飛機在穿越云層飛行時,云層中的過冷水滴撞擊到飛機表面,會發(fā)生結(jié)冰現(xiàn)象,飛機結(jié)冰對飛行安全造成很大的危害,因此飛機結(jié)冰的研究歷來受到世界各國的重視.飛機結(jié)冰是一個復(fù)雜的傳熱傳質(zhì)現(xiàn)象,涉及到流體力學(xué)、傳熱學(xué)以及空氣動力學(xué)等多個領(lǐng)域,由于國內(nèi)不具備冰風(fēng)洞試驗條件,飛機防/除冰系統(tǒng)設(shè)計中往往依賴于工程估算,本文采用數(shù)值模擬對飛機結(jié)冰現(xiàn)象進行了研究,這可以一定程度上彌補試驗條件欠缺的不足,這方面的工作國內(nèi)尚處于起步階段.

When an aircraft flies through the clouds, the impact of the super cooled water droplets in the clouds on the surface of the aircraft will create an ice-up phenomenon; icing on aircraft is a grave danger to aviation safety, so the research of aircraft icing has always been the world’s focus of attention. Icing on aircraft is a complex heat and mass transfer phenomenon, it involves many fields such as fluid mechanics, heat transfer, air dynamics etc. As there is a lack of icing tunnel experiment conditions in China, the prevention and deicing system designs often have to rely on engineering estimations. This paper adopts the method of numerical simulations to study the phenomenon of icing on aircraft; this can make up for the lack of testing conditions to a certain extent, and this kind of work in China  is still in the infant stage.      

本文的研究工作主要有以下幾個方面：
1）簡述了飛機結(jié)冰現(xiàn)象及其主要研究方法,著重介紹了飛機結(jié)冰數(shù)值模擬研究的發(fā)展?fàn)顩r；
2）在對發(fā)生飛機結(jié)冰現(xiàn)象的飛行和氣象條件分析的基礎(chǔ)上,確定了采用求解N-S 方程來計算結(jié)冰時的空氣流場,選用了適用于飛機結(jié)冰研究的湍流模型.
3）對建立水滴運動方程的歐拉型方法進行了研究,在合理的假設(shè)和簡化的基礎(chǔ)上,建立了適用于飛機結(jié)冰研究的空氣/過冷水滴兩相流控制方程.根據(jù)飛機結(jié)冰氣象條件的特點,研究了方程的求解方法.
4）對熱載荷模型進行了研究,分析討論了各個熱流的求法.
5）利用本文提出的方法,進行了機翼結(jié)冰的數(shù)值模擬,通過FLUENT加載用戶自定義函數(shù)（UDF）,計算得到防冰表面的各項熱流密度,并對其進行分析.
6）對本文的工作進行了總結(jié)

The research of this paper mainly consists of the following aspects:

1.     It  briefly describes the aircraft icing phenomenon and its major research methodology; it emphatically presents the development situation of the numerical simulation of icing on aircraft;

2.      Based on the analysis of flight and meteorological conditions when aircraft icing occurs, the use of solution of N-S equations is confirmed for calculating the airflow field when icing is formed, and the turbulence model suitable for the aircraft icing research is selected;

3.      Study is conducted on the Eulerian Method for setting up the droplet trajectory equation; the air and super cooled waterdroplet two-phase flow control equation is established on the basis of reasonable hypothesis and simplification, and based on the characteristics of weather conditions when aircraft icing occurs, the method of solving the equation is studied;

4.      Research is conducted on the thermal load model, and the solutions of the various heat flux are analyzed and discussed;  

5.      By applying the method proposed by this paper, numerical simulation of icing on the aircraft wings is conducted, and through the FLUENT loaded User Defined Function (UDF), the various heat flux densities on the surface of icing prevention are obtained, and analysis is conducted on them.

6. Finally, the work of this paper is summarized.