收稿日期: 2016-10-28
修回日期: 2017-01-12
网络出版日期: 2017-01-11
基金资助
国家自然科学基金（61403096）；中国博士后科学基金（2014M551242）；中央高校基本科研业务费专项资金（HIT.NSRIF.2014036，HIT.NSRIF.2015036）；黑龙江省博士后资助经费（LBH-Z12112）
Integrated guidance and control design considering input saturation
Received date: 2016-10-28
Revised date: 2017-01-12
Online published: 2017-01-11
Supported by
National Natural Science Foundation of China (61403096);China Postdoctoral Science Foundation (2014M551242);the Fundamental Research Funds for the Central Universities (HIT.NSRIF.2014036,HIT.NSRIF.2015036);Heilongjiang Postdoctoral Fund (LBH-Z12112)
高超声速飞行器俯冲时具有快时变特性，执行机构限于物理约束极易导致控制输入达到饱和，针对该问题提出考虑输入饱和约束的制导与控制一体化设计方法。首先，建立纵向制导与控制一体化设计模型，采用干扰观测器对系统不确定性进行估计补偿，然后结合加幂积分方法与嵌套饱和方法设计了新的制导控制一体化非线性控制律。通过严格的理论分析证明了带有饱和约束的控制器可令系统状态全局有限时间稳定，由于控制律中的虚拟控制量均考虑了饱和约束，做到了全局协调抗饱和，从而可更充分地利用飞行器控制能力去实现精准控制。数值仿真实例验证了提出方法的有效性及鲁棒性。
王松艳 , 孙向宇 , 杨胜江 , 晁涛 . 考虑输入饱和的制导控制一体化设计[J]. 航空学报, 2017 , 38(10) : 320897 -320897 . DOI: 10.7527/S1000-6893.2017.320897
Hypersonic vehicle is fast varying in dive phase,so its actuator is easy to be saturated because of the physical constraint.Integrated guidance and control method considering input constraint is proposed.The longitudinal design model for integrated guidance and control is built.An extended state observer is taken to estimate the uncertainties and compensate them.A new integrated guidance and control method is built for the cascaded system based on the method of adding a power integrator and the method of nested anti-windup.Rigorous theoretic analysis proves that the control strategy can result in expected equilibrium of all system states in finite time.Because all the virtual control variables consider the saturation restraint,much more control capacity of the vehicle can be saved to realize accurate manipulation.A numerical simulation case is adopted to verify the effectiveness and robustness of the proposed method.
[1] 孙长银, 穆朝絮, 余瑶. 近空间高超声速飞行器控制的几个科学问题研究[J]. 自动化学报, 2013, 39(11):1901-1913. SUN C Y, MU C X, YU Y. Some control problems for near space hypersonic vehicles[J]. Acta Automatica Sinica, 2013, 39(11):1901-1913(in Chinese).
[2] 崔尔杰. 近空间飞行器研究发展现状及关键技术问题[J]. 力学进展, 2009, 39(6):658-673. CUI E J. Research statutes, development trends and key technical problems of near space flying[J]. Advances in Mechanics, 2009, 39(6):658-673(in Chinese).
[3] 张金鹏, 周池军, 雷虎民. 基于滑模反演控制方法的纵向制导控制一体化设计[J]. 固体火箭技术, 2013, 36(1):11-16. ZHANG J P, ZHOU C J, LEI H M. Integrated guidance and control design based on sliding-mode and back-stepping control[J]. Journal of Solid Rocket Technology, 2013, 36(1):11-16(in Chinese).
[4] 董飞垚, 雷虎民, 李炯, 等. 拦截弹自适应最优滑模制导和控制一体化设计[J]. 宇航学报, 2013, 34(11):1456-1461. DONG F Y, LEI H M, LI J, et al. Design of integrated adaptive optimal sliding-mode guidance and control for interceptor[J]. Journal of Astronautics, 2013, 34(11):1456-1461(in Chinese).
[5] 董飞垚, 雷虎民, 周池军, 等. 导弹鲁棒高阶滑模制导控制一体化研究[J]. 航空学报, 2013, 34(9):2212-2218. DONG F Y, LEI H M, ZHOU C J, et al. Research of integrated robust high order sliding mode guidance and control for missiles[J]. Acta Aeronautica et Astronautica Sinica, 2013, 34(9):2212-2218(in Chinese).
[6] 查旭, 崔平远, 常伯浚. 攻击固定目标的飞行器制导控制一体化设计[J]. 宇航学报, 2005, 26(1):13-18. ZHA X, CUI P Y, CHANG B J. An integrated approach to guidance and control for aircraft applying to attack the ground fixed targets[J]. Journal of Astronautics, 2005, 26(1):13-18(in Chinese).
