Frequency-domain methods are used to identify the open-loop dynamics of the XV-15 tilt-rotor aircrafl from flight tests. Piloting and data analysis techniques are presented to determine frequency response plots and equivalent transfer funclion models. The open-loop pitch and roll dynamics for the hover flight condition exhibit unstable low-frequency oscillations, whereas the dynamics in the remaining degrees of freedom are lighlly damped and generally decoupled. Comparisons of XV-15 flight-test and simulator data are more favorable for high-frequency inpuls (o>1.0 rad/sec) lhsn low-frequency inpuls. Time-domain comparisons of the extracted lransfer funclions with step response flight data are very favorable, even for large amplitude motions. The results presented in this peper demonstrate the utility of the frequency-domain techniques for dynamics identification and simulator fidelilv studies.
Notation6. , 6, , 6, az =vertical acceleration, uositive downward, g's f =discrete frequency, an =transfer function {P, rr ~, V )~G u~Y )~G , v~) =input, output, and cross-spectral functions Wp.% Lan =aileron roll sensitivi l / deg-aileron T~,~~, T~, T + L Mae =elevator pitch senslnvlry, ueg/ sec2/dea-elevator =aileron surface deflection (deg), elevator surface deflection (deg), and rudder surface deflection (deg), respectively =pitch and roll mode damping ratios, respectively =pitch and roll mode natural frequencies, respectively =heave, pitch, roll, and yaw transfer function time delays, sec -P. 4. r =roll rate, pitch rate, and yaw rate, respectively, deg/sec