Theoretical Design of Coaxial Rotor Micro Air Vehicle

In recent years, there has been rapid development of autonomous unmanned aircraft equipped with autonomous control devices called unmanned aerial vehicles (UAVs) and micro aerial vehicles (MAVs). These have become known as “robotic aircraft,” and their use has become wide spread. They can be classified according to their application for military or civil use. There has been remarkable development of UAVs and MAVs for military use. However, it can be said that the infinite possibilities of utilizing their outstanding characteristics for civil applications remain hidden. In this paper detailed design procedure for designing a micro air vehicle weighing from 20 gram to 500 gram is presented. Using such design procedure for pay load capacity of 10 grams is design. Different parameters like rotor blade length, length of stabilizer bar, length of fuselage, total length of body, totalpower required is find out. To check feasibility of vehicle in hover condition checking parameters like thrust force, lift force, centrifugal force are find out.