Steady state structural analysis of Quad copter arm using finite element methods 

A Quad-copter, also called as rotor-craft that is lifted and propelled by four rotors. Quad-copters are classified as rotorcraft, as opposed to fixed-wing aircraft, because their lift is generated by set of rotors. Basically a quad-copter uses two sets of identical pitch propellers, two clockwise and two counter-clockwise. The rotors use different of RPM to control lift and torque. Control of flight motion is achieved by altering the RPM of one or more rotor, thereby changing its torque load and lift properties. In this design structural analysis has undertaken to determine the maximum displacement & bending stress produced in one arm only. This CAE analysis has done by considering; the part is made of ABS materials & having cantilever boundary condition.