CN115723905B - Towing type retraction device - Google Patents
Towing type retraction device Download PDFInfo
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- CN115723905B CN115723905B CN202211620406.0A CN202211620406A CN115723905B CN 115723905 B CN115723905 B CN 115723905B CN 202211620406 A CN202211620406 A CN 202211620406A CN 115723905 B CN115723905 B CN 115723905B
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Abstract
The invention discloses a towing type retraction device, which relates to the technical field of underwater vehicle recovery and solves the problem that the conventional similar-purpose technology usually adopts ropes or suspension arms to fix an ocean vehicle, and the motions generated by ships under the action of waves cause difficulty in deployment operation of underwater robots, and the technical scheme is as follows: a buoyancy body having a docking channel; the fixed end of the transverse clamping device is arranged on the buoyancy body; the vertical clamping device is arranged at the movable end of the transverse clamping device, and is used for supporting the telescopic device, and the fixed end of the telescopic device is arranged on the buoyancy body; the invention can adapt to the outer surfaces of aircrafts with different sizes and shapes so as to realize the function of recycling various aircrafts by a single device.
Description
Technical Field
The invention relates to the technical field of underwater vehicle recovery, in particular to a towing type retraction device.
Background
The craft is the most commonly used tool for marine resource exploration, marine environment monitoring, marine scientific investigation, underwater operation and the like, and a plurality of marine craft such as unmanned ships, wave gliders, autonomous underwater robots (AUVs) and the like can be generally arranged on a mother ship for scientific investigation operation. Particularly, for three-dimensional monitoring of marine environment, various types of aircrafts can be put in, and the traditional arrangement and recovery mode is adopted, so that the problems of working efficiency, operation cost and the like are all relatively large.
The main drawbacks of the prior art include: 1. the adaptability to severe sea conditions is not strong, the prior similar-purpose technology generally adopts ropes or suspension arms to fix the marine craft, and the motions generated by the ship under the action of waves cause difficulty in the deployment and recovery operation of the underwater robot and even cause the damage of equipment; 2. the aircraft can only enter the recovery device from the front inlet of the device, so that the requirements on docking precision and operability are high; 3. at present, a cloth recycling device which takes the water surface and underwater recycling modes into consideration is not available.
Disclosure of Invention
The invention aims to provide a towing type retraction device which can be adapted to the outer surfaces of aircrafts with different sizes and shapes so as to clamp the aircrafts with different types, so that a single device can realize the function of recycling the aircrafts with different types.
The technical aim of the invention is realized by the following technical scheme: a towed retraction device comprising:
a buoyancy body having a docking channel into which the aircraft may enter;
the transverse clamping devices are at least two in number, and the fixed ends of the transverse clamping devices are arranged on the buoyancy body;
the transverse clamping devices are oppositely arranged along the butt joint channel, and the movable ends of the transverse clamping devices which are arranged in pairs can be mutually close to or far away from each other;
the vertical clamping device is arranged at the movable end of the transverse clamping device, and the movable end of the vertical clamping device can be overturned to be pressed on the top of the aircraft or overturned to be far away from the top of the aircraft;
the fixed end of the supporting telescopic device is arranged on the buoyancy body, and the movable end of the supporting telescopic device can extend or contract towards the butt joint channel so as to support the bottom of the aircraft.
After the aircraft enters the docking channel, the transverse clamping device can provide clamping limit for the left side and the right side of the aircraft, and the vertical clamping device and the bearing telescopic device can provide clamping limit for the upper side and the lower side of the aircraft; therefore, the scheme can provide a stable recycling clamping and positioning implementation mode for the aircraft,
and because the movable end of the transverse clamping device and the movable end of the other transverse clamping device can be mutually close to each other 5 so as to finish transverse clamping, the movable end of the vertical clamping device and the movable end of the bearing telescopic device are mutually close to finish vertical clamping, and therefore, the scheme can be adapted to the outer surfaces of aircrafts with different sizes and shapes so as to realize clamping of aircrafts with different types.
Secondly, considering that the aircraft is in the tight location in-process of clamp of vertical orientation, because the weight of aircraft self is great, and the buoyancy of aircraft is limited, and the top of aircraft generally can be provided with antenna 0 or be used for retrieving the couple moreover, consequently this scheme will be can the support telescoping device of bearing great weight set up alone on the buoyancy body, in order to guarantee to have good bearing effect to the aircraft, set up vertical clamping device on the movable end of horizontal clamping device, in order to reduce the influence of antenna or the couple at aircraft top to vertical clamping device setting position, this scheme provides a vertical clamping device's concrete arrangement mode promptly, it can accomplish the installation simply and conveniently, and make docking channel top remain sufficient 5 space.
