[1] 杨靖, 王旭刚, 王中原,等. 考虑自动驾驶仪动态特性和攻击角约束的鲁棒末制导律[J]. 兵工学报, 2017, 38(5): 900-909. YANG Jing, WANG Xu-gang, WANG Zhong-yuan, et al. Robust terminal guidance law with autopilot lag and impact angle constraints[J]. Acta Armamentarii, 2017, 38(5): 900-909. (in Chinese) [2] Song T, Lin D F, Wang J. Dynamic stability of rolling missiles with angle-of-attack feedback three-loop autopilot considering parasitic effect[J]. Aerospace Science and Technology, 2017,71(5): 592-602. [3] 张凯, 杨锁昌, 张宽桥,等. 考虑导弹自动驾驶仪动态特性的新型制导律[J]. 北京航空航天大学学报, 2017, 43(8): 1693- 1704. ZHANG Kai, YANG Suo-chang, ZHANG Kuan-qiao, et al. Novel guidance law accounting for dynamics of missile autopilot [J]. Journal of Beijing University of Aeronautics and Astronautics, 2017, 43(8): 1693-1704. (in Chinese) [4] 刘昕戈, 刘藻珍, 单家元. 导弹系统的复合分层抗干扰自动驾驶仪设计[J]. 控制工程, 2017, 24(3): 500-504. LIU Xin-ge, LIU Zao-zhen, SHAN Jia-yuan. Composite hierarchical anti-disturbance autopilot design for missile systems[J]. Control Engineering of China, 2017, 24(3): 500-504. (in Chinese) [5] Han T, Hu Q L. Robust autopilot design for STT missiles with multiple disturbances using twisting control[J]. Aerospace Science and Technology, 2017, 70(4): 428-434. [6] Ramesh H, Anshul T, Nandan K S. Design and simulation of autopilot control system for stratospheric airship[J]. IFAC PapersOnLine, 2016, 49(1): 712-717. [7] Abd-Elatif M A, Qian L J, Bo Y M. Optimization of three-loop missile autopilot gain under crossover frequency constraint[J]. Defence Technology,2016, 12(1): 32-38. [8] 李蒙, 石泳, 刘莉. 基于鲁棒H∞的无人机飞行控制系统设计及实现[J]. 北京理工大学学报, 2016, 38(8): 807-812. LI Meng, SHI Yong, LIU Li. Development of UAV autopilot based on robust H∞ theory[J]. Transactions of Beijing Institute of Technology, 2016, 38(8): 807-812. (in Chinese)
[9] Feng Z X, Guo J G, Zhou J. Robust constrained autopilot control for a generic missile in the presence of state and input constraints[J]. Optik-International Journal for Light and Electron Optics, 2017, 149(1): 49-58.
[10] 孟克子, 周荻. 考虑导弹自动驾驶仪动态特性的H∞导引律[J]. 兵工学报, 2016, 37(7): 1194-1202. MENG Ke-zi, ZHOU Di. H∞ guidance law accounting for dynamics of missile autopilot[J]. Acta Armamentarii, 2016, 37(7): 1194-1202. (in Chinese)
[11] Lee J. Guidance law to control impact time and angle [J]. IEEE Transaction on Aerospace and Electronic Systems, 2007, 43(1):301-310. [12] Siddhardha K. Novel two phase algorithm to design three loop autopilot using parameter plane technique and particle swarm optimization[J]. IFAC PapersOnLine, 2016, 49(1): 830-835. [13] Lee L, Kim Y, Moon G. Adaptive backstepping autopilot design for missiles of fast time-varying velocity[J]. IFAC PapersOnLine, 2016, 49(17): 474-479. [14] 刁兆师. 导弹精确高效末制导与控制若干关键技术研究[D]. 北京:北京理工大学, 2015. DIAO Zhao-shi. Research on high-precision and high-efficiency terminal guidance and control key technologies for missile [D]. Beijing: Beijing Institute of Technology, 2015. (in Chinese) [15] Xu B, Yuan Y. Two performance enhanced control of flexible-link manipulator with system uncertainty and disturbances[J]. Science China:Information Sciences, 2017, 60 (5) : 050202-1-050202-11. [16] Guo Z Y, Zhou J, Guo J G. Robust autopilot design for bank-to-turn missiles using adaptive dual-layer sliding mode control[J]. Optik-International Journal for Light and Electron Optics, 2017, 131: 383-398. [17] Lyu S, Yan X D, Tang T. Prescribed performance interceptor guidance with terminal line of sight angle constraint accounting for missile autopilot lag[J]. Aerospace Science and Technology, 2017, 69: 171-180. [18] 马悦悦. 敏捷导弹大攻角高机动飞行控制方法研究[D]. 北京:北京理工大学, 2015. MA Yue-yue. Research on flight control design under high angle of attack maneuvering for agile missiles[D]. Beijing: Beijing Institute of Technology, 2015. (in Chinese)
[19] 熊少锋, 王卫红, 刘晓东. 考虑导弹自动驾驶仪动态特性的带攻击角度约束制导律[J]. 控制与决策, 2015, 30(4): 585- 592. XIONG Shao-feng,WANG Wei-hong,LIU Xiao-dong. Impact angle guidance law considering missile's dynamics of autopilot[J]. Control and Decision, 2015, 30(4): 585-592.(in Chinese) [20] 商巍, 唐胜景, 郭杰. 考虑自动驾驶仪特性的自适应模糊动态面滑模制导律设计[J]. 兵工学报, 2015,36(4): 660-667.
SHANG Wei, TANG Sheng-jing, GUO Jie. Design of adaptive fuzzy dynamic surface sliding-mode guidance law considering autopilot lag[J]. Acta Armamentarii, 2015,36(4): 660-667.(in Chinese) [21] Davad A, Wang H P. Roll-pitch-yaw autopilot design for nonli- near time-varying missile using partial state observer based global fast terminal sliding mode control[J]. Chinese Journal of Aeronautics, 2016, 29(5): 1302-1312. [22] Kedarisetty S, Vignesh N, Pulak H. Autopilot design for flexible tactical aerospace vehicle using parameter plane technique[J]. IFAC Proceedings, 2014, 47(1): 211-218. [23] Zhou D, Shao C T. Dynamics and autopilot design for endoatmospheric interceptors with dual control systems[J]. Aerospace Science and Technology, 2014, 13(6): 291-300.
第39卷第12期 2018 年12月兵工学报ACTA ARMAMENTARIIVol.39No.12Dec. 2018
|