Determine the steady–state amplitude of vibration if one of the blades in Figure P4.30 snaps off during flight.

Refer to the following situation: The tail rotor section of the helicopter of Figure P4.30 consists of four blades, each of mass \(2.1 \mathrm{~kg}\), and an engine box of mass \(25 \mathrm{~kg}\). The center of gravity of each blade is \(170 \mathrm{~mm}\) from the rotational axis. The tail section is connected to the main body of the helicopter by an elastic structure. The natural frequency of the tail section has been observed as \(150 \mathrm{rad} / \mathrm{s}\). During flight the rotor operates at \(900 \mathrm{rpm}\). Assume the system has a damping ratio of 0.05 .

Transcribed Image Text:

FIGURE P4.30