In some embodiments, the lateral clamping device comprises:
the blocking baffle plate and the vertical clamping device are arranged on the blocking baffle plate;
one end of the first blocking swinging rod is rotationally connected with the blocking baffle plate;
the fixed end of the first linear moving assembly is arranged on the butt joint channel, and the movable end of the first linear moving assembly is rotationally connected with the first blocking 0 swinging rod;
one end of the second blocking swing rod is rotatably connected to the butt joint channel, and the other end of the second blocking swing rod is rotatably connected with the blocking baffle;
under the drive of the movable end of the first linear moving assembly, the first blocking swinging rod and the second blocking swinging rod drive the blocking baffle to approach or depart from the central axis direction of the butt joint channel.
5 from this, this scheme provides a concrete structure of horizontal clamping device, and the second stops the swinging arms as the pivot of swing, and first stops the swinging arms as the driving member of first rectilinear movement subassembly, compares the drive force that directly utilizes the rectilinear movement subassembly active end conventionally, and this scheme converts the rectilinear drive force of first rectilinear movement subassembly active end into the slant drive force to the baffle to make full use of stops the great area of force of baffle, and then realizes the better clamp of aircraft.
0 in some specific embodiments, the first blocking swinging rod is provided with an adjusting groove, the movable end of the first linear moving assembly is provided with a second sliding block, and the second sliding block is connected in the adjusting groove in a sliding way; a plurality of connecting columns are uniformly distributed on the blocking baffle, and the first blocking swinging rod and the second blocking swinging rod can be rotatably connected to the connecting columns.
Therefore, in this embodiment, one end of the second slider is provided with the limiting portion, and the other 5 ends of the second slider are connected with the movable ends of the first linear moving assemblies through the bolt pairs, and then the second blocking swinging rods are rotatably connected to the connecting columns at different positions so as to cooperate with the adjustment of the positions of the first blocking swinging rods, and further the inclined moving distance of the blocking baffle plate to the aircraft with different sizes can be conveniently adjusted. It can be seen that this scheme provides a blocking baffle and the particular embodiment of first rectilinear motion assembly active end cooperation regulation.
In some embodiments, the vertical clamping device comprises:
the first sliding block is connected to the movable end of the transverse clamping device in a sliding manner;
the fixed end of the second linear moving assembly is arranged on the movable end of the transverse clamping device, and the movable end of the second linear moving assembly is connected with the first sliding block;
the movable plate is pressed down, and is connected with the first slider in a turnover mode, and under the driving of the movable end of the second linear movement assembly, the movable plate can be turned over to be clamped on the first slider, so that the lower pressing plate can be pressed on the top of the aircraft.
From this, this scheme provides vertical clamping device's concrete structure, and it can be with the straight line driving force of second rectilinear movement subassembly turn into the power of pushing down the fly leaf upset, pushes down the fly leaf moreover and can overturn to the joint on first slider to make the fly leaf that pushes down can the butt and compress tightly in the top of aircraft.
In some embodiments, the vertical clamping device further comprises:
the swinging connecting rod is rotationally connected with the pressing movable plate;
the sliding rail is provided with a locking slide way and an unlocking slide way which are mutually communicated and then are L-shaped, one end of the swinging connecting rod is slidably connected in the locking slide way and the unlocking slide way, and the other end of the swinging connecting rod is rotationally connected with the pressing movable plate;
when one end of the swing connecting rod is connected to the locking slideway in a sliding way, the pressing movable plate is turned over to be clamped on the first sliding block;
when one end of the swing connecting rod is connected to the unlocking slide way in a sliding way, the pressing movable plate is turned over to be separated from the first sliding block in a clamping way.
In some embodiments, the pressing movable plate is provided with a connecting part, the connecting part is rotationally connected with the swinging connecting rod, a locking groove is formed in the connecting part, and the connecting part can be clamped in the locking groove along with the turning of the pressing movable plate.
In some embodiments, the movable end of the transverse clamping device is provided with a second through groove, the swing connecting rod is slidably arranged in the second through groove, the swing connecting rod is provided with a third sliding block, and the third sliding block is in limiting sliding connection with the locking slide way and the unlocking slide way.
