CN113911281B - Underwater vehicle appearance optimization performance test platform and method - Google Patents
Underwater vehicle appearance optimization performance test platform and method Download PDFInfo
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- CN113911281B CN113911281B CN202111210745.7A CN202111210745A CN113911281B CN 113911281 B CN113911281 B CN 113911281B CN 202111210745 A CN202111210745 A CN 202111210745A CN 113911281 B CN113911281 B CN 113911281B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
- B63B—SHIPS OR OTHER WATERBORNE VESSELS; EQUIPMENT FOR SHIPPING
- B63B71/00—Designing vessels; Predicting their performance
- B63B71/20—Designing vessels; Predicting their performance using towing tanks or model basins for designing
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- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
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Abstract
The invention relates to an underwater vehicle appearance optimization performance test platform and method, belonging to the technical field of vehicle test; comprises a circulating water tank, a carrying platform and a testing system; the circulating water tank is used for providing a circulating water flow environment; the carrying platform is of a frame type structure, the top and the bottom of the carrying platform are provided with air floatation systems, the air floatation systems at the top are used for fixing the aircraft through the mounting platform, and the air floatation systems at the bottom are used for fixing the high-speed camera through the mounting platform; the top air floatation system is connected with the bottom air floatation system through a vertically arranged synchronous connecting rod, so that the synchronous movement of the top and bottom mounting platforms is realized, and the synchronous movement of the aircraft and the high-speed camera is further realized; in the experiment, the aircraft is fixed on the air bearing through the mounting platform, and the motion of the aircraft under water drives the motion of the air bearing, so that more real simulation motion is realized; meanwhile, synchronous follow-up of the high-speed camera is realized through the synchronous connecting rod, and synchronous shooting can be carried out on the flow field and the gesture of each aircraft.
Description
Technical Field
The invention belongs to the technical field of aircraft testing, and particularly relates to an underwater vehicle appearance optimization performance testing platform and method.
Background
The deep sea is provided with a large amount of material resources and numerous undisolved puzzles, and the underwater vehicle is used as an effective underwater vehicle and plays an increasingly important role in the aspects of strong national sea defense strength, exploration of deep sea mystery and the like. In the design of underwater vehicles, how to use profiles to reduce the fluid resistance and how to design a suitable profile to meet a complex marine environment is an important index of design. When the thrust coefficient, the propulsion efficiency, the lift-drag ratio and the flow field characteristics of the aircraft under different shapes are explored, the test is an indispensable link, and the shape of the aircraft which is most suitable for the target parameters is determined through the test.
Chinese patent CN202011343769.5 relates to a device and a method for measuring hydrodynamic performance of bionic flexible fins, and provides a testing device and a testing method. However, in the invention, the experimental model can only be fixed at a certain position to perform a water flow scouring experiment, but cannot perform an autonomous swimming experiment, so that the experimental application range is limited. The water tank of the invention only maintains stable flow field in the water tank through the water pump, the wave suppression plate, the water outlet and the water outlet, the water outlet is required to be regulated for each change of the incoming flow speed so that the flow field in the water tank is stable, and the scheme inevitably causes water resource waste and simultaneously causes larger water flow speed error and unstable flow field environment.
The invention provides an underwater vehicle appearance optimization performance test platform and method, which can provide a test platform for carrying out an underwater vehicle appearance optimization performance test in a circulating water tank and a test method based on the same.
The invention is that
Disclosure of Invention
The technical problems to be solved are as follows:
in order to avoid the defects of the prior art, the invention provides an underwater vehicle appearance optimization performance test platform and method, which are matched with a circulating water tank for testing; and carrying out high-precision hydrodynamic experiments of the aircraft through the circulating water tank and the air floatation system. Specifically, when the air floatation system is started, a hydrodynamic experiment in an autonomous swimming state can be performed; and when the air floatation system is closed, a still water flushing experiment can be performed. The invention can measure the key parameters of the propulsion efficiency, the thrust coefficient, the lift-drag ratio, the flow field characteristic and the like of the underwater vehicle under different shapes to measure the motion performance quality of the underwater vehicle, can determine the shape of the vehicle which is the most suitable for the target parameter according to experimental data, can provide experimental verification for traditional CFD numerical simulation and theoretical research, and is an underwater vehicle shape optimization performance test platform and test method with simple operation and high precision.
