Free Vibration Analysis of Accelerated Helicopter Rotor Blade

In this study, the structural model of a helicopter rotor blade which is made of isotropic material is built. The model consists of bending bending torsion coupled Euler Bernoulli beam that assumes pre-twist and precone. Firstly, kinetic and potential energy expressions are derived by applying the Euler-Bernoulli beam theory. Then, beam-like finite element model that has 5 degrees of freedom for both nodes is built up and vibrational properties of the rotor blade are inspected. Bo105 helicopter blade model is selected from the literature to be conducted free vibration study on. Free vibration analysis is carried out with the different rotational values from 0 to 100 rad/s which is the extension of the nominal working speed of helicopter rotor to validate the in-house structural code. Afterwards, different acceleration values are examined using the structural code to find its effects on the Bo105 helicopter rotor blade.