Nonlinear static aeroelastic trim and stability analysis of highly flexible all-wing aircraft

The static aeroelastic responses, trim solutions and stability analysis of a high aspect-ratio all-wing aircraft is presented. The basics of the computational framework is the coupling of a geometrically nonlinear 3D co-rotational double-spar structural model with a 3D non-planar vortex lattice aerodynamic model. Inertia relief is exploited in the aeroelastic calculation to count for the effects of mass distribution on the static deformations of the unconstrained flying aircraft. A static structural test of the outer wing is conducted to verify the numerical model. Numerical results of the aeroelastic deflections, lift distributions, aerodynamic coefficients and their derivatives, as well as the trim solutions and flight dynamic roots are presented and analyzed in detail and compared with rigid, linear and nonlinear structural models. The present work provides sound insights on the aeroelastic behaviors of the flexible high aspect-ratio all-wing aircraft, which emphasizing once more the importance of taking into account the geometric nonlinearity in the design and analysis of flexible aircraft.