CN109515749B - Helicopter model water forced landing test device and test method - Google Patents
Helicopter model water forced landing test device and test method Download PDFInfo
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- CN109515749B CN109515749B CN201811533705.4A CN201811533705A CN109515749B CN 109515749 B CN109515749 B CN 109515749B CN 201811533705 A CN201811533705 A CN 201811533705A CN 109515749 B CN109515749 B CN 109515749B
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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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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M99/00—Subject matter not provided for in other groups of this subclass
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Abstract
The invention discloses a helicopter model water forced landing test device and a test method, aiming at the defects of the domestic existing test method and test device, the test method designs and develops a special rotor lift force simulation device to simulate the rotor lift force, ensures that the magnitude of the simulated rotor lift force is constant and always keeps the whole process of model water landing and water sliding. A wireless power control system is built, and the simplicity and convenience in operation are guaranteed. A test system is designed, and a light and small-size sensor and a test acquisition system are adopted. The test steps are optimized and improved according to the water forced landing test steps of the rotor type airplane.
Description
Technical Field
The invention relates to the field of helicopter model water forced landing tests, in particular to a helicopter model water forced landing test method with a rotor lift force simulation device.
Background
The research and the start of the overwater forced landing technology of the helicopter are earlier, model tests and real-machine tests are developed on partial models of helicopters, and a related helicopter overwater forced landing model lift force simulation device is designed and developed to form a related helicopter model overwater forced landing test method with a rotor wing lift force device. The technology of the fifth and sixty years of the last century is the most, and the following defects appear to exist at present:
the rotor lift force simulation is generated by a motor outside the model, and after the model is separated from the testing device, the lift force is maintained by the rotation inertia of the rotor and is continuously reduced all the time, so that the rotor lift force required in the regulation is not satisfied. But also the real motion situation of the model.
Secondly, the model is small in size, a test sensor and a data acquisition system cannot be carried on the model, test results can be obtained only by external observation, the precision of test data is low, and errors are large.
The research on the overwater forced landing technology of the helicopter in China is late, and a related lift force simulation device is not developed yet to form a related test method.
Disclosure of Invention
Object of the Invention
Aiming at the defects of the existing domestic test method and test device, the invention provides a helicopter model water forced landing test method with a rotor lift force simulation device, designs and develops a special rotor lift force simulation device to simulate the rotor lift force, ensures that the magnitude of the simulated rotor lift force is constant, and always keeps the whole process of model water landing and water sliding. A wireless power control system is built, and the simplicity and convenience in operation are guaranteed. A test system is designed, and a light and small-size sensor and a test acquisition system are adopted. The test steps are optimized and improved according to the water forced landing test steps of the rotor type airplane.
Technical solution of the invention
In order to achieve the purpose, the invention adopts the following technical scheme:
the helicopter model water forced landing test device comprises a test device, an airborne power and control system, an airborne test system and a rotor lift force calibration device; the test device comprises a rotor wing lift force simulation device connected to the helicopter model through an upper mounting plate; the upper end of a bearing shaft arranged at the gravity center position of the helicopter model is connected with a model mounting plate, and the lower end of the bearing shaft is connected with a lower mounting plate; the model mounting plate is connected with a model posture adjusting device through an electromagnetic release, and the model posture adjusting device is fixed on a side bridge at the bottom of the high-speed trailer through a round pipe fitting; the airborne power and control system comprises a power motor and a rotor wing which are arranged on the rotor wing lift force simulation device; the power battery, the electronic speed regulator and the receiver are arranged in the helicopter model; the transmitter is arranged on the high-speed trailer; the airborne test system comprises a pressure sensor fixed at the bottom of the helicopter model; the acceleration sensor, the inertia measurement unit and the miniature data acquisition module are fixed on the helicopter model; the rotor lift force calibration device comprises a test bed, a force measuring balance and a data acquisition computer.
Preferably, the rotorcraft lift simulation device includes: the device comprises a lower gear, an upper gear, a rotor outer shaft sleeve, a rotor outer shaft, a lower rotor mounting bracket, a rotor inner shaft sleeve, a rotor inner shaft and an upper rotor mounting bracket; the whole rotor wing lift force simulation device is sleeved on the bearing shaft; lower gear and last rotor installing support install respectively in the rotor in the bottom and the top of axle, axle sleeve and the outer hub connection of rotor in the rotor, go up gear and lower rotor installing support and install respectively in the outer axle of rotor in the bottom and upper end, the outer axle of rotor is connected with last mounting panel through outer axle sleeve of rotor.
