摘要
针对软管-锥套式空中加油系统在进行对接时,受油机在接近锥套时因其头波效应会对锥套产生气动影响,导致加剧锥套摆动、增大对接难度的问题,提出了一种受油机头波流场建模方法。基于势流理论,利用数学公式法对F-18战斗机的头波效应建模,结合软管-锥套系统动力学模型和加油机尾流场模型进行空中加油对接过程的数值仿真,并与NASA的飞行试验结果进行对比。仿真结果证实了该建模方法的有效性。
In the docking process of a hose-drogue aerial refueling system,the bow wave effect of a approaching receiver aircraft will produce a strong aerodynamic effect on the drogue which intensifies the deviation of drogue,and increases the difficulty of the docking.A method for modeling the bow wave effect of a receiver aircraft is presented.Based on potential flow theory,the bow wave effect of F-18 fighter is modeled by mathematical formula method.Combined with the hose-drogue dynamic model and tanker wake dynamic model,the numerical simulation of air refueling docking process is carried out,and compared with the NASA flight test results.Simulation results show the effectiveness of the modeling method.
作者
徐坚
张晓非
XU Jian;ZHANG Xiao-fei(Design and Research Institute,AVIC Shaanxi Aircraft Industry(Group)Corporation Ltd.,Hanzhong723213,China;95039 Troops of the PLA,Shantou515049,China)
出处
《飞行力学》
CSCD
北大核心
2019年第5期40-44,共5页
Flight Dynamics
关键词
空中加油
头波效应
软管-锥套建模
对接
aerial refueling
bow wave effect
hose-drogue modeling
docking
