Vibration Analysis of Remote Controlled Helicopter Composite Rotor Blade Through Fast Fourier Transform (Fft) Analysis

The vibrations (resonance phenomenon) in the remote-controlled (RC) helicopter rotor blade, as it is the major cause of failure. In this research, modal analysis is performed on an RC helicopter rotor blade with unidirectional epoxy carbon, titanium alloy, aluminium alloy, and high strength low alloy steel (HSLA). The initial frequency of the unidirectional epoxy carbon material is highest among the other materials, so for manufacturing and experimental testing unidirectional epoxy carbon material is preferred. The rotor blade is manufactured through hand lay-up method and impact hammer test with Fast Fourier Transform (FFT) is performed as experimental testing. The initial frequency prevailed in modal analysis for the unidirectional epoxy carbon is 53.196 Hz, while the initial frequency obtained in the impact hammer test is 58.59 Hz. It is discovered that there is good agreement in the modal analysis and the experimental analysis.