Volume 39, Number 3, June 2021
|Page(s)||675 - 684|
|Published online||09 August 2021|
Analysis on controllability and stability of quad-tilt-rotor aircraft in helicopter mode
The controllability and stability of quad-tilt-rotor aircraft in helicopter mode are modeled and analyzed, which will provide a theoretical guidance for the subsequent control system design. First of all, the flight dynamics model is established considering rotor-wing interference and verified with relevant experiments. Then, a control strategy for helicopter mode is proposed with trim characteristic analysis. Finally, corresponding control efficiency and cross coupling are calculated and analyzed along with characteristics of the stability derivatives and eigenvalues. The results show that the value of heading control efficiency is much smaller than that of other channels. The longitudinal force and pitch moment caused by vertical control input increase with the increase of the velocity. Yawing moment caused by lateral control input shows similar variations. The velocity stability becomes worse with the increase of the velocity. The stability of all other modes is augmented as velocity increases except the spiral mode.
Key words: quad-tilt-rotor / flight dynamics model / trim / control strategy / controllability / stability
关键字 : 倾转四旋翼飞行器 / 飞行动力学模型 / 配平 / 操纵策略 / 操纵性 / 稳定性
© 2021 Journal of Northwestern Polytechnical University. All rights reserved.
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