Therefore, the scheme provides a specific implementation mode capable of realizing unlocking of the pressing movable plate in one overturning direction and locking in the other overturning direction. The third sliding block can slide in the unlocking slide way and the locking slide way under the driving of the movable end of the second linear moving assembly.
When the third slider slides on the unblock slide, the third slider drives the swing connecting rod and moves towards the direction that is close to the blocking baffle for connecting portion and pushing down the fly leaf and can upwards overturn along vertical direction, and then make the fly leaf that pushes down no longer butt in the top of aircraft, and then realize pushing down the fly leaf and realize the unblock to the aircraft in one of them upset direction.
When the third sliding block slides on the locking slide way, due to the existence of the unlocking slide way, a space is reserved between the locking slide way and the blocking baffle plate, the third sliding block can drive the swinging connecting rod to move in the direction away from the blocking baffle plate, and then the connecting part and the pressing movable plate are enabled to downwards overturn along the vertical direction until the pressing movable plate is overturned to be in a relative horizontal state, at the moment, the third sliding block is clamped in the locking groove, and further the pressing movable plate is locked in the other overturning direction.
In some embodiments, a third through groove is formed in the sliding rail, and the connection part of the locking sliding rail and the unlocking sliding rail is in arc transition.
Therefore, the position of the third sliding block between the locking slide way and the unlocking slide way is switched more smoothly and naturally, and the overturning action of the pressing movable plate is smoother.
In some embodiments, the bearing telescoping device comprises:
the fixed end of the third linear moving assembly is arranged on the buoyancy body, and the movable end of the third linear moving assembly can extend or contract towards the butt joint channel;
and the bearing seat is arranged on the movable end of the third linear movement assembly and is matched with the bottom of the aircraft.
Therefore, the scheme provides a specific structural structure of the bearing telescopic device.
In some embodiments, the drag type retraction device further includes: a recovery guide net and a guide device;
the number of the recovery guide nets is at least two, and the recovery guide nets are respectively arranged at the two inner sides of the docking channel and are used for protecting the aircraft;
the guide device includes:
a lateral door assembly rotatably coupled to the buoyancy body for closing or opening the docking channel;
and the buffer roller is rotatably arranged on the lateral door assembly.
Therefore, the buffer roller is made of rubber, and when the aircraft enters the docking channel, the buffer roller can better avoid the occurrence of scratch between the aircraft and the lateral door assembly, so that the safety of the docking process of the aircraft is protected.
In summary, the invention can adapt to the outer surfaces of aircrafts with different sizes and shapes so as to clamp aircrafts with different types, so that a single device can complete the recovery function of various aircrafts.
Drawings
FIG. 1 is a schematic diagram of the structure of the present invention;
FIG. 2 is a schematic illustration of the connection of the present invention to an aircraft;
FIG. 3 is an enlarged view at A in FIG. 2;
FIG. 4 is a schematic view of another perspective connection of the present invention to an aircraft;
fig. 5 is an enlarged view at B in fig. 4;
FIG. 6 is a schematic view of another perspective connection of the present invention to an aircraft;
fig. 7 is an enlarged view at C in fig. 6;
FIG. 8 is a schematic view of the connection of the lateral clamping device to the vertical clamping device in the present invention;
fig. 9 is an enlarged view of D in fig. 8;
FIG. 10 is a schematic view of a lateral clamp device and a vertical clamp device according to another aspect of the present invention;
fig. 11 is an enlarged view at E in fig. 10;
FIG. 12 is a schematic illustration of the connection of the present invention to another type of aircraft.
Reference numerals: 1. a buoyancy body; 10. a docking channel; 10a, recovering a guide net; 11. dragging the hanging ring; 12. an aircraft barrier; 2. a transverse clamping device; 21. a blocking baffle; 210. a connecting column; 211. a first through groove; 212. a second through slot; 22. a first blocking swing lever; 220. an adjustment tank; 23. a first linear motion assembly; 231. a second slider; 24. a second blocking swing lever; 3. a vertical clamping device; 31. a first slider; 32. a second linear motion assembly; 321. a second screw rod; 322. a second nut; 323. a second rotating device; 33. pressing down the movable plate; 330. a connection part; 330a, locking grooves; 34. swinging the connecting rod; 341. a third slider; 35. a slide rail; 350. a third through slot; 351. locking the slideway; 352. unlocking the slideway; 4. a supporting telescopic device; 41. a third linear motion assembly; 42. a socket; 5. a buoyancy adjusting mechanism; 6. a guide device; 61. a lateral door assembly; 62. a buffer roller; 7. an aircraft.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings.
