高速风洞大振幅俯仰动态试验技术研究  

Investigation of dynamic test technology for a model pitching oscillation with large amplitude in high speed wind tunnels

作　　者：李其畅[1] 伍开元[1] 郑世华[1] 徐永长[1] 黄存栋[1] 王涛[1] 

机构地区：[1]中国空气动力研究与发展中心,四川绵阳621000

出　　处：《实验流体力学》2004年第4期67-71,77,共6页Journal of Experiments in Fluid Mechanics

基　　金：空气动力学预研基金(863 2 6 05)

摘　　要：在高速大迎角时的动态气动特性是衡量新一代高机动飞行器气动性能的重要参数之一。笔者介绍了在CARDC的FL 21与FL 24高速风洞配套的大振幅俯仰动态失速实验系统。该系统包括:FL 21与FL 24高速风洞大振幅俯仰运动机构;俯仰运动控制系统;数据采集与处理软件系统。该系统可以在高速风洞中真实模拟飞行器大振幅俯仰运动,并测量其相应的非定常气动力的变化,也可以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。试验研究初步揭示了航天飞机OV102模型高速大迎角俯仰运动的动态气动特性。Dynamic aerodynamics characteristics is one of very important parameters of modern maneuverable aircrafts to be scaled in high angle of attack and high speed. The test equipment matching of FL-21 and FL-24 wind tunnel of CARDC for a model pitching oscillation with large amplitude is introduced, and this system includes three parts: dynamic mounts of pitching oscillation rig model, electronic-control system for pitching motion, data acquisition and processing software. This system can be used to simulate the real status change of the aircraft in high speed wind tunnel and to measure unsteady aerodynamics for flight dynamic analysis and flight simulation. The dynamic aerodynamics performances of OV102 space shuttle model pitching oscillation in large amplitude in high speed is simply presented in the paper.

关 键 词：风洞试验 动态失速 大振幅 俯仰 非定常空气动力 

分 类 号：V211.74[航空宇航科学与技术—航空宇航推进理论与工程]