基于微分器的轨迹线性化控制方法及其应用

邵星灵; 王宏伦; 张惠平; 张晓峰

doi:10.13700/j.bh.1001-5965.2014.0544

基于微分器的轨迹线性化控制方法及其应用

doi: 10.13700/j.bh.1001-5965.2014.0544

邵星灵^1,2,
王宏伦^1,2, ,,
张惠平³,
张晓峰^1,2

1.
北京航空航天大学自动化科学与电气工程学院, 北京 100191
2. 北京航空航天大学飞行器控制一体化技术重点实验室, 北京 100191
3. 北京航天自动控制研究所, 北京 100854

基金项目: 国家自然科学基金(61175084); 长江学者和创新团队发展计划(IRT 13004); 航空科学基金(2014ZA51002)

详细信息

作者简介:
邵星灵(1988—),男,江苏扬州人,博士研究生,huanying3557913@sina.com

通讯作者:
王宏伦(1970—),男,陕西蓝田人,教授,hl_wang_2002@126.com,主要研究方向为无人机自主飞行控制、管理与决策.

中图分类号: TP249.1
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- 被引次数: 0
出版历程
- 收稿日期: 2014-09-05
- 修回日期: 2014-10-17
- 刊出日期: 2015-07-20

Control method and applications of robust trajectory linearization via nonlinear differentiators

1.
School of Automation Science and Electrical Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China
2. Science and Technology on Aircraft Control Laboratory, Beijing University of Aeronautics and Astronautics, Beijing 100191, China
3. Beijing Aerospace Automatic Control Institute, Beijing 100854, China

摘要

摘要: 针对当前轨迹线性化控制(TLC)方法对系统中的不确定性存在鲁棒性不足的问题,受非线性跟踪微分器设计思路的启发,提出了一种基于微分器设计原则的轨迹线性化控制方法.首先,引入二阶线性微分器(SOLD)的概念,通过理论分析指出了当前轨迹线性化控制方法中采用一阶惯性+伪微分器求取标称指令的微分信号时,会存在与二阶线性微分器类似的峰值现象,随后利用韩式跟踪微分器(TD)求取标称指令及其微分信号,避免了该现象的同时又赋予了系统在控制量的约束范围内调节响应快慢的能力;其次,通过构造期望的闭环系统,跟踪误差动态,直接获取线性时变(LTV)系统的控制量, 使得参数整定不再依赖于并行微分(PD)谱理论,在此基础上,将混合微分器(HD)的非摄动形式等价为期望的闭环系统跟踪误差动态,以提升轨迹线性化控制方法的鲁棒性,同时借助Lyapunov稳定性理论证明了受扰系统的跟踪误差最终一致有界;最后,利用所提出的轨迹线性化控制方法设计了高超声速飞行器的姿控系统并进行了相应的仿真.结果表明:存在大范围气动参数摄动的情况下,本方法仍具有较好的控制性能及抗干扰能力,能够满足高超声速飞行器快时变、高精度以及强鲁棒的控制需求.
- 轨迹线性化控制方法 /
- 二阶线性微分器 /
- 非线性跟踪微分器 /
- 混合微分器 /
- 高超声速飞行器
Abstract: Considering the lack of enough robustness against uncertainties in conventional trajectory linearization control (TLC) method, an improved robust control method was proposed, based on the design principle of nonlinear differentiators. Firstly, via introducing the concept of second-order linear differentiator (SOLD), it was indicated that peaking phenomenon which was similar with using high-gains in SOLD would emerge during the transient profile of differentiation of the nominal command in the existing TLC. And then, tracking differentiator (TD) was used to produce the nominal command and its derivative, peaking phenomenon was totally eliminated and the ability of adjusting the response speed of closed-loop system under the physical limitations was endowed simultaneously. Secondly, by constructing the desired tracking error dynamics of closed-loop system, the control law of the linear time-varying (LTV) system could be directly obtained, PD-spectrum theorem and real time tuning of the time varying bandwidth (TVB) of TLC were both avoided. Meanwhile, by utilizing the non-perturbation form of hybrid differentiator (HD) as the desired error dynamics of closed-loop system, the robustness of the system was thus enhanced. In addition, the boundedness of the tracking error in interference system was proved by Lyapunov theory. Finally, the proposed method was applied to the attitude tracking problem of hypersonic vehicle. The simulation results demonstrate the proposed method can still exhibit better control performance and anti-interference capability even if there exist large uncertainties in the aerodynamic parameters, thus the effectiveness and robustness of the control scheme is validated.
- trajectory linearization control method /
- second-order linear differentiator /
- nonlinear tracking differentiator /
- hybrid differentiator /
- hypersonic vehicle

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参考文献(18)