Examples:
a drag type retraction device, as shown in fig. 1 to 12, comprising: the buoyancy body 1, the transverse clamping device 2, the vertical clamping device 3 and the bearing telescopic device 4 are specifically as follows:
a buoyancy body 1 having a docking channel 10 into which an aircraft 7 may enter; the docking channel 10 is provided with at least two recycling guide nets 10a, which are respectively arranged at two inner sides of the docking channel 10 and are used for protecting the aircraft 7.
The buoyancy body 1 is an installation frame for connecting a towing type retraction device with other equipment (in this embodiment, the hoisting equipment of the ship is not labeled in the drawing), the buoyancy body 1 provides installation support and buoyancy for the whole device, the two buoyancy bodies 1 are connected through a connecting bridge, a towing hanging ring 11 and an aircraft baffle 12 are installed at the top of the connecting bridge, and the towing hanging ring 11 can be connected with the hoisting equipment of the ship, so that towing and hoisting are realized. In particular, the buoyancy adjustment mechanism 5 is an offshore buoyancy adjustment structure commonly used in the art.
Wherein, the number of the transverse clamping devices 2 is at least two, and the fixed ends of the transverse clamping devices are arranged on the buoyancy body 1;
the transverse clamping devices 2 are oppositely arranged along the butt joint channel 10, and the movable ends of the transverse clamping devices 2 which are arranged in pairs can be mutually close to or far away from each other;
specifically, the lateral clamping device 2 comprises: the blocking baffle 21, the first blocking swing rod 22, the first linear motion assembly 23, and the second blocking swing rod 24 are specifically as follows:
a blocking baffle 21, and a vertical clamping device 3 is arranged on the blocking baffle 21;
a first blocking swing lever 22, one end of which is rotatably connected to the blocking plate 21;
the fixed end of the first linear moving assembly 23 is arranged on the docking channel 10, and the movable end of the first linear moving assembly is rotatably connected with the first blocking swinging rod 22; specifically, the first linear moving assembly 23 is a hydraulic telescopic cylinder commonly used in the art, a piston rod of the hydraulic telescopic cylinder is a movable end, and a sleeve of the hydraulic telescopic cylinder is a fixed end. Preferably, the number of first linear moving assemblies 23 is two.
A second blocking swing lever 24, one end of which is rotatably connected to the docking channel 10 and the other end of which is rotatably connected to the blocking baffle 21; preferably, the second blocking swing lever 24 is parallel to the first blocking swing lever 22.
The first blocking swinging rod 22 and the second blocking swinging rod 24 drive the blocking baffle 21 to approach or separate from the central axis direction of the docking channel 10 under the driving of the movable end of the first linear moving assembly 23.
Therefore, the specific structural structure of the transverse clamping device 2 is provided, the second blocking swinging rod 24 is used as a swinging fulcrum, the first blocking swinging rod 22 is used as a transmission part of the first linear moving assembly 23, compared with the conventional driving force directly utilizing the movable end of the linear moving assembly, the linear driving force of the movable end of the first linear moving assembly 23 is converted into the oblique driving force of the blocking baffle 21, so that the larger stressed area of the blocking baffle 21 is fully utilized, and better clamping of the aircraft 7 is realized.
Preferably, the first blocking swinging rod 22 is provided with an adjusting groove 220, the movable end of the first linear moving assembly 23 is provided with a second sliding block 231, and the second sliding block 231 is slidably connected in the adjusting groove 220; the blocking baffle 21 is uniformly provided with a plurality of connecting columns 210, and the first blocking swinging rod 22 and the second blocking swinging rod 24 can be rotatably connected to the connecting columns 210.
Therefore, in the present embodiment, one end of the second slider 231 is provided with a limiting portion, the other end of the second slider 231 is connected with the movable end of the first linear moving assembly 23 through a bolt pair, and then the second blocking swinging rod 24 is rotatably connected to the connecting post 210 at different positions, so as to cooperate with the adjustment of the position of the first blocking swinging rod 22, thereby facilitating the adjustment of the oblique moving distance of the blocking baffle 21 for different size craft 7. It will be seen that this embodiment provides an embodiment in which the blocking plate 21 is adjusted in cooperation with the movable end of the first linear motion assembly 23. It will be seen that this embodiment provides an embodiment in which the blocking plate 21 is adjusted in cooperation with the movable end of the first linear motion assembly 23.