[7] SHIMA T, IDAN M, GOLAN O M. Sliding-mode control for integrated missile autopilot guidance[J]. Journal of Guidance, Control, and Dynamics, 2006, 29(2):250-260.
[8] 尹永鑫, 石文, 杨明. 基于动态逆和状态观测的制导控制一体化设计[J]. 系统工程与电子技术, 2011, 33(6):1342-1345. YIN Y X, SHI W, YANG M. Integrated guidance and control based on dynamic inverse and extended state observer method[J]. Systems Engineering and Electronics, 2011, 33(6):1342-1345(in Chinese).
[9] HOU M Z, LIANG X L, DUAN G R. Adaptive block dynamic surface control for integrated missile guidance and autopilot[J]. Chinese Journal of Aeronautics, 2013, 26(3):741-750.
[10] 张尧, 郭杰, 唐胜景, 等. 导弹制导与控制一体化三通道解耦设计方法[J]. 航空学报, 2014, 35(12):3438-3450. ZHANG Y, GUO J, TANG S J, et al. Integrated missile guidance and control three-channel decoupling design method[J]. Acta Aeronautica et Astronautica Sinica, 2014, 35(12):3438-3450(in Chinese).
[11] 赵国荣, 冯淞琪. 适用于制导控制一体化的模糊滑模方法[J]. 控制与决策, 2014, 29(7):1321-1324. ZHAO G R, FENG S Q. Fuzzy sliding model method for integrated guidance and control[J]. Control and Decision, 2014, 29(7):1321-1324(in Chinese).
[12] TEEL. Global stabilization and restricted tracking for multiple integrators with bounded controls[J]. Systems and Control Letters, 1992, 18(3):165-171.
[13] ZHOU B, DUAN G R. A novel nested non-linear feedback law for global stabilization of linear systems with bounded controls[J]. International Journal of Control, 2008, 81(9):1352-1363.
[14] SUSSMANN H J, SONTAG E D, YANG Y. A general result on the stabilization of linear systems using bounded controls[J]. IEEE Transactions on Automatic Control, 1994, 39(12):2411-2425.
[15] MARCHAND N, HABLY A. Global stabilization of multiple integrators with bounded controls[J]. Automatica, 2005, 41(12):2147-2152.
[16] ZHOU B, DUAN G R, HE K. Global stabilization of linear systems with bounded controls using state-dependent saturation functions[J]. Journal of Systems Science and Complexity, 2011, 24:477-490.
[17] LIN Z, SABERI S. Semi-global exponential stabilization of linear systems subject to "input saturation" via linear feedbacks[J]. Systems and Control Letters, 1993, 21(3):225-239.
[18] ZHOU B, DUAN G R. Global stabilization of linear systems via bounded controls[J]. Systems & Control Letters, 2009, 58(1):54-61.
[19] ZHOU B, ZHENG W X, DUAN G R. An improved treatment of saturation nonlinearity with its application to control of systems subject to nested saturation[J]. Automatica, 2011, 47(1):306-315.
[20] LIANG X L, HOU M Z, DUAN G R. Integrated guidance and control for missile in the presence of input saturation and angular constraints[C]//IEEE Control Conference. Piscataway, NJ:IEEE Press, 2013:1070-1075.
[21] LIANG X L, HOU M Z, DUAN G R. Adaptive dynamic surface control for integrated missile guidance and autopilot in the presence of input saturation[J]. Journal of Aerospace Engineering, 2015, 28(5):401-412.
[22] YAN H, JI H B. Integrated guidance and control for dual-control missiles based on small gain theorem[J]. Automatica, 2012, 48(1):2686-2692.
[23] QIAN C J, LIN W. A continuous feedback approach to global strong stabilization of nonlinear systems[J]. IEEE Transactions on Automatic Control, 2001, 46(7):1061-1076.
[24] HARDY G H, LITTLEWOOD J E. Inequalities[M]. Cambridge:Cambridge University Press, 1952.
[25] 卜祥伟, 吴晓燕, 陈永兴, 等. 基于非线性干扰观测器的高超声速飞行器滑模反演控制[J]. 控制理论与应用, 2014, 31(11):1473-1479. BU X W, WU X Y, CHEN Y X. Nonlinear disturbance observer based sliding mode backstepping control of hypersonic vehicle[J]. Control Theory and Applications, 2014, 31(11):1473-1479(in Chinese).
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