飞行器纵向阻尼动导数直接测量实验研究  

Investigation of longitudinal damping derivative of aircraft by direct measurement tests

作　　者：卜忱[1] 杜希奇[1] 王学俭[1] 

机构地区：[1]中国航空工业空气动力研究院,哈尔滨150001

出　　处：《实验流体力学》2005年第1期31-34,共4页Journal of Experiments in Fluid Mechanics

摘　　要：介绍了新研制的"FL-8风洞大幅升沉和俯仰耦合振荡实验系统"及采用该系统产生纯俯仰运动测量飞行器纵向阻尼动导数的试验技术,给出了部分试验结果。实验结果表明,阻尼导数和时差导数在中、大迎角时存在明显的非线性耦合,采用纯俯仰运动直接测量的阻尼导数在整个迎角范围内都是合理的。This paper introduces the large amplitude descent-pitch coupling forced oscillation system recently developed in FL-8 wind tunnel, and the new test technology of measuring longitudinal damping derivative of aircraft model by pure-pitching movement as well as some test data. The experiment result shows that damping derivative and time delay derivative doesn't follow the theory of linear combination at middling, high angle of attack, and that damping derivative measured directly by pure-pitching movement is reasonable at all attack angles.

关 键 词：升沉俯仰耦合 振荡实验系统 纯俯仰运动 阻尼导数 风洞设备 

分 类 号：V211.72[航空宇航科学与技术—航空宇航推进理论与工程]