Mathematical Modeling and Stability Analysis of Tiltrotor Aircraft

• Published in: Drones (Basel) Vol. 6; no. 4; p. 92
• Main Authors: Sheng, Hanlin, Zhang, Chen, Xiang, Yulong
• Format: Journal Article
• Language: English
• Published: Basel MDPI AG 01.04.2022
• Subjects: Aerodynamics; Aircraft; Aircraft stability; Airframes; blade element theory; Blades; Center of gravity; Dynamic models; Flapping; flight mechanical model; flight simulation; Fluid dynamics; Fuselages; Kinematics; Mathematical analysis; Mathematical models; Moments of inertia; Parameter identification; Simulation; Stability analysis; Tilt rotor aircraft; tiltrotor; Velocity; Wings (aircraft)
• ISSN: 2504-446X; 2504-446X
• DOI: 10.3390/drones6040092

The key problem in the development process of a tiltrotor is its mathematical modeling. Regarding that, this paper proposes a dividing modeling method which divides a tiltrotor into five parts (rotor, wing, fuselage, horizontal tail, and vertical fin) and to develop aerodynamic models for each of them. In that way, force and moment generated by each part are obtained. Then by blade element theory, we develop the rotor’s dynamic model and rotor flapping angle expression; by mature lifting line theory, the build dynamic models of the wings, fuselage, horizontal tail and vertical fin and the rotors’ dynamic interference on wings, as well as nacelle tilt’s variation against center of gravity and moment of inertia, are taken into account. In MATLAB/Simulink simulation environment, a non-linear tiltrotor simulation model is built, Trim command is applied to trim the tiltrotor, and the XV-15 tiltrotor is taken as an example to validate rationality of the model developed. In the end, the non-linear simulation model is linearized to obtain a state-space matrix, and thus the stability analysis of the tiltrotor is performed.