Transition Flight Trajectory Optimization for a Flapping-Wing Micro Air Vehicle with Unsteady Vortex-Lattice Method

Flapping-wing micro air vehicles (FWMAVs) have the capability of performing various flight modes like birds and insects. Therefore, it is necessary to understand FWMAVs in order fully utilize vehicle. The unique can be studied through trajectory optimization. This paper proposes a optimization framework an FWMAV. A high-fidelity simulation model included sufficiently consider complicated dynamics unsteady aerodynamics are modeled with panel method (UPM) vortex-lattice (UVLM). effect wing inertia also considered model. In this study, transition trajectories searched proposed framework. An optimal control problem formulated for from hovering forward transcribed parameter direct shooting method. cost function defined as energy consumption. same converged solution obtained different initial guesses. results show that FWMAV utilizes pitch-up maneuver increase altitude, although speed reduced. performed more actively when target velocity low, or wind condition favorable acceleration.