带碰撞角约束的三维有限时间滑模制导律

赵曜; 李璞; 刘娟; 陈喆; 刘向东

doi:10.13700/j.bh.1001-5965.2017.0087

带碰撞角约束的三维有限时间滑模制导律

doi: 10.13700/j.bh.1001-5965.2017.0087

赵曜^1, ,,
李璞^{1, 2},
刘娟¹,
陈喆¹,
刘向东³

1.
中国运载火箭技术研究院, 北京 100076
2.
国防科学技术大学, 长沙 410073
3.
北京理工大学自动化学院, 北京 100081

详细信息

作者简介:
赵曜男, 博士, 工程师。主要研究方向:制导及精度总体设计

通讯作者:
赵曜, E-mail:shine3y9r@126.com

中图分类号: V448
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- 文章访问数: 908
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- 被引次数: 0
出版历程
- 收稿日期: 2017-02-21
- 录用日期: 2017-05-05
- 网络出版日期: 2018-02-20

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

ZHAO Yao^{1
, ,},
LI Pu^{1, 2},
LIU Juan¹,
CHEN Zhe¹,
LIU Xiangdong³

1.
China Academy of Launch Vehicle Technology, Beijing 100076, China
2.
National University of Defense Technology, Changsha 410073
3.
School of Automation, Beijing Institute of Technology, Beijing 100081, China

More Information

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

摘要

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。
- 制导 /
- 碰撞角约束 /
- 滑模控制 /
- 非线性 /
- 鲁棒性
Abstract:
To deal with the guidance problem of missile for intercepting ground fixed targets, a three-dimensional finite-time sliding mode control based guidance law is proposed in this paper. It is proved by the Lyapunov theory that the guidance law can steer the missile to intercept target with the desired impact angles in both azimuth and elevation. The guidance law has four advantages. First, model decoupling or model linearization is not needed in this work; second, the impact angles in both longitudinal and horizontal can be controled; third, the guidance command can be analytically derived; fourth, the closed-loop system is insensitive to external disturbance as well as parameter uncertainty. The simulation results show that high terminal accuracy and good robustness can be achieved by the proposed guidance law.
- guidance /
- impact angle constraints /
- sliding mode control /
- nonlinear /
- robustness

HTML全文

图 1 不同发射角条件下仿真结果

Figure 1. Simulation results with different launch angles

下载: 全尺寸图片幻灯片

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

下载: 全尺寸图片幻灯片

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]

下载: 全尺寸图片幻灯片

参考文献(18)

[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. doi: 10.1016/S1000-9361(08)60021-7
[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.aspx PENG 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=yhxb200406018 SHE 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.