly 30, the side airbags 61 adjust the lateral force state of the transport assembly 30, and the top airbag 61, in conjunction with the bottom airbag 61, adjusts the overall attitude of the transport assembly 30. Based on the buoyancy and tilt state of the transport assembly 30, the operator controls the control valves on the corresponding air supply and exhaust circuits to inflate or deflate the corresponding airbags 61, limiting the lateral and pitch swings of the transport assembly 30 near the water surface and keeping the inlet of the mounting position 31a near the approach direction of the vehicle.

[0037] The auxiliary compensation assembly includes a longitudinal compensation winch 51, an auxiliary winch 52, and a lateral compensation winch 53. The longitudinal compensation winch 51 is fixed to the vessel and connected to the top of the transport assembly 30 via a traction member. The auxiliary winch 52 is fixed to the vessel and connected to the lower middle part of the transport assembly 30 via a traction member. The lateral compensation winch 53 is fixed to the vessel and connected to the side of the transport assembly 30 via a traction member. The traction member is a steel cable, traction rope, or flexible traction belt. The longitudinal compensation winch 51 compensates for the vertical displacement of the transport assembly 30, the auxiliary winch 52 provides traction restraint for the lower middle swing of the transport assembly 30, and the lateral compensation winch 53 compensates for the lateral offset and lateral attitude of the transport assembly 30. When the transport assembly 30 is in a low-position operating position, the three winches apply traction force to the transport assembly 30 from different points of application, maintaining a relatively stable operating position for the transport assembly 30 under the influence of hull heave, roll, and waves.

[0038] In at least one embodiment of this application, the deployment and recovery device 100 for the aircraft further includes a traction winch 70 and a traction guide for steering the traction cable. The traction winch 70 is fixed to the vessel, and the traction guide for steering the traction cable is disposed on the transport assembly 30 and located near the mounting position 31a. The traction guide for steering the traction cable is a guide wheel, guide ring, guide hole, or pulley block. The traction cable of the traction winch 70 extends into the mounting cavity 40a via the traction guide for steering the traction cable, and the traction direction of the traction cable in the mounting cavity 40a is consistent with the guide direction of the mounting position 31a. When recovering the aircraft, the traction cable is connected to the traction connection on the aircraft, the traction winch 70 winds up the traction cable, and the aircraft enters the mounting cavity 40a along the guide direction of the mounting position 31a. After the aircraft is clamped by the clamp assembly 40, the traction cable maintains a predetermined tension or is disconnected from the aircraft.

[0039] In this embodiment, when recovering the vehicle, the transport component 30 is first controlled to descend along the guide frame 20, moving the cage 31 from a high recovery position to a low working position. During the descent of the transport component 30, the longitudinal compensation winch 51, auxiliary winch 52, and lateral compensation winch 53 raise and lower the traction components according to the position change of the transport component 30, so that the transport component 30 rises and falls stably along the guide rail 22. After the transport component 30 approaches the water surface, the operators inflate or deflate the airbags 61 at the corresponding positions according to the buoyancy and tilt of the cage 31, so that the entrance of the installation position 31a faces the direction in which the vehicle approaches.

[0040] After the transport component 30 reaches the low-position working area, the drive telescopic component 44 drives the arc-shaped clamping arm 43 to open, and the clamp assembly 40 is in the open state. When the vehicle approaches the installation position 31a, the traction cable of the traction winch 70 is connected to the vehicle, and the traction winch 70 winds up the traction cable, causing the vehicle to move along the guide direction of the installation position 31a. When the vehicle enters the entrance of the cage 31, the guide structure 33 guides the vehicle, and after the vehicle's outer shell contacts the guide surface, guide rollers, or elastic guide blocks 34, it gradually moves towards the center area of ​​the installation position 31a. After the vehicle continues to enter the installation position 31a, the bottom of the vehicle contacts the support part 32 and is supported and limited by the support part 32.

[0041] After the aircraft enters the mounting position 31a and is supported by the support part 32, the drive telescopic member 44 pushes the arc-shaped clamping arm 43 to rotate inward, and the two sets of clamping assemblies 42 move closer to each other. After the locking member 422 locks with the locking position 421, the arc-shaped fixing member 41, the arc-shaped clamping arm 43, and the mounting position 31a together form the mounting cavity 40a, and the aircraft is clamped in the mounting cavity 40a. The buffer pad is located between the aircraft shell and the clamping assembly 40 to reduce hard contact during the clamping process.

[0042] After the vehicle is clamped, the transport assembly 30 rises along the guide frame 20. The longitudinal compensation winch 51 raises and lowers the traction components to coordinate with the vertical lifting of the transport assembly 30, the auxiliary winch 52 applies traction constraints to the lower middle part of the transport assembly 30, and the lateral compensation winch 53 restricts the lateral swing of the transport assembly 30. After the transport assembly 30 rises from the low working position to the high recovery position, the vehicle moves with the transport assembly 30 to the vicinity of the ship's side or deck, completing the recovery of the vehicle.

[0043] When deploying the vehicle, it is first clamped within the mounting cavity 40a, and the transport component 30 is positioned in the high-level recovery position. Then, the transport component 30 is controlled to descend along the guide frame 20 to the low-level working position. During the descent, the auxiliary compensation component continuously provides traction compensation to the transport component 30, and the buoyancy adjustment component 60 adjusts the inflation and deflation of the corresponding airbag 61 according to the transport component 30's approach to the water surface. After the transport component 30 reaches the low-level working position, the drive telescopic component 44 rotates the arc-shaped clamping arm 43 outward, the locking component 422 disengages from the locking position 421, and the mounting cavity 40a opens. After the mounting cavity 40a opens, the vehicle, under its own buoyancy, the guidance of the traction cable, or external pushing, leaves the mounting position 31a in the outgoing direction and is released into the water. After the vehicle leaves the mounting position 31a, the transport component 30 either rises along the guide frame 20 or remains in the low-level working position awaiting the next operation.