The technical scheme of the invention is as follows: the appearance optimization performance test platform of the underwater vehicle is characterized by comprising a circulating water tank, a carrying platform and a test system; the circulating water tank is used for providing a circulating water flow environment;
the carrying platform is of a frame type structure, the top and the bottom of the carrying platform are provided with air floatation systems, the air floatation systems at the top are used for fixing the aircraft through the mounting platform, and the air floatation systems at the bottom are used for fixing the high-speed camera through the mounting platform; the air floating system comprises a polished rod, a polished rod supporting seat and an air floating bearing, wherein the four polished rods are symmetrically arranged at the top and the bottom of the frame respectively through the polished rod supporting seat, and the air floating bearing is coaxially arranged on the polished rod; the two ends of the installation platform are respectively fixed on air bearing at two sides, and the aircraft is fixed under the installation platform through the telescopic rod; the air compressor is used for filling pressure air into the polish rod from the small hole of the air bearing, and simultaneously, the air pump is used for pumping out redundant pressure air, so that the air pressure saturation between the air bearing and the polish rod is kept, and the aircraft can freely move along the axial direction of the polish rod through the mounting platform; the air bearing at two sides of the top air floatation system is fixedly connected with the air bearing at two sides of the bottom air floatation system through a vertically arranged synchronous connecting rod respectively, so that the synchronous movement of the mounting platforms at the top and the bottom is realized, and the synchronous movement of the aircraft and the high-speed camera is further realized;
the test system comprises a six-axis force/moment sensor and a DPIV system; the DPIV system comprises a light source system, a high-speed camera, fluorescent particles and a computer containing a flow field analysis module; the light source system is arranged outside the carrying platform and used for illumination; the high-speed camera is arranged on a bottom mounting platform of the carrying platform and is positioned right below the aircraft and used for shooting flow fields, vortex fields and flapping wing movement modes.
The invention further adopts the technical scheme that: the circulating water tank comprises a circulating water tank, an impeller and an experiment section, wherein the circulating water tank comprises four corners, and a connecting pipeline between the first corner and the second corner is a backflow pipeline close to the ground;
the upper wall surface of the return pipe extends to a second corner, and a through hole is formed in the upper wall surface of the return pipe positioned at the second corner; the impeller is arranged at the through hole at the second corner, and is driven to rotate by the motor, so that water is pumped out of the through hole, the water level at the rear end is improved to flow to the downstream, and the water flow direction in the water tank is clockwise;
the experimental section is a section of water tank between the first corner and the fourth corner, the carrying platform is arranged on the outer side of the experimental section, the top air floatation system is positioned above the water tank, and the bottom air floatation system is positioned below the bottom of the water tank; the aircraft stretches into the water tank through the telescopic rod.
The invention further adopts the technical scheme that: the number of the impellers is 3, and the impellers are all aluminum impellers with the diameter of 0.6 m.
The invention further adopts the technical scheme that: the aperture of the through hole is larger than the diameter of the impeller.
The invention further adopts the technical scheme that: the return-type water tank comprises a frame and a wall surface, the wall surface has lateral bearing capacity through the frame, and the wall surface is a transparent acrylic plate.
The invention further adopts the technical scheme that: the experimental section is a cube structure with the thickness of 1.2mx1.2mx1.2m, the flow velocity in the central area is continuously adjustable from 0.1m/s to 0.8m/s, the control precision is 0.01m/s, and the flow velocity stabilizing time is 2min.
The invention further adopts the technical scheme that: the polish rod has a coefficient of friction of 0.0005.
