航空学报 > 1992, Vol. 13 Issue (6): 241-248

特征结构配置在设计直接升力控制律中的应用

王建培, 王忠俊   

  1. 西北工业大学503教研室 西安 710072
  • 收稿日期:1991-05-01 修回日期:1991-09-01 出版日期:1992-06-25 发布日期:1992-06-25

APPLICATION OF EIGENSTRUCTURE ASSIGNMENT TO DESIGN DIRECT LIFT CONTROL LAW

Wang Jian-pei, Wang Zhong-jun   

  1. Faculty 503, Northwestern Polytechnical University
  • Received:1991-05-01 Revised:1991-09-01 Online:1992-06-25 Published:1992-06-25

摘要: 采用直接力控制可弥补常规飞机在轨迹操纵方面的不足,并产生某些新的运动模式。文中首先对飞机直接升力控制的3种基本运动模式进行了讨论。归纳出直接升力控制律的设计就是输出解耦控制系统的设计问题。在简述了用特征结构配置和模型跟踪技术求算反馈和前馈增益阵的主要步骤之后,以CitationⅡ型飞机为算例,设计了其直接升力控制律。计算结果是令人满意的,说明特征结构配置是一种设计飞行控制系统的有效方法。

关键词: 直接升力控制, 输出解耦, 特征结构配置, 模型跟踪

Abstract: The disadvantages of normal aircraft to realize flight path control can be overcome by using direct force control, and some new motion modes can be created. The three principal motion of direct lift control are discussed first, and the direct lift control law design which is a problem of output decoupling is summed up. The main steps of how to use the eigenstructure assignment and model following technique to calculate the feedback and feedforward gain are explained. By using aircraft Citation Ⅱ as an example, the direct lift control law is designed. The computation results are satisfactory, showing that the eigenstructure assignment method is an effective tool for flight control system design.

Key words: direct lift control, output decoupling, eigenstructure assignment, model following