Active and Passive Control for Acceleration Reduction of an Aeroelastic Typical Wing Section

被引：6

作者：

Silva, Gefferson C. ^{[1
]}

Silvestre, Flavio J. ^{[1
]}

Donadon, Mauricio V. ^{[1
]}

Santos, Osmar S. ^{[1
]}

Guimaraes Neto, Antonio B. ^{[1
]}

da Silva, Roberto G. A. ^{[1
]}

Versiani, Thiago de S. S. ^{[1
]}

Gonzalez, Pedro J. ^{[1
]}

Bertolin, Rafael M. ^{[1
]}

机构：

[1] Inst Technol Aeronaut, Dept Aeronaut, Sao Jose Dos Campos, Brazil

来源：

JOURNAL OF VIBRATION AND CONTROL | 2018年 / 24卷 / 13期

关键词：

Aeroelasticity; flutter suppression; linear quadractic regulator; shape memory alloy; typical airfoil section; FLUTTER SUPPRESSION; TRAILING-EDGE; AIRCRAFT; ALLOYS; MODEL;

D O I：

10.1177/1077546317728147

中图分类号：

O42 [声学];

学科分类号：

070206 ; 082403 ;

摘要：

The main concern related to the flutter phenomenon is predicting and avoiding it. This paper describes the application of a flexural-torsional flutter testbed for acceleration reduction by applying active and passive model-based control. The model consists of the 2D typical section, with aerodynamic loads estimated by an unsteady time-domain formulation based on Wagner's function. The active control architecture consists of a stability augmentation system with output feedback and gain scheduling via the linear-quadratic regulator theory and actuation by servomechanism. The passive control employs a shape-memory alloy to provide additional torsional stiffness. Experimental results show considerable reduction of oscillations at a relative low cost for both active and passive control strategies, and that the use of shape memory alloys in aeroelastic stability problems is promising.

引用

页码：2673 / 2687

页数：15

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