The tail rotor of a helicopter has a mass of MR =60 kg, including a rotating unbalance of me=0.075 kgm. The tail section has a length of 4 m, has a mass of MT = 600 kg, and can be simulated as a cantilever beam with an approximate constant circular cross-sectional area of diameter=200 mm, made of aluminum (E=73 GPa). The tail has a damping mechanism not shown that provides a damping coefficient of $\zeta$ =0.15
Determine the force transmitted to the base of the tail section when the blades rotate at 1600 rpm.
Hint: Model the tail section as a cantilever beam of mass MT with an end mass MR, the Area moment of Inertia of a circular rod is I=(1/4) $\pi$R^4
295.4 N
230.9 N
197.7 N
178.3 N