In this embodiment, the vertical clamping device 3 is disposed at the movable end of the transverse clamping device 2, and the movable end thereof can be overturned to be pressed on the top of the aircraft 7 or overturned to be far away from the top of the aircraft 7;
the vertical clamping device 3 comprises: the first slider 31, the second linear motion assembly 32, the pressing movable plate 33, the swinging connecting rod 34, and the slide rail 35 are specifically as follows:
a first slider 31 slidingly coupled to the blocking plate 21 in the movable end of the lateral clamping device 2; specifically, the blocking plate 21 is provided with a first through groove 211, and the first slider 31 is slidably disposed in the first through groove 211.
The second linear moving assembly 32, the fixed end of which is arranged on the blocking baffle 21 in the movable end of the transverse clamping device 2, and the movable end of which is connected with the first sliding block 31; specifically, the second linear motion assembly 32 includes a second screw rod 321, a second nut 322, and a second rotating device 323, where the second screw rod 321 is rotatably disposed on a sidewall of the blocking plate 21 near the buoyancy body 1 along a vertical direction, the second rotating device 323 is disposed on the blocking plate 21 and is in transmission connection with the second screw rod 321, the second rotating device 323 provides rotation power for the second screw rod 321, and the second nut 322 is screwed on the second screw rod 321, preferably, the second rotating device 323 is a conventional rotation power source in the art. Preferably, the number of second rectilinear motion assemblies 32 is two.
The pressing movable plate 33 is connected with the first sliding block 31 in a reversible manner, and under the driving of the movable end of the second linear moving assembly 32, the pressing movable plate 33 can be turned over to be clamped on the first sliding block 31, so that the pressing plate can be pressed on the top of the aircraft 7.
A swing link 34 rotatably connected to the pressing movable plate 33;
as shown in fig. 8 and 9, the slide rail 35 has a locking slide 351 and an unlocking slide 352 which are mutually communicated and are L-shaped, one end of the swinging connecting rod 34 is slidably connected in the locking slide 351 and the unlocking slide 352, and the other end of the swinging connecting rod 34 is rotatably connected with the pressing movable plate 33;
when one end of the swing link 34 is slidably connected to the locking slide 351, the pressing movable plate 33 is turned over to be clamped on the first slider 31;
when one end of the swing link 34 is slidably connected to the unlocking slide 352, the pressing movable plate 33 is turned over to disengage from the first slider 31.
The present solution provides a specific structural configuration of the vertical clamping device 3, which can convert the linear driving force of the second linear moving assembly 32 into the power for turning the pressing movable plate 33, and the pressing movable plate 33 can be turned over to be clamped on the first sliding block 31, so that the pressing movable plate 33 can be abutted and pressed on the top of the aircraft 7.
Preferably, as shown in fig. 11, in the present embodiment, the pressing movable plate 33 has a connecting portion 330, the connecting portion 330 is rotatably connected to the swinging link 34, a locking groove 330a is formed on the connecting portion 330, and the connecting portion 330 can be clamped in the locking groove 330a along with the turning of the pressing movable plate 33.
The blocking baffle 21 in the movable end of the transverse clamping device 2 is provided with a second through groove 212, the swinging connecting rod 34 is arranged in the second through groove 212 in a sliding way, the swinging connecting rod 34 is provided with a third sliding block 341, and the third sliding block 341 is in limiting sliding connection in the locking slide 351 and the unlocking slide 352.
Thus, the present embodiment provides a specific embodiment capable of realizing unlocking in one of the turning directions and locking in the other turning direction of the pressing movable plate 33. The third slider 341 is capable of sliding within the unlocking slide 352 and the locking slide 351 by the driving of the movable end of the second rectilinear motion assembly 32.
When the third slider 341 slides on the unlocking slide way 352, the third slider 341 drives the swing link 34 to move in a direction close to the blocking plate 21, so that the connecting portion 330 and the pressing movable plate 33 can be turned upwards along the vertical direction, and the pressing movable plate 33 is not abutted to the top of the aircraft 7 any more, and the pressing movable plate 33 is unlocked in one of the turning directions.
