本文關鍵詞： 飛機結冰 臨界冰形 結冰敏感性分析 數(shù)值模擬 氣動性能 適航規(guī)章 符合性驗證　出處：《空氣動力學學報》2016年06期 　論文類型：期刊論文

【摘要】：臨界冰形是指在適航規(guī)章結冰包線內,每個可用飛行構型下,對飛機操縱性和穩(wěn)定性影響最嚴重的冰形,臨界冰形分析是飛機適航取證中的重要工作。對臨界冰形確定方法,及臨界冰形對氣動特性的影響進行了研究。發(fā)展了基于CFD方法計算臨界冰形的一般方法,包括臨界冰形分析狀態(tài)、敏感性分析截面確定、結冰參數(shù)敏感性分析、臨界結冰條件確定、臨界冰形確定等。流場計算采用中航工業(yè)空氣動力研究院氣動力計算平臺(UNSMB),基于Jameson中心格式的有限體積法求解N-S方程;水滴撞擊特性計算采用Eulerian方法求解水滴軌跡運動方程;結冰計算采用經典的Messinger熱力學模型。選取CRM飛機為研究對象,以機翼外翼50%展長處為敏感性分析截面,在典型飛行條件下,分析了結冰對環(huán)境溫度、水滴直徑、飛行速度、飛行迎角等參數(shù)的敏感性。利用"幾何外形敏感性分析方法",即通過對比冰形的上下冰角角度和冰角厚度等冰形幾何參數(shù)來確定最嚴重冰形,得到了CRM飛機的臨界結冰條件和臨界冰形,其中敏感性分析截面在水滴直徑為30μm時上冰角厚度和下冰角厚度最大,冰角最大厚度約41mm。計算了結冰后的氣動性能衰減規(guī)律,臨界冰形對飛機氣動性能影響嚴重,導致升力降低6.7%~23.8%,阻力增加17%~70.9%。發(fā)展了45min待機臨界冰形確定方法,基于幾何外形敏感性分析方法進行環(huán)境溫度、水滴直徑、飛行條件等各類參數(shù)的結冰敏感性分析,得到飛機的臨界結冰條件和臨界冰形,對于民用飛機設計和適航取證具有一定的工程應用價值。
[Abstract]:Critical ice shape refers to the ice shape which has the most serious effect on aircraft maneuverability and stability in the icing envelope line of airworthiness regulations. Critical ice shape analysis is an important work in aircraft seaworthiness forensics. And the influence of critical ice shape on aerodynamic characteristics is studied. A general method for calculating critical ice shape based on CFD method is developed, including critical ice shape analysis state, sensitivity analysis section determination, ice parameter sensitivity analysis. The determination of critical ice condition and the determination of critical ice shape etc. The flow field calculation is carried out by using the aerodynamics calculation platform of the China Aeronautical Industrial aerodynamic Research Institute and the finite volume method based on the Jameson central scheme to solve the N-S equation. The water droplet trajectory motion equation is solved by Eulerian method, and the classical Messinger thermodynamic model is used for ice calculation. The CRM aircraft is selected as the object of study, and the outer wing 50% is taken as the sensitivity analysis cross section. Under typical flight conditions, the ice effect on ambient temperature, droplet diameter and flying speed was analyzed. The sensitivity of flight angle of attack. By means of "geometric shape sensitivity analysis method", the most serious ice shape is determined by comparing the ice shape geometric parameters, such as the ice angle between the upper and lower ice angles and the ice angle thickness. The critical icing condition and critical ice shape of CRM aircraft are obtained. The sensitivity analysis section has the largest ice angle thickness and ice angle thickness when the diameter of water droplet is 30 渭 m, and the maximum ice angle thickness is about 41 mm. The aerodynamic performance attenuation law after icing is calculated. The critical ice shape has a serious effect on the aerodynamic performance of the aircraft, resulting in the reduction of lift by 6.7and 23.8m, and the increase of resistance by 17 / 70.9.The method of determining critical ice shape for 45min standby is developed, and the environmental temperature and the diameter of water droplet are carried out based on the sensitivity analysis method of geometric shape. Based on the analysis of icing sensitivity of flight conditions and other parameters, the critical icing conditions and the critical ice shapes of aircraft are obtained, which has certain engineering application value for civil aircraft design and airworthiness identification.
【作者單位】： 中航工業(yè)空氣動力研究院;高速高雷諾數(shù)氣動力航空科技重點實驗室;
【分類號】：V211.4

【相似文獻】

相關期刊論文 前9條

1 趙賓賓;黎先平;張淼;周峰;;民用飛機翼面冰形的工程修正[J];民用飛機設計與研究;2013年04期

2 申曉斌;郁嘉;林貴平;卜雪琴;曾宇;;基于特征正交分解法的翼型結冰冰形快速預測[J];航空動力學報;2013年04期

3 杜晨慧;郁嘉;林貴平;申曉斌;卜雪琴;;二維翼型大尺寸過冷水滴撞擊特性及冰形分析[J];航空動力學報;2014年04期

4 楊勝華;林貴平;;機翼結冰過程的數(shù)值模擬[J];航空動力學報;2011年02期

5 付斌;孫志國;朱程香;朱春玲;;機翼表面結冰熱力學模型[J];工程熱物理學報;2010年10期

6 張強;曹義華;胡利;;翼型表面明冰的數(shù)值模擬[J];航空動力學報;2009年01期

7 楊勝華;林貴平;;霜冰生長過程的數(shù)值模擬[J];計算機工程與設計;2010年01期

8 申曉斌;林貴平;卜雪琴;郁嘉;侯盼雪;;發(fā)動機進氣道短艙前緣結冰三維模擬研究[J];航空學報;2013年03期

9 ;[J];;年期

相關碩士學位論文 前3條

1 陳曉圓;飛機結冰多參數(shù)影響研究[D];南京航空航天大學;2015年

2 卞少兵;飛機機翼積冰數(shù)值模擬方法研究[D];南京航空航天大學;2015年

3 何舟東;典型冰形結冰機理的數(shù)值模擬與試驗研究[D];南京航空航天大學;2009年

，

本文編號：1544744