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A wind tunnel test method for helicopter rotor model icing

A technology for helicopter rotor and wind tunnel testing, applied in the field of wind tunnel testing, can solve the problem that the experimental research has not been carried out effectively.

Active Publication Date: 2020-08-21
LOW SPEED AERODYNAMIC INST OF CHINESE AERODYNAMIC RES & DEV CENT
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  • Description
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  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The experimental research on helicopter rotor icing is still in its infancy in our country, and the experimental research in this area has not yet been effectively carried out.

Method used

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  • A wind tunnel test method for helicopter rotor model icing
  • A wind tunnel test method for helicopter rotor model icing

Examples

Experimental program
Comparison scheme
Effect test

Embodiment

[0035] A kind of helicopter rotor model icing wind tunnel test method, such as figure 1 with figure 2 shown, including the following steps:

[0036] Step 1, each system of the rotor model test bench completes pre-test debugging, and after each system works normally, perform step 2;

[0037] Step 2, when the inclination angle of the rotor shaft is zero, collect the zero reading as the initial reading, if the initial reading is correct, go to step 3;

[0038] Step 3: Start the rotor for safe operation, then turn on the cooling system of the wind tunnel, start the wind tunnel, and adjust the wind speed to cool down. During the cooling process, the rotor is controlled in real time to keep the lift, pitch moment and roll moment of the rotor within a safe range. , after the ambient temperature of the wind tunnel drops to the test value and stabilizes, go to step 4;

[0039] Step 4: The rotor speed is increased to the test speed, and then the wind speed is adjusted to the test w...

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Abstract

The invention discloses a helicopter rotor model icing wind tunnel test method, which belongs to the technical field of wind tunnel tests; the invention mainly uses the icing wind tunnel system to realize the icing effect, and combines the helicopter rotor test platform to measure the aerodynamic performance of the helicopter rotor ; Based on a large-scale icing wind tunnel and a helicopter rotor wind tunnel test platform, the present invention first proposes a helicopter rotor model icing characteristic test method, standardizes the helicopter rotor wind tunnel test process, and can achieve high quality, high efficiency, safety and reliability It can conveniently and accurately evaluate the influence of icing on the aerodynamic performance of the helicopter rotor model, and can provide powerful wind tunnel test data for the research on helicopter rotor icing in my country.

Description

technical field [0001] The invention relates to a helicopter rotor model icing wind tunnel test method, which belongs to the technical field of wind tunnel tests. Background technique [0002] Helicopter is a special aircraft that relies on rotor rotation to provide lift, forward force and control force to effectively hover in the air, take off and land vertically, and fly forward, backward, and sideways. When a helicopter flies to a certain height in the air and passes through icy clouds, the moving or non-moving parts exposed outside the body may be icy, and the rotor blades are more sensitive to icing, and the icing on the rotor blades is asymmetrical. The resulting vibration, as well as the great increase of the main rotor torque in a very short icing time, seriously affect the safe flight of the helicopter. Therefore, in order to achieve the ability of helicopters to fly in all weathers, one of the main factors affecting flight safety must be solved, that is, the impac...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64F5/60G01M9/02
CPCB64F5/60G01M9/02
Inventor 袁红刚黄明其彭先敏章贵川梁鉴柳庆林罗欢田斌魏一博
Owner LOW SPEED AERODYNAMIC INST OF CHINESE AERODYNAMIC RES & DEV CENT
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