The method for testing the appearance optimization performance test platform of the underwater vehicle is characterized by comprising the following specific steps of:
step 1: before starting an experiment, installing an aircraft, and zeroing the initial movement position of the aircraft;
step 2: all power supplies of the test platform are connected;
step 3: opening sensor recording software, testing the communication conditions of all sensors and a computer, checking whether the installation direction of the sensors is correct, and ensuring that experimental data can be accurately recorded and transmitted in experiments;
step 4: opening DPIV system recording software, firstly adjusting the position of a high-speed camera to ensure that the region of interest can be completely shot, then setting parameters of the aperture size, shooting frequency and focal length of the camera, and ensuring that the shooting of flow field, vortex field and flapping wing movement forms can be accurately performed in an experiment;
step 5: if a water flow flushing experiment is carried out, only the circulating water tank is started, the water flow speed is set to be the experiment flow speed v, the air compressor and the air extractor are not started, and the position of the aircraft is kept fixed; if the autonomous swimming experiment of the aircraft is carried out, the air compressor and the air extractor are started, so that the aircraft and the high-speed camera can carry out low-friction synchronous free movement on the polished rod;
step 6: when the aircraft keeps steady movement, starting to record experimental data, storing and exporting mechanical data recorded by the six-axis force/moment sensor, and storing and exporting flow field parameters recorded by the DPIV system;
step 7: when replacing aircrafts with different shapes for experiments, the operation of power-off is needed to prevent experiment personnel from getting electric shock and damaging experiment equipment, and the steps 1-6 are repeated after waiting for the stable liquid level in the circulating water tank;
step 8: after the experiment is finished, all power supplies are turned off;
step 9: and processing data, calculating parameters such as thrust coefficient, propulsion efficiency, lift-drag ratio and the like, and analyzing a flow field by utilizing an analysis module in the DPIV system to obtain vortex flow field, speed field and pressure field information.
The invention further adopts the technical scheme that: the power supply in the step 2 comprises an external power supply of the sensor net cage, a power supply of the DPIV system and a power supply of the circulating water tank.
Advantageous effects
The invention has the beneficial effects that:
(1) The invention realizes synchronous follow-up (friction coefficient is about 0.0005) by means of the air floatation system to achieve the drag reduction effect, the air floatation system does not contain a driving device, and only an air compressor and an air extractor are used for maintaining the air pressure between the air floatation bearing and the polish rod to be stable. In the experiment, the aircraft is fixed on the air bearing through the mounting platform, and the motion of the aircraft under water drives the motion of the air bearing, so that more real simulation motion is realized; meanwhile, synchronous follow-up of the high-speed camera is realized through the synchronous connecting rod, and synchronous shooting can be carried out on the flow field and the gesture of each aircraft.
(2) The size of the experimental section of the circulating water channel used in the invention is 1.2 x 1.2m 3 In the experiment, the dimension design of the experimental model is carried out according to the similarity criterion and the size of the driving device of the model. In the test, the hydrodynamic force experiment in an autonomous swimming state can be carried out when the air floatation system is started; and when the air floatation system is closed, a still water flushing experiment can be performed.
(3) The underwater vehicle appearance optimization performance test platform and method can test and measure key parameters such as propulsion efficiency, thrust coefficient, lift-drag ratio, flow field characteristics and the like of the underwater vehicle under different appearances to measure the motion performance of the vehicle, so that the appearance of the vehicle which is most matched with the target parameters can be obtained, and experimental verification can be provided for traditional CFD numerical simulation and theoretical research.
Drawings
FIG. 1 is a top view of a circulation tank;
FIG. 2 is a layout view of a circulating water tank and a carrying platform;
FIG. 3 is a diagram of a mounting platform;
fig. 4 is a test flow chart.
Reference numerals illustrate: 1-a circulating water tank, 2-a circulating water tank experimental section, 3-a second corner, 4-a third corner, 5-a fourth corner, 6-a first corner, 7-an impeller, 8-a carrying platform, 9-a polished rod supporting seat, 10-a polished rod, 11-a synchronous connecting rod, 12-an air bearing, 13-a high-speed camera, 14-a mounting platform, 15-a light source system and 16-an aircraft.
