A Calculation Method of Ice Shape Area in Icing Wind Tunnel Test

A calculation method, a technique of wind tunnel testing, applied in the field of aviation

Active Publication Date: 2020-08-07
LOW SPEED AERODYNAMIC INST OF CHINESE AERODYNAMIC RES & DEV CENT
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Problems solved by technology

[0005] In order to solve the problem of quantitative evaluation of the ice area in the icing wind tunnel test, the present invention provides a calculation method for the ice area in the icing wind tunnel test. The calculation process of the method does not involve complicated mathematical formulas and time-consuming numerical iteration processes, and can Quickly and efficiently complete the quantitative calculation of ice shape area parameters, which is suitable for large-scale experimental ice shape area quantitative evaluation tasks

Method used

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  • A Calculation Method of Ice Shape Area in Icing Wind Tunnel Test
  • A Calculation Method of Ice Shape Area in Icing Wind Tunnel Test
  • A Calculation Method of Ice Shape Area in Icing Wind Tunnel Test

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[0070] Embodiments of the present invention are described in detail below, examples of which are shown in the drawings, wherein the same or similar reference numerals designate the same or similar elements or elements having the same or similar functions throughout. The embodiments described below by referring to the figures are exemplary and are intended to explain the present invention and should not be construed as limiting the present invention.

[0071] In order to make the object, technical solution and advantages of the present invention clearer, the present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments.

[0072] A method for calculating the ice shape area of ​​an icing wind tunnel test, comprising the following steps, such as figure 1 Shown:

[0073] (1) Digitized ice contours

[0074] Aiming at the grid drawing of the ice contour line drawn in the experiment, digital scanning technology is used to d...

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Abstract

The present invention is applicable to the field of aviation, and provides a method for calculating the ice shape area of ​​an icing wind tunnel test. First, aiming at the ice shape contour obtained in the icing wind tunnel test, the ice shape contour is obtained by digitizing the ice shape geometric contour Then, for the discrete points of ice shape, a calculation method of ice shape area parameters based on ice accumulation thickness distribution and ice shape area unit is developed, and an efficient ice shape area calculation method for icing wind tunnel test is proposed. Solve the quantitative evaluation problem of ice shape area in icing wind tunnel test, and realize the quantitative post-processing of ice shape. The calculation method does not involve complex mathematical formulas and time-consuming numerical iteration process, and can quickly and efficiently complete the quantitative calculation of ice shape area parameters, which is suitable for large-scale experimental ice shape area quantitative evaluation tasks.

Description

technical field [0001] The invention belongs to the field of aviation, and in particular relates to a method for calculating the ice shape area of ​​an icing wind tunnel test. Background technique [0002] When an aircraft is flying in clouds, supercooled water droplets (ie, liquid water droplets whose temperature is below freezing point) in the clouds will continuously hit the windward side of the aircraft, causing the surface to freeze. Aircraft icing widely exists in flight practice and seriously threatens flight safety. The icing wind tunnel is an important ground test equipment for aircraft icing research and aircraft component anti-icing system verification, and it plays an important role in aircraft icing airworthiness certification. In the icing wind tunnel test, the ice accretion morphology is the most important icing test result, and it is the key parameter to realize the test objectives such as critical ice shape selection, anti-icing system performance evaluatio...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01M9/06G01B5/26
CPCG01B5/26G01M9/06
Inventor 郭向东赵献礼王梓旭李明周靓
Owner LOW SPEED AERODYNAMIC INST OF CHINESE AERODYNAMIC RES & DEV CENT
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