翼型风洞实验模型姿态角的测量与控制  

The measurement and control of the model attitude angle in airfoil wind tunnel test

作　　者：尹迪义[1] 竹朝霞[1] 惠增宏[1] 金承信[1] 

机构地区：[1]西北工业大学翼型研究中心,陕西西安710072

出　　处：《流体力学实验与测量》2001年第1期70-79,共10页Experiments and Measurements in Fluid Mechanics

基　　金：国防科技预研基金资助项目

摘　　要：介绍NF 3低速翼型风洞常规和动态实验模型姿态角测量和控制系统的特点以及为提高角度测量精度和准度所采取的措施。应用一种直流伺服系统 ,采用电机位置和速度闭环方法 ,已经获得模型姿态角的精度在± 0 .0 5°以内。为进一步提高测控性能 ,对于二元实验在翼型轴上安装圆感应同步器 ,测量模型的实际角度 ,并作为反馈信号。这种位置全闭环系统 ,可使角度精度达到± 0 .0 0 83°。对于三元实验 ,用一个加速度计固定在模型内 ,实时测量模型的实际攻角 ,并对实验结果进行预处理 ,从而减少因气动弹性角产生的误差。This paper describes the characteristics of model attitude angle measurement and control system for normal and dynamic test,and the effective methods for advancing the precision and accuracy of angle measurement in NF 3 low speed airfoil wind tunnel.Used a DC servo system based micro computer,we have achieved the precision of the model attitude angle in±3′,by means of motor position and velocity closed loop.For higher performance of the measurement and control to 2 dimensional test,used a round inductive synchronous transducer fixed on airfoil axis measuring model actual angle and acting as feed back signal.This all position closed loop system can arrive at angle precision in ±0.0083°.To 3 dimonsional test,used an accelerometer fixed in model measuring in time the model actual attack angle,and preprocessed to test results,so that diminished those errors as a consequence of the aeroelastic angle.

关 键 词：攻角 滑角 翼型风洞 模型姿态角 测量 控制 

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]