Advances in aircraft and spacecraft science

  • 제3권4호
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  • Pages.447-470
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  • 2016
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  • 2287-528X(pISSN)
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  • 2287-5271(eISSN)
테크노프레스 (Techno-Press)
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Effect of sweep angle on bifurcation analysis of a wing containing cubic nonlinearity

  • Irani, Saied (Department of Aerospace Engineering, Khaje Nasir Toosi University of Technology) ;
  • Amoozgar, Mohammadreza (Department of Aerospace Engineering, Khaje Nasir Toosi University of Technology) ;
  • Sarrafzadeh, Hamid (Department of Aerospace Engineering, Khaje Nasir Toosi University of Technology)
  • 투고 : 2015.09.06
  • 심사 : 2016.06.10
  • 발행 : 2016.10.25
⟨ 이전 논문 다음 논문 ⟩

초록

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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참고문헌

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