Abstract
A coupled rotor/airframe vibration analysis is performed by the matching of rotor and fuselage impedances. The rotor impedance for b blades is calculated from the periodic-coefficient equations of a single blade in forward flight. Three flapping modes are included, and the equation is solved by harmonic balance. The fuselage impedance, including structural damping, is calculated for 3 rigid-body and 3 elastic modes in plunge, roll, and pitch. The results show that the effect of hub motions on rotor loads is greatest for relatively stiff rotors, and is not well approximated by lumped-mass or purely inertial rotor models.
| Original language | English |
|---|---|
| Pages (from-to) | 25-34 |
| Number of pages | 10 |
| Journal | Journal of the American Helicopter Society |
| Volume | 27 |
| Issue number | 1 |
| DOIs | |
| State | Published - 1982 |