Trim Analysis of Highly Flexible Aircraft via a Coupled DG-VLM Framework

An original computational framework for the trim analysis of highly-flexible aircraft is presented in this work. The framework is based on the combination of a discontinuous Galerkin (DG) method and a non-planar Vortex Lattice Method (VLM). The DG method is employed for solving three-dimensional finite-strain, whereas the non-planar VLM is employed for solving potential-flow aerodynamics of the deformed structure. The DG-VLM coupling is performed by considering the forces generated by the vortexes as energetically equivalent to body forces acting on the structure. The framework is validated by considering the finite-strain response of a cantilever beam, the finite-strain response of a highly flexible wing, and the angle of attack and elevator deflection at longitudinal trim condition of an aircraft featuring the same highly flexible wing.