International Journal of Aerospace Engineering / 2019 / Article / Tab 2

Research Article

Flight Dynamics Modeling and Dynamic Stability Analysis of Tilt-Rotor Aircraft

Table 2

Hover mode eigenvalue validation.

Hover modeNatural modeCalculatedReference[20]Flight test

Pitch subsidence-1.0-0.5979-1.32
Heave subsidence-0.17-0.2086-0.105
LateralDutch roll
Spiral subsidence-0.1609-0.0728-0.102
Roll subsidence-2.6539−1.1247-1.23

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