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A method for measuring aerodynamic disturbance of helicopter coaxial rigid rotor model

A technology of interference measurement and helicopter, applied in the field of wind tunnel test, can solve problems such as separate measurement of aerodynamic performance

Active Publication Date: 2020-07-07
LOW SPEED AERODYNAMIC INST OF CHINESE AERODYNAMIC RES & DEV CENT
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Problems solved by technology

[0006] The technical problem to be solved by the present invention is to overcome the deficiencies of the prior art and provide an aerodynamic interference measurement method suitable for the helicopter coaxial rigid rotor model, which solves the aerodynamic performance of the upper and lower hub models and the upper and lower rotor models. The problem of separate measurement can be used to study the aerodynamic interference characteristics of dual rotors

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  • A method for measuring aerodynamic disturbance of helicopter coaxial rigid rotor model
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  • A method for measuring aerodynamic disturbance of helicopter coaxial rigid rotor model

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Embodiment Construction

[0045] In order to make the purpose, technical solutions and advantages of the present invention clearer, the technical solutions of the present invention will be clearly and completely described below in conjunction with the embodiments and accompanying drawings. Obviously, the specific embodiments described here are only used to explain the present invention , and are not intended to limit the present invention.

[0046] Those skilled in the art can understand that, unless otherwise defined, all terms (including technical terms and scientific terms) used herein have the same meaning as commonly understood by those of ordinary skill in the art to which this invention belongs. It should also be understood that terms such as those defined in commonly used dictionaries should be understood to have a meaning consistent with the meaning in the context of the prior art, and unless defined as herein, are not to be interpreted in an idealized or overly formal sense explain.

[0047]...

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Abstract

The invention discloses an aerodynamic interference measuring method for a helicopter coaxial rigid rotor model, and belongs to the technical field of wind tunnel test. The measuring method is mainlyrelying on a twin rotors wind tunnel test platform, and can be used for conducting the aerodynamic load and aerodynamic interference test of the coaxial rigid rotor model with large forward ratio. According to the measuring method, the aerodynamic load of the upper hub model, the lower hub model, the upper rotor model, the lower rotor model and the different combinations of the four models are respectively measured by the upper and lower rotor measuring systems, and the problem of separately measuring the aerodynamic performance of the upper and lower hub models and the upper and lower rotor models by acquiring the separate aerodynamics of the four models and the aerodynamic interference laws in different combinations. The method can be used for the study of the aerodynamic interference characteristics of twin rotors.

Description

technical field [0001] The invention belongs to the technical field of wind tunnel tests, in particular to a wind tunnel test method for studying the aerodynamic characteristics of a coaxial rigid rotor model rotor and the aerodynamic interference characteristics. Background technique [0002] When the coaxial rigid rotor is at high speed, the backward blades are unloaded, and the lift force of the forward blades is utilized to the greatest extent, so that the speed limit of the helicopter can be broken and the helicopter's mission field can be broadened. [0003] However, the new rotor aerodynamic problems such as the high forward ratio, large reversing area, strong radial flow, and large hub resistance of the coaxial rigid dual-rotor helicopter give rise to the unsteady aerodynamic characteristics analysis and layout design of the coaxial rigid dual-rotor helicopter. posed serious challenges. The wind tunnel test is an economical and efficient means to understand and mast...

Claims

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Application Information

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IPC IPC(8): G01M9/08G01M9/06
CPCG01M9/06G01M9/08
Inventor 黄明其何龙杨永东王畅徐栋霞唐敏梁鉴
Owner LOW SPEED AERODYNAMIC INST OF CHINESE AERODYNAMIC RES & DEV CENT
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