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A platform for research: civil engineering, architecture and urbanism
Absolute Nodal Coordinate Formulation for Aeroelastic Analysis of Panel
This paper deals with supersonic/hypersonic flutter analysis of panels. A 3-D rectangular plate element of variable thickness based on absolute nodal coordinate formulation (ANCF) has been developed for the structural model. A continuum mechanics approach for the definition of the elastic forces within the finite element is considered. Both shear strain and transverse normal strain are taken into account. The aerodynamic force is evaluated by considering the first-order piston theory to linearize the potential flow and is coupled with the structural model to account for pressure loading. A provision is made to take into account the effect of arbitrary flow directions with respect to the panel edges. Aeroelastic equations using ANCF are derived and solved numerically. Values of critical dynamic pressure are obtained by a modal approach, in which the mode shapes are obtained by ANCF. A detailed parametric study is carried out to observe the effects of different flow angle directions and aspect ratios on the flutter boundary.
Absolute Nodal Coordinate Formulation for Aeroelastic Analysis of Panel
This paper deals with supersonic/hypersonic flutter analysis of panels. A 3-D rectangular plate element of variable thickness based on absolute nodal coordinate formulation (ANCF) has been developed for the structural model. A continuum mechanics approach for the definition of the elastic forces within the finite element is considered. Both shear strain and transverse normal strain are taken into account. The aerodynamic force is evaluated by considering the first-order piston theory to linearize the potential flow and is coupled with the structural model to account for pressure loading. A provision is made to take into account the effect of arbitrary flow directions with respect to the panel edges. Aeroelastic equations using ANCF are derived and solved numerically. Values of critical dynamic pressure are obtained by a modal approach, in which the mode shapes are obtained by ANCF. A detailed parametric study is carried out to observe the effects of different flow angle directions and aspect ratios on the flutter boundary.
Absolute Nodal Coordinate Formulation for Aeroelastic Analysis of Panel
Abbas, Laith K. (author) / Rui, Xiao-Ting (author) / Marzocca, Piergiovanni (author)
2012
5 Seiten
Conference paper
English
Application of Absolute Nodal Coordinate Formulation for Dynamic Progressive Collapse Analysis
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