Ice breaking test system for pull-type underwater vehicle

Abstract

The invention discloses a traction type underwater vehicle icebreaking test system, which comprises a pool body, a vehicle model and a traction assembly, and is characterized in that the pool body is used for storing water, and the vehicle model is arranged in the pool body and can float in water and linearly advance. The traction assembly comprises a lifting part and a traction part, the lifting part is provided with a lifting end capable of synchronously floating upwards along with the aircraft model, one end of the traction part is connected with the aircraft model, and the other end of the traction part is connected with the lifting end so that the aircraft model can rotate around the lifting part in the floating-upwards process. Enabling the aircraft model to float in the pool body, and advancing in the floating process. Due to the fact that the lifting end synchronously floats upwards along with the aircraft model, under the traction effect of the traction piece, the aircraft model can rotate around the lifting piece in the floating process, the aircraft model floats upwards to break ice in the process of moving along the arc, the moving track of the aircraft model is closer to the complex moving track of the underwater aircraft, and the moving efficiency of the underwater aircraft is improved. And various icebreaking test data are obtained, so that the test data have more reference significance.

Description

Technical Field

[0001] The invention relates to the field of icebreaking tests, and in particular to an icebreaking test system for a towed underwater vehicle. Background Art

[0002] In today's polar exploration process, polar icebreaking is very important for polar exploration operations. For underwater vehicles, polar navigation and surfacing, the main threat factors include floating ice, near the surface and thick ice layers. For waters covered with ice, submarines can use their own power to break ice and surface urgently, but the ice in the channel may pose a threat to submarines that break ice and surface. The hydrodynamic load, ice load, flow field between ice-water-submarine and ice layer damage mode of submarines when breaking ice are still unclear, so relevant research is needed.

[0003] The existing underwater vehicle icebreaking test system can be found in the patent application number CN202410197331.2. The existing underwater vehicle usually uses linear motion to surface and break ice. However, in real scenarios, due to the influence of water flow and objective factors such as the turning of the underwater vehicle, the underwater vehicle will cause the underwater vehicle to perform complex arc motion during the icebreaking process.

[0004] Therefore, how to simulate the icebreaking scene of underwater vehicles during arc motion is a technical problem that needs to be solved urgently. Summary of the invention

[0005] The purpose of the present invention is to overcome the above technical deficiencies and propose a towed underwater vehicle icebreaking test system to solve the technical problem in the prior art that it is difficult to simulate the icebreaking scene of an underwater vehicle during arc motion.

[0006] In order to achieve the above technical objectives, the present invention adopts the following technical solutions: The present invention provides a towed underwater vehicle icebreaking test system, which comprises: A tank body, which is used to store water; a model of an aircraft, which is built into the pool and can float and travel straight in water; and The traction assembly comprises a lifting member and a traction member, wherein the lifting member has a lifting end which can float synchronously with the aircraft model and can rotate, one end of the traction member is connected to the aircraft model, and the other end is connected to the lifting end, so that the aircraft model rotates around the lifting member during the floating process.

[0007] In some embodiments, the lifting member includes a lifting platform and a rotating seat, the rotating seat is rotatably installed on the lifting platform, the height of the lifting platform is adjustable so that the rotating seat floats synchronously with the rotating seat, and the lifting end is located on the rotating seat.

[0008] In some embodiments, the lifting platform includes a base cylinder, a sliding column and a lifting drive unit. The base cylinder is installed on the pool body, one end of the sliding column is movably inserted into the base cylinder, and the rotating seat is rotatably installed on the other end of the sliding column. The lifting drive unit is transmission-connected to the sliding column to drive the sliding column to slide relative to the base cylinder.

[0009] In some embodiments, the slide column is provided with a plurality of driving teeth along its length direction, and the lifting drive unit includes a lifting motor and a lifting gear, the lifting gear is sleeved on the rotating shaft of the lifting motor and meshes with a plurality of the driving teeth, and the lifting motor drives the lifting gear to drive the slide column to slide relative to the base tube.

