摘要
为满足国内战斗机型号研制对大迎角过失速机动过程中非定常气动力问题研究的需求,中国航空工业空气动力研究院在FL-8风洞开发了一套基于电液伺服马达和电机耦合驱动的双自由度大幅振荡试验技术。简单介绍了该系统的基本组成和试验原理,给出了FL-8风洞动态标准模型双自由度大幅振荡试验的典型结果,分析表明:该系统运行性能稳定,试验数据可靠,重复性精度较高,可以有效应用于飞行器双自由度耦合运动气动特性研究。
AVIC Aerodynamics Research Institute developed a double degree-of-freedom large amplitude oscillation testing technique based on driving technology coupled hydraulic motor and servo motor in FL-8wind tunnel in order to study the aircraft unsteady aerodynamics during post maneuver at high angle-of-attack.This paper presents the basic components and test principle,as well as the FL-8wind tunnel test results of the standard model test.It is indicated that the system has high stability,reliability and repeatability precision.The technology can be effectively applied to studying and predicting the aerodynamic characteristics of double degree-of-freedom coupled motion.
出处
《航空学报》
EI
CAS
CSCD
北大核心
2016年第8期2417-2425,共9页
Acta Aeronautica et Astronautica Sinica
基金
航空科学基金(20143203002)~~
关键词
大迎角
大振幅
双自由度
非定常气动力
风洞试验
high angle-of-attack
large amplitude oscillation
double degree-of-freedom
unsteady aerodynamics
wind tunnel test
