Hostname: page-component-586b7cd67f-l7hp2 Total loading time: 0 Render date: 2024-11-28T14:26:57.988Z Has data issue: false hasContentIssue false
  • English
  • Français

Distributed synergetic guidance law for multiple missiles with angle-of-attack constraint

Published online by Cambridge University Press:  02 March 2020

H. You Open the ORCID record for H. You [Opens in a new window]  and
F.-J. Zhao
H. You
Affiliation:
Xi’an Research Institute of High Technology, Xi’an, [email protected]
F.-J. Zhao
Affiliation:
Xi’an Research Institute of High Technology, Xi’an, [email protected]
Get access Rights & Permissions [Opens in a new window]

Abstract

Based on the missiles with adjustable thrust, a distributed synergetic guidance law for multiple missiles with angle-of-attack constraint is designed to achieve a cooperative attack by multiple missiles on a moving target. Divide the guidance law into two parts: the line of sight (LOS) direction and the normal direction of LOS. The guidance law is designed in LOS direction based on the multi-agent system cooperative control theory and super-twisting algorithm, which can control missiles’ time-to-go converging in finite time. In the normal direction of LOS, the other guidance law is designed to control missiles hitting the target with impact angle constraint based on zeroing LOS rate thought and finite-time sliding mode control theory. The two non-homogeneous disturbance observers are designed to estimate the target manoeuvring information in the two parts of the guidance law. The simulation results show that the guidance law designed by this paper can complete the cooperative attack task while suppressing the chattering phenomenon effectively.

Keywords

Angle-of-attackSynergetic guidanceDistributed communication topologyManoeuvring target
Type
Research Article
Information
The Aeronautical Journal , Volume 124 , Issue 1274 , April 2020 , pp. 533 - 548
Copyright
© Royal Aeronautical Society 2020

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

REFERENCES

Huang, J., Zhang, Y. and Liu, Y.A biased proportional guidance algorithm for moving target with impact angle and field-of-view constraints. Journal of Astronautics, 2016, 37, (2), pp 195–202.Google Scholar
Erer, K.S. and Tekin, R.Impact time and angle control based on constrained optimal solutions. Journal of Guidance Control and Dynamics, 2016, 39, (10), pp 1–7.CrossRefGoogle Scholar
Jeon, I.S., Lee, J.I. