| [1] Jiang Y X, Cui J. Effectiveness of weaving maneuver strategy of a missile[J]. Journal of Beijing University of Aeronautics and Astronautics, 2002, 28(2): 133-136. (in Chinese) 姜玉宪, 崔静. 导弹摆动式突防策略的有效性[J].北京航空航天大学学报, 2002, 28(2): 133-136.[2] Yan X Y, Yang S X, Zhang C. Analysis of stability for coning motion of rockets based on theory of nutation movement[J]. Acta Armamentarii, 2009, 30(10): 1291-1296. (in Chinese) 闫晓勇, 杨树兴, 张成. 基于章动运动理论的火箭弹锥形运动稳定性分析[J]. 兵工学报, 2009, 30(10): 1291-1296.[3] Mao X R, Yang S X, Xu Y. Coning motion stability of wrap around fin rockets[J]. Science in China Series E: Technological Sciences, 2007, 50(3): 343-350.[4] Xu H J, Zhu J T, Zeng F. Three-dimensional circular guidance law with impact angle constraints[J]. Acta Aeronautica et Astronautica Sinica, 2003, 24(3): 255-258. (in Chinese) 徐浩军, 朱建太, 曾凡. 飞机纵向摆动及飞行安全评估[J]. 航空学报, 2003, 24(3): 255-258.[5] Zhou D, Zou X G, Sun D B. A sliding-mode guidance law for homing missiles breaking through defense with maneuver[J]. Journal of Astronautics, 2006, 27(2): 213-216. (in Chinese) 周荻, 邹昕光, 孙德波. 导弹机动突防滑模制导律[J]. 宇航学报, 2006, 27(2): 213-216.[6] Gu W J, Zhao H C. Research on terminal nonplanar maneuver of supersonic anti-ship missile[J]. Flight Dynamics, 2003, 21(3): 36-40. (in Chinese) 顾文锦, 赵红超. 超声速反舰导弹末端非平面机动研究[J]. 飞行力学, 2003, 21(3): 36-40.[7] Gu W J, Zhao H C, Wang F L, et al. Integrative control model of missiles terminal maneuver[J]. Journal of Astronautics, 2004, 25(6): 677-680. (in Chinese) 顾文锦, 赵红超, 王凤莲, 等. 导弹末端机动的一体化控制模型[J]. 宇航学报, 2004, 25(6): 677-680.[8] Gu W J. An overload control of anti-ship missile[J]. Journal of Projectiles Rockets Missiles and Guidance, 2002, 22(1): 14-18. (in Chinese) 顾文锦. 反舰导弹的过载控制[J]. 弹箭与制导学报, 2002, 22(1): 14-18.[9] Li S D, Ren X, Wu R L. Research of spiral maneuver of reentrying missile[J]. Journal of Astronautics, 2000, 21(4): 41-48. (in Chinese) 郦苏丹, 任萱, 吴瑞林. 再入弹头的螺旋机动研究[J]. 宇航学报, 2000, 21(4): 41-48.[10] Xie Y, Liu L H, Tang G J, et al. Weaving maneuver trajectory design for hypersonic glide vehicles[J]. Acta Aeronautica et Astronautica Sinica, 2011, 32(12): 2174-2180. (in Chinese) 谢愈, 刘鲁华, 汤国建, 等. 高超声速滑翔飞行器摆动式机动突防弹道设计[J]. 航空学报, 2011, 32(12): 2174-2180.[11] Chen W C, Nie R M, Liu J Q. Patriot PAC-3 interceptor missile terminal guidance accuracy simulation study[J]. Winged Missiles Journal, 1999, 19(7): 57-62. (in Chinese) 陈万春, 聂蓉梅, 刘佳琪. PAC-3爱国者拦截弹末制导精度仿真研究[J]. 飞航导弹. 1999, 19(7): 57-62.[12] Zarchan P. Proportional navigation and weaving target[J]. Journal of Guidance Control and Dynamics, 1995, 18(5): 969-974.[13] Enomoto K, Yamasakiy T, Taknoz H. A study on a velocity control system design using the dynamic inversion method//AIAA Guidance, Navigation, and Control Conference, 2010: 563-568.[14] Bruyère L, Whitey B A, Tsourdos A. Dynamic inversion for missile lateral velocity control via polynomial eigenstructure assignment//AIAA Guidance, Navigation, and Control Conference and Exhibit, 2003: 437-443.[15] Hu X J, Huang X M. Three-dimensional circular guidance law with impact angle constraints[J]. Acta Aeronautica et Astronautica Sinica, 2012, 33(3): 508-519. (in Chinese) 胡锡精, 黄雪梅. 具有碰撞角约束的三维圆轨迹制导律[J]. 航空学报, 2012, 33(3): 508-519. |
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