| 歼击机纵向多模态控制规律设计方法初探 |
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| 引用本文： | 路精保.歼击机纵向多模态控制规律设计方法初探[J].航空学报,1986,7(4):405-411. |
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| 作者姓名： | 路精保 |
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| 作者单位： | 北京航空学院 |
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| 摘 要： | 一、问题的提出 多模态控制规律在现代飞行控制系统中得到广泛应用。由于采用多控制面控制飞机的机动运动,仅仅采用仿真的方法来选择控制律的参数是很困难的。在此,我们对AFTI/F-16飞机多模态飞行控制规律按已知控制律结构及基本设计思想进行设计,探索其主要通道的基本功能及参数选择方法,以便对其系统设计方法进行深入探讨和分析。
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| 收稿时间： | 1984-12-01; |
PRELIMINARY STUDY OF MULTI-MODE CONTROL LAWS DESIGN METHODS FOR FIGHTER'S LONGITUDINAL CONTROL |
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| Lu Jing Bao.PRELIMINARY STUDY OF MULTI-MODE CONTROL LAWS DESIGN METHODS FOR FIGHTER'S LONGITUDINAL CONTROL[J].Acta Aeronautica et Astronautica Sinica,1986,7(4):405-411. |
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| Authors: | Lu Jing Bao |
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| Institution: | Beijing Institute of Aeronautics and Astronautics |
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| Abstract: | This paper disccuses the methods of the optimal control systems design for fighter. The both pre-closed-loop method and open loop method are studied according to control law structures and functions which are required py different flight conditions and tasks. Some numeric examples are provided. The performance index with degree of stability a is used and precise steady decoupling is obtained. |
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