Deterministic global optimization of flapping wing motion for micro air vehicles

The kinematics of a flapping plate are optimized by combining the unsteady vortex lattice method with a deterministic global optimization algorithm. A constraint to keep the lift from taking large negative values at anytime is also imposed by following a penalty function approach. The design parameters are the amplitudes, mean values, frequencies, and phase angles of the flapping motion. The results suggest that imposing a delay between the different oscillatory motions and controlling the way through which the wing rotates at the end of each half stroke would enhance the lift generation. The use of a general unsteady numerical aerodynamic model and the implementation of a deterministic global optimization algorithm provide guidance and a baseline for future efforts to identify optimal stroke trajectories for micro air vehicles with higher fidelity models.