摘要
主要介绍了一套用于３ｍ低速风洞的俯仰－滚转两自由度大振幅非定常实验系统。该系统由三大部分组成：俯仰－滚转两自由度的模型动态支撑机构；俯仰－滚转两自由度电控液压系统；数据采集与处理软件系统。该系统可以在风洞中真实模拟飞行器姿态变化，并测量其相应的六分量非定常气动力变化。为飞行器的飞行力学动态性能分析或飞行模拟器提供非定常气动力数据。另外，用三角翼在３ｍ风洞进行了多种运动状态的非定常气动力特性测量。
The test system in unsteady wind tunnel for modelling pitching rolling motion with large amplitude is introduced, and this system is built in 3 m low speed wind tunnel in Nanjing University of Aeronautics & Astronautics, and it includes three parts: dynamic mount of pitching rolling unsteady rig model; electronic control servo valve system for pitching rolling motion; data acquisition and processing software. This system can be used to simulate the real status change of the aircraft in the wind tunnel and to measure six components of unsteady aerodynamics for flight dynamics analysis and flight simulation. The unsteady aerodynamic characteristics of a delta wing in this system are tested and the results indicate the aerodynamic characteristics of the delta wing oscillating in large amplitude pitching rolling motion.
出处
《南京航空航天大学学报》
EI
CAS
CSCD
北大核心
1999年第2期121-126,共6页
Journal of Nanjing University of Aeronautics & Astronautics
基金
国家"863"计划资助
关键词
俯仰
滚转
大振幅
非定常
风洞试验
战斗机
pitch
rolling
large amplitude
unsteady aerodynamic
wind tunnel test
