Analysis and Control for the Mode Transition of Tandem-Wing Aircraft with Variable Sweep

Morphing aircraft can alter their aerodynamic configuration to obtain multitask adaptability and improve flight performance. In this paper, we apply the variable sweep concept on a tandem-wing micro aerial vehicle (MAV) for adaptability, two canards of which undergo backward wings forward sweep. The morphing mode not only weaken additional inertia forces moments caused by morphing, but also maintain longitudinal dynamic balance without elevator changes, generates trim drag. What is more, it was demonstrated that exert great effect characteristics during transition process, are functionalized with inputs. addition process analyzed response, stability MAV were evaluated based linear parameter varying (LPV) model. Due dramatic effects stability, gain scheduled controller convex hull algorithm proposed guarantee robustness, quadratic regulator (LQR) used boundary point consideration input saturation. Finally, superior performance theoretical simulation nonlinear