On the Effects of Stiffness Ratio in Nonlinear Aeroelastic Stability of a Folding Wing
عنوان مقاله: On the Effects of Stiffness Ratio in Nonlinear Aeroelastic Stability of a Folding Wing
شناسه ملی مقاله: AEROSPACE21_013
منتشر شده در بیست و یکمین کنفرانس بین المللی انجمن هوا فضای ایران در سال 1401
شناسه ملی مقاله: AEROSPACE21_013
منتشر شده در بیست و یکمین کنفرانس بین المللی انجمن هوا فضای ایران در سال 1401
مشخصات نویسندگان مقاله:
Sayed Hossein Moravej Barzani - Department of Mechanical Engineering, Faculty of Engineering, University of isfahan, Iran
Hossein Shahverdi - Department of Aerospace Engineering, Amirkabir University of Technology (Tehran Polytechnic), Iran
Mahdi Mortazavi - Department of Mechanical Engineering, Faculty of Engineering, University of isfahan, Iran
خلاصه مقاله:
Sayed Hossein Moravej Barzani - Department of Mechanical Engineering, Faculty of Engineering, University of isfahan, Iran
Hossein Shahverdi - Department of Aerospace Engineering, Amirkabir University of Technology (Tehran Polytechnic), Iran
Mahdi Mortazavi - Department of Mechanical Engineering, Faculty of Engineering, University of isfahan, Iran
In this paper, the effects of stiffness ratio in nonlinear aeroelastic stability of a folding wing by using the geometrically exact fully intrinsic beam equations are investigated. The important advantages of these equations in comparison with other structural beam equations are complete modeling without simplifying assumptions in large deformations, low-order nonlinearities, and thus less complexity. For the first time, folding angles have been implemented in the geometrically exact fully intrinsic beam equations and hence this is the main novelty of this study. The applied aerodynamic loads in an incompressible flow regime are determined using Peter’s unsteady aerodynamic model. In order to check the stability of the system, first the resulting non-linear partial differential equations are discretized, and then linearized about the nonlinear steady-state condition. By obtaining the eigenvalues of the linearized system, the stability of the wing is evaluated. Furthermore, investigation of the effects of the stiffness on the flutter speed of the folding wing for various folding angles, is another achievement of this study. It is observed that the geometrically exact fully intrinsic beam equations can model the folding angles for the aeroelastic analysis more accurately.
کلمات کلیدی: Folding wing-nonlinear aeroelasticity-fully intrinsic equations-folding angle.
صفحه اختصاصی مقاله و دریافت فایل کامل: https://civilica.com/doc/1668256/