纵置双涵道式飞行器悬停控制系统设计  

Design of Control System for Hover of Longitudinal Double Ducted-Fan Aircraft

作　　者：李明喜[1,2] 项昌乐[1] 徐彬[1] 苑卫松[1] 智晋宁[1] 

机构地区：[1]北京理工大学机械与车辆学院,北京100081 [2]军事交通学院汽车工程系,天津300161

出　　处：《控制工程》2011年第4期520-523,538,共5页Control Engineering of China

基　　金：国际预研支撑项目:多域机动平台研制(404010602)

摘　　要：涵道风扇较同样直径的螺旋桨能产生更大的升力,且结构紧凑、安全性高、噪音低。以此为推力装置的可垂直起降飞行器具有良好发展前景。但其系统动力学特性是属于多变量、强耦合的非线性系统,在控制系统的设计中必须进行良好的解耦设计。纵置双涵道式飞行器的飞行控制系统的控制特征进行了分析,建立基本的控制系统动力学模型,利用模型跟踪解耦自适应控制系统原理进行飞行控制系统设计,并在多域机动平台上完成了验证试验,结果证明该方法有效地减小了轴间耦合,飞行器悬停状态基本稳定。The design problem of the ducted fan propeller with compact structure,high safety,low noise is dealt with,which can provide more power than common propeller.The thrust ducted fan VTOL aircraft has good prospects for development.To the problem that,the ducted fan system dynamics are multi-variables,and strongly coupled nonlinearity,the control system decoupled design process is presented the Longitudinal double ducted-fan aircraft flight control system characteristics are analyzed to establish the basic control system model,by using the model tracking adaptive decoupling the design control principle.The testing result shows the effectiveness in reducing the coupling between axes and the stability of the hover system.

关 键 词：涵道风扇 飞行控制系统 试验 

分 类 号：TP273[自动化与计算机技术—检测技术与自动化装置]