临界冰形确定方法及其对气动特性影响研究

发布时间：2018-02-27 23:17

本文关键词： 飞机结冰临界冰形结冰敏感性分析数值模拟气动性能适航规章符合性验证　出处：《空气动力学学报》2016年06期 　论文类型：期刊论文

【摘要】：临界冰形是指在适航规章结冰包线内,每个可用飞行构型下,对飞机操纵性和稳定性影响最严重的冰形,临界冰形分析是飞机适航取证中的重要工作。对临界冰形确定方法,及临界冰形对气动特性的影响进行了研究。发展了基于CFD方法计算临界冰形的一般方法,包括临界冰形分析状态、敏感性分析截面确定、结冰参数敏感性分析、临界结冰条件确定、临界冰形确定等。流场计算采用中航工业空气动力研究院气动力计算平台(UNSMB),基于Jameson中心格式的有限体积法求解N-S方程;水滴撞击特性计算采用Eulerian方法求解水滴轨迹运动方程;结冰计算采用经典的Messinger热力学模型。选取CRM飞机为研究对象,以机翼外翼50%展长处为敏感性分析截面,在典型飞行条件下,分析了结冰对环境温度、水滴直径、飞行速度、飞行迎角等参数的敏感性。利用"几何外形敏感性分析方法",即通过对比冰形的上下冰角角度和冰角厚度等冰形几何参数来确定最严重冰形,得到了CRM飞机的临界结冰条件和临界冰形,其中敏感性分析截面在水滴直径为30μm时上冰角厚度和下冰角厚度最大,冰角最大厚度约41mm。计算了结冰后的气动性能衰减规律,临界冰形对飞机气动性能影响严重,导致升力降低6.7%~23.8%,阻力增加17%~70.9%。发展了45min待机临界冰形确定方法,基于几何外形敏感性分析方法进行环境温度、水滴直径、飞行条件等各类参数的结冰敏感性分析,得到飞机的临界结冰条件和临界冰形,对于民用飞机设计和适航取证具有一定的工程应用价值。
[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.
【作者单位】：中航工业空气动力研究院;高速高雷诺数气动力航空科技重点实验室;
【分类号】：V211.4

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