翼尖法向吹气对编队飞行安全性的影响  

Influence of Wingtip Normal Blowing on Safety of Formation Flight

作　　者：钟林龙 韩尘傲 冯路启 刘学强[1] ZHONG Linlong;HAN Chen’ao;FENG Luqi;LIU Xueqiang(College of Aerospace Engineering,Nanjing University of Aeronautics&Astronautics,Nanjing 210016,China)

机构地区：[1]南京航空航天大学航空学院,南京210016

出　　处：《南京航空航天大学学报》2024年第5期922-931,共10页Journal of Nanjing University of Aeronautics & Astronautics

摘　　要：为了提高编队飞行的安全性,提出了采用翼尖法向吹气的方法削弱前机尾流的影响。采用数值模拟方法进行了不同编队位置飞行过程中前机尾流对后机气动特性的仿真分析,并通过仿真方法对翼尖法向吹气进行了数值仿真。仿真结果表明:编队飞行过程中,后机在横向穿越前机的涡区时受到很大的扰动力矩,加大了舵面操纵和飞机控制的难度,严重危害到后机的安全性。引入翼尖法向吹气后,后机的翼尖涡被削弱,升阻比随着吹气动量系数的增大而增大。随后在Simulink中搭建了带有翼尖法向吹气的编队飞行控制系统进行仿真模拟。仿真结果表明:所提出的翼尖法向吹气减弱了前机尾流的影响,使后机在横向穿越前机涡区过程中位置偏差和速度偏差减小,同时后机副翼偏转量大幅减小,后机安全性得以提高。In order to improve the safety of formation flight,a method using wingtip normal blowing is proposed to weaken the influence of the wake generated by the leading aircraft.Numerical simulation methods are employed to analyze the aerodynamic characteristics of the following aircraft affected by the wake of the leading aircraft during different formation positions.Additionally,numerical simulation is conducted on the wingtip normal blowing.The simulation results indicate that during formation flight,the following aircraft experiences significant disturbance torque when transiting laterally through the vortex area of the leading aircraft,which increases the difficulty of rudder manipulation and aircraft control,posing a serious threat to the safety of the following aircraft.After introducing wingtip normal blowing,the wingtip vortex of the following aircraft is weakened,and the lift-to-drag ratio increases with the augmentation of the blowing momentum coefficient.Subsequently,a formation flight control system with wingtip normal blowing is established in Simulink for simulation.The simulation results demonstrate that the proposed wingtip normal blowing mitigates the influence of the wake from the leading aircraft,reducing both the lateral position and velocity deviations of the following aircraft as it traverses the vortex area of the leading aircraft.Concurrently,the aileron deflection of the following aircraft is significantly decreased,thereby improving the safety of the following aircraft.

关 键 词：编队飞行 翼尖吹气 尾流 计算流体力学 飞行动力学仿真 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]