摘要
推力矢量是提高战斗机大迎角动态气动特性,提升其过失速机动能力和飞行品质的重要手段。新一代战斗机的高机动性要求也使气动和推力矢量的融合控制研究日益重要。针对中国空气动力研究与发展中心3.2m开口低速风洞,研制了喷流模拟器和通气动态试验装置,建立了带推力矢量的大迎角动态试验技术。开展了不同减缩频率、不同落压比、不同喷管偏角时的大迎角俯仰振荡运动特性试验研究。结果表明:与无喷流试验相比,带喷流时模型的动态特性均随着落压比和喷管偏角的变化呈现规律性的变化;力和力矩系数形成的迟滞曲线面积随着落压比和偏角的增加而增加;减缩频率的变化对模型的动态特性影响小于无喷流时的影响。总的来说,推力矢量的影响未改变模型大迎角动态特性的基本规律,但是随着推力矢量角度和大小的变化,有规律地改变了模型动态气动力和力矩的变化幅度。
The influence of thrust vector on aerodynamic characteristics at high angles of attack is an important part of improving the dynamic performance of aircraft.The high maneuverability of the new generation fighter also makes the fusion control research of aerodynamic characteristics and thrust vector more and more important.In the3.2 mlow speed wind tunnel of China Aerodynamics Research and Development Center,a dynamic test technique for thrust vector at large angle of attack is developed by means of a jet simulator and a ventilation dynamic test device.Experimental research on high angle of attack pitching oscillation characteristics with different reduction frequencies,pressure drop ratios and nozzle deflection angles is carried out.The results show that compared with the non-jet test,the dynamic characteristics of the model with the jet flow changing regularly along with the change of the pressure drop ratio and the nozzle deflection angle.The hysteresis curve area formed by force and moment coefficients increases with the increase of the pressure drop ratio and the deflection angle.The influence of the reduced frequency on the dynamic characteristics of the model is less than that without the jet flow.In general,thrust vector does not change the basic rules of dynamic characteristics at high angle of attack,but with the change of angle and force of thrust vector,thrust vector also regularly increases the change magnitude of the dynamic aerodynamic force and moment.
作者
汤伟
黄勇
傅澔
TANG Wei;HUANG Yong;FU Hao(School of Aeronautics, Northwestern Polytechnical University, Xi＇an 710072, China;Low Speed Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China)
出处
《航空学报》
EI
CAS
CSCD
北大核心
2018年第4期83-89,共7页
Acta Aeronautica et Astronautica Sinica
关键词
推力矢量
大迎角
气动特性
低速风洞
喷流模拟
thrust vector
high angle of attack
aerodynamic characteristics
low speed wind tunnel
jet simulation
