全部 标题 作者
关键词 摘要

OALib Journal期刊
ISSN: 2333-9721
费用:99美元

查看量下载量

相关文章

更多...
弹道学报  2012 

临近空间飞行器滑模控制中的指令参数化方法

Keywords: 临近空间飞行器,纵向模型,反馈线性化,滑模控制,指令参数化

Full-Text   Cite this paper   Add to My Lib

Abstract:

为了研究临近空间飞行器滑模控制方法,建立了临近空间飞行器无动力滑翔阶段的纵向运动模型,并应用动态逆方法证明模型是可逆的,且可实现绕质心运动模型的线性化.以动态逆控制为内环,滑模控制为外环,设计了飞行器纵向控制系统.从提高信息利用率和增加控制系统设计自由度的角度出发,提出俯仰角变化率指令参数化计算方法.仿真结果表明:纵向控制系统可以准确跟踪攻角指令,满足控制精度要求;俯仰角变化率指令参数主要影响控制系统的动态响应能力和稳态控制精度.

References

[1]  SNELL S A,ENNS D F,GARRARD L.Nonlinear inversion flight control for a super maneuverable aircraft[J].Journal of Guidance,Control,and Dynamics,1992,15(4):976-984.
[2]  KEUM W L,SUBRAMANIAN R,SAHJENDRA N S.Adaptive sliding mode 3?D trajectory control of F/A?18 model via SDU decomposition,AIAA 20086460[R].2008.
[3]  LI H F,SUN W C,LI Z Y,et al.Index approach law based sliding control for a hypersonic aircraft,AIAA 20091734[R]. 2009.
[4]  WANG Q,STENGEL R F.Robust nonlinear control of a hypersonic aircraft[J].Journal of Guidance,Control,and Dynamics,2000,23(4):577-585.
[5]  刘燕斌,陆宇平.非线性动态逆控制在高超飞控系统中的应用[J].应用科学学报,2006,24(6):613-617.LIU Yan?bin,LU Yu?ping.Application of nonlinear dynamic inversion control in flight control of hypersonic vehicle[J].Journal of Application Sciences,2006,24(6):613-617.(in Chinese)
[6]  LEE H P,REIMAN S E,DILLON C H.Robust nonlinear dynamic inversion control for a hypersonic cruise vehicle,AIAA 20076685[R].2007.
[7]  XU H J,MIRMIRANI M D,IOANNOU P A.Adaptive sliding mode control design for a hypersonic flight vehicle[J].Journal of Guidance,Control and Dynamics,2004,27(5):829-838.
[8]  刘金琨,孙富春.滑模变结构控制理论及其算法研究与进展[J].控制理论与应用,2007,24(3):407-418.LIU Jin?kun,SUN Fu?chun.Research and development on theory and algorithms of sliding mode control[J].Control Theory & Applications,2007,24(3):407-418.(in Chinese)
[9]  戴先中.多变量非线性系统的神经网络逆控制方法[M].北京:科学出版社,2005.DAI Xian?zhong.Neural network inverse control method for multivariable nonlinear system[M].Beijing:Science Press,2005.(in Chinese)
[10]  刘燕斌,陆宇平.基于变结构理论的高超音速飞机纵向逆飞行控制[J].信息与控制,2006,35(3):388-392.LIU Yan?bin,LU Yu?ping.Longitudinal inversion flight control based on variable structure theory for hypersonic vehicle[J].Information and Control,2006,35(3):388-392.(in Chinese)

Full-Text

Contact Us

service@oalib.com

QQ:3279437679

WhatsApp +8615387084133