| [1] Shkolnikov I, Shtessel Y, Lianos D. Integrated guidance-control system of a homing interceptor: sliding mode approach. AIAA-2001-4218, 2001.[2] Shtessel Y, Shkolnikov I. Integrated guidance and control of advanced interceptors using second order sliding modes. Proceeding of the 42nd IEEE Conference on Decision and Control, 2003: 4587-4592.[3] Shima T, Idan M, Golan O M. Sliding mode control for integrated missile autopilot guidance. Journal of Guidance, Control, and Dynamics, 2006, 29(2): 250-260.[4] Hughes T L, McFarland M B. Integrated missile guidance law and autopilot design using linear optimal control. AIAA-2000-4163, 2000.[5] Xin M, Balakrishnan S N, Ohlmeyer E J. Integrated guidance and control of missiles with θ-D method. IEEE Transactions on Control Systems Technology, 2006, 14(6): 981-992.[6] Duan G R, Hou M Z, Tan F. Adaptive, integrated guidance and control law design using sliding mode approach. Acta Armamentarii, 2010, 31(2): 191-198. (in Chinese) 段广仁, 侯明哲, 谭峰. 基于滑模方法的自适应一体化导引与控制律设计. 兵工学报, 2010, 31(2): 191-198.[7] Theodoulis S, Duc G. Missile autopilot design: gain-scheduling and the gap metric. Journal of Guidance, Control, and Dynamics, 2009, 32(3): 986-996.[8] Defoort M, Floquet T, Kokosy A, et al. A novel higher order sliding mode control scheme. System & Control Letters, 2009, 58(2): 102-108.[9] Bhat S P, Bernstein D S. Finite-time stability of homogenous systems. Proceedings of the American Control Conference, 1997: 2513-2514.[10] Moreno J A, Osorio M. Strict Lyapunov function for the super-twisting algorithm. IEEE Transactions on Automatic Control, 2012, 57(4): 1035-1040.[11] Atassi A N, Khalil H K. Separation results for the stabilization of nonlinear systems using different high-gain observer designs. Systems & Control Letters, 2000, 39(3): 183-191.[12] Levant A. Higher-order sliding modes, differentiation and output-feedback control. International Journal of Control, 2003, 76(9/10): 924-941.[13] Menon P K, Iragavarapu V R, Sweriduk G, et al. Software tools for nonlinear missile autopilot design. AIAA-1999-3975, 1999.[14] Zhang Y A, Hu Y A, Su S B. Geometric approach and robust control approach to three-dimentional missile guidance. Acta Aeronautica et Astronautica Sinica, 2002, 23(1): 88-90. (in Chinese) 张友安, 胡云安, 苏身榜. 三维制导的几何方法与鲁棒控制方法. 航空学报, 2002, 23(1): 88-90.[15] Dong F Y, Lei H M, Li J, et al. Design of incremental dynamic inversion control law for missiles with tracking differentiator. Journal of Astronautics, 2012, 33(10): 1439-1444. (in Chinese) 董飞垚, 雷虎民, 李炯, 等. 带有跟踪微分器的导弹增量动态逆控制律设计. 宇航学报, 2012, 33(10): 1439-1444. |
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