ROTOR BLADE AEROELASTICITY IN FORWARD FLIGHT WITH AN IMPLICIT AERODYNAMIC FORMULATION

被引：21

作者：

CELI, R ^{[1
]}

FRIEDMANN, PP ^{[1
]}

机构：

[1] UNIV CALIF LOS ANGELES,DEPT MECH AEROSP & NUCL ENGN,LOS ANGELES,CA 90024

来源：

AIAA JOURNAL | 1988年 / 26卷 / 12期

关键词：

Helicopters--Rotors - Mathematical Techniques--Numerical Methods - Turbomachinery--Blades;

D O I：

10.2514/3.10060

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

This paper describes a new methodology for formulating the aeroelastic stability and response problem for helicopter rotor blades. The mathematical expressions for the aerodynamic loads need not be explicit functions of the blade displacement quantities. The methodology is combined with a finite-element model of the blade and a quasilinearization solution technique. The resulting computer program is used to study the behavior of blades with noncoincident elastic axis, aerodynamic centers, and centers of mass.

引用

页码：1425 / 1433

页数：9

共 28 条

[1]

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[2]

Celi R., 1987, THESIS U CALIFORNIA

[3]

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[4]

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[5]

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[6]

FRIEDMANN PP, 1983, VERTICA, V7, P101

[7]

FRIEDMANN PP, 1987, VERTICA, V11, P139

[8]

FRIEDMANN PP, 1980, J AM HELICOPTER SOC, V25, P36

[9]

GIBBONS MP, 1984, VERTICA, V8, P229

[10]

Hodges D. H., 1987, J AM HELICOPTER SOC, V32, P78, DOI [10.4050/JAHS.32.78, DOI 10.4050/JAHS.32.78]

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