Abstract:
This project presents the Conceptual Design of Flapping Wing L.A.V. Starting from a set of initial design specifications namely: weight, maximum flapping frequency and maximum and minimum velocity of the model. The model -aerodynamic surfaces and internal structure- was drawn using CATIA software. Then the aerodynamic forces were estimated analytically and with C.F.D methods for pure flapping motion.
Structure analysis was made through ANSYS software for the main components. The flapping mechanism was made and drawn depending on the movement angles to create enough lift and thrust resulted from C.F.D analysis.
The results of these analysis showed that: The maximum positive lift is created during down stroke phase, and vice versa the maximum negative lift is created during upstroke phase and Due to suitable and perfect material selection, there was no any redounded deformation in the structure and it can handle with the maximum load applied on it. These results prove that our model is able to generate required lift and thrust to fly without any failure.
During structure analysis with wing skin there was a problem of skweens being equal to one and this is not acceptable. This problem was solved by analyze the wing without skin.
