發(fā)布時間：2018-07-28 06:57

【摘要】：隨著我國科學技術與國民經濟的高速發(fā)展，飛機作為必要的交通工具進入了人們的生活，已經成為人們生活的一部分。飛機給人們帶來方便、快捷和舒適的生活，也帶來了一定的風險，飛行安全時刻敲醒警鐘。其中，飛機結冰造成的飛行風險占據(jù)顯著地位，已經成為危害飛行安全的頭號因素。 飛機在穿過云層飛行的過程中，當遇到結冰氣象條件時，會在機體表面就會形成積冰。這些結冰云層里面存在著未凍結的液態(tài)小水滴，他們分布在云層里面，當飛機高速穿過結冰云層時，這些小水滴與飛機發(fā)生碰撞，打破了他們原來保持的穩(wěn)定，部分液態(tài)小水滴就會瞬間變成細小的冰顆粒，附著在翼型表面上，使得飛機出現(xiàn)結冰現(xiàn)象。飛機結冰是伴隨著蒸發(fā)、對流、摩擦、熱傳導、氣動加熱等一系列的質量和能量變化的復雜過程。 本文介紹了與飛機結冰相關的一些基本概念，簡要概括了結冰對飛機飛行性能和操縱性能等方面的影響。概括了飛機結冰現(xiàn)象的一些研究方法。應用Fluent軟件求解二元翼型周圍的繞流情況，應用求解偏微分方程的方法對二維翼型進行網格劃分，利用翼型算例對流場的算法進行了驗證。研究了水滴在流場中的運動情況，闡述了水滴沖擊翼型的相關概念，特別分析了水滴撞擊特性的影響因素，應用Lagrange法建立了水滴的運動方程，根據(jù)數(shù)值求解的方法（Runge-Kutta），得到了翼型上下表面水滴的撞擊極限，進而得到水滴的運動軌跡。建立了二維翼型的Messinger結冰數(shù)學模型，根據(jù)假設建立并求解了翼型表面的質量平衡方程和能量守恒方程，考慮了結冰表面粗糙度對翼型結冰的影響，給出了翼型表面積冰形狀的確定方法。 最后對NACA0012翼型的三個結冰算例進行了數(shù)值模擬計算，將模擬的結果與實驗給出的結果展開比較分析，結果基本符合實驗結果中積冰生長趨勢，證明了本文算法是有效的和可行的，同時，從對升力與阻力方面的影響出發(fā)，簡要說明了翼型表面結冰后氣動特性的改變。
[Abstract]:With the rapid development of science and technology and national economy in China, aircraft, as a necessary means of transportation, has become a part of people's life. Aircraft brings people a convenient, fast and comfortable life, but also brings certain risks. Among them, the flight risk caused by aircraft icing occupies a prominent position and has become the number one factor that endangers flight safety. As the plane travels through the clouds, ice accumulates on the body's surface when it encounters icy weather conditions. There are small, unfrozen droplets of liquid water in these frozen clouds, and they are distributed in the clouds, and as the plane passes through the frozen clouds at high speed, the droplets collide with the plane, disrupting the stability they once maintained. Some small liquid droplets will instantly become small ice particles, attached to the surface of the airfoil, causing the aircraft ice phenomenon. Aircraft icing is a complex process of mass and energy changes, such as evaporation, convection, friction, heat conduction, aerodynamic heating, etc. In this paper, some basic concepts related to aircraft icing are introduced, and the effects of icing on aircraft flight performance and maneuverability are briefly summarized. Some research methods of aircraft ice phenomenon are summarized. The flow around a binary airfoil is solved by using Fluent software. The method of solving partial differential equation is used to mesh the two-dimensional airfoil, and the algorithm of flow field is verified by an example of airfoil. In this paper, the motion of water droplets in the flow field is studied, the related concepts of water droplet impingement airfoils are expounded, and the influence factors of water droplet impact characteristics are analyzed, and the equation of motion of water droplets is established by using Lagrange method. According to the numerical solution method (Runge-Kutta), the impact limit of the water droplets on the upper and lower surfaces of the airfoil is obtained, and then the trajectory of the water droplets is obtained. The Messinger icing mathematical model of two dimensional airfoil is established. The mass balance equation and energy conservation equation of airfoil surface are established and solved according to the hypothesis. The influence of icing surface roughness on airfoil icing is considered. The method of determining the ice shape of airfoil surface area is given. Finally, three ice forming examples of NACA0012 airfoil are numerically simulated and compared with the experimental results. The results basically accord with the trend of ice accumulation in the experimental results. It is proved that the proposed algorithm is effective and feasible. At the same time, the change of aerodynamic characteristics after icing on airfoil surface is briefly explained from the effect on lift and resistance.
【學位授予單位】：哈爾濱工程大學
【學位級別】：碩士
【學位授予年份】：2013
【分類號】：V328

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本文編號：2149273