Detailed Description
The embodiments described below by referring to the drawings are illustrative and intended to explain the present invention and should not be construed as limiting the invention.
In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings are merely for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present invention.
Referring to fig. 2, the invention relates to an underwater vehicle appearance optimization performance test platform and method, which is completed based on a circulating water tank, wherein the underwater vehicle appearance optimization performance test platform comprises a circulating water tank 1, a carrying platform 8 and a test system, wherein the carrying platform 8 is provided with two sets of air floatation systems, the air floatation system positioned above a circulating water tank experimental section 2 is used for fixing a vehicle 16 through a mounting platform 14, the mounting platform 14 is fixed on an air floatation bearing 12, and the vehicle is beneficial to extending into the circulating water tank experimental section 2; the air floatation system positioned below the experiment section 2 of the circulating water tank is used for fixing the high-speed camera 13 through the mounting platform 14.
Referring to fig. 1, the circulating water tank comprises a circulating water tank, an impeller 7 and an experiment section 2, wherein the circulating water tank comprises four corners, and a connecting pipeline between a first corner 6 and a second corner 3 is a backflow pipeline close to the ground; the upper wall surface of the return pipe extends to the second corner 3, and a through hole is formed in the upper wall surface of the return pipe positioned at the second corner 3; the impeller 7 is arranged at the through hole of the second corner 3, and the impeller 7 is driven to rotate by a motor to pump water out of the through hole, so that the water level at the rear end is increased to flow downstream, and the water flow direction in the water tank is clockwise; the experimental section 2 is a section of water tank between the first corner 6 and the fourth corner 5, the carrying platform 8 is arranged outside the experimental section 2, the top air floatation system is positioned above the water tank, and the bottom air floatation system is positioned below the bottom of the water tank; the aircraft 16 is extended into the flume by a telescoping rod.
Referring to fig. 3, the carrying platform 8 is in a frame structure, the top and the bottom of the carrying platform are respectively provided with an air floatation system, the air floatation system at the top is used for fixing the aircraft through the mounting platform, and the air floatation system at the bottom is used for fixing the high-speed camera 13 through the mounting platform; the air floatation system comprises a polished rod 10, a polished rod supporting seat 9 and an air floatation bearing 12, wherein the four polished rods 10 are symmetrically arranged at the top and the bottom of the frame respectively through the polished rod supporting seat 9, and the air floatation bearing 12 is coaxially arranged on the polished rod 10; the two ends of the mounting platform 14 are respectively fixed on the air bearing 12 at the two sides, and the aircraft 16 is fixed under the mounting platform 14 through a telescopic rod; filling pressure air into the polish rod 10 from the small hole of the air bearing 12 through an air compressor, and simultaneously pumping out redundant pressure air through an air pump, so that air pressure saturation between the air bearing 12 and the polish rod 10 is kept, and the aircraft 16 can freely move along the axial direction of the polish rod 10 through the mounting platform 14; the air bearing 12 on two sides of the top air floatation system is fixedly connected with the air bearing 12 on two sides of the bottom air floatation system through a vertically arranged synchronous connecting rod 11 respectively, so that the synchronous movement of the mounting platform 14 on the top and the mounting platform on the bottom is realized, and the synchronous movement of the aircraft 16 and the high-speed camera 13 is further realized;
the test system comprises a six-axis force/moment sensor and a DPIV system; the DPIV system comprises a light source system 15, a high-speed camera 13, fluorescent particles and a computer containing a flow field analysis module; the light source system 15 is arranged outside the carrying platform and used for illumination; the high-speed camera 13 is arranged on a bottom mounting platform 14 of the carrying platform 8 and is positioned right below the aircraft 16 for shooting of flow fields, vortex fields and flapping wing movement forms.