[1]	Zhu J J, Banker B D, Hall C E.X-33 ascent flight control design by trajectory linearization-a singular perturbation approach[C]// AIAA Guidance, Navigation and Control Conference.Reston: AIAA, 2000: 4159-4178.
[2]	Bevacqua T, Best E, Huizenga A, et al.Improved trajectory linearization flight controller for reusable launch vehicles[C]//AIAA Aerospace Sciences Meting and Exhibit.Reston: AIAA, 2004: 875-887.
[3]	Liu Y, Zhu J J, Robert L, et al.Omni-directional mobile robot controller based trajectory linearization[J].Robotics and Autonomous Systems, 2008, 56(5): 461-479.
[4]	Liu Y, Zhu J J. Regular perturbation analysis for trajectory linearization control[C]//Proceedings of the 2007 American Control Conference.Piscataway, NJ: IEEE Press, 2007: 3053-3058.
[5]	Liu Y, Huang R, Zhu J J.Adaptive neural network control based on trajectory linearization control[C]//The 6th World Congress on Intelligent Control and Automation.2006: 417-421.
[6]	朱亮, 姜长生, 陈海通, 等.基于单隐层神经网络的空天飞行器直接自适应轨迹线性化控制[J].宇航学报, 2006, 27(3): 338-344. Zhu L, Jiang C S, Chen H T, et al.Direct adaptive trajectory linearization control of aerospace vehicle using SHLNN[J].Journal of Astronautics, 2006, 27(3): 338-344(in Chinese).
[7]	朱亮, 姜长生, 薛雅莉.基于单隐层神经网络的空天飞行器鲁棒自适应轨迹线性化控制[J].兵工学报, 2008, 29(1): 52-56. Zhu L, Jiang C S, Xue Y L.Robust adaptive trajectory linearization control for aerospace vehicle using single hidden layer neutral networks[J].Acta Armamentarii, 2008, 29(1): 52-56(in Chinese).
[8]	薛雅丽, 姜长生, 朱亮. 一类径向基神经网络干扰观测器轨迹线性化控制[J].系统工程与电子技术, 2008, 19(4): 522-526. Xue Y L, Jiang C S, Zhu L.Trajectory linearization control of an aerospace vehicle based on RBF neutral network[J].Journal of Systems Engineering and Electronics, 2008, 19(4): 522-526(in Chinese).
[9]	Jiang C S, Zhang C Y, Zhu L.Research of robust adaptive trajectory linearization control based on T-S fuzzy system[J].Journal of Systems Engineering and Electronics, 2008, 19(3): 537-545.
[10]	韩京清, 袁露林. 跟踪-微分器的离散形式[J].系统科学与数学, 1999, 19(3): 268-273. Han J Q, Yuan L L.The discrete tracking differentiator[J].System Science and Mathematics, 1999, 19(3): 268-273(in Chinese).
[11]	Su Y X, Duan B Y, Zheng C H, et al.Disturbance-rejection high-precision motion control of a stewart platform[J].IEEE Transactions on Control Systems Technology, 2004, 12(3): 264-274.
[12]	王新华, 陈增强, 袁著祉.全程快速非线性跟踪-微分器[J].控制理论与应用, 2003, 20(6): 875-878. Wang X H, Chen Z Q, Yuan Z Z.Nonlinear tracking-differentiator with high speed in whole course[J].Journal of Control Theory & Applications, 2003, 20(6): 875-878(in Chinese).
[13]	Wang X H, Chen Z Q.Finite-time-convergent differentiator based on singular perturbation technique[J].IEEE Transactions on Automatic Control, 2007, 52(9): 1731-1737.
[14]	宿敬亚, 张瑞峰, 王新华, 等.基于滤噪微分器的四旋翼飞行器控制[J].控制理论与应用, 2009, 26(8): 827-832. Su J Y, Zhang R F, Wang X H, et al.Controlling a four-rotor aircraft based on noise-attenuation differentiator[J].Journal of Control Theory & Applications, 2009, 26(8): 827-832(in Chinese).
[15]	Ibrir S. Linear time-derivative trackers[J].Automatica, 2004, 40(3): 397-405.
[16]	韩京清. 自抗扰控制技术[M].北京: 国防工业出版社, 2008: 56-66. Han J Q.Active disturbance rejection control technique[M].Beijing: National Defense Industry Press, 2008: 56-66(in Chinese).
[17]	Haimo V T. Finite time controllers[J]Siam Journal on Control and Optimization, 1986, 24(4): 760-771.
[18]	陈小庆. 高超声速滑翔飞行器机动技术研究[D].长沙: 国防科学技术大学, 2011. Chen X Q.The key technology relative to the maneuverability of hypersonic gliding vehicle[D].Changsha: National University of Defense Technology, 2011(in Chinese).