[0044] The above are merely preferred embodiments of the present invention and do not limit the patent scope of the present invention. Any equivalent structural transformations made based on the description and drawings of the present invention, or direct or indirect applications in other related technical fields, are similarly included within the patent protection scope of the present invention.

Claims

1. A deployment and recovery device for a vessel, applied to small and medium-sized ships, characterized in that, include: Support base, fixed to the deck of the ship; The guide frame is located on the outside of the ship's hull and is installed on the outer plating of the side of the hull; The transport component is slidably connected to the guide frame and reciprocates between a high-level recovery position and a low-level working position along the guide frame. The transport component has an installation position. A clamp assembly is installed on the mounting position and together with the mounting position forms a mounting cavity to clamp and release the aircraft located in the mounting cavity; An auxiliary compensation component is mounted on the vessel at one end and connected to the transport component via a towing device at the other end to compensate for the angle and position of the transport component and / or the vehicle.

2. The deployment and recovery device for a spacecraft according to claim 1, characterized in that, The guide frame includes: The bracket is fixed to the outer side plating of the vessel and extends outward from the hull. The guide rail is mounted on the bracket and extends vertically. The transport component is slidably connected to the guide rail and reciprocates between the high-level recovery position and the low-level operation position along the guide rail.

3. The deployment and recovery device for a spacecraft according to claim 1, characterized in that, The transport component includes: The cage is slidably connected to the guide frame on one side and has the mounting position on the other side; A support section, located at the bottom of the cage, is used to support and limit the movement of the aircraft entering the mounting cavity; A guide structure is provided at the entrance of the mounting position to guide the aircraft entering the mounting cavity.

4. The deployment and recovery device for a spacecraft according to claim 3, characterized in that, The guiding structure includes: The guide surface gradually expands towards the entrance of the mounting position; Guide rollers and / or elastic guide blocks are disposed on both sides of the guide surface to guide the vehicle when it enters the mounting cavity.

5. The deployment and recovery device for a spacecraft according to claim 1, characterized in that, The clamp assembly includes: An arc-shaped fastener is installed at the mounting position; Two sets of clamping components are symmetrically arranged at both ends of the arc-shaped fixing member, and one set of clamping components has a locking position, while the other set of clamping components has a locking member; The two sets of clamping assemblies are brought close to each other so that the locking member locks with the locking position and together with the mounting position forms the mounting cavity; the two sets of clamping assemblies are moved away from each other so that the locking position and the locking member disengage to release the vehicle.

6. The deployment and recovery device for a spacecraft according to claim 1, characterized in that, The deployment and retrieval device also includes: The buoyancy adjustment assembly is partially installed on the vessel and partially installed on the transport assembly; The buoyancy adjustment component includes an air supply unit installed on the vessel and airbags installed on the bottom, side walls and top of the transport component. The air supply unit includes multiple independent air supply and exhaust circuits that are respectively connected to each of the airbags. Each air supply and exhaust circuit is provided with a control valve so that each of the airbags can be inflated and deflated independently.

7. The deployment and recovery device for a spacecraft according to claim 1, characterized in that, The auxiliary compensation component includes: A longitudinally compensating winch is fixed to the vessel and connected to the top of the transport assembly via a traction member; An auxiliary winch is fixed to the vessel and connected to the lower middle part of the transport assembly via a traction component; A lateral compensating winch is fixed to the vessel and connected to the side of the transport assembly via a traction member; The longitudinal compensation winch, the auxiliary winch, and the lateral compensation winch are used to compensate for the vertical displacement, lateral offset, and attitude deflection of the transport component, respectively.

8. The deployment and recovery device for a spacecraft according to claim 1, characterized in that, The deployment and recovery system for the spacecraft also includes: A traction winch, fixed to the ship; A traction guide is provided on the transport assembly; The traction winch's traction cable extends into the mounting cavity via the traction guide, and the traction direction of the traction cable within the mounting cavity is consistent with the guide direction of the mounting position. The traction winch is used to assist the vehicle in entering and exiting the mounting cavity.

9. The deployment and recovery device for a spacecraft according to claim 5, characterized in that, Each set of clamping components includes: An arc-shaped clamping arm, one end of which is rotatably connected to the arc-shaped fixing member, and the other end of which has a locking position or locking member; The drive telescopic component has one end rotatably connected to the arc-shaped fixing component and the other end rotatably connected to the arc-shaped clamping arm, so as to drive the arc-shaped clamping arm to rotate. A cushioning pad is disposed on the side of the arc-shaped fixing member and / or the arc-shaped clamping arm facing the mounting cavity.

10. A method for deploying and recovering a spacecraft, characterized in that, Deploying and recovering a spacecraft using the deployment and recovery apparatus of any one of claims 1 to 9, comprising: When recovering the vehicle, the transport components are lowered to a low working position along the guide frame, and the clamp assembly is kept in the open position. The vehicle is guided into the mounting position via the transport assembly, and the clamp assembly is controlled to close to clamp the vehicle located in the mounting position. Control the transport components to rise along the guide frame to the high recovery position for the recovery of the vehicle; When deploying the aircraft, the transport component clamping the aircraft is lowered along the guide frame to a low working position, and the clamping assembly is opened to release the aircraft.

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