Advanced analysis on tiltrotor aircraft flutter stability, including unsteady aerodynamics

Taeseong Kim, SangJoon Shin

Research output: Contribution to journalJournal articleResearchpeer-review

Abstract

The whirl-flutter-instability phenomenon imposes a serious limit on the forward speed in tiltrotor aircraft. In this paper, an advanced analysis is formulated to predict an aeroelastic stability for a gimballed three-bladed rotor with flexible wing based on three different types of aerodynamic model. Among them, the one with the full unsteady aerodynamics is most sophisticated, because it may represent more realistic operating conditions. A nine-degree-of- freedom model is newly developed to predict the complete tiltrotor aircraft. Numerical results are obtained in both time and frequency domains. A generalized eigenvalue is used to estimate whirl-flutter stability in the frequency domain, and the Runge-Kutta method is used in the time domain. Control system flexibility is further included in the present analysis to give the capability for a more accurate stability prediction. Results from such an improved analysis are validated with the other existing predictions and show good agreement. The present model with unsteady aerodynamics will be extended to further consider an aerodynamic interaction between the rotor and wing.
Original languageEnglish
JournalAIAA Journal
Volume46
Issue number4
Pages (from-to)1002-1012
ISSN0001-1452
DOIs
Publication statusPublished - 2008
Externally publishedYes

Cite this

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title = "Advanced analysis on tiltrotor aircraft flutter stability, including unsteady aerodynamics",
abstract = "The whirl-flutter-instability phenomenon imposes a serious limit on the forward speed in tiltrotor aircraft. In this paper, an advanced analysis is formulated to predict an aeroelastic stability for a gimballed three-bladed rotor with flexible wing based on three different types of aerodynamic model. Among them, the one with the full unsteady aerodynamics is most sophisticated, because it may represent more realistic operating conditions. A nine-degree-of- freedom model is newly developed to predict the complete tiltrotor aircraft. Numerical results are obtained in both time and frequency domains. A generalized eigenvalue is used to estimate whirl-flutter stability in the frequency domain, and the Runge-Kutta method is used in the time domain. Control system flexibility is further included in the present analysis to give the capability for a more accurate stability prediction. Results from such an improved analysis are validated with the other existing predictions and show good agreement. The present model with unsteady aerodynamics will be extended to further consider an aerodynamic interaction between the rotor and wing.",
author = "Taeseong Kim and {SangJoon Shin}",
year = "2008",
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Advanced analysis on tiltrotor aircraft flutter stability, including unsteady aerodynamics. / Kim, Taeseong; SangJoon Shin.

In: AIAA Journal, Vol. 46, No. 4, 2008, p. 1002-1012.

Research output: Contribution to journalJournal articleResearchpeer-review

TY - JOUR

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AU - Kim, Taeseong

AU - SangJoon Shin, null

PY - 2008

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AB - The whirl-flutter-instability phenomenon imposes a serious limit on the forward speed in tiltrotor aircraft. In this paper, an advanced analysis is formulated to predict an aeroelastic stability for a gimballed three-bladed rotor with flexible wing based on three different types of aerodynamic model. Among them, the one with the full unsteady aerodynamics is most sophisticated, because it may represent more realistic operating conditions. A nine-degree-of- freedom model is newly developed to predict the complete tiltrotor aircraft. Numerical results are obtained in both time and frequency domains. A generalized eigenvalue is used to estimate whirl-flutter stability in the frequency domain, and the Runge-Kutta method is used in the time domain. Control system flexibility is further included in the present analysis to give the capability for a more accurate stability prediction. Results from such an improved analysis are validated with the other existing predictions and show good agreement. The present model with unsteady aerodynamics will be extended to further consider an aerodynamic interaction between the rotor and wing.

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