Publication Type : Conference Proceedings
Publisher : 6th Symposium on Applied Aerodynamics and Design of Aerospace Vehicles (SAROD 2013)
Source : 6th Symposium on Applied Aerodynamics and Design of Aerospace Vehicles (SAROD 2013), Hyderabad (2014)
Url : https://www.researchgate.net/publication/297715807_Design_and_Development_of_Flapping_Wing_MAV
Campus : Coimbatore
School : Department of Aerospace Engineering, School of Engineering
Department : Aerospace
Verified : Yes
Year : 2014
Abstract : A flapping wing MAV (FMAV) named KAVAS was made in which the potential energy stored in a rubber band was converted to kinetic energy (mechanical) using a simple 4-bar mechanism. Rubber bands of three kinds - conventional, light weight elastic and heavy were used along with along with ice cream sticks, balsa wood, mild steel wire, beads, carbon fiber and tissue paper for fabrication. A parametric study on flapping mechanism gave the relationship between the flapping frequency and the frequency provided by the rubber band to the crank. The flapping frequency of the wing during flight was measured to be 6.15Hz. It was estimated that 25% of the rubber band energy was used and that the forward velocity of the model was experimentally found to be 2.8m/s. The figure of 8 trajectory followed by the wingtip was revealed, demonstrating the flexibility of the wing. The aerodynamic parameters of the final model were evaluated using the DeLaurier’s strip theory with a modification to account for the relatively high maximum flap angle of greater than 20 degrees. It was theoretically predicted that the dynamic twist should be 3 degrees/cm and the angle between flapping axis and the free stream should be 9 degrees to produce the required thrust and lift. Based on this, instantaneous lift and thrust over a cycle were plotted. Effects of using different wing and tail material were also studied.
Cite this Research Publication : Rajesh Senthil Kumar T., R. Narayan, A., S. Girish, S., Sarath, M. R., and Ananthakrishnan, V., “Design and Development of Flapping Wing MAV”, 6th Symposium on Applied Aerodynamics and Design of Aerospace Vehicles (SAROD 2013). Hyderabad, 2014.