Effect of sweep angle on bifurcation analysis of a wing containing cubic nonlinearity

Saied Irani, Mohammadreza Amoozgar, Hamid Sarrafzadeh

Research output: Contribution to journalArticle

Abstract

Limit cycle oscillations (LCO) as well as nonlinear aeroelastic analysis of a swept aircraft wing with cubic restoring moments in the pitch degree of freedom is investigated. The unsteady aerodynamic loading applied on the wing is modeled by using the strip theory. The harmonic balance method is used to calculate the LCO frequency and amplitude for the swept wing. Finally the super and subcritical Hopf bifurcation diagrams are plotted. It is concluded that the type of bifurcation and turning point location is sensitive to the system parameters such as wing geometry and sweep angle.

Original languageEnglish
Pages (from-to)447-470
Number of pages24
JournalAdvances in Aircraft and Spacecraft Science
Volume3
Issue number4
DOIs
Publication statusPublished - 25 Oct 2016
Externally publishedYes

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Swept wings
Hopf bifurcation
Nonlinear analysis
Aerodynamics
Geometry

Cite this

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title = "Effect of sweep angle on bifurcation analysis of a wing containing cubic nonlinearity",
abstract = "Limit cycle oscillations (LCO) as well as nonlinear aeroelastic analysis of a swept aircraft wing with cubic restoring moments in the pitch degree of freedom is investigated. The unsteady aerodynamic loading applied on the wing is modeled by using the strip theory. The harmonic balance method is used to calculate the LCO frequency and amplitude for the swept wing. Finally the super and subcritical Hopf bifurcation diagrams are plotted. It is concluded that the type of bifurcation and turning point location is sensitive to the system parameters such as wing geometry and sweep angle.",
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Effect of sweep angle on bifurcation analysis of a wing containing cubic nonlinearity. / Irani, Saied; Amoozgar, Mohammadreza; Sarrafzadeh, Hamid.

In: Advances in Aircraft and Spacecraft Science, Vol. 3, No. 4, 25.10.2016, p. 447-470.

Research output: Contribution to journalArticle

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AU - Irani, Saied

AU - Amoozgar, Mohammadreza

AU - Sarrafzadeh, Hamid

PY - 2016/10/25

Y1 - 2016/10/25

N2 - Limit cycle oscillations (LCO) as well as nonlinear aeroelastic analysis of a swept aircraft wing with cubic restoring moments in the pitch degree of freedom is investigated. The unsteady aerodynamic loading applied on the wing is modeled by using the strip theory. The harmonic balance method is used to calculate the LCO frequency and amplitude for the swept wing. Finally the super and subcritical Hopf bifurcation diagrams are plotted. It is concluded that the type of bifurcation and turning point location is sensitive to the system parameters such as wing geometry and sweep angle.

AB - Limit cycle oscillations (LCO) as well as nonlinear aeroelastic analysis of a swept aircraft wing with cubic restoring moments in the pitch degree of freedom is investigated. The unsteady aerodynamic loading applied on the wing is modeled by using the strip theory. The harmonic balance method is used to calculate the LCO frequency and amplitude for the swept wing. Finally the super and subcritical Hopf bifurcation diagrams are plotted. It is concluded that the type of bifurcation and turning point location is sensitive to the system parameters such as wing geometry and sweep angle.

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KW - Cubic nonlinearity

KW - Harmonic balance method

KW - Limit cycle oscillations (LCO)

KW - Sweep angle

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