Abstract
The conversion mode in tiltrotor aircraft is of paramount importance and complexity, necessitating the trim results to ensure stable tilting using the trim model. Quick trim modeling is conducted for tiltrotor aircraft in conversion mode, focusing on the aerodynamics of the rotor using modified lift line theory. Furthermore, we develop the nonlinear flight dynamics of tilt-rotor aircraft. Based on this aircraft model, a double-layer cycle iterations method is employed to establish an efficient and rapid trim model for the tiltrotor in conversion mode at any tilt angle or during any aerial maneuver. Using Boeing Model 222 as an example, trim results for conversion mode are calculated and compared with reference data to validate the effectiveness and precision of our model.
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