[0010] In some embodiments, the length of the traction member is adjustable to change the turning radius of the aircraft model during the floating process.

[0011] In some embodiments, the traction member includes a traction rope and a winch, one end of the traction rope is wound around the winch, and the other end is connected to the aircraft model. The winch is rotatably installed at the lifting end and can stay at any position on its rotation trajectory.

[0012] In some embodiments, the traction member also includes a guide male wheel and a guide female wheel rotatably installed on the lifting end, the outer periphery of the guide female wheel is provided with a receiving groove, the traction rope is passed through the receiving groove, and the guide male wheel presses against the receiving groove to prevent the traction rope from escaping from the receiving groove.

[0013] In some embodiments, the traction member includes a traction motor, and the traction motor is drivingly connected to the capstan to drive the capstan to rotate.

[0014] In some embodiments, the aircraft model has a first traction buckle, and the traction rope has a second traction buckle, and the second traction buckle is connected to the first traction buckle so that the traction rope is connected to the aircraft model, wherein the first traction buckle has a first state of locking the second traction buckle, and a second state of disengaging from the second traction buckle.

[0015] In some embodiments, the aircraft model has a first flotation lock buckle, and the pool body has a second flotation lock buckle, and the second flotation lock buckle is connected to the first flotation lock buckle to fix the aircraft model to the pool body, wherein the first flotation lock buckle has a third state of locking the second flotation lock buckle, and a fourth state of disengaging from the second flotation lock buckle.

[0016] First, the floating ice is floated on the surface of the pool, and then the aircraft model is floated up in the pool and moves forward during the floating process. Since the lifting end floats up synchronously with the aircraft, under the traction of the traction member, the aircraft model can rotate around the lifting member during the floating process, so that the aircraft model can float up and break ice during the arc movement, so that the movement trajectory of the aircraft model can be closer to the complex movement trajectory of the underwater aircraft, and more diverse icebreaking test data can be obtained, making the test data more meaningful for reference. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 It is a structural schematic diagram of a towed underwater vehicle icebreaking test system provided by an embodiment of the present invention; Figure 2 is a schematic diagram of the structure of a traction assembly provided by an embodiment of the present invention; Figure 3 is a schematic structural diagram of a traction assembly provided by an embodiment of the present invention from another perspective; Figure 4 is a partial schematic diagram of an aircraft provided by an embodiment of the present invention; Explanation of the accompanying drawings: pool body 100, second flotation lock buckle 110, aircraft model 200, first traction lock buckle 210, first flotation lock buckle 220, traction assembly 300, lifting member 310, lifting platform 311, base cylinder 3111, sliding column 3112, driving tooth 31121, lifting drive unit 3113, lifting motor 31131, lifting gear 31132, rotating seat 312, traction member 320, traction rope 321, second traction lock buckle 3211, winch 322, guide male wheel 323, guide female wheel 324, traction motor 325. DETAILED DESCRIPTION

[0018] In order to make the purpose, technical solution and advantages of the present invention more clearly understood, the present invention is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not intended to limit the present invention.

[0019] In order to solve the technical problem that it is difficult to simulate the icebreaking scene of an underwater vehicle during its arc movement, the present invention provides a towed underwater vehicle icebreaking test system, which can enable the vehicle model 200 to float up and break ice during the arc movement, so that the movement trajectory of the vehicle model 200 can be closer to the complex movement trajectory of the underwater vehicle.

[0020] It should be noted that the towed underwater vehicle icebreaking test system of the present invention is used for underwater vehicle icebreaking tests. For the convenience of explanation, in the present invention, the towed underwater vehicle icebreaking test system is used for underwater vehicle icebreaking tests.

