Micro Aerial Vehicle, Flapping Wing, Genetic Algorithm, Optimization, Force Measurement, Flow Visualization, Hovering Flight.

• Main Author: Satria Palar, Pramudita
• Format: Theses
• Language: Indonesia
• Subjects: Teknik (Rekayasa, enjinering dan kegiatan berkaitan)
• Online Access: https://digilib.itb.ac.id/gdl/view/38896
• Institution: Institut Teknologi Bandung

The development of Micro Aerial Vehicles (MAV) is driven by its potential use as a vehicle that can perform remote observation in hazardous environment. Because of the operational Reynolds number of MAV is low, flapping wing type MAV is supposed to be superior to other types. Currently, there are no operational flapping MAVs available. The main reason for this is the lack of understanding of flapping aerodynamics. This present work is mainly concerned about the development and application of Micro Genetic Algorithm (MGA) as a special type of Genetic Algorithm (GA) to optimize the trajectory of flapping wing motion experimentally. To speed up the search process, a hybridization of genetic algorithm with Hooke Jeeves pattern search method is employed. The purpose of the optimization is to see a better link between optimal trajectory, force generation, and complex fluid dynamic around flapping motion. Flow visualization was done using time-exposure technique via digital camera. By using this technique, instantaneous velocity of flow field can be revealed and qualitative analysis can be done. On downstroke phase, large force should be generated by performing the translation motion with high angle of attack. This high angle of attack translation create large leading edge vortex that keeps attached on the plate until it reaches a distance where this vortex finally sheds. Attachment of this large vortex at downstroke phase provides large drag force production for the plate. Rotational circulation and wake capture plays significant role in force production at rotation phase where the degree of importance for both mechanisms is almost the same for asymmetric flapping flight. At the upstroke phase, the optimal solution moves with low angle of attack and generates smaller drag force compared to the downstroke phase. However, the upstroke phase should be performed with not extreme low angle of attack to still maintain force production at upstroke phase but consumes low profile power. Another interesting phenomenon is discovered here where vortex sheds from previous stroke of half stroke affect the flow field around the plate and force generation. Optimal solution is able to gain the advantage of this shedding vortex and produces more drag forces in upstroke phase compared to the sub-optimal solution.