Examples:
fig. 1 is a plan view of a circulating water tank, wherein a test section is formed by bonding transparent acrylic plates, a tension-restraining frame is arranged around the test section to enable the test section to have lateral bearing capacity, and other parts of a main body of a hole body are formed by welding 15mm thick PP plates. The power of the circulating water tank is provided by three aluminum impellers (8 blades) 10 with the diameter of 0.6 m; the connecting pipeline between the first corner 6 and the second corner 3 is a backflow pipeline close to the ground and extends to the second corner 3, a circular hole with a diameter slightly larger than 0.6m is formed in the upper surface of the second corner 3, water is pumped out of the circular hole when the impeller rotates, the water level at the rear end is increased, and the water flows to the downstream, so that the water flow direction is clockwise; the experimental section 2 is a 1.2mx1.2mx1.2mcube, the flow rate in the central area is continuously adjustable from 0.1m/s to 0.8m/s, the control precision is 0.01m/s, and the flow rate stabilizing time is 2min.
Fig. 2 is a layout diagram of the circulating water tank and the carrying platform, wherein the supporting frame part of the carrying platform 8 is constructed by alloy steel and is fixed on the horizontal ground. Two sets of air floatation systems are arranged on the carrying platform 8, the air floatation systems above the circulating water tank experimental section 2 are used for fixing the aircraft 16 through the mounting platform 14, and the mounting platform 14 is fixed on the air floatation bearing 12, so that the aircraft can extend into the circulating water tank experimental section 2; the air floatation system positioned below the experiment section 2 of the circulating water tank is provided with a high-speed camera 13 fixed through a mounting platform 14, and a light source system 15 is distributed on the side of the experiment section 2 so as to conveniently illuminate the whole experiment section.
Fig. 3 is a view of a carrying platform, two sets of air floating systems consisting of a polished rod 10, a polished rod supporting seat 9 and an air floating bearing 12 are fixed at the upper end and the lower end of the carrying platform 8, and two mounting platforms 14 are fixed on the air floating bearing 12 for fixing an aircraft 16 and a high-speed camera 13. Simultaneously, the upper air bearing 12 and the lower air bearing 12 on the same side are connected through the synchronous connecting rod 11, so that when the aircraft 16 moves in the circulating water tank 1, the upper installation platform 14 is driven to move, and the lower installation platform 14 is driven to synchronously move, so that the high-speed camera synchronously shoots the flow field and the gesture of the aircraft; the air compressor and the air extractor are closed when the water flow scouring experiment is carried out, so that the aircraft 16 can be ensured to keep fixed in position.
The testing method comprises the following steps:
step one: before starting an experiment, installing an aircraft, and zeroing the initial movement position of the aircraft;
step two: all power supplies of the test platform are connected, including an external power supply of the sensor net cage, a power supply of the DPIV system and a power supply of the circulating water tank;
step three: opening sensor recording software, testing the communication conditions of all sensors and a computer, checking whether the installation direction of the sensors is correct, and ensuring that experimental data can be accurately recorded and transmitted in later experiments;
step four: opening DPIV system recording software, firstly adjusting the position of a high-speed camera to ensure that the concerned region can be completely shot, then setting parameters such as the aperture size, shooting frequency, focal length and the like of the camera, and ensuring that the shooting of flow fields, vortex fields and flapping wing movement forms can be accurately carried out in later experiments;
step five: if a water flow flushing experiment is carried out, only the circulating water tank is started, the water flow speed is set to be the experiment flow speed v, the air compressor and the air extractor are not started, and the position of the aircraft is kept fixed; if the autonomous swimming experiment of the aircraft is carried out, the air compressor and the air extractor are started, so that the aircraft and the high-speed camera can carry out low-friction synchronous free movement on the polished rod;
step six: when the aircraft keeps steady movement, starting to record experimental data, storing and exporting mechanical data recorded by the six-axis force/moment sensor, and storing and exporting flow field parameters recorded by the DPIV system;
step seven: when replacing aircrafts with different shapes for experiments, the operation of power-off is needed to prevent the experimenters from electric shock and damaging experimental equipment, and the steps 1-6 are repeated stably waiting for the liquid level in the circulating water tank;
step eight: and (5) after the test is finished, turning off all power supplies.