[0021] See also Figure 1 , Figure 1 The structure diagram of the towed underwater vehicle icebreaking test system in one embodiment of the present invention includes a pool 100, a vehicle model 200 and a towing assembly 300. The pool 100 is used to store water. The vehicle model 200 is built in the pool 100 and can float and move in a straight line in the water. The towing assembly 300 includes a lifting member 310 and a towing member 320. The lifting member 310 has a lifting end that can float synchronously with the vehicle model and can rotate. One end of the towing member 320 is connected to the vehicle model 200, and the other end is connected to the lifting end, so that the vehicle model 200 rotates around the lifting member 310 during the floating process.

[0022] In this embodiment, the floating ice is first floated on the water surface of the pool 100, and then the aircraft model 200 is floated in the pool 100 and moves forward during the floating process. Since the lifting end floats synchronously with the aircraft, under the traction of the traction member 320, the aircraft model 200 can rotate around the lifting member 310 during the floating process, so that the aircraft can float and break ice during the arc movement, so that the movement trajectory of the aircraft model 200 can be closer to the complex movement trajectory of the underwater aircraft, and more diverse icebreaking test data can be obtained, making the test data more meaningful for reference.

[0023] It should be noted that any aircraft model 200 that can float in water and has a driving force for linear movement is feasible. Such aircraft models 200 have simple functions and have very detailed public information in various public materials. Therefore, the specific structure of the aircraft model 200 is not elaborated in detail in this application.

[0024] In some embodiments, the lifting member 310 includes a lifting platform 311 and a rotating seat 312. The rotating seat 312 is rotatably mounted on the lifting platform 311. The height of the lifting platform 311 is adjustable so that the rotating seat 312 floats synchronously with the rotating seat 312, and the lifting end is located at the rotating seat 312. In the process of the aircraft model 200 floating up, the lifting platform 311 is raised synchronously with the aircraft model 200, so that the aircraft model 200, the traction member 320 and the rotating seat 312 are at the same horizontal height, and then the aircraft model 200 can change the moving trajectory under the traction of the traction member 320, so that the aircraft model 200 rotates around the rotating seat 312, and the rotation center of the rotating seat 312 is the center of the trajectory of the aircraft model 200.

[0025] It is understandable that the height of the lifting platform 311 needs to change as the aircraft model 200 floats upward, so it is necessary to obtain the vertical position information of the aircraft model 200 in real time, and then adjust the height of the lifting platform 311 according to the vertical position information of the aircraft model 200. The following are three ways to obtain the vertical position information of the aircraft model 200 in real time: 1. A pressure sensor can be installed on the outside of the aircraft model 200 to sense the water pressure through the pressure sensor, and then the depth of the aircraft model 200 can be inferred by the water pressure, so as to obtain the vertical position information of the aircraft model 200. However, it should be noted that the movement of the aircraft model 200 will cause the movement of the water flow. Due to the Bernoulli principle, the pressure detected by the pressure sensor is smaller than the static pressure. Therefore, when calculating the depth of the aircraft model 200, it is necessary to try to exclude the pressure change caused by the water flow speed.

[0026] 2. A number of optical sensors may be arranged in the vertical direction in the pool body 100. When the aircraft model 200 floats to the height where the optical sensors are located, the optical sensors may be used to capture the position information of the aircraft model 200 in the vertical direction. The denser the optical sensors are arranged, the more accurate the position information of the aircraft model 200 in the vertical direction is.

[0027] 3. A sonar system may be installed in the pool body 100 to obtain the vertical position information of the aircraft model 200 through the sonar system.

[0028] It should be noted that no matter how the position information of the aircraft model 200 in the vertical direction is obtained, the position information of the aircraft model 200 in the vertical direction will be fed back to the controller in the form of a signal, and the controller controls the lifting platform 311 to change its height according to the feedback signal. The controller and the control circuit related to the controller are not described in detail here, and those skilled in the art can make adaptive adjustments according to the actual usage scenario.

[0029] It should be emphasized that the implementation method of the lifting platform 311 is not the only one. As long as the implementation method of the lifting platform 311 can be adjusted in height, it is feasible. For example, the lifting platform 311 can be a simple hydraulic cylinder. The hydraulic cylinder is set vertically, and the piston rod of the hydraulic cylinder slides back and forth to change the total height of the hydraulic cylinder.