Preferably, the model pose adjustment apparatus includes: the device comprises a longitudinal limiting plate, a transverse limiting plate, a lower mounting plate, a roll angle locking pin, a roll angle adjusting plate, a pitch angle locking pin, an upper mounting plate and a pitch angle adjusting plate; the longitudinal limiting plate and the transverse limiting plate are fixed on the lower mounting plate, the lower mounting plate is connected with the roll angle adjusting plate through a roll angle locking pin, the roll angle adjusting plate is connected with the pitching angle adjusting plate through a pitching angle locking pin, and the pitching angle adjusting plate is fixed on the upper mounting plate; the model posture adjusting device is connected with the round pipe fitting through the upper mounting plate.
The method for testing by using the helicopter model water forced landing test device comprises the following steps: 1) calibrating the lift force of the rotor wing; 2) debugging and installing an onboard power and control system and an onboard test system to enable the weight, the gravity center and the inertia of the helicopter model to meet the test requirements; 3) mounting a helicopter model which meets the test requirement in debugging on a test device; 4) powering up the airborne power and control system, and entering a waiting operation state; 5) powering on the airborne test system, and entering a trigger acquisition state; 6) starting an onboard test system to start acquisition, controlling an onboard power system to start by a transmitter, operating at the speed of 200 rpm at idle speed, and starting the operation of a high-speed trailer; 7) after the speed of the high-speed trailer is stable, the transmitter controls a power motor to drive a rotor wing to run to the rotating speed required by the test, and an electromagnetic release acts to put down a helicopter model; 8) after the helicopter model stops watering and water sliding, the transmitter controls the onboard power system to stop; 9) salvaging and recovering the helicopter model to a dock, and recovering test data; 10) and (5) checking the state of the helicopter model, and repeating the steps 3) -9) until the model test condition is finished.
Preferably, the process of step 1) rotor lift calibration is as follows: the test bench is arranged on a force balance, a rotor wing lift force simulation device is arranged on the test bench, a power motor and a rotor wing are arranged on the rotor wing lift force simulation device, a power battery, an electronic speed regulator and a receiver are arranged in the test bench, and a transmitter is controlled by a tester; a tester controls the transmitter to start the power motor to drive the rotor to rotate to 200 rpm, then accelerates to 3000 rpm step by step with 200 rpm step by step, the rotor lift force on the force measuring balance is recorded by the data acquisition computer every 5 seconds of the one-step accelerated speed, and the rotor speed, the rotor lift force and the corresponding position of the transmitter are recorded.
Preferably, the transmitter transmits a wireless signal to the receiver in the step 6), the electronic speed regulator receives the signal of the receiver and then controls the power motor to rotate to an idling speed of 200 rpm, and the rotor wing rotates along with the power motor.
Preferably, in the step 7), the transmission signal of the transmitter is slowly changed, the power motor is controlled to drive the rotor wing to increase the rotating speed to the rotating speed required by the test at the speed of 100 revolutions per second, after the rotating speed is stable, the electromagnetic release acts to throw off the helicopter model, and the rotor wing catches water along with the helicopter model at a constant rotating speed.
THE ADVANTAGES OF THE PRESENT INVENTION
The invention has the advantages that:
(1) in the test process, the rotor lift force can be constantly kept to the whole process of model water landing and sliding, and the test repeatability and reliability are high.
(2) The airborne test system is convenient and reliable, the test data is reliable, and the error is small.
Drawings
Fig. 1 is a schematic structural diagram of a helicopter model water forced landing test device.
Fig. 2 is a schematic structural diagram of the rotor lift simulation device of the present invention.
FIG. 3 is a schematic structural diagram of a model attitude adjustment apparatus according to the present invention.
Fig. 4 is a schematic structural view of the rotor lift calibration device of the present invention.
