双涵道倾转垂直起降飞行器模型与系统研究

Double Tilting Ducted Aircraft Model and System Design

设计了一种新型的双涵道倾转垂直起降飞行器,采用双涵道动力降低了对起降场地的要求。通过双涵道倾转飞行器动力学分析,得到飞行器在不同飞行姿态时的运动状态。飞控系统通过双闭环PID控制器控制电动涵道系统和伺服舵机系统,实现飞行器的姿态稳定。通过分析样机实验数据验证了双涵道倾转垂直起降飞行器设计的可行性。

A novel dual tilting ducted VTOL aircraft is designed, dual ducted power applied lowers the landing site requirements. By analyzing double-ducted tilting vehicle dynamics, aircraft motions at different flight attitude are obtained. The electric ducted systems and servo steering system are controlled by flight control system using the double-loop PID controller to realize aircraft attitude stability. The feasibility of double tilting ducted VTOL prototype design is validated by analyzing experimental data.