摘要
扇翼飞行器是近年来发展起来的一种新型大载荷低速飞行器,在机翼上安装风扇吹气装置,将升力和推力结合起来,大大提高了飞行器的飞行效率,在民用和军事上都具有很高的应用价值.以某型扇翼飞行器为研究对象,在分析其结构特点和飞行原理的基础上,建立扇翼飞行器的纵向数学模型;并采用计算流体力学工具FLUENT模拟风洞试验确定数学模型中的各个参数,分析了自然飞机的系统性能;建立起的纵向模型为控制对象,采用易于工程实现的PID算法,并在Matlab下对控制律进行仿真实验,仿真结果表明了该控制律的有效性.
In recent years, the fanwing aircraft has been developed as a new large-load and low--speed aircraft. A fan blowing device is fixed to the fixed-wing to combine lift and thrust, which can achieve more efficiency. As a new unmanned aircraft to serve military and civilian markets, the fawning aircraft has a broad prospect. A certain type of fanwing aircraft was studied based on its structure characteristics and operating principle. A longitudinal mathematical model was built And the model parameters were determined by the CFD software FLUENT to analyze the system performance of a natural aircraft. Finally, an easily realized PID control law is designed for the longitudinal mathematical model. Effectiveness of the control law was verified via a Matlab Simulink program.
出处
《应用科技》
CAS
2011年第11期5-8,53,共5页
Applied Science and Technology
基金
国家自然科学基金资助项目(60674100)