[0030] In some embodiments, the lifting platform 311 includes a base tube 3111, a sliding column 3112 and a lifting drive unit 3113. The base tube 3111 is installed on the pool body 100, one end of the sliding column 3112 is movably installed in the base tube 3111, and the rotating seat 312 is rotatably installed on the other end of the sliding column 3112. The lifting drive unit 3113 is connected to the sliding column 3112 to drive the sliding column 3112 to slide relative to the base tube 3111. During the floating process of the aircraft model 200, the sliding column 3112 can be synchronously slid relative to the base tube 3111, and the sliding column 3112 can push the rotating seat 312 to rise synchronously, so that the rotating seat 312 can always be at the same level as the aircraft model 200.

[0031] It is understandable that the implementation method of the lifting drive unit 3113 is diverse, and the requirements can be met by pushing the sliding column 3112 to slide relative to the base cylinder 3111. The lifting drive unit 3113 can adopt an electric push rod structure, a screw slider structure, a hydraulic cylinder, etc.

[0032] In some preferred embodiments, the slide column 3112 is provided with a plurality of driving teeth 31121 along its length direction, and the lifting drive unit 3113 includes a lifting motor 31131 and a lifting gear 31132. The lifting gear 31132 is sleeved on the rotating shaft of the lifting motor 31131 and meshes with the plurality of driving teeth 31121. The lifting motor 31131 drives the lifting gear 31132 to drive the slide column 3112 to slide relative to the base tube 3111. The lifting motor 31131 drives the lifting gear 31132 to rotate, and since the lifting gear 31132 meshes with the plurality of driving teeth 31121, the sliding column 3112 can be driven to slide relative to the base tube 3111 through the rotating lifting gear 31132.

[0033] In some embodiments, the length of the traction member 320 is adjustable to change the rotation radius of the aircraft model 200 during the floating process. The length of the traction member 320 determines the rotation radius of the aircraft model 200. By using different lengths of the traction member 320, navigation trajectories with different radii can be obtained.

[0034] On the basis of the above embodiment, the length of the traction member 320 can be changed during the buoyancy of the aircraft model 200, so as to obtain a navigation trajectory with a gradually changing turning radius, thereby simulating a more complex driving scene of the underwater aircraft.

[0035] It is understandable that the traction member 320 can be implemented in various ways. The traction member 320 can be rigid or flexible. The traction member 320 can be a rigid telescopic rod (or telescopic frame). The two ends of the telescopic rod (or telescopic frame) are respectively connected to the aircraft model 200 and the lifting end, which can then tow the aircraft model 200 to rotate around the lifting member 310. The rotation radius of the aircraft model 200 can be adjusted by changing the length of the telescopic rod (or telescopic frame).

[0036] In some other embodiments, the traction member 320 includes a traction rope 321 and a capstan 322. One end of the traction rope 321 is wound around the capstan 322, and the other end is connected to the aircraft model 200. The capstan 322 is rotatably installed at the lifting end and can stay at any position on its rotation trajectory. By rotating the capstan 322, the length of the portion of the traction rope 321 wound around the capstan 322 can be changed, and the length of the portion of the traction rope 321 extending from the capstan 322 can be changed. The length of the portion of the traction rope 321 extending from the capstan 322 determines the rotation radius of the aircraft model 200.

[0037] It is understandable that if the rotation direction of the aircraft model 200 is the same as the winding direction of the traction rope 321 on the capstan 322, the rotation of the aircraft model 200 will drive the lifting end to rotate, and will not change the length of the portion of the traction rope 321 wound around the capstan 322. If the rotation direction of the aircraft model 200 is opposite to the winding direction of the traction rope 321 on the capstan 322, the rotation of the aircraft model 200 will not drive the lifting end to rotate, but will change the length of the portion of the traction rope 321 wound around the capstan 322.

