Abstract
To study the influence of rotation speed and rotor diameter on the control characteristics and flight performance of a tilt-rotor aircraft, a flight dynamics model and a required power calculation model of the tilt-rotor were established. Trim analysis was carried out under three typical flight modes, and the change of the required power was further analyzed. The results showed that as the rotor speed/diameter increased, the collective pitch and cyclic pitch of the rotor and the pitching angle of the fuselage decreased, and the deflection angle of the elevator increased. As the rotor speed increased, the required power of the tilt-rotor aircraft increased. In helicopter mode, the required power decreased with increasing rotor diameter, while in fixed-wing mode, the required power increased with increasing rotor diameter.
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Acknowledgements
This work is supported by the National Key Laboratory Foundation of China (no. 61422200101), the National Natural Science Foundation of China (nos. 12102186, 11872211), the Natural Science Foundation of Jiangsu Province (no. BK20200433), as well as the Priority Academic Program Development of Jiangsu Higher Education Institutions.
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Wu, R., Zhang, X., Zhao, Q., Wang, B. (2023). Flight Dynamics Modeling and Flight Performance Analysis of Variable Rotor Speed and Variable Diameter of Tilt-Rotor Aircraft. In: Lee, S., Han, C., Choi, JY., Kim, S., Kim, J.H. (eds) The Proceedings of the 2021 Asia-Pacific International Symposium on Aerospace Technology (APISAT 2021), Volume 2. APISAT 2021. Lecture Notes in Electrical Engineering, vol 913. Springer, Singapore. https://doi.org/10.1007/978-981-19-2635-8_61
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DOI: https://doi.org/10.1007/978-981-19-2635-8_61
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