When the third slider 341 slides on the locking slide way 351, due to the unlocking slide way 352, a space is reserved between the locking slide way 351 and the blocking baffle 21, so that the third slider 341 can drive the swinging connecting rod 34 to move in a direction away from the blocking baffle 21, and further the connecting portion 330 and the pressing movable plate 33 are turned downwards along the vertical direction until the pressing movable plate 33 is turned to be in a relative horizontal state, and at the moment, the third slider 341 is clamped in the locking groove 330a, and further the pressing movable plate 33 is locked in the other turning direction.
Preferably, the sliding rail 35 is provided with a third through groove 350, and the connection part of the locking sliding rail 351 and the unlocking sliding rail 352 is in arc transition. Therefore, the position of the third slider 341 is switched between the locking slide 351 and the unlocking slide 352 more smoothly and naturally, so that the turning action of the pressing movable plate 33 is smoother.
Wherein, the fixed end of the supporting telescopic device 4 is arranged on the buoyancy body 1, and the movable end of the supporting telescopic device can extend or retract towards the docking channel 10 so as to support the bottom of the aircraft 7.
Specifically, as shown in fig. 7, the bearing expansion device 4 includes: the third linear motion assembly 41 and the receiving seat 42 are as follows:
a third linear movement assembly 41 having a fixed end provided to the buoyancy body 1 and a movable end capable of extending or contracting toward the docking passage 10; specifically, the third linear moving assembly 41 is a hydraulic telescopic cylinder commonly used in the art, a piston rod of the hydraulic telescopic cylinder is a movable end, and a sleeve of the hydraulic telescopic cylinder is a fixed end.
A socket 42, which is provided on the movable end of the third rectilinear movement assembly 41, matches the bottom of the aircraft 7.
Thus, the present solution provides a specific structural configuration of the support telescopic device 4.
Preferably, a towed retraction device further comprises a guiding device 6 comprising: the side door assembly 61, the damping roller 62 are as follows:
a lateral door assembly 61 rotatably coupled to the buoyancy body 1 for closing or opening the docking channel 10;
a buffer roller 62 rotatably provided to the side door assembly 61.
Therefore, the buffer roller 62 is made of rubber, the recovery guide net 10a is made of flexible metal net, and when the aircraft 7 enters the docking channel 10, the buffer roller 62 and the recovery guide net 10a can better avoid the scratch between the aircraft 7 and the lateral door assembly 61, so that the safety of the docking process of the aircraft 7 is protected.
Working procedure of drag recovery
In the initial state, as shown in fig. 1, the movable end of the transverse clamping device 2, the movable end of the vertical clamping device 3 and the movable end of the supporting telescopic device 4 are all in a contracted state, and the buoyancy adjusting mechanism 5 carries out buoyancy adjustment to enable the buoyancy body 1 to sink into water; the craft 7 can enter from below, in front of, behind the docking channel 10;
as shown in fig. 2, the lateral door assemblies 61 at the front and rear ends of the buoyancy body 1 are opened, and when the aircraft 7 enters the docking channel 10, the movable end of the bearing telescopic device 4 drives the bearing seat 42 to approach the aircraft 7 until bearing action is generated;
then, as shown in fig. 3 and 4, the movable ends of the transverse clamping devices 2 positioned at the two sides of the docking channel 10 approach the aircraft 7 until the transverse clamping is completed; the specific process is as follows: the movable end of the first linear moving assembly 23 extends out to drive the first blocking swinging rod 22 to swing, so that the blocking baffle 21 approaches to the direction of the aircraft 7 until abutting against the lateral side wall of the aircraft 7;
then, as shown in fig. 5, the movable end of the vertical clamping device 3 approaches to the top of the aircraft 7 until the vertical clamping device 3 and the bearing telescopic device 4 complete clamping of the aircraft 7 in the vertical direction; the specific process is that the second rotating device 323 drives the second screw rod 321 to rotate, so that the second screw nut drives the second sliding block 231 to slide downwards; the second slider 231 drives the third slider 341 to move downwards by means of the swing link 34, so that the third slider 341 can slide from the unlocking channel to the locking channel, and the pressing movable plate 33 is turned over to abut against the top of the aircraft 7;
finally, buoyancy adjustment is performed through the buoyancy adjusting mechanism 5, so that the buoyancy body 1 floats to the water surface, and finally the lifting ring 11 is hooked and towed through the lifting equipment of the ship body, so that recovery and towing of the aircraft 7 are realized.