Step nine: and processing data, calculating parameters such as thrust coefficient, propulsion efficiency, lift-drag ratio and the like, and analyzing a flow field by utilizing an analysis module in the DPIV system to obtain information such as a vortex flow field, a speed field, a pressure field and the like.
Autonomous swimming experiment notice:
(1) In order to sufficiently improve the test accuracy in the experiment, wind resistance measurement should be performed on the mounting platform 14 and the synchronous connecting rod 11 before the mounting model performs the experiment. The method aims to accurately obtain the net thrust value when experimental mechanical data are processed in the later period.
(2) When the air floatation system is started, the air compressor is started firstly, air is filled into the air floatation bearing, and the air extractor is started after sufficient air exists in the bearing, so that the air pressure in the bearing is kept stable; when the air compressor is closed, the air inflow of the air compressor is firstly regulated to enable the air pump to pump out air, when the indication number of the barometer to be observed is close to the outside air pressure, the air pump and the air compressor are turned off, the residual air is naturally discharged, and the damage of a polish rod caused by untimely closing of the air pump is avoided.
The image file shot by the high-speed camera is imported into post-processing software to perform flow field characteristic analysis such as generation, diffusion and dissipation processes of leading vortex, wake vortex and wingtip vortex, speed difference of different points in the flow field, pressure distribution of points in the flow field and the like, and track tracking can be performed on each key position point of the aircraft body through the post-processing software, so that the appearance of the aircraft which is most suitable for target parameters can be obtained, and experimental verification can be provided for traditional CFD numerical simulation and theoretical research.
Although embodiments of the present invention have been shown and described above, it will be understood that the above embodiments are illustrative and not to be construed as limiting the invention, and that variations, modifications, alternatives, and variations may be made in the above embodiments by those skilled in the art without departing from the spirit and principles of the invention.
Claims (9)
1. The appearance optimization performance test platform of the underwater vehicle is characterized by comprising a circulating water tank, a carrying platform and a test system; the circulating water tank is used for providing a circulating water flow environment;
the carrying platform is of a frame type structure, the top and the bottom of the carrying platform are provided with air floatation systems, the air floatation systems at the top are used for fixing the aircraft through the mounting platform, and the air floatation systems at the bottom are used for fixing the high-speed camera through the mounting platform; the air floating system comprises a polished rod, a polished rod supporting seat and an air floating bearing, wherein the four polished rods are symmetrically arranged at the top and the bottom of the frame respectively through the polished rod supporting seat, and the air floating bearing is coaxially arranged on the polished rod; the two ends of the installation platform are respectively fixed on air bearing at two sides, and the aircraft is fixed under the installation platform through the telescopic rod; the air compressor is used for filling pressure air into the polish rod from the small hole of the air bearing, and simultaneously, the air pump is used for pumping out redundant pressure air, so that the air pressure saturation between the air bearing and the polish rod is kept, and the aircraft can freely move along the axial direction of the polish rod through the mounting platform; the air bearing at two sides of the top air floatation system is fixedly connected with the air bearing at two sides of the bottom air floatation system through a vertically arranged synchronous connecting rod respectively, so that the synchronous movement of the mounting platforms at the top and the bottom is realized, and the synchronous movement of the aircraft and the high-speed camera is further realized;
the test system comprises a six-axis force/moment sensor and a DPIV system; the DPIV system comprises a light source system, a high-speed camera, fluorescent particles and a computer containing a flow field analysis module; the light source system is arranged outside the carrying platform and used for illumination; the high-speed camera is arranged on a bottom mounting platform of the carrying platform and is positioned right below the aircraft and used for shooting flow fields, vortex fields and flapping wing movement modes.
