BPNG Law with Arbitrary Initial Lead Angle and Terminal Impact Angle Constraint and Time-to-go Estimation

doi:10.3969/j.issn.1000-1093.2019.01.009

Abstract

Abstract: A biased proportional navigation guidance (BPNG) law with arbitrary initial lead angle and impact angle constraint is designed for a large change in lead angle due to external disturbance during missile flight. The convergence of system parameters under this guidance law is proved. The problem of the existence of singularity in existing piecewise iterative method is solved by expanding the existing method, and the time-to-go estimation method under this guidance law is presented. The proposed guidance law and the improved piecewise iterative method were simulated. The simulated results show that the guidance law can satisfy the requirements of miss distance and terminal impact angle of missile under the constraints of arbitrary initial lead angle and arbitrary impact angle, and the acceleration command also converges to zero at the flight terminal. Compared with previous research results,the proposed biased proportional navigation guidance law can achieve the effective control of missile when the lead angle is greater than π/2 rad. The proposed estimation method is used to estimate the time-to-go with small estimation error and fast error convergence. Simulated results demonstrate the effectiveness of the proposed guidance law and time-to-go estimation method. Key

Key words: biasedproportionalnavigationguidancelaw, arbitraryinitialleadangle, terminalimpactangleconstraint, time-to-goestimation

CLC Number:

TJ765.2⁺2

MA Shuai， WANG Xugang， WANG Zhongyuan， YANG Jing. BPNG Law with Arbitrary Initial Lead Angle and Terminal Impact Angle Constraint and Time-to-go Estimation[J]. Acta Armamentarii, 2019, 40(1): 68-78.

References

［1］ LEE C H, KIM T H, TAHK M J. Interception angle control gui- dance using proportional navigation with error feedback[J]. Journal of Guidance, Control, and Dynamics, 2013, 36(5):1556-1561.
[2］ ZHANG Y A, MA G X, LIU A L. Guidance law with impact time and impact angle constraints[J]. Chinese Journal of Aeronautics, 2013, 26(4):960-966.
[3］ ZHANG Y A, MA G X, WU H L. A biased proportional navigation guidance law with large impact angle constraint and the time-to-go estimation[J]. Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 2014, 228(10): 1725-1734.
[4］赵建博, 杨树兴. 多导弹协同制导研究综述[J]. 航空学报, 2017, 38(1):17-29.
ZHAO J B, YANG S X. Review of multi-missile cooperative gui- dance[J]. Acta Aeronautica et Astronautica Sinica, 2017, 38(1): 17-29. (in Chinese)
[5］ JEON I S, LEE J I, TAHK M J. Homing guidance law for cooperative attack of multiple missiles[J]. Journal of Guidance, Control, and Dynamics, 2010, 33(1):275-280.
[6］ ZHOU J L, YANG J Y. Distributed guidance law design for cooperative simultaneous attacks with multiple missiles[J]. Journal of Guidance, Control, and Dynamics, 2016, 39(10):1-9.
[7］叶鹏鹏, 盛安东, 张蛟, 等. 非持续连通通信拓扑下的多导弹协同制导[J]. 兵工学报, 2018, 39(3):474-484.
YE P P, SHENG A D, ZHANG J, et al. Cooperative guidance of multi-missile with unsustainable connected communication topology[J]. Acta Armamentarii, 2018, 39(3):474-484. (in Chinese)
[8］吕腾,吕跃勇,李传江,等. 带视线角约束的多导弹有限时间协同制导律[J]. 兵工学报, 2018, 39(2):305-314.
LYU T, LYU Y Y, LI C J, et al. Finite time cooperative guidance law for multiple missiles with line-of-sight angle constraint[J]. Acta Armamentarii, 2018, 39(2):305-314. (in Chinese)
[9］ CHEN X T, WANG J Z. Nonsingular sliding-mode control for field-of-view constrained impact time guidance[J]. Journal of Guidance, Control, and Dynamics, 2018, 41(5):1210-1218.

[10］ WANG X L, ZHANG Y A, WU H L. Distributed cooperative guidance of multiple anti-ship missiles with arbitrary impact angle constraint[J]. Aerospace Science & Technology, 2015, 46:299-311.
[11］ ZARCHAN P. Tactical and strategic missile guidance [M]. Reston, VA, US: AIAA, Inc., 2012:777-788.
[12］ KIM B S, LEE J G, HAN H S. Biased PNG law for impact with angular constraint[J]. IEEE Transactions on Aerospace & Electronic Systems, 1998, 34(1):277-288.
[13］高峰, 唐胜景, 师娇, 等. 一种基于落角约束的偏置比例导引律[J]. 北京理工大学学报, 2014, 34(3):277-282.
GAO F, TANG S J, SHI J, et al. A bias proportional navigation guidance law based on terminal impact angle constraint[J]. Transactions of Beijing Institute of Technology,2014, 34(3):277-282. (in Chinese)
[14］ KIM T H, PARK B G, TAHK M J. Bias-shaping method for biased proportional navigation with terminal-angle constraint[J]. Journal of Guidance, Control, and Dynamics, 2013, 36(6):1810-1816.
[15］张春妍, 宋建梅, 侯博,等. 带落角和时间约束的网络化导弹协同制导律[J]. 兵工学报, 2016, 37(3):431-438.
ZHANG C Y, SONG J M, HOU B, et al. Cooperative guidance law with impact angle and impact time constraints for networked missiles[J]. Acta Armamentarii, 2016, 37(3):431-438.(in Chinese)
[16］ DHANANJAY N, GHOSE D. Accurate time-to-go estimation for proportional navigation guidance[J]. Journal of Guidance, Control, and Dynamics, 2014, 37(4):1378-1383.
[17］ CHO N, KIM Y. Modified pure proportional navigation guidance law for impact time control[J]. Journal of Guidance, Control, and Dynamics, 2016, 39(4): 852-872.
[18］ TAHK M J, RYOO C K, CHO H J. Recursive time-to-go estimation for homing guidance missiles[J]. IEEE Transactions on Aerospace & Electronic Systems, 2002, 38(1):13-24.
[19］张友安, 马国欣. 大前置角下比例导引律的剩余时间估计算法[J]. 哈尔滨工程大学学报, 2013,34(11):1409-1414.
ZHANG Y A, MA G X. Time-to-go estimation algorithm for the proportional navigation guidance law with a large lead angle[J]. Journal of Harbin Engineering University, 2013, 34(11):1409-1414. (in Chinese)
[20］ ZHANG Y, WANG X, MA G. Impact time control guidance law with large impact angle constraint[J]. Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 2015, 229(11): 2119-2131.

第40卷第1期
2019 年1月兵工学报ACTA
ARMAMENTARIIVol.40No.1Jan.2019