Rotorcraft aeroelastic stability using robust analysis

被引：0

作者：

Quaranta G. ^{[1
]}

Tamer A. ^{[1
]}

Muscarello V. ^{[1
]}

Masarati P. ^{[1
]}

Gennaretti M. ^{[2
]}

Serafini J. ^{[2
]}

Colella M.M. ^{[2
]}

机构：

[1] Dipartimento di Scienze e Tecnologie Aerospaziali, Politecnico di Milano, Via La Masa 34, Milano

[2] Dipartimento di Ingegneria, Università Roma Tre, via della Vasca Navale 79, Roma

来源：

CEAS Aeronautical Journal | 2014年 / 5卷 / 01期

关键词：

Robust stability; Rotorcraft aeroelasticity; Rotorcraft-pilot couplings;

D O I：

10.1007/s13272-013-0082-z

中图分类号：

学科分类号：

摘要：

This paper discusses the impact of different models of aerodynamic loads on rotorcraft-pilot couplings stability using a robust stability analysis approach. The aeroelasticity of the main rotor of a helicopter is formulated using aerodynamic models based on the blade element/momentum theory and boundary element method coupled to a finite element model of the blade. The resulting linearized models are used to determine stability limits according to the generalized Nyquist criterion, associated with the accelerations of the pilot’s seat caused by the involuntary action of the pilot on the control inceptors. The resulting stability curves are discussed considering examples of involuntary pilot transfer functions from the literature. © Deutsches Zentrum für Luft- und Raumfahrt e.V. 2013

引用

页码：29 / 39

页数：10

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