Helicopter rotor model icing wind tunnel test method

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

Active Publication Date: 2020-07-10
LOW SPEED AERODYNAMIC INST OF CHINESE AERODYNAMIC RES & DEV CENT
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  • Abstract
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  • Claims
  • Application Information

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Problems solved by technology

[0005] The experimental research on helicopter rotor icing is still in its infancy in our c

Method used

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  • Helicopter rotor model icing wind tunnel test method
  • Helicopter rotor model icing wind tunnel test method

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Experimental program
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Example Embodiment

[0034] Example

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

[0036] Step 1. Each system of the rotor model test bench is debugged before the test. After each system works normally, go to step 2;

[0037] Step 2. When the rotor shaft inclination angle 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 safe operation of the rotor, then turn on the wind tunnel cooling system, and drive in the wind tunnel to cool down by adjusting the wind speed. During the cooling process, the rotor is operated in real time to keep the rotor lift, pitch and roll moments within a safe range. , After the wind tunnel ambient temperature 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 wind speed. During the wind ...

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Abstract

The invention discloses a helicopter rotor model icing wind tunnel test method, and belongs to the technical field of wind tunnel tests. An icing wind tunnel system is mainly used for achieving the icing effect, and the helicopter rotor aerodynamic performance is measured by combining a helicopter rotor test platform; based on a large-scale icing wind tunnel and a helicopter rotor wing wind tunneltest platform, the helicopter rotor wing model icing characteristic test method is provided for the first time, so that the helicopter rotor wing wind tunnel test process is standardized, and a windtunnel test task can be safely and reliably carried out with high quality and high efficiency; and influence of icing on the aerodynamic performance of the helicopter rotor model can be conveniently and accurately evaluated, and powerful wind tunnel test data can be provided for developing helicopter rotor icing problem research in China.

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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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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