Geometrically Nonlinear Effects on the Aeroelastic Response of a Transport Aircraft Configuration

This paper investigates geometrically nonlinear aeroelastic effects on an industry-level aircraft configuration. Results are obtained via a new approach that uses geometrical information to compute and seamlessly integrates with conventional, linear load packages. The starting point is generic finite-element model frequency-domain aerodynamic influence coefficient matrices, the resulting system includes control inputs, longitudinal trim, or gust disturbances in time domain, which can be employed separately combination obtain dynamic for loads stability analysis. response of long range studied, highlighting difference between approaches calculations flying equilibrium, perturbations, variations flutter boundary. justify need analysis production environment airplanes ultrahigh-aspect-ratio wings.