Development of VTOL Research Aircraft Supported by Ducted Fans

在这项研究中，一个实验的垂直起降飞机支持涵道风扇的发展。主要目的是进行有关技术问题的试验研究，如气动力问题、稳定性和操纵性问题、飞行控制系统设计等。为深入研究涵道风扇式垂直起落飞机，研制了一种由往复式发动机驱动的四个涵道风扇支持的遥控研究飞机和起重机型试验台等试验设备。自动飞行控制系统，帮助远程驾驶的目的是控制这些模型的姿态和高度。控制系统采用惯性导航系统和微波高度表作为传感器。控制风扇叶片桨距和发动机节气门的伺服电机用作致动器。利用奇异摄动法对未建模动力学的影响进行了理论分析。将鲁棒控制系统理论应用于数字飞行控制系统的设计。将理论分析结果与多种控制台架试验和自由飞试验结果进行了比较。通过大量的飞行试验，研究模型在悬停和低速飞行条件下实现了较好的姿态和高度自动稳定。

In this research an experimental VTOL aircraft supported by ducted fans is developed. Main purpose is the experimental studies conceming the technical issues such as aerodynamic problem, stability and control problem, design of flight control system, etc.. A remotely piloted research aircraft supported by four ducted fans driven by a reciprocal engine and the test facilities such as crane type test stand are developed for the purpose of detailed investigation of ducted fan type VTOL aircrafts. Automatic flight control systems which aid remote piloting are designed to control the attitude and altitude of these models. The control system uses an inertial navigation system and a micro-wave altimeter as sensors. The servo motors to control fan blade pitch and engine throttle are used as actuators. The effect of unmodeled dynamics is analyzed theoretically by using singular perturbation method. Theory of robust control system is applied for the design of digital flight control system. The results of theoretical analysis are compared with the experimental results obtained by many kinds of control tests on test stand and free flight tests. As the result of a lot of flight tests, fairly well automatic stabilization of attitude and altitude of the research model was achieved in hovering and low speed flight condition.