Attitude μ-control with initiative morphing strategy for a gull-wing

Instead of regarding morphing of aircrafts as a way to adapt the environment, this paper is focused on using morphing as a mean of flight control. With morphing aircrafts taken as bodies with variable center of mass and inertia tensor, the centroid dynamic equations are analyzed, which are then simplified for gull-wings with folding angles as the morphing parameters, and linearized and decoupled to meet the controller design requirements. The μ - synthesis is introduced and the control channels are specified for the convenience of aircraft design and control parameters modification. The attitude control approach is validated by the nonlinear simulations, which show that the initiative morphing strategy has the ability to reduce the influence of the nonlinearity.