Aeroelastic stability of hingeless rotor blades in hover using fully intrinsic equations

M. R. Amoozgar, H. Shahverdi, A. S. Nobari

Research output: Contribution to journalArticle

9 Citations (Scopus)

Abstract

In this paper, the aeroelastic stability of a hingeless rotor blade in hover is investigated. The blade is modeled using the geometrically exact, fully intrinsic beam equations, whereas the aerodynamic loads applied on the blade are simulated based on the quasi-steady Greenberg aerodynamic theory. Using the generalized differential quadrature method, the resultant coupled aeroelastic equations are discretized and solved, and the eigenvalues of the linearized system are determined. By inspecting the eigenvalues, the stability of the system is examined for variations in different parameters. The obtained results are validated through comparison against those reported in the literature. Furthermore, the effects of offset of the aerodynamic center from the reference axis, the precone angle, the lead-lag frequency, static stall, and the drag coefficient on the stability boundaries of the system are evaluated. It is found that, by using the geometrically exact, fully intrinsic beam equations along with the generalized differential quadrature method, the aeroelastic instabilities of the hingeless rotor blades in hover can be determined accurately.

Original languageEnglish
Pages (from-to)2450-2460
Number of pages11
JournalAIAA Journal
Volume55
Issue number7
Early online date2 May 2017
DOIs
Publication statusPublished - 1 Jul 2017
Externally publishedYes

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Turbomachine blades
Rotors
Aerodynamics
Aerodynamic loads
Drag coefficient
Lead

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Amoozgar, M. R. ; Shahverdi, H. ; Nobari, A. S. / Aeroelastic stability of hingeless rotor blades in hover using fully intrinsic equations. In: AIAA Journal. 2017 ; Vol. 55, No. 7. pp. 2450-2460.
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Aeroelastic stability of hingeless rotor blades in hover using fully intrinsic equations. / Amoozgar, M. R.; Shahverdi, H.; Nobari, A. S.

In: AIAA Journal, Vol. 55, No. 7, 01.07.2017, p. 2450-2460.

Research output: Contribution to journalArticle

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