[0038] In order to prevent the problem that the rotation of the aircraft model 200 will change the length of the portion of the traction rope 321 wound around the winch 322, in some embodiments, the traction member 320 also includes a guide male wheel 323 and a guide female wheel 324 rotatably installed at the lifting end, and the outer periphery of the guide female wheel 324 is provided with a receiving groove, and the traction rope 321 is inserted into the receiving groove, and the guide male wheel 323 presses the receiving groove to prevent the traction rope 321 from escaping from the receiving groove. Since the traction rope 321 is clamped by the guide male wheel 323 and the guide female wheel 324, even if the rotation direction of the aircraft model 200 is opposite to the winding direction of the traction rope 321 on the winch 322, the length of the portion of the traction rope 321 wound around the winch 322 will not be changed.

[0039] In some embodiments, the traction member 320 includes a traction motor 325, which is connected to the capstan 322 to drive the capstan 322 to rotate. The traction motor 325 drives the capstan 322 to rotate, thereby changing the length of the portion of the traction rope 321 wound around the capstan 322. When the traction motor 325 locks the capstan 322, the length of the portion of the traction rope 321 wound around the capstan 322 can be maintained.

[0040] In some embodiments, the aircraft model 200 has a first traction buckle 210, and the traction rope 321 has a second traction buckle 3211. The second traction buckle 3211 is connected to the first traction buckle 210 so that the traction rope 321 is connected to the aircraft model 200, wherein the first traction buckle 210 has a first state of locking the second traction buckle 3211, and a second state of being detached from the second traction buckle 3211. During the process of the aircraft model 200 floating up, the first traction buckle 210 locks the second traction buckle 3211, so that the traction rope 321 is connected to the aircraft model 200, and the aircraft model 200 moves along an arc trajectory under the traction of the traction rope 321. When the aircraft model 200 floats up to the location of the floating ice, the first traction buckle 210 can be adjusted to the second state so that the aircraft model 200 is detached from the influence of the traction rope 321.

[0041] In some embodiments, the aircraft model 200 has a first floating lock buckle 220, and the pool body 100 has a second floating lock buckle 110, and the second floating lock buckle 110 is connected to the first floating lock buckle 220, so that the aircraft model 200 is fixed to the pool body 100, wherein the first floating lock buckle 220 has a third state of locking the second floating lock buckle 110, and has a fourth state of being separated from the second floating lock buckle 110. Before the aircraft model 200 floats, the first floating lock buckle 220 is in the third state, thereby fixing the aircraft model 200 on the inner wall of the pool body 100, and when the first floating lock buckle 220 is switched to the fourth state, the aircraft model 200 that has lost its restraint can float freely.

[0042] It is understandable that the implementation methods of the first traction lock buckle 210 and the second traction lock buckle 3211 are various, and the implementation methods of the first floating lock buckle 220 and the second floating lock buckle 110 are also various. The above-mentioned locks can adopt electromagnetic locks or electrically controlled mechanical locks.

[0043] In order to better understand the present invention, the following Figures 1 to 4 The technical solution of the present invention is described in detail: First, the floating ice is floated on the water surface of the pool 100. Before the aircraft model 200 floats, the first floating lock 220 is in the third state, so that the aircraft model 200 can be fixed on the inner wall of the pool 100. When the first floating lock 220 is switched to the fourth state, the aircraft model 200 that is free from restraint can float freely, and the aircraft can move forward. During the floating process of the aircraft model 200, the sliding column 3112 can be synchronously slid relative to the base tube 3111, and the sliding column 3112 can push the rotating seat 312 to rise synchronously, so that the rotating seat 312 can always be at the same level as the aircraft model 200. Under the traction of the traction member 320, the aircraft model 200 can rotate around the lifting member 310 during the floating process, so that the aircraft can float and break ice during the arc movement, so that the movement trajectory of the aircraft model 200 can be closer to the complex movement trajectory of the underwater aircraft, and more diverse icebreaking test data can be obtained, making the test data more meaningful for reference.

