Aeroelasticity of Structurally Nonlinear Lifting Surfaces Using Linear Modally Reduced Aerodynamic Generalized Forces

Structural nonlinear efiects in aeroelasticity can be important and afiect overall nonlinear behavior in cases where the aerodynamic forces are still linear. Such is the case of the joined-wing conflguration in attached ∞ow. Since modal reduction of the structural deformation problem is often not successful when complex lifting surface conflgurations are involved, full order flnite element analysis is used to model structural behavior here, static or dynamic. Linear unsteady aerodynamics of lifting surfaces in aeroelasticity is usually modeled in the frequency domain using modal coordinates. The goal of the present efiort is to combine the full order nonlinear flnite element analysis of the structure with modally based generalized unsteady aerodynamic forces. Initial studies in which coupling of full order nonlinear flnite element models with generalized aerodynamic force models is compared to coupling of full order nonlinear flnite element models with full order aerodynamic panel methods is presented here with focus on the steady case. Unsteady cases will be described in a future paper.

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