基于滚转力矩系数的尾涡简化危险区计算分析  

Calculation and analysis of the simplified hazard area of thewake vortex based on the rolling moment coefficient

作　　者：潘卫军[1] 尹子锐 黄园晶 王安鼎 罗玉明 PAN Weijun;YIN Zirui;HUANG Yuanjing;WANG Anding;LUO Yuming(School of Air Traffic Control,Civil Aviation Flight University of China,Guanghan 618307,China)

机构地区：[1]中国民航飞行学院空中交通管理学院,四川广汉618307

出　　处：《兵器装备工程学报》2023年第3期137-142,190,共7页Journal of Ordnance Equipment Engineering

基　　金：国家自然科学基金项目(U1733203);民航局安全能力建设项目(TM2019-16-1/3)。

摘　　要：为进一步在保证安全的前提下提升飞行效率,提出了一种尾涡简化危险区的划设方法,避开这些区域可以实现飞行安全。基于飞机遭遇尾涡时的空气动力学模型,计算了飞机在不同位置遭遇尾涡时的滚转力矩;以滚转力矩系数作为安全指标,对大于滚转力矩极限值的区域进行包络,划设了尾涡简化危险区;在考虑后机自身体积的情况下,结合尾涡自身的演化、运动特性以及不同的侧风条件,对遭遇尾涡时的危险概率进行了计算分析。研究结果表明:尾涡简化危险区的侧向和垂向边界会随着尾涡的演化而减小,且远涡阶段比近涡阶段减小速度更快。对于初始环量为500 m2/s的尾涡,尾涡在自身的下沉作用下经过约11.6 s后,后机可完全脱离尾涡危险区;4.48 m/s的侧风可对危险区在侧向产生相同的作用,速度更大的侧风可使后机完全脱离尾涡危险区的时间进一步缩短。In order to further enhance flight efficiency under the premise of ensuring safety,this paper introduces a method for the delineation of a simplified hazard area of wake vortexes,and flight safety can be achieved by avoiding these areas.Based on an aerodynamics model in which an aircraft encounters a wake vortex,this paper firstly calculates the rolling moments of the aircraft encountering the wake vortex at different positions.After that,with the rolling moment coefficient being the safety index,the regions with a value higher than the limit of the rolling moment are enveloped,and the simplified hazard area of the wake vortex is delineated.Finally,considering the volume of the rear engine itself,the hazard probability of encountering the wake vortex is calculated and analyzed by combining the evolution and motion characteristics of the wake vortex as well as different crosswind conditions.The results show that the lateral and vertical boundaries of this simplified hazard area decrease with the evolution of the wake vortex,and the far vortex phase decreases more rapidly than the near vortex phase.For the wake vortex with an initial circulation of 500 m 2/s,the rear engine can completely escape the simplified hazard area under the sinking action of the wake vortex for about 11.6 s.The side wind at 4.48 m/s can have the same effect on the side of the simplified hazard area,and the crosswind with a higher speed can further shorten the time for the rear engine to completely escape this area.

关 键 词：尾流遭遇 空气动力学模型 滚转力矩系数 简化危险区 尾流间隔 

分 类 号：V211.4[航空宇航科学与技术—航空宇航推进理论与工程]