基于计算流体动力学的发动机喷流影响下后侧飞机受力分析  

CFD-based Analysis of Rear-side Aircraft Forces under the Influence of Engine Jet

作　　者：何昕[1] 王琴 郭东鑫 陈亚青 HE Xin;WANG Qin;GUO Dong-xin;CHEN Ya-qing(School of Air Traffic Management,Civil Aviation Flight University of China,Guanghan 618307,China;Civil Aviation Administration of China(CAAC)Academy of Flight Technology and Safety,Civil Aviation Flight University of China,Guanghan 618307,China)

机构地区：[1]中国民用航空飞行学院空中交通管理学院,广汉618307 [2]中国民用航空飞行学院飞行技术与飞行安全科研基地,广汉618307

出　　处：《科学技术与工程》2023年第33期14443-14451,共9页Science Technology and Engineering

基　　金：民航局安全能力项目(〔2022〕186);中国民用航空飞行学院科研创新团队(JG2022-09)。

摘　　要：实施运行起飞点后侧穿越跑道方式的关键是确定两机安全间隔,后机受到前机发动机喷流作用则是确定安全间隔的重要影响因素。基于起飞点后侧穿越跑道方式,采用计算流体动力学(computational fluid dynamics,CFD)数值模拟方法对一定距离下前机发动机喷流直接作用于后机的场景进行研究。根据数值模拟结果,后机整体压力值最大范围分布在迎喷流一侧的垂直尾翼、水平尾翼表面和机身尾部。后机表面沿喷流方向上的受力为18404.1 N,结合其抗侧偏能力分析,认为基于最大安全裕度,为保证后机(空重)在前机发动机喷流作用下,还能保持在滑行道中线上运行,应在487 m的基础上再适当增加间隔。The key to the implementation of the runway crossing at the rear side of the take-off point is to determine the safety separation between the two aircraft,and the rear aircraft is affected by the engine jet of the front aircraft as an important factor of the safety separation.Based on the runway crossing at the rear side of the take-off point,computational fluid dynamics(CFD)numerical simulation was used to study the scenario of the front engine jet acting directly on the rear aircraft at a certain distance.According to the results of the numerical simulation,the maximum range of overall pressure values of the rear aircraft is distributed on its vertical tail,horizontal tail surface and fuselage tail on the side facing the jet stream.The force on the surface of the rear aircraft along the jet direction is 18404.1 N,combined with its ability to resist lateral deflection analysis,that based on the maximum safety margin,in order to ensure that the rear machine(empty weight)under the action of the front engine jet,but also to maintain the operation of the taxiway centerline,should be in 487 m on the basis of an appropriate increase in the separation.

关 键 词：穿越跑道方式 数值模拟 飞机受力 发动机喷流 安全间隔 

分 类 号：V212.121[航空宇航科学与技术—航空宇航推进理论与工程]