CN113650805B - Device and method for testing water surface floating characteristic model of rotor wing type aircraft - Google Patents
Device and method for testing water surface floating characteristic model of rotor wing type aircraft Download PDFInfo
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- CN113650805B CN113650805B CN202110872120.0A CN202110872120A CN113650805B CN 113650805 B CN113650805 B CN 113650805B CN 202110872120 A CN202110872120 A CN 202110872120A CN 113650805 B CN113650805 B CN 113650805B
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- 238000004088 simulation Methods 0.000 claims abstract description 32
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- 229920000271 Kevlar® Polymers 0.000 claims description 22
- 239000004761 kevlar Substances 0.000 claims description 22
- 238000005259 measurement Methods 0.000 claims description 11
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
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Abstract
The invention belongs to the technical field of aviation aircraft tests, and particularly relates to a device and a method for testing a water surface floating characteristic model of a rotor wing type aircraft. The device comprises a rotor wing type aircraft water surface floating characteristic test model (100), a water area guide rail (200), a test water area adjusting bracket (300), a wind speed simulation system (400), a wave generation system (500), a model connecting part (600), a sensor system (700) and a control system (800). According to the invention, by developing a test method of the water surface floating characteristic model of the rotary wing aircraft, the stable balance capacity, the stormy wave response parameters and the floating time of the rotary wing aircraft model in the water surface floating process can be measured, so that technical support is provided for the water surface use condition and emergency escape programming of the full-size rotary wing aircraft, and guiding advice is provided for reducing casualties and damage to the body structure of the rotary wing aircraft caused by insufficient floating capacity. The method is practical, feasible, simple to operate, reliable in test result and wide in application range.
Description
Technical Field
The invention belongs to the technical field of aviation aircraft tests, and particularly relates to a device and a method for testing a water surface floating characteristic model of a rotor wing type aircraft.
Background
The rotor wing type aircraft has the characteristics of vertical lifting, hovering, low-altitude or low-speed flight and the like which are not possessed by a common fixed wing aircraft. But is widely applied to the fields of transportation, patrol, maritime search and rescue, and the like. However, as the flight time of rotorcraft increases, so does the likelihood of failure in performing the mission. When the rotor aircraft adopts water forced landing, irregular swinging and attack movement can occur under the interference of sea storm, and the structural strength of a water contact part and the emergency escape reaction capability of personnel in the aircraft are directly affected. The 27 th part of the China civil aviation regulation, the normal type rotor craft aviation regulation and the 29 th part of the transportation type rotor craft aviation regulation put forward specific requirements on the water surface floating capacity of the rotor craft, and under reasonable and possible water conditions, the floating time and balancing of the rotor craft can enable all passengers to leave the rotor craft and take on life rafts required by regulations. "
In the process of verifying the compliance of regulations, a model test or a rotorcraft analogy method similar to the known configuration is generally adopted, but the rotorcraft with the similar configuration has less performance research data due to the fact that the research of the water forced landing problem in China starts later and the restrictions of various technical levels are added. In order to research the water surface floating characteristics of the rotary wing aircraft, the most intuitive and effective method at present is to research the parameters such as stable balance performance, response characteristics, capsizing limit conditions, floating time and the like of a rotary wing aircraft scaling model under different water surface conditions through a rotary wing aircraft scaling model test. By developing response characteristic forecast research of the full-size aircraft, technical support is provided for sea condition judgment of water entering and floating stability of the real aircraft.
At present, the prior art does not disclose a practical device and a method for testing the water surface floating characteristic model of a rotor wing type aircraft.
Disclosure of Invention
The purpose of the invention is that: aiming at the defects of the prior art, a practical rotor wing type aircraft water surface floating characteristic model test device and a method are provided.