2. The underwater vehicle profile optimization performance testing platform of claim 1, wherein: the circulating water tank comprises a circulating water tank, an impeller and an experiment section, wherein the circulating water tank comprises four corners, and a connecting pipeline between the first corner and the second corner is a backflow pipeline close to the ground;
the upper wall surface of the return pipe extends to a second corner, and a through hole is formed in the upper wall surface of the return pipe positioned at the second corner; the impeller is arranged at the through hole at the second corner, and is driven to rotate by the motor, so that water is pumped out of the through hole, the water level at the rear end is improved to flow to the downstream, and the water flow direction in the water tank is clockwise;
the experimental section is a section of water tank between the first corner and the fourth corner, the carrying platform is arranged on the outer side of the experimental section, the top air floatation system is positioned above the water tank, and the bottom air floatation system is positioned below the bottom of the water tank; the aircraft stretches into the water tank through the telescopic rod.
3. The underwater vehicle profile optimization performance testing platform of claim 2, wherein: the number of the impellers is 3, and the impellers are all aluminum impellers with the diameter of 0.6 m.
4. The underwater vehicle profile optimization performance testing platform of claim 2, wherein: the aperture of the through hole is larger than the diameter of the impeller.
5. The underwater vehicle profile optimization performance testing platform of claim 2, wherein: the return-type water tank comprises a frame and a wall surface, the wall surface has lateral bearing capacity through the frame, and the wall surface is a transparent acrylic plate.
6. The underwater vehicle profile optimization performance testing platform of claim 2, wherein: the experimental section is a cube structure with the thickness of 1.2mx1.2mx1.2m, the flow velocity in the central area is continuously adjustable from 0.1m/s to 0.8m/s, the control precision is 0.01m/s, and the flow velocity stabilizing time is 2min.
7. The underwater vehicle profile optimization performance testing platform of claim 1, wherein: the polish rod has a coefficient of friction of 0.0005.
8. A method for testing an underwater vehicle appearance optimization performance test platform as claimed in any one of claims 1 to 7, characterized by the specific steps of:
step 1: before starting an experiment, installing an aircraft, and zeroing the initial movement position of the aircraft;
step 2: all power supplies of the test platform are connected;
step 3: opening sensor recording software, testing the communication conditions of all sensors and a computer, checking whether the installation direction of the sensors is correct, and ensuring that experimental data can be accurately recorded and transmitted in experiments;
step 4: opening DPIV system recording software, firstly adjusting the position of a high-speed camera to ensure that the region of interest can be completely shot, then setting parameters of the aperture size, shooting frequency and focal length of the camera, and ensuring that the shooting of flow field, vortex field and flapping wing movement forms can be accurately performed in an experiment;
step 5: if a water flow flushing experiment is carried out, only the circulating water tank is started, the water flow speed is set to be the experiment flow speed v, the air compressor and the air extractor are not started, and the position of the aircraft is kept fixed; if the autonomous swimming experiment of the aircraft is carried out, the air compressor and the air extractor are started, so that the aircraft and the high-speed camera can carry out low-friction synchronous free movement on the polished rod;
step 6: when the aircraft keeps steady movement, starting to record experimental data, storing and exporting mechanical data recorded by the six-axis force/moment sensor, and storing and exporting flow field parameters recorded by the DPIV system;
step 7: when replacing aircrafts with different shapes for experiments, the operation of power-off is needed to prevent experiment personnel from getting electric shock and damaging experiment equipment, and the steps 1-6 are repeated after waiting for the stable liquid level in the circulating water tank;
step 8: after the experiment is finished, all power supplies are turned off;
step 9: and processing data, calculating parameters such as thrust coefficient, propulsion efficiency, lift-drag ratio and the like, and analyzing a flow field by utilizing an analysis module in the DPIV system to obtain vortex flow field, speed field and pressure field information.
9. The method for testing an underwater vehicle profile optimization performance test platform according to claim 8, wherein: the power supply in the step 2 comprises an external power supply of the sensor net cage, a power supply of the DPIV system and a power supply of the circulating water tank.
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