飞机直接侧力控制律设计  

Aircraft Direct Side Force Control Law Design

作　　者：王建培[1] 王忠俊[1] 

机构地区：[1]西北工业大学,陕西西安710072

出　　处：《空气动力学学报》1993年第1期33-41,共9页Acta Aerodynamica Sinica

摘　　要：采用直接侧力控制可消除常规飞机在航迹操纵方面的不足,并产生某些新的运动模式,这对横航向运动优点更为突出。文中首先对飞机直接侧力控制的三种基本运动模式进行了分析。然后简述了用特征结构配置和模型跟踪技术计算反馈和前馈增益以设计输出解耦控制系统的主要步骤。最后以CitattonⅡ型飞机为算例,设计了其直接侧力控制律。计算结果是令人满意的,说明所采用的原理和方法对直接侧力控制律的设计是行之有效的。The disadvanteages of normal aircraft to realize flight path control could be overcome by using direct side force control, and some new motion modes could be created, especially for aircraft directional-lateral motion. The three principle motion modes of direct side force control are analysed first, then the main steps of how to use the eigen-structure assignment and model following technique to calculate the feedback and feedforward gain to design an output decoupling control system are summarized. Finally, using aircraft CitationII as an example, the direct side force control law are designed. The computation results are satisfactory, and it shows that the design method and steps used in the paper are effective for direct side force control lav/ design.

关 键 词：直接侧力控制 模型跟踪 输出解耦 

分 类 号：V212.11[航空宇航科学与技术—航空宇航推进理论与工程]