In the figure: 1-helicopter model, 2-rotor lift force simulator, 2-1-lower gear, 2-2-upper gear, 2-4-rotor outer shaft, 2-5-lower rotor mounting bracket, 2-6-rotor inner shaft sleeve, 2-7-rotor inner shaft, 2-8-upper rotor mounting bracket, 3-upper mounting plate, 4-lower mounting plate, 5-bearing shaft, 6-model mounting plate, 7-electromagnetic trip, 8-model posture regulator, 8-1-longitudinal spacing plate, 8-2-transverse spacing plate, 8-3-lower mounting plate I, 8-4-roll angle locking pin, 8-5-roll angle regulating plate, 8-6-pitch angle locking pin, 8-7-upper mounting plate I, 8-8-pitching angle adjusting plate, 9-round pipe fitting, 10-high-speed trailer, 11-side bridge, 12-power motor, 13-electronic speed regulator, 14-transmitter, 15-receiver, 16-power battery, 17-rotor, 18-pressure sensor, 19-acceleration sensor, 20-inertia measuring unit, 21-micro data acquisition module, 22-test bench, 23-force balance and 25-data acquisition computer.
Detailed Description
The detailed description of the embodiments of the present invention is provided in conjunction with the summary of the invention and the accompanying drawings.
The helicopter model water forced landing test device comprises a test device, an airborne power and control system, an airborne test system and a rotor lift force calibration device;
the test device comprises a rotor lift force simulation device 2 connected to a helicopter airplane model 1 through an upper mounting plate 3; the upper end of a bearing shaft 5 arranged at the gravity center position of a helicopter airplane model 1 is connected with a model mounting plate 6, and the lower end is connected with a lower mounting plate 4; the model mounting plate 6 is connected with a model posture adjusting device 8 through an electromagnetic release 7, and the model posture adjusting device 8 is fixed on a side bridge 11 at the bottom of a high-speed trailer 10 through a vertically arranged round pipe fitting 9;
the airborne power and control system comprises a power motor 12 and a rotor 17, wherein the power motor 12 and the rotor 17 are arranged on the rotor and are arranged on the rotor lift force simulation device 2; the power battery 16, the electronic speed regulator 13 and the receiver 15 are arranged in the helicopter model 1; the transmitter 14 is mounted on the high-speed trailer 10 for manipulation by a human tester.
The airborne test system comprises a pressure sensor 17 fixed at the bottom of the helicopter model 1; a pressure sensor 18, an acceleration sensor 19, an inertia measurement unit 20 and a micro data acquisition module 21 which are fixed on the helicopter model 1.
The rotor lift calibration device comprises a test bench 22, a force measuring balance 23 and a data acquisition computer 25.
The rotor lift simulation device 2 includes: the rotor wing mounting bracket comprises a lower gear 2-1, an upper gear 2-2, a rotor wing outer shaft sleeve 2-3, a rotor wing outer shaft 2-4, a lower rotor wing mounting bracket 2-5, a rotor wing inner shaft sleeve 2-6, a rotor wing inner shaft 2-7 and an upper rotor wing mounting bracket 2-8. The whole rotor lift force simulation device 2 is sleeved outside the bearing shaft 5 and is installed on the helicopter model 1 through the upper installation plate 3. The lower gear 2-1 and the upper rotor wing mounting bracket 2-8 are respectively mounted at the bottom end and the upper end of the rotor wing inner shaft 2-7, and the rotor wing inner shaft 2-7 is sleeved on the bearing shaft 5; the rotor wing inner shaft 2-7 is connected with the rotor wing outer shaft 2-4 through a rotor wing inner shaft sleeve 2-6, the rotor wing outer shaft 2-4 is sleeved on the rotor wing inner shaft sleeve 2-6 and is detachably connected with the rotor wing inner shaft sleeve 2-6, the upper gear 2-2 and the lower rotor wing mounting bracket 2-5 are respectively mounted at the bottom end and the upper part of the rotor wing outer shaft 2-4, the lower rotor wing mounting bracket 2-5 is positioned below the upper rotor wing mounting bracket 2-8, and the teeth of the upper gear 2-2 and the lower gear 2-1 are oppositely arranged; the upper mounting plate 3 is arranged in the middle of the outer shaft 2-4 of the rotor wing, a bearing groove is formed in the bottom of the upper mounting plate 3, two deep groove ball bearings are arranged in the bearing groove, the bottom of the lowermost bearing is limited through a pin shaft, and a bearing cover detachably connected to the bottom of the bearing groove of the upper mounting plate 3 is further arranged on the lower portion of the lowermost bearing. The bottom of the bearing shaft 5 is detachably connected with the lower mounting plate 4. The components of the rotor lift simulator 2 below the upper mounting plate 3 extend into the helicopter model airplane 1. The rotor 17 is respectively mounted on the lower rotor mounting bracket 2-5 and the upper rotor mounting bracket 2-8. The transmission gear is fastened on a shaft of the power motor 12, the fastened transmission gear is inserted between the upper gear 2-2 and the lower gear 2-1, the connecting plate is fastened on the lower surface of the upper mounting plate 3, the position of the connecting plate is adjusted, and the power motor 12 is fixed on the connecting plate.
