飞机遭遇尾涡的安全性分析

分析了飞机遭遇尾涡后的响应机理,建立了飞机受扰诱导力矩计算模型;综合考虑飞机阻尼特性、反应时间以及操纵品质等因素,建立了飞机滚转参数计算模型;以抖动失速作为飞机遭遇尾涡后改出过程的坡度角极限,建立了可接受最大坡度角计算模型。采用Delphi7.0计算了给定尾涡流场条件下的飞机受扰后滚转参数和尾涡安全间隔,分析了飞机质量、速度、高度容差以及初始坡度角对飞行安全的影响。分析结果表明:在速度一定时,飞机质量越大,可接受最大坡度角越小;在相同质量情况下,安全间隔随速度增加而缓慢减小,随高度容差的减小而减小,随初始坡度角增大而增大;安全间隔计算结果与国际民用航空组织(ICAO)标准数据之间的最大偏差是1.56%,因此,计算方法正确。

Safety analysis of aircraft encountering wake vortex

The response mechanism of aircraft encountering wake vortex was analyzed,and the calculation model of induced moment was developed.The calculating model of aircraft’s rolling parameters was constructed based on considering of the damping characteristics of aircraft,the response times,the handling qualities and so on.The calculation model of the accepted maximum bank angle was constructed based on the assumption that the buffet stall speed was posed as a critical limit in calculating the rolling progress.The rolling parameters and safe intervals of wake vortex under certain wake vortex’s field condition were calculated by using Delphi7.0.The influences of aircraft mass,speed,altitude tolerance and initial bank angle on flight safety were analyzed.Research result shows that at a certain speed,the greater aircraft mass is,the smaller the accepted maximum bank angle is.The safe interval of aircraft with certain mass decreases with the increase of speed and the decrease of altitude tolerance,while it increases with the increase of initial bank angle.Comparing the data calculated by the models with ICAO standard data,the maximal deviation is 1.56%,which verifies the correctness of the computation method.