RLV再入结构化鲁棒控制器设计
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摘要
RLV再入飞行动态快速时变,强耦合与非线性严重,为此在非线性动态逆控制的基础上,提出了一种结构化的鲁棒控制器设计方法。根据RLV再入飞行动态,建立了其姿态控制仿射非线性模型。基于时标分离原理应用NDI方法进行了RLV控制结构的线性化,克服了小扰动线性化损失飞行器动态信息的缺点。根据RLV再入控制性能指标要求引入优化的思想,采用鲁棒优化方法实现对性能指标与干扰抑制能力的折衷。所设计的结构化鲁棒控制器能有效实现对RLV再入姿态的控制,并具有抗干扰能力,克服了NDI方法对模型的依赖性。
The flight dynamics of RLV reentry is fast time-varying,strongly coupled and seriously nonlinear. A structured robust controller was designed for RLV reentry attitude control. According to RLV reentry flight dynamics,the attitude control affine nonlinear model was established. Standard NDI method was applied to design the dual-loop control structure based on time-scale separation principle,overcoming the disadvantage of losing dynamic information compared with small perturbation linearization method. The robust optimization was adopted in the dual-loop control structure to compromise the performance index and the interference suppression ability. The proposed structured robust controller reduces the dependence on strict model of NDI. The simulation results show that the structured robust controller can effectively control the RLV reentry attitude and have anti-interference ability.
The flight dynamics of RLV reentry is fast time-varying,strongly coupled and seriously nonlinear. A structured robust controller was designed for RLV reentry attitude control. According to RLV reentry flight dynamics,the attitude control affine nonlinear model was established. Standard NDI method was applied to design the dual-loop control structure based on time-scale separation principle,overcoming the disadvantage of losing dynamic information compared with small perturbation linearization method. The robust optimization was adopted in the dual-loop control structure to compromise the performance index and the interference suppression ability. The proposed structured robust controller reduces the dependence on strict model of NDI. The simulation results show that the structured robust controller can effectively control the RLV reentry attitude and have anti-interference ability.
引文
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[6]余光学,李昭莹,林平.可重复使用运载器再入数学建模研究[J].中国空间科学技术,2014,34(3):23-31.
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[2]包为民.航天飞行器控制技术研究现状与发展趋势[J].自动化学报,2013,39(6):697-702.
[3]Z T Dydek,A M Annaswamy,E Lavretsky.Adaptive Control and the NASA X-15-3 Flight Revisited[J].IEEE Control Systems Magazie,2010,30(3):32-48.
[4]周克敏.鲁棒与最优控制[M].北京:国防工业出版社,2006.
[5]P Apkarian and D Noll.Nonsmooth H-infinity Synthesis[J].IEEE Transactions on Automatic Control,2006 51(1):71-86.
[6]余光学,李昭莹,林平.可重复使用运载器再入数学建模研究[J].中国空间科学技术,2014,34(3):23-31.
[7]Subbaram D Naidu,Anthony J Calise.Singular Perturbations and Time Scales in Guidance and Control of Aerospace Systems:A Survey[J].Journal of Guidance,Control,and Dynamics,2001,24(6):1057-1070.
[8]D Ito,J Georgie,J Valasek,and D T Ward.Re-entry Vehicle Flight Controls Designs Guielines:Dynamic Inversion[R].NASA report,2002:NASA/TP 2002-210771.