The model posture adjustment device 8 includes: the device comprises a longitudinal limiting plate 8-1, a transverse limiting plate 8-2, a lower mounting plate 8-3, a rolling angle locking pin 8-4, a rolling angle adjusting plate 8-5, a pitching angle locking pin 8-6, an upper mounting plate 8-7 and a pitching angle adjusting plate 8-8. The longitudinal limiting plate 8-1 and the transverse limiting plate 8-2 are fixed on the bottom surface of the lower mounting plate 8-3, the lower mounting plate 8-3 is connected with a roll angle adjusting plate 8-5 through a roll angle locking pin 8-4, the roll angle adjusting plate 8-5 is connected with a pitch angle adjusting plate 8-8 through a pitch angle locking pin 8-6, and the pitch angle adjusting plate 8-8 is fixed on the upper mounting plate 8-7. The whole model attitude adjusting device 8 is connected with a circular pipe fitting 9 through an upper mounting plate 8-7.
The test device is installed by firstly installing a round pipe fitting 9 in the middle of a side bridge of a high-speed trailer through a screw, fixing an upper mounting plate 8-7 on a model attitude adjusting device 8 at the bottom of the round pipe fitting 9 through the screw, and fixing an electromagnetic release 7 in the middle of a lower mounting plate 8-3 of the model attitude adjusting device 8 through the screw. And loosening the roll angle locking pin 8-4 and the pitch angle locking pin 8-6, and locking the screws on the longitudinal limiting plate 8-1 and the transverse limiting plate 8-2.
The test model is prepared by fixing the rotor lift force simulator 2 on the helicopter model 1 through the upper mounting plate 3, and fixing the bearing shaft 5 on a bearing frame in the helicopter model 1 through the lower mounting plate 4 by using a screw. Then the power motor 12 is installed at a designated position inside the helicopter model 1 through a screw, the power battery 16, the electronic speed regulator 13 and the receiver 15 are fixed inside the helicopter model 1 through double faced adhesive and a binding tape, and the rotor 17 is separately installed on the lower rotor installation bracket 2-5 and the upper rotor installation bracket 2-8 on the rotor lift simulation device 2 and locked through the screw. The pressure sensor 17 and the pressure sensor 18 are arranged at the position of the bottom surface of the helicopter model 1, which needs to test pressure, through threaded ports, and the acceleration sensor 19, the inertia measurement unit 20 and the miniature data acquisition module 21 are arranged in the middle inside the helicopter model 1.
When the test model is installed, the hook of the electromagnetic release 7 is firstly released, and the hook is closed after hooking the hanging point on the model installation plate 6. And respectively propping the longitudinal limiting plate 8-1 and the transverse limiting plate 8-2 of the model attitude adjusting device 8 against the limiting blocks on the mounting plate 6. And adjusting the roll angle adjusting plate 8-5 to ensure that the roll angle of the model meets the test requirements, then locking the roll angle locking pin 8-4, and adjusting the pitch angle adjusting plate 8-8 to ensure that the pitch angle of the model meets the test requirements, then locking the pitch angle locking pin 8-6.
The method for testing by using the helicopter model water forced landing test device comprises the following steps:
1) calibrating the lift force of the rotor wing;
2) debugging and installing an onboard power and control system and an onboard test system; the weight, the gravity center and the inertia of the helicopter model meet the test requirements;
3) mounting a helicopter model which meets the test requirement in debugging on a test device;
4) powering up the airborne power and control system, and entering a waiting operation state;
5) powering on the airborne test system, and entering a trigger acquisition state;
6) starting the airborne test system to start collection, controlling the airborne power system to start by the transmitter 14, operating at the idling speed of 200 rpm, and starting the high-speed trailer 10 to operate;
7) after the speed of the high-speed trailer 10 is stable, the transmitter 14 controls the power motor 12 to drive the rotor 17 to run to the rotating speed required by the test, and the electromagnetic release 7 acts to put down a helicopter model;
8) after the helicopter model stops watering and water sliding, the transmitter 14 controls the onboard power system to stop;
9) salvaging and recovering the helicopter model to a dock, and recovering test data;
10) and (5) checking the state of the helicopter model, and repeating the steps 3) -9) until the model test condition is finished.
