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《中国工程科学》 >> 2011年 第13卷 第3期

V/STOL飞机建模与仿真分析

1. 清华大学计算机科学与技术系,北京 100084;

2. 海军装备研究院,北京 100161

资助项目 :国家863计划项目(2008AAJ114,2008AAJ201);国家自然科学基金项目(60974142,U0970112) 收稿日期: 2009-12-25 发布日期: 2011-03-17 11:26:00.000

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摘要

以原理验证机为背景,建立了无尾布局垂直/短距起降飞行器的数学模型,并通过智能自适应方法对其进行了闭环飞行控制,控制量通过控制分配合理的协调各操纵面,最后在MATLAB7.0/Simulink环境下通过数值仿真进行了验证。结果显示,该平台具备垂直/短距起降能力和较好的飞行性能。

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参考文献

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[ 5 ] 王健.先进短距起飞垂直着陆飞机的非线性动态逆控制[D].南京:南京航空航天大学,2000.

[ 6 ] Joseph S, Brinker, Kevin A, et al.Reconfigurable flight control for a tailless advanced fighter aircraft[ J] .AIAA Guidance, Navi- gation and Control Conference and Exhibit, 1998 ,( 8 ) :10 -12. 链接1

[ 7 ] Joseph S,Brinker, Kevin A, et al.Nonlinear simulation analysis of a tailless advanced fighter aircraft reconfigurable flight control law[ J] .AIAA Guidance, Navigation and Control Conference and Exhibit, 1999 ,( 8 ) :9 -11. 链接1

[ 8 ] Calise A J,Lee S,Sharma M.Direct adaptive reconfigurable con- trol of a tailless fighter aircraft [ J] .AIAA Guidance, Navigation and Control Conference and Exhibit, 1998 ,( 8 ) :10 -12. 链接1

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[10] Bodson M.Evaluation of optimization method for control alloca- tion [ J] .Journal of Guidance, 2002 , 25 ( 4 ) : 703 -711. 链接1

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