Experimental active control of a typical section using a trailing-edge flap

被引：54

作者：

Vipperman, JS ^{[1
]}

Clark, RL ^{[1
]}

Conner, M ^{[1
]}

Dowell, EH ^{[1
]}

机构：

[1] Duke Univ, Dept Mech Engn & Mat Sci, Durham, NC 27708 USA

来源：

JOURNAL OF AIRCRAFT | 1998年 / 35卷 / 02期

关键词：

D O I：

10.2514/2.2312

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

This paper presents an experimental implementation of an active control system used to suppress flutter in a typical section airfoil. The H-2 optimal control system design is based on experimental system identifications of the transfer functions between three measured system variables-pitch, plunge, and flap position-and a single control signal that commands the flap of the airfoil. Closed-loop response of the airfoil demonstrated gust alleviation below the open-loop flutter boundary, In addition, the flutter boundary was extended by 12.4% through the application of active control, Cursory robustness tests demonstrate stable control for variations in now speed of +/-10%.

引用

页码：224 / 229

页数：6

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