Step 1) the rotor lift force calibration process is as follows: a test bench 22 is installed on a force measuring balance 23, a rotor wing lift force simulation device 2 is installed on the test bench 22, a power motor 12 and a rotor wing 17 are installed on the rotor wing lift force simulation device, a power battery 16, an electronic speed regulator 13 and a receiver 15 are installed inside the test bench 22, and a transmitter 14 is controlled by a tester. A tester controls the transmitter 14 to start the power motor 12 to drive the rotor 17 to rotate to 200 rpm, then accelerates to 3000 rpm step by step at 200 rpm step, the rotor lift force on the force measuring balance 23 is recorded by the data acquisition computer 25 every 5 seconds of the one-step accelerated speed, and the rotating speed of the rotor 17, the magnitude of the rotor lift force and the corresponding position of the transmitter 14 are recorded.
And 6) the transmitter 14 transmits a wireless signal to the receiver 15, the electronic governor 13 receives the signal of the receiver 15 and then controls the power motor 12 to rotate to an idle speed of 200 rpm, and the rotor 17 rotates along with the power motor 12.
And step 7) controlling the power motor 12 to drive the rotor 17 to increase the rotating speed to the rotating speed required by the test at the speed of 100 revolutions per second by slowly changing the transmitting signal of the transmitter 14, and after the rotating speed is stable, the electromagnetic release 7 acts to put down the helicopter model, and the rotor 17 catches water along with the helicopter model at a constant rotating speed.
Claims (6)
1. The helicopter model water forced landing test device is characterized by comprising a test device main body, an airborne power and control system, an airborne test system and a rotor lift force calibration device;
the testing device main body comprises a rotor lift force simulation device (2) connected to a helicopter model (1) through an upper mounting plate (3), a model mounting plate (6) at the upper end of a bearing shaft (5) at the gravity center position of the helicopter model (1) and a lower mounting plate (4) at the lower end of the bearing shaft, and a model attitude adjusting device (8) connected with the model mounting plate (6) through an electromagnetic trip (7); the model attitude adjusting device (8) is fixed on a side bridge (11) at the bottom of the high-speed trailer (10) through a round pipe fitting (9);
the airborne power and control system comprises a power motor (12) and a rotor (17) which are arranged on a rotor lift force simulation device (2), a power battery (16), an electronic speed regulator (13) and a receiver (15) which are arranged in a helicopter model (1), and a transmitter (14) which is arranged on a high-speed trailer (10);
the airborne test system comprises a pressure sensor (18) fixed at the bottom of the helicopter model (1), an acceleration sensor (19) fixed on the helicopter model (1), an inertia measurement unit (20) and a micro data acquisition module (21);
the rotor lift force calibration device comprises a test bench (22), a force measuring balance (23) and a data acquisition computer (25);
the rotor wing lift force simulation device (2) comprises a lower gear (2-1), an upper gear (2-2), a rotor wing outer shaft sleeve (2-3), a rotor wing outer shaft (2-4), a lower rotor wing mounting bracket (2-5), a rotor wing inner shaft sleeve (2-6), a rotor wing inner shaft (2-7) and an upper rotor wing mounting bracket (2-8); the whole rotor wing lift force simulation device (2) is sleeved on the bearing shaft (5); the lower gear (2-1) and the upper rotor mounting bracket (2-8) are respectively mounted at the bottom end and the top end of the rotor inner shaft (2-7), the rotor inner shaft (2-7) is connected with the rotor outer shaft (2-4) through the rotor inner shaft sleeve (2-6), and the upper gear (2-2) and the lower rotor mounting bracket (2-5) are respectively mounted at the bottom end and the upper end of the rotor outer shaft (2-4).