Advantageous effects
After the aircraft 7 enters the docking channel 10, the transverse clamping device 2 can provide clamping limit for the left side and the right side of the aircraft 7, and the vertical clamping device 3 and the bearing telescopic device 4 can provide clamping limit for the upper side and the lower side of the aircraft 7; therefore, this scheme can provide firm recovery clamp location implementation mode for aircraft 7, moreover because the expansion end of horizontal clamping device 2 and the expansion end of another horizontal clamping device 2 can be close each other in order to accomplish horizontal clamp, the expansion end of vertical clamping device 3 and the expansion end of bearing telescoping device 4 are close each other in order to accomplish vertical clamp, therefore the surface of aircraft 7 of different sizes and shapes can be adapted to this scheme to realize the clamp to different types of aircraft 7, with the function that the realization single equipment accomplished the recovery of multiple types of aircraft.
Secondly, considering that the aircraft 7 is in the tight location process of clamp of vertical direction, because the weight of aircraft 7 is great, and the buoyancy of aircraft 7 is limited, and the top of aircraft 7 generally can be provided with the antenna or be used for retrieving the couple moreover, consequently this scheme will be able to bear the support telescoping device 4 of great weight alone to set up on buoyancy body 1, in order to guarantee to have good bearing effect to aircraft 7, set up vertical clamping device 3 on the movable end of horizontal clamping device 2, in order to reduce the influence of the antenna or the couple at aircraft 7 top to vertical clamping device 3 setting position, this scheme provides a concrete arrangement mode of vertical clamping device 3 promptly, it can accomplish the installation simply and conveniently, and make docking channel 10 top remain sufficient space. The invention effectively expands the access space for docking and recycling of the aircraft 7 by opening the top and bottom of the docking channel 10.
The present embodiment is only for explanation of the present invention and is not to be construed as limiting the present invention, and modifications to the present embodiment, which may not creatively contribute to the present invention as required by those skilled in the art after reading the present specification, are all protected by patent laws within the scope of claims of the present invention.
Claims (9)
1. A drag-type retraction device, comprising:
a buoyancy body having a docking channel into which the aircraft may enter;
the transverse clamping devices are at least two in number, and the fixed ends of the transverse clamping devices are arranged on the buoyancy body;
the transverse clamping devices are oppositely arranged along the butt joint channel, and the movable ends of the transverse clamping devices which are arranged in pairs can be mutually close to or far away from each other;
the vertical clamping device is arranged at the movable end of the transverse clamping device, and the movable end of the vertical clamping device can be overturned to be pressed on the top of the aircraft or overturned to be far away from the top of the aircraft;
the fixed end of the supporting telescopic device is arranged on the buoyancy body, and the movable end of the supporting telescopic device can extend or retract towards the docking channel so as to support the bottom of the aircraft;
the lateral clamping device comprises:
the vertical clamping device is arranged on the blocking baffle;
one end of the first blocking swinging rod is rotationally connected with the blocking baffle plate;
the fixed end of the first linear moving assembly is arranged on the butt joint channel, and the movable end of the first linear moving assembly is rotationally connected with the first blocking swinging rod;
one end of the second blocking swing rod is rotatably connected to the butt joint channel, and the other end of the second blocking swing rod is rotatably connected with the blocking baffle;
under the drive of the movable end of the first linear moving assembly, the first blocking swinging rod and the second blocking swinging rod drive the blocking baffle to approach or depart from the central axis direction of the butt joint channel.
2. The towing type retraction device according to claim 1 wherein the first blocking swing rod is provided with an adjusting groove, the movable end of the first linear moving assembly is provided with a second sliding block, and the second sliding block is slidably connected in the adjusting groove; the blocking baffle is uniformly provided with a plurality of connecting columns, and the first blocking swinging rod and the second blocking swinging rod can be rotatably connected to the connecting columns.
3. A towing attachment in accordance with claim 1 wherein the vertical clamping means comprises:
the first sliding block is connected to the movable end of the transverse clamping device in a sliding manner;
the fixed end of the second linear moving assembly is arranged on the movable end of the transverse clamping device, and the movable end of the second linear moving assembly is connected with the first sliding block;
the movable plate is connected with the first sliding block in a turnover mode, and under the driving of the movable end of the second linear moving assembly, the movable plate can be turned over to be clamped on the first sliding block, so that the movable plate can be pressed on the top of the aircraft.
