## 留言板

 引用本文: 赵曜, 李璞, 刘娟, 等 . 带碰撞角约束的三维有限时间滑模制导律[J]. 北京航空航天大学学报, 2018, 44(2): 273-279.
ZHAO Yao, LI Pu, LIU Juan, et al. Finite-time sliding mode control based 3D guidance law with impact angle constraints[J]. Journal of Beijing University of Aeronautics and Astronautics, 2018, 44(2): 273-279. doi: 10.13700/j.bh.1001-5965.2017.0087(in Chinese)
 Citation: ZHAO Yao, LI Pu, LIU Juan, et al. Finite-time sliding mode control based 3D guidance law with impact angle constraints[J]. Journal of Beijing University of Aeronautics and Astronautics, 2018, 44(2): 273-279. (in Chinese)

• 中图分类号: V448

## Finite-time sliding mode control based 3D guidance law with impact angle constraints

###### Corresponding author:ZHAO Yao, E-mail:shine3y9r@126.com
• 摘要:

针对导弹对地面静止目标的打击问题，提出了一种三维有限时间滑模制导律。利用Lyapunov方法证明了该制导律能够控制导弹以期望的纵向和侧向碰撞角对目标进行精确打击。该方法具有以下4点优势：无需对系统模型作解耦或线性化处理，可以同时对纵向和侧向碰撞角进行约束，可以得到解析的制导指令，闭环系统对外部扰动和参数不确定性具有不敏感特性。仿真结果验证了该制导方法能够保证较高的终端精度和较强的鲁棒性。

• 图 1  不同发射角条件下仿真结果

Figure 1.  Simulation results with different launch angles

图 2  本文制导律蒙特卡罗仿真结果

Figure 2.  Results of Monte Carlo simulation with proposed guidance law

图 3  文献[17]制导律蒙特卡罗仿真结果

Figure 3.  Results of Monte Carlo simulation with guidance law in Ref. 17]

•  [1] KIM M, GRIDER K V.Terminal guidance for impact attitude angle constrained flight trajectories[J].IEEE Transactions on Aerospace and Electronic Systems, 1973, 9(6):852-859. http://yadda.icm.edu.pl/yadda/element/bwmeta1.element.ieee-000004103230 [2] SIOURIS G M.Missile guidance and control systems[M].Berlin:Springer, 2003. [3] ZARCHAN P.Tactical and strategic missile guidance[M].4th ed.Reston:AIAA, 2002. [4] GHAW S N, GHOSE D.Pure proportional navigation against time-varying target maneuvers[J].IEEE Transactions on Aerospace and Electronic Systems, 1996, 32(3):1336-1346. http://ieeexplore.ieee.org/articleDetails.jsp?arnumber=543854 [5] KIM B S, LEE J G, HAN H S.Biased PNG law for impact with angular constraint[J].IEEE Transactions on Aerospace and Electronic Systems, 1998, 34(1):277-288. doi: 10.1109/7.640285 [6] JEONG S K, CHO S J, KIM E G. Angle constraint biased PNG[C]//Proceedings of 5th Asian Control Conference. Piscataway, NJ: IEEE Press, 2004: 1849-1854. [7] LU P, DOMAN D B, SCHIERMAN J D.Adaptive terminal guidance for hypervelocity impact in specified direction[J].Journal of Guidance, Control, and Dynamics, 2006, 29(2):269-278. doi: 10.2514/1.14367 [8] RATNOO A, GHOSE D.Impact angle constrained interception of stationary targets[J].Journal of Guidance, Control, and Dynamics, 2008, 31(6):1816-1821. https://www.researchgate.net/publication/238189369_Impact_Angle_Constrained_Interception_of_Stationary_Targets [9] RATNOO A, GHOSE D.Impact angle constrained guidance against nonstationary nonmaneuvering targets[J].Journal of Guidance, Control, and Dynamics, 2010, 33(1):269-275. doi: 10.2514/1.45026 [10] ZHOU D, MU C D, XU W L.Adaptive sliding-mode guidance of a homing missile[J].Journal of Guidance, Control, and Dynamics, 1999, 22(4):589-594. doi: 10.2514/2.4421 [11] SHIMA T.Intercept-angle guidance[J].Journal of Guidance, Control, and Dynamics, 2011, 34(2):484-492. doi: 10.2514/1.51026 [12] TAUB I, SHIMA T.Intercept angle missile guidance under time varying acceleration bounds[J].Journal of Guidance, Control, and Dynamics, 2013, 36(3):686-699. doi: 10.2514/1.59139 [13] HOU M Z, DUAN G R.Integrated guidance and control of homing missiles against ground fixed targets[J].Chinese Journal of Aeronautics, 2008, 21(2):162-168. [14] 彭双春, 潘亮, 韩大鹏, 等.一种新型三维制导律设计的非线性方法[J].航空学报, 2010, 31(10):2018-2025. http://d.wanfangdata.com.cn/Periodical_hkxb201010016.aspxPENG S C, PAN L, HAN D P, et al.A new 3D guidance law based on nonlinear method[J].Acta Aeronautica et Astronautica Sinca, 2010, 31(10):2018-2025(in Chinese). http://d.wanfangdata.com.cn/Periodical_hkxb201010016.aspx [15] 佘文学, 周凤岐.三维非线性变结构寻的制导律[J].宇航学报, 2004, 25(6):681-685. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=yhxb200406018SHE W X, ZHOU F Q.High precision 3-D nonlinear variable structure guidance law for homing missile[J].Journal of Astronautics, 2004, 25(6):681-685(in Chinese). http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=yhxb200406018 [16] OZA H B, PADHI R.Impact-angle-constrained suboptimal model predictive static programming guidance of air-to-ground missiles[J].Journal of Guidance, Control, and Dynamics, 2012, 35(1):153-164. doi: 10.2514/1.53647 [17] RATNOO A, GHOSE D.State-dependent Riccati-equation-based guidance law for impact-angle-constrained trajectories[J].Journal of Guidance, Control, and Dynamics, 2009, 32(1):320-325. doi: 10.2514/1.37876 [18] IMADO F, KURODA T, TAHK M J. A new missile guidance algorithm against a maneuvering target[C]//Proceedings of the AIAA Guidance, Navigation, and Control Conference. Reston: AIAA, 1998: 145-153.

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##### 出版历程
• 收稿日期:  2017-02-21
• 录用日期:  2017-05-05
• 刊出日期:  2018-02-20

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