2. A helicopter model water forced landing test apparatus as claimed in claim 1, wherein the model attitude adjustment means (8) comprises: the device comprises a longitudinal limiting plate (8-1), a transverse limiting plate (8-2), a lower mounting plate I (8-3), a rolling angle locking pin (8-4), a rolling angle adjusting plate (8-5), a pitching angle locking pin (8-6), an upper mounting plate I (8-7) and a pitching angle adjusting plate (8-8); the longitudinal limiting plate (8-1) and the transverse limiting plate (8-2) are fixed on the lower mounting plate I (8-3), the lower mounting plate I (8-3) is connected with a rolling angle adjusting plate (8-5) through a rolling angle locking pin (8-4), the rolling angle adjusting plate (8-5) is connected with a pitching angle adjusting plate (8-8) through a pitching angle locking pin (8-6), and the pitching angle adjusting plate (8-8) is fixed on the upper mounting plate I (8-7); the model attitude adjusting device (8) is connected with the round pipe fitting (9) through an upper mounting plate I (8-7).
3. A method of testing using a helicopter model water forced landing test apparatus as claimed in any one of claims 1 to 2, comprising the steps of:
1) calibrating the lift force of the rotor wing;
2) debugging and installing an onboard power and control system and an onboard test system to enable the weight, the gravity center and the inertia of the helicopter model (1) to meet the test requirements;
3) mounting a helicopter model (1) which meets the test requirement in debugging on a test device;
4) powering up the airborne power and control system, and entering a waiting operation state;
5) powering on the airborne test system, and entering a trigger acquisition state;
6) starting an airborne test system to start collection, controlling the start of an airborne power system by a transmitter (14), operating at the idling speed of 200 rpm, and starting the operation of a high-speed trailer (10);
7) after the speed of the high-speed trailer (10) is stable, the transmitter (14) controls the power motor (12) to drive the rotor wing (17) to run to the rotating speed required by the test, and the electromagnetic release (7) acts to throw the helicopter model (1);
8) after the helicopter model (1) stops catching water and sliding water, the transmitter (14) controls the onboard power system to stop;
9) salvaging and recovering the helicopter model (1) to a dock, and recovering test data;
10) and (4) checking the state of the helicopter model (1), and repeating the step 3) -the step 9) until the model test condition is finished.
4. The assay of claim 3, wherein: step 1) the process of rotor lift force calibration is as follows: the method comprises the following steps of (1) installing a test bench (22) on a force measuring balance (23), installing a rotor wing lift force simulation device (2) on the test bench (22), installing a power motor (12) and a rotor wing (17) on the rotor wing lift force simulation device (2), installing a power battery (16), an electronic speed regulator (13) and a receiver (15) in the test bench (22), and controlling a transmitter (14) by a tester; a tester controls the transmitter (14) to start the power motor (12) to drive the rotor (17) to rotate to 200 rpm, then accelerates to 3000 rpm step by step with 200 rpm step by step, the rotor lift force on the force measuring balance (23) is recorded by the data acquisition computer (25) when the first-stage rotation speed is stabilized for 5 seconds, and the rotation speed of the rotor (17), the size of the rotor lift force and the corresponding position of the transmitter (14) are recorded.
5. The assay of claim 3, wherein: in the step 6), the transmitter (14) transmits a wireless signal to the receiver (15), the electronic governor (13) receives the signal of the receiver (15) and then controls the power motor (12) to rotate to an idling speed of 200 rpm, and the rotor (17) rotates along with the power motor (12).
6. The assay of claim 3, wherein: and 7) controlling the power motor (12) to drive the rotor wing (17) to increase the rotating speed to the rotating speed required by the test at the speed of 100 revolutions per second by slowly changing the transmitting signal of the transmitter (14), after the rotating speed is stable, the electromagnetic release (7) acts to put down the helicopter model, and the rotor wing (17) follows the helicopter model to land on water at a constant rotating speed.
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| CN111222268B (en) * | 2019-12-04 | 2022-10-18 | 中国直升机设计研究所 | Helicopter short-wing overwater forced landing strength calculation method provided with emergency floating system |
| CN112504623B (en) * | 2020-11-05 | 2023-01-13 | 中国特种飞行器研究所 | Helicopter overwater forced landing model regular wave fixed-point launching test device and method |
| CN112607052B (en) * | 2020-12-24 | 2022-07-12 | 中国特种飞行器研究所 | Rotor craft buoy water-skiing load model |
| CN114275189B (en) * | 2021-12-29 | 2023-06-20 | 绵阳小巨人动力设备有限公司 | Fixing and recovering device for underwater emission simulation of navigation device |
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| CN102901623A (en) * | 2012-10-24 | 2013-01-30 | 哈尔滨东安发动机（集团）有限公司 | Device for testing coaxial inversion rotor wing of helicopter |
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