4. A towing attachment in accordance with claim 3 wherein the vertical gripping device further comprises:
the swinging connecting rod is rotationally connected with the pressing movable plate;
the sliding rail is provided with a locking slide way and an unlocking slide way which are mutually communicated and then are L-shaped, one end of the swinging connecting rod is slidably connected into the locking slide way and the unlocking slide way, and the other end of the swinging connecting rod is rotationally connected with the pressing movable plate;
when one end of the swing connecting rod is connected to the locking slideway in a sliding way, the pressing movable plate is turned over to be clamped on the first sliding block;
when one end of the swing connecting rod is connected with the unlocking slide way in a sliding way, the pressing movable plate is turned over to be separated from the first sliding block in a clamping way.
5. The device of claim 4, wherein the pushing movable plate has a connecting portion, the connecting portion is rotatably connected with the swinging connecting rod, the connecting portion is provided with a locking groove, and the connecting portion can be clamped in the locking groove along with the turning of the pushing movable plate.
6. The towing type folding and unfolding apparatus as claimed in claim 4, characterized in that a third through groove is formed in the sliding rail, and a joint of the locking slide rail and the unlocking slide rail is in arc transition.
7. The towing type folding and unfolding apparatus according to claim 4, wherein a second through groove is formed in the movable end of the transverse clamping device, the swinging connecting rod is slidably arranged in the second through groove, a third sliding block is arranged on the swinging connecting rod, and the third sliding block is in limiting sliding connection with the locking slide way and the unlocking slide way.
8. A towing extension and retraction apparatus according to claim 1 wherein said bearing extension includes:
the fixed end of the third linear moving assembly is arranged on the buoyancy body, and the movable end of the third linear moving assembly can extend or retract towards the butt joint channel;
and the bearing seat is arranged on the movable end of the third linear movement assembly and is matched with the bottom of the aircraft.
9. The towed retraction device of claim 1, further comprising: a recovery guide net and a guide device;
the number of the recovery guide nets is at least two, and the recovery guide nets are respectively arranged at the two inner sides of the docking channel and are used for protecting the aircraft;
the guide device includes:
a lateral door assembly rotatably coupled to the buoyancy body for closing or opening the docking channel;
and the buffer roller is rotatably arranged on the lateral door assembly.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202211620406.0A CN115723905B (en) | 2022-12-15 | 2022-12-15 | Towing type retraction device |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202211620406.0A CN115723905B (en) | 2022-12-15 | 2022-12-15 | Towing type retraction device |
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| CN115723905B true CN115723905B (en) | 2023-07-25 |
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Family Cites Families (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102007031156B4 (en) * | 2007-06-11 | 2009-04-16 | Diehl Bgt Defence Gmbh & Co. Kg | Device and method for suspending and recovering an underwater vehicle and method for docking an underwater vehicle to such a device |
| FR2917708B1 (en) * | 2007-06-19 | 2009-09-18 | Dcn Sa | SUBMARINE EQUIPPED WITH A DEVICE FOR LARGING AND RECOVERING A SECOND SUBMARINE DEVICE |
| CN106314732B (en) * | 2016-10-14 | 2018-01-26 | 中国船舶科学研究中心（中国船舶重工集团公司第七0二研究所） | AUV underwater matings and draw off gear |
| NO345094B1 (en) * | 2018-09-21 | 2020-09-28 | Usea As | A marine structure comprising a launch and recovery system |
| CN109367706B (en) * | 2018-10-26 | 2019-07-12 | 河海大学 | A kind of unmanned boat actively captures the device and method of underwater unmanned vehicle in the water surface |
| CN109367707B (en) * | 2018-10-26 | 2019-07-12 | 河海大学 | A kind of unmanned boat recycling Autonomous Underwater Vehicle device and method based on guide cable |
| CN112960086B (en) * | 2021-02-03 | 2022-03-22 | 吉林大学 | Seat formula AUV is butt joint platform under water |
| CN113879493A (en) * | 2021-11-23 | 2022-01-04 | 广东海洋大学 | Underwater vehicle salvage mechanical claw |
| CN114394216B (en) * | 2022-03-02 | 2024-05-10 | 集美大学 | Unmanned underwater vehicle retraction device and retraction method |
| CN114435545A (en) * | 2022-03-16 | 2022-05-06 | 上海交通大学 | Aircraft retraction device with power positioning function and recovery and deployment method |
| CN115056924B (en) * | 2022-06-14 | 2023-06-09 | 广东智能无人系统研究院(南沙) | Autonomous deployment and recovery system device of submersible |
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