[0044] In the description of the present application, it should be noted that the terms "upper" and "lower" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present application. Unless otherwise expressly specified and limited, the terms "installed", "connected" and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be an indirect connection through an intermediate medium, or it can be a connection between the two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present application can be understood according to the specific circumstances.

[0045] It should be noted that, in this application, relational terms such as "first" and "second" are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, the elements defined by the sentence "comprise a ..." do not exclude the presence of other identical elements in the process, method, article or device including the elements.

[0046] The specific implementation of the present invention described above does not constitute a limitation on the protection scope of the present invention. Any other corresponding changes and modifications made based on the technical concept of the present invention should be included in the protection scope of the claims of the present invention.

Claims

1. A towed underwater vehicle icebreaking test system, characterized in that: include: A tank body, which is used to store water; A model of an aircraft, which is built into the pool and can float and travel straight in the water; as well as The traction assembly comprises a lifting member and a traction member, wherein the lifting member has a lifting end which can float synchronously with the aircraft model and can rotate, one end of the traction member is connected to the aircraft model, and the other end is connected to the lifting end, so as to pull the aircraft model to perform arc motion during the floating process.

2. The towed underwater vehicle icebreaking test system according to claim 1 is characterized in that: The lifting member comprises a lifting platform and a rotating seat, the rotating seat is rotatably mounted on the lifting platform, the height of the lifting platform is adjustable so that the rotating seat can float synchronously with the rotating seat, and the lifting end is located on the rotating seat.

3. The towed underwater vehicle icebreaking test system according to claim 2 is characterized in that: The lifting platform includes a base cylinder, a sliding column and a lifting drive unit. The base cylinder is installed on the pool body. One end of the sliding column is movably inserted into the base cylinder. The rotating seat is rotatably installed on the other end of the sliding column. The lifting drive unit is transmission-connected to the sliding column to drive the sliding column to slide relative to the base cylinder.

4. The towed underwater vehicle icebreaking test system according to claim 3 is characterized in that: The slide post is provided with a plurality of driving teeth along its length direction. The lifting drive unit includes a lifting motor and a lifting gear. The lifting gear is sleeved on the rotating shaft of the lifting motor and meshes with a plurality of the driving teeth. The lifting motor drives the lifting gear to drive the slide post to slide relative to the base tube.

5. The towed underwater vehicle icebreaking test system according to claim 1, characterized in that: The length of the traction member is adjustable to change the rotation radius of the aircraft model during the floating process.

6. The towed underwater vehicle icebreaking test system according to claim 5, characterized in that: The traction member includes a traction rope and a winch, one end of the traction rope is wound around the winch, and the other end is connected to the aircraft model. The winch is rotatably installed on the lifting end and can stay at any position on its rotation trajectory.

7. The towed underwater vehicle icebreaking test system according to claim 6, characterized in that: The traction member also includes a guide male wheel and a guide female wheel rotatably installed on the lifting end. The outer periphery of the guide female wheel is provided with a receiving groove, the traction rope is passed through the receiving groove, and the guide male wheel presses against the receiving groove to prevent the traction rope from escaping from the receiving groove.

8. The towed underwater vehicle icebreaking test system according to claim 6, characterized in that: The traction member comprises a traction motor, and the traction motor is drivingly connected to the capstan to drive the capstan to rotate.

9. The towed underwater vehicle icebreaking test system according to claim 6, characterized in that: The aircraft model has a first traction buckle, and the traction rope has a second traction buckle, and the second traction buckle is connected to the first traction buckle so that the traction rope is connected to the aircraft model, wherein the first traction buckle has a first state of locking the second traction buckle, and has a second state of disengaging from the second traction buckle.

10. The towed underwater vehicle icebreaking test system according to claim 1, characterized in that: The aircraft model has a first flotation lock buckle, and the pool body has a second flotation lock buckle, and the second flotation lock buckle is connected to the first flotation lock buckle to fix the aircraft model to the pool body, wherein the first flotation lock buckle has a third state of locking the second flotation lock buckle, and a fourth state of disengaging from the second flotation lock buckle.

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