Perpustakaan Digital ITB

Ever growing criminal action and military interest have pushed the increased demand on Micro Aerial Vehicle having capability to conduct espionage mission. This MAV should not make the enemy aware of its presence earlier before it finished the mission. Camouflage is one of the alternatives to carry out the mission, but there is always challenge to mimicking nature. Flapping wing is a great idea by which researcher and engineers ever implemented this concept on MAV. This also push author to conduct a research on aerodynamic design and analysis for flapping wing. Pigeon bird wing has been chosen as a research model due to its size and flight speed. Analytical calculation and CFD simulation approaches are used to design kinematics of flapping wing with requirement of simple model, be able mimicking the Pigeon bird flapping. The assumption used in design and analysis is straight level flight condition, simple rectangular and rigid wing. This research starts with the design of kinematic of flapping wing including the determination of flapping path, attitude, size of each part and target of lift and thrust. Each length of the crank segment will decided first and then kinematics equation is obtained. The simulation using computational fluid dynamics is conducted to obtained instantaneous aerodynamic forces and moment of the wings for various parameters of flapping including flapping frequency, free-stream velocity, pitching and aerofoil type using the solution of Reynold Averaged Navier-Stokes equation. Behavioural of those physical parameters within simulation case variations is being discussed to determine the final configuration. It comes out that all of them are significantly affecting the lift and thrust production. Finally, maximum weight during flight and motor requirement are obtained for further development and UAV testing.