The technical scheme of the invention is as follows: in order to achieve the above object, according to a first aspect of the present invention, a rotor type aircraft water surface floating characteristic model test device is provided, which comprises a rotor type aircraft water surface floating characteristic test model 100, a water area guide rail 200, a test water area adjusting bracket 300, a wind speed simulation system 400, a wave generation system 500, a model connecting part 600, a sensor system 700 and a control system 800;
the rotor wing type aircraft water surface floating characteristic test model 100 is arranged in a test water area pool;
the water area guide rail 200 is two steel rails parallel to the pool walls at the two sides of the water area pool of the test water area and is fixedly connected with the pool walls at the two sides of the water area pool of the test water area; the test waters adjustment carriage 300 is located above the test waters pool and is free to slide along the waters rail 200; the method can be used for model position adjustment and course control in the test process;
the wind speed simulation system 400 is positioned above the water surface of the water pool of the test water area, and two ends of the wind speed simulation system are fixedly connected with the pool walls at two sides of the water pool of the test water area respectively, so that the wind load meeting the test requirements can be simulated and output;
the wave generation system 500 is installed at one end of the water pool of the test water area, which is close to the wind speed simulation system 400, and two side pool walls, and can be used for outputting and adjusting target parameter waves;
the rotor wing type aircraft water surface floating characteristic test model 100 is connected with the test water area adjusting bracket 300 through the model connecting part 600; during the test, the tester can control and adjust the model heading and position through the model connecting part 600;
the sensor system 700 is installed on the rotor plane water surface floating characteristic test model 100, and is used for monitoring and collecting motion gesture information of the model in a floating process in real time and communicating with the control system 800;
the control system 800 is disposed on the test waters adjustment stand 300 and is communicatively coupled to the sensor system 700.
In one possible embodiment, the test waters adjustment stand 300 comprises a test operation platform 301, a bottom reinforcement structure 302, a pulley arrangement 303; the test operation platform 301 is located on the upper plane of the test water area adjusting bracket 300 and can be used as a movable area of a tester; the bottom reinforcing structure 302 is a truss structure, and is fixedly connected below the test operation platform 301, and is used for reinforcing the overall structural strength of the test operation platform; the pulley devices 303 are arranged at two symmetrical positions below the test operation platform 301 and are fixedly connected with the lower part of the test operation platform 301; the pulley device 303 is connected with the water area guide rail 200 in a sliding fit manner, and can be used for adjusting the relative position between the test water area adjusting bracket and the water area guide rail.
In one possible embodiment, the wind speed simulation system 400 includes a wind turbine group 401, a wind turbine mounting beam 402; the fan installation beam 402 is used for installing the fan set 401, and two ends of the fan installation beam 402 are fixedly connected with two lateral tank walls of a water tank of the test water area respectively; the fan set 401 is installed below the fan installation beam 402, and the fan set 401 can simulate and output the wind load size meeting the test requirement.
In one possible embodiment, the wave generating system 500 includes a wave generator electric control part, an electric cylinder 502, a wave generating plate 503, and a wave absorbing plate 504; the wave generator control part can be used for inputting wave parameters and controlling the motion frequency and the motion thread of the electric cylinder 502; the electric cylinder 502 is fixedly connected with the pool wall of the water pool of the test water area; the electric cylinder 502 is fixedly connected with the wave-making plate 503; the electric cylinder 502 can drive the wave-making plate 503 to perform mechanical motion, so as to realize the analog output of the target wave parameters; the wave-absorbing plate 504 is hinged with the lateral pool walls at two sides of the water pool of the test water area, and the wave-absorbing plate 504 can absorb waves of water surface waves of the test water area, so that the test water area can be quickly restored to calm.
In one possible embodiment, the model connection part 600 comprises a suspension loop 601, a kevlar mooring line 602; the hanging ring 601 is fixedly connected with the head end and the tail end of the rotor wing type aircraft water surface floating characteristic test model 100 and is used for solidifying the Kevlar mooring ropes 602; the kevlar mooring rope 602 is used for controlling the water surface floating posture/wave encountering direction of the test model, one end of the kevlar mooring rope is fixedly connected with the hanging ring 601, and the other end of the kevlar mooring rope is connected with the test water area adjusting bracket 300 and is manually controlled by a test person on the test operation platform 301.
In one possible embodiment, the sensor system 700 includes an inertial measurement unit 701, a wireless collector 702, a battery 703, a signal receiving antenna 704, a power control switch 705; the inertial measurement unit 701 is fixed at the gravity center of the rotor aircraft water surface floating characteristic test model 100 and is used for monitoring the motion gesture of the model in the floating process in real time; the wireless collector 702 and the battery 703 are fixed inside the rotor wing type aircraft water surface floating characteristic test model 100, and the wireless collector 702 is used for collecting and recording test parameters of the inertial measurement unit 701; the battery 703 is electrically connected with the inertial measurement unit 701, the wireless collector 702 and the signal receiving antenna 704 respectively, and is used for supplying power to the sensor inside the model; the signal receiving antenna 704 is fixed at the top position outside the rotor aircraft water surface floating characteristic test model 100 and is used for receiving a control signal sent by a control system; the power supply control switch 705 is fixed at the top position outside the rotor type aircraft water surface floating characteristic test model 100, and is electrically connected to the battery 703 as a control switch of the battery 703.
In one possible embodiment, the control system 800 includes a remote control 801, a data analysis system 803; the remote control device 801 is disposed on the test operation platform 301, and is configured to send a control signal to the signal receiving antenna 704 in the sensor system 700, so as to implement remote operation on the working state of the wireless collector 702; the data analysis system 803 is used to analytically demonstrate the effectiveness of the test data collected by the sensor system 700.
Further, the control system 800 further includes a camera system 802, where the camera system 802 may be one or a combination of a fixed camera and a handheld camera, and is used to capture a test status image of the rotor plane water surface floating characteristic test model 100 during the test, which is manually controlled by a worker on the operation platform 301.
According to a second aspect of the present invention, there is provided a method for testing a water surface floating characteristic model of a rotary wing type aircraft, using the above-mentioned device for testing a water surface floating characteristic model of a rotary wing type aircraft, comprising the steps of:
step 1: pre-debugging the operation parameters of the wind speed simulation system 400 and the wave generation system 500 to ensure that the wind speed and wave parameters of the simulation output meet the test precision requirements;
step 2: after the preparation of the work is completed, the wave-absorbing plate 504 in the wave-making system 500 is pulled up, so that the wave-absorbing plate 504 is far away from the water surface and keeps a vertical state with the water surface of the pool of the test water area;
step 3: after a power supply control switch 705 in the sensor system 700 is turned on, the rotor type aircraft water surface floating characteristic test model 100 is placed in a test water area between the test water area adjusting bracket 300 and the wind speed simulation system 400 through the movable end of the kevlar mooring rope 602 in the model connecting part 600, and is adjusted to a test target course;
step 4: the wave generation system 500, the wind speed simulation system 400 and the control system 800 are sequentially started to work normally;
step 5: when wave and wind speed interference reach the test water area where the rotor wing type aircraft water surface floating characteristic test model 100 is located, the model encountering wave direction is controlled by adjusting and controlling the relative angle and absolute length between the movable end of the Kevlar mooring rope 602 and the model; in the test process, the wireless collector 702 records parameters of roll angle, pitch angle, roll angular velocity and pitch angular velocity of the rotor type aircraft water surface floating characteristic test model 100 in the water surface floating process in real time, and the camera system 802 records the whole motion process of the rotor type aircraft water surface floating characteristic test model 100;
step 6: when the floating time of the rotor plane water surface floating characteristic test model 100 on the water surface reaches a target value, closing a remote control device 801 and a shooting system 802 in the wave making system 500, the wind speed simulation system 400 and the control system 800 to stop swinging and drifting of the rotor plane water surface floating characteristic test model 100, and fishing the rotor plane water surface floating characteristic test model 100 through a Kevlar mooring rope 601 to recheck and adjust the test state;
step 7: by adopting the data analysis system 803 in the control system 800, the roll angle, pitch angle, roll angle speed and pitch angle speed parameters acquired by the sensor system 700 are utilized to draw a time history change curve of the roll angle along with time, the validity of the test state is evaluated by analyzing the correlation between the change rule of the curve and the motion state of the model, invalid data are removed, and the recorded valid data comprise the change curve conditions of the model weight, the gravity center position, the wind speed, the model heading, the wave parameters, the roll angle, the pitch angle, the roll angle speed and the pitch angle speed along with time.
In one possible embodiment, in the step 5, the relative position of the test waters adjusting carriage 300 on the waters guide rail 200 is adjusted to avoid the adverse collision interference generated between the rotor plane water surface floating characteristic test model 100 and the test waters adjusting carriage 300 during the movement.
The invention has the beneficial effects that: according to the invention, by developing a test method of the water surface floating characteristic model of the rotary wing aircraft, the stable balance capacity, the stormy wave response parameters and the floating time of the rotary wing aircraft model in the water surface floating process can be measured, so that technical support is provided for the water surface use condition and emergency escape programming of the full-size rotary wing aircraft, and guiding advice is provided for reducing casualties and damage to the body structure of the rotary wing aircraft caused by insufficient floating capacity. The method is practical, feasible, simple to operate, reliable in test result and wide in application range.
Drawings
FIG. 1 is a schematic view of a test apparatus according to a preferred embodiment of the present invention
FIG. 2 is a schematic diagram showing the structure of a wave generating system 500 in a test apparatus according to a preferred embodiment of the present invention
FIG. 3 is a schematic diagram of a wind speed simulation system 400 in a test apparatus according to a preferred embodiment of the present invention
FIG. 4 is a schematic diagram showing the structure of the test waters area adjusting stand 300, the sensor system 700, and the control system 800 in the test apparatus according to the preferred embodiment of the present invention
Detailed Description
The present invention will be described in further detail with reference to the drawings and examples, in order to make the objects, technical solutions and advantages of the present invention more apparent. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the scope of the invention.
As shown in fig. 1, according to a first aspect of the present invention, a rotor type aircraft water surface floating characteristic model test device is provided, which comprises a rotor type aircraft water surface floating characteristic test model 100, a water area guide rail 200, a test water area adjusting bracket 300, a wind speed simulation system 400, a wave generation system 500, a model connecting part 600, a sensor system 700 and a control system 800;
the rotor wing type aircraft water surface floating characteristic test model 100 is arranged in a test water area pool;
the water area guide rail 200 is two steel rails parallel to the pool walls at the two sides of the water area pool of the test water area and is fixedly connected with the pool walls at the two sides of the water area pool of the test water area; the test waters adjustment carriage 300 is located above the test waters pool and is free to slide along the waters rail 200; the method can be used for model position adjustment and course control in the test process;
the wind speed simulation system 400 is positioned above the water surface of the water pool of the test water area, and two ends of the wind speed simulation system are fixedly connected with the pool walls at two sides of the water pool of the test water area respectively, so that the wind load meeting the test requirements can be simulated and output;
the wave generation system 500 is installed at one end of the water pool of the test water area, which is close to the wind speed simulation system 400, and two side pool walls, and can be used for outputting and adjusting target parameter waves;
the rotor wing type aircraft water surface floating characteristic test model 100 is connected with the test water area adjusting bracket 300 through the model connecting part 600; during the test, the tester can control and adjust the model heading and position through the model connecting part 600;
the sensor system 700 is installed on the rotor plane water surface floating characteristic test model 100, and is used for monitoring and collecting motion gesture information of the model in a floating process in real time and communicating with the control system 800;
the control system 800 is disposed on the test waters adjustment stand 300 and is communicatively coupled to the sensor system 700.
As shown in fig. 4, in one possible embodiment, the test waters adjustment stand 300 includes a test operation platform 301, a bottom reinforcement structure 302, and a pulley arrangement 303; the test operation platform 301 is located on the upper plane of the test water area adjusting bracket 300 and can be used as a movable area of a tester; the bottom reinforcing structure 302 is a truss structure, and is fixedly connected below the test operation platform 301, and is used for reinforcing the overall structural strength of the test operation platform; the pulley devices 303 are arranged at two symmetrical positions below the test operation platform 301 and are fixedly connected with the lower part of the test operation platform 301; the pulley device 303 is connected with the water area guide rail 200 in a sliding fit manner, and can be used for adjusting the relative position between the test water area adjusting bracket and the water area guide rail.
In one possible embodiment, as shown in FIG. 3, the wind speed simulation system 400 includes a wind turbine group 401, a wind turbine mounting beam 402; the fan installation beam 402 is used for installing the fan set 401, and two ends of the fan installation beam 402 are fixedly connected with two lateral tank walls of a water tank of the test water area respectively; the fan set 401 is installed below the fan installation beam 402, and the fan set 401 can simulate and output the wind load size meeting the test requirement.
In one possible embodiment, as shown in fig. 2, the wave generating system 500 includes a wave generator electric control part, an electric cylinder 502, a wave generating plate 503, and a wave absorbing plate 504; the wave generator control part can be used for inputting wave parameters and controlling the motion frequency and the motion thread of the electric cylinder 502; the electric cylinder 502 is fixedly connected with the pool wall of the water pool of the test water area; the electric cylinder 502 is fixedly connected with the wave-making plate 503; the electric cylinder 502 can drive the wave-making plate 503 to perform mechanical motion, so as to realize the analog output of the target wave parameters; the wave-absorbing plate 504 is hinged with the lateral pool walls at two sides of the water pool of the test water area, and the wave-absorbing plate 504 can absorb waves of water surface waves of the test water area, so that the test water area can be quickly restored to calm.
In one possible embodiment, as shown in fig. 4, the model connection part 600 includes a suspension loop 601, a kevlar mooring line 602; the hanging ring 601 is fixedly connected with the head end and the tail end of the rotor wing type aircraft water surface floating characteristic test model 100 and is used for solidifying the Kevlar mooring ropes 602; the kevlar mooring rope 602 is used for controlling the water surface floating posture/wave encountering direction of the test model, one end of the kevlar mooring rope is fixedly connected with the hanging ring 601, and the other end of the kevlar mooring rope is connected with the test water area adjusting bracket 300 and is manually controlled by a test person on the test operation platform 301.
In one possible embodiment, as shown in fig. 4, the sensor system 700 includes an inertial measurement unit 701, a wireless collector 702, a battery 703, a signal receiving antenna 704, and a power control switch 705; the inertial measurement unit 701 is fixed at the gravity center of the rotor aircraft water surface floating characteristic test model 100 and is used for monitoring the motion gesture of the model in the floating process in real time; the wireless collector 702 and the battery 703 are fixed inside the rotor wing type aircraft water surface floating characteristic test model 100, and the wireless collector 702 is used for collecting and recording test parameters of the inertial measurement unit 701; the battery 703 is electrically connected with the inertial measurement unit 701, the wireless collector 702 and the signal receiving antenna 704 respectively, and is used for supplying power to the sensor inside the model; the signal receiving antenna 704 is fixed at the top position outside the rotor aircraft water surface floating characteristic test model 100 and is used for receiving a control signal sent by a control system; the power supply control switch 705 is fixed at the top position outside the rotor type aircraft water surface floating characteristic test model 100, and is electrically connected to the battery 703 as a control switch of the battery 703.
In one possible embodiment, the control system 800 includes a remote control 801, a data analysis system; the remote control device 801 is disposed on the test operation platform 301, and is configured to send a control signal to the signal receiving antenna 704 in the sensor system 700, so as to implement remote operation on the working state of the wireless collector 702; the data analysis system is used to analytically demonstrate the effectiveness of the test data collected by the sensor system 700.
Further, the control system 800 further includes a camera system 802, where the camera system 802 may be one or a combination of a fixed camera and a handheld camera, and is used to capture a test status image of the rotor plane water surface floating characteristic test model 100 during the test, which is manually controlled by a worker on the operation platform 301.
According to a second aspect of the present invention, a method for testing a water surface floating characteristic model of a rotor wing type aircraft is provided, and the method for testing a water surface floating characteristic model of a rotor wing type aircraft includes the following steps:
step 1: pre-debugging the operation parameters of the wind speed simulation system 400 and the wave generation system 500 to ensure that the wind speed and wave parameters of the simulation output meet the test precision requirements;
step 2: after the preparation of the work is completed, the wave-absorbing plate 504 in the wave-making system 500 is pulled up, so that the wave-absorbing plate 504 is far away from the water surface and keeps a vertical state with the water surface of the pool of the test water area;
step 3: after a power supply control switch 705 in the sensor system 700 is turned on, the rotor type aircraft water surface floating characteristic test model 100 is placed in a test water area between the test water area adjusting bracket 300 and the wind speed simulation system 400 through the movable end of the kevlar mooring rope 602 in the model connecting part 600, and is adjusted to a test target course;
step 4: the wave generation system 500, the wind speed simulation system 400 and the control system 800 are sequentially started to work normally;
step 5: when wave and wind speed interference reach the test water area where the rotor wing type aircraft water surface floating characteristic test model 100 is located, the model encountering wave direction is controlled by adjusting and controlling the relative angle and absolute length between the movable end of the Kevlar mooring rope 602 and the model; in the test process, the wireless collector 702 records parameters of roll angle, pitch angle, roll angular velocity and pitch angular velocity of the rotor type aircraft water surface floating characteristic test model 100 in the water surface floating process in real time, and the camera system 802 records the whole motion process of the rotor type aircraft water surface floating characteristic test model 100;
step 6: when the floating time of the rotor plane water surface floating characteristic test model 100 on the water surface reaches a target value, closing a remote control device 801 and a shooting system 802 in the wave making system 500, the wind speed simulation system 400 and the control system 800 to stop swinging and drifting of the rotor plane water surface floating characteristic test model 100, and fishing the rotor plane water surface floating characteristic test model 100 through a Kevlar mooring rope 601 to recheck and adjust the test state;
step 7: by adopting the data analysis system 803 in the control system 800, the roll angle, pitch angle, roll angle speed and pitch angle speed parameters acquired by the sensor system 700 are utilized to draw a time history change curve of the roll angle along with time, the validity of the test state is evaluated by analyzing the correlation between the change rule of the curve and the motion state of the model, invalid data are removed, and the recorded valid data comprise the change curve conditions of the model weight, the gravity center position, the wind speed, the model heading, the wave parameters, the roll angle, the pitch angle, the roll angle speed and the pitch angle speed along with time.
In one possible embodiment, in the step 5, the relative position of the test waters adjusting carriage 300 on the waters guide rail 200 is adjusted to avoid the adverse collision interference generated between the rotor plane water surface floating characteristic test model 100 and the test waters adjusting carriage 300 during the movement.
Claims (10)
1. The device for testing the water surface floating characteristic model of the rotor wing type aircraft is characterized by comprising a water surface floating characteristic test model (100) of the rotor wing type aircraft, a water area guide rail (200), a test water area adjusting bracket (300), a wind speed simulation system (400), a wave generation system (500), a model connecting component (600), a sensor system (700) and a control system (800);
the rotor wing type aircraft water surface floating characteristic test model (100) is arranged in a test water area pool;
the water area guide rail (200) is two steel rails parallel to the pool walls at the two sides of the water area pool in the test water area and is fixedly connected with the pool walls at the two sides of the water area pool in the test water area; the test water area adjusting bracket (300) is positioned above the test water area pool and can freely slide along the water area guide rail (200); the method can be used for model position adjustment and course control in the test process;
the wind speed simulation system (400) is positioned above the water surface of the water pool of the test water area, and two ends of the wind speed simulation system are fixedly connected with the pool walls at two sides of the water pool of the test water area respectively, so that the wind load meeting the test requirements can be simulated and output;
the wave generating system (500) is arranged at one end of the water pool of the test water area, which is close to the wind speed simulation system (400), and two side pool walls, and can be used for outputting and adjusting target parameter waves;
the rotor wing type aircraft water surface floating characteristic test model (100) is connected with the test water area adjusting bracket (300) through the model connecting component (600); during the test, the tester can control and adjust the model course and position through the model connecting component (600);
the sensor system (700) is arranged on the rotor wing type aircraft water surface floating characteristic test model (100) and is used for monitoring and collecting motion attitude information of the model in a floating process in real time and communicating with the control system (800);
the control system (800) is arranged on the experimental water area adjusting bracket (300) and is in communication connection with the sensor system (700).
2. The device for testing the water surface floating characteristic model of the rotary wing aircraft according to claim 1, wherein the test water area adjusting bracket (300) comprises a test operation platform (301), a bottom reinforcing structure (302) and a pulley device (303); the test operation platform (301) is positioned on the upper plane of the test water area adjusting bracket (300); the bottom reinforcing structure (302) is a truss structure and is fixedly connected below the test operation platform (301); the pulley devices (303) are arranged at symmetrical positions on two sides below the test operation platform (301) and are fixedly connected with the lower part of the test operation platform (301); the pulley device (303) is connected with the water area guide rail (200) in a sliding fit manner.
3. The device for testing the water surface floating characteristic model of the rotor type aircraft according to claim 1, wherein the wind speed simulation system (400) comprises a fan set (401) and a fan mounting beam (402); the fan installation beam (402) is used for installing the fan set (401), and two ends of the fan installation beam (402) are fixedly connected with two lateral tank walls of a water tank of a test water area respectively; the fan set (401) is mounted below the fan mounting beam (402).
4. The device for testing the water surface floating characteristic model of the rotor type aircraft according to claim 1, wherein the wave generating system (500) comprises an electric control part of the wave generator, an electric cylinder (502), a wave generating plate (503) and a wave absorbing plate (504); the wave generator control part can be used for inputting wave parameters and controlling the motion frequency and the motion thread of the electric cylinder (502); the electric cylinder (502) is fixedly connected with the pool wall of the water pool of the test water area; the electric cylinder (502) is fixedly connected with the wave-making plate (503); the electric cylinder (502) can drive the wave-making plate (503) to mechanically move so as to realize the analog output of the target wave parameters; the wave absorbing plate (504) is hinged with lateral tank walls at two sides of a water tank of the test water area.
5. The model test device for the water surface floating characteristics of the rotor type aircraft according to claim 1, wherein the model connecting component (600) comprises a hanging ring (601) and a kevlar mooring rope (602); the hanging ring (601) is fixedly connected with the head end and the tail end of the rotor wing type aircraft water surface floating characteristic test model (100); one end of the Kevlar mooring rope (602) is fixedly connected with the hanging ring (601), and the other end of the Kevlar mooring rope is connected with the experimental water area adjusting bracket (300).
6. The rotor type aircraft water surface floating characteristic model test device according to claim 1, wherein the sensor system (700) comprises an inertial measurement unit (701), a wireless collector (702), a battery (703), a signal receiving antenna (704), and a power supply control switch (705); the inertial measurement unit (701) is fixed at the gravity center of the rotor type aircraft water surface floating characteristic test model (100); the wireless collector (702) and the battery (703) are fixed in the rotor wing type aircraft water surface floating characteristic test model (100); the battery (703) is electrically connected with the inertial measurement unit (701), the wireless collector (702) and the signal receiving antenna (704) respectively and is used for supplying power to the sensor inside the model; the signal receiving antenna (704) is fixed at the external top position of the rotor wing type aircraft water surface floating characteristic test model (100); the power supply control switch (705) is fixed at the external top position of the rotor type plane water surface floating characteristic test model (100), and is used as a control switch of the battery (703) and is electrically connected with the battery (703).
7. The model test device for the water surface floating characteristics of the rotary wing aircraft according to claim 1, wherein the control system (800) comprises a remote control device (801) and a data analysis system (803); the remote control device (801) is arranged on the test water area adjusting bracket (300) and is used for sending a control signal to the sensor system (700); the data analysis system (803) is used for performing analysis demonstration on the validity of test data acquired by the sensor system (700).
8. The device for testing the water surface floating characteristic model of the rotary wing aircraft according to claim 7, wherein the control system (800) further comprises a photographing system (802), and the photographing system (802) can be one or a combination of a fixed camera and a handheld camera, so as to capture a test state image of the water surface floating characteristic test model (100) of the rotary wing aircraft during the test.
9. A method for testing a water surface floating characteristic model of a rotary wing type aircraft, characterized in that the method for testing the water surface floating characteristic model of the rotary wing type aircraft by adopting the device for testing the water surface floating characteristic model of the rotary wing type aircraft according to any one of claims 1 to 7 comprises the following steps:
step 1: operating parameters of the wind speed simulation system (400) and the wave generation system (500) are pre-debugged, so that the wind speed and wave parameters of simulation output are ensured to meet the test precision requirement;
step 2: pulling up a wave-absorbing plate (504) in the wave-making system (500), so that the wave-absorbing plate (504) is far away from the water surface and keeps a vertical state with the water surface of a pool of the test water area;
step 3: after a power supply control switch (705) in the sensor system (700) is turned on, the rotor type aircraft water surface floating characteristic test model (100) is placed in a test water area between the test water area adjusting bracket (300) and the wind speed simulation system (400) through a movable end of a Kevlar mooring rope (602) in a model connecting part (600), and is adjusted to a test target course;
step 4: the wave generating system (500), the wind speed simulation system (400) and the control system (800) are sequentially started to work normally;
step 5: when wave and wind speed interference reach a test water area where the rotor wing type aircraft water surface floating characteristic test model (100) is located, the model encounters wave direction by adjusting and controlling the relative angle and absolute length between the movable end of the Kevlar mooring rope (602) and the model; in the test process, a wireless collector (702) records parameters of roll angle, pitch angle, roll angular speed and pitch angular speed of the rotor wing type aircraft water surface floating characteristic test model (100) in the water surface floating process in real time, and a shooting system (802) records the whole process of the movement of the rotor wing type aircraft water surface floating characteristic test model (100);
step 6: when the floating time of the rotor wing type aircraft water surface floating characteristic test model (100) on the water surface reaches a target value, closing a remote control device (801) and a shooting system (802) in the wave making system (500), the wind speed simulation system (400) and the control system (800) to stop swinging and drifting of the rotor wing type aircraft water surface floating characteristic test model (100), and fishing the rotor wing type aircraft water surface floating characteristic test model (100) through a Kevlar mooring rope (602) to recheck and adjust a test state;
step 7: the data analysis system (803) in the control system (800) is adopted, the roll angle, the pitch angle, the roll angular velocity and the pitch angular velocity parameters acquired by the sensor system (700) are utilized to draw a time calendar change curve of the roll angle along with time, the validity of the test state is evaluated by analyzing the correlation between the change rule of the curve and the motion state of the model, invalid data are removed, and the recorded valid data comprise the change curve conditions of the model weight, the gravity center position, the wind speed, the model course, the wave parameters, the roll angle, the pitch angle, the roll angular velocity and the pitch angular velocity along with time.
10. The method according to claim 9, wherein in the step 5, the adverse collision interference generated between the rotor type aircraft water surface floating characteristic test model (100) and the test water area adjusting bracket (300) during the movement is avoided by adjusting the relative position of the test water area adjusting bracket (300) on the water area guide rail (200).
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA2537352A1 (en) * | 2006-02-20 | 2006-05-17 | Merv Byron | Modular experimental gyroplane float system |
| CN106323592A (en) * | 2016-11-07 | 2017-01-11 | 中国特种飞行器研究所 | Pool testing method for storm rolling model of helicopter |
| CN109596308A (en) * | 2018-12-04 | 2019-04-09 | 中国特种飞行器研究所 | Ground effect vehicle fly close to water surface Stability Model basin test device and method |
| CN111017257A (en) * | 2019-12-19 | 2020-04-17 | 中国特种飞行器研究所 | Equivalent simulation method and test system for seepage characteristics |
| CN112793806A (en) * | 2020-12-30 | 2021-05-14 | 中国特种飞行器研究所 | Fixed-wing aircraft draft line model test device and method |
-
2021
- 2021-07-30 CN CN202110872120.0A patent/CN113650805B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA2537352A1 (en) * | 2006-02-20 | 2006-05-17 | Merv Byron | Modular experimental gyroplane float system |
| CN106323592A (en) * | 2016-11-07 | 2017-01-11 | 中国特种飞行器研究所 | Pool testing method for storm rolling model of helicopter |
| CN109596308A (en) * | 2018-12-04 | 2019-04-09 | 中国特种飞行器研究所 | Ground effect vehicle fly close to water surface Stability Model basin test device and method |
| CN111017257A (en) * | 2019-12-19 | 2020-04-17 | 中国特种飞行器研究所 | Equivalent simulation method and test system for seepage characteristics |
| CN112793806A (en) * | 2020-12-30 | 2021-05-14 | 中国特种飞行器研究所 | Fixed-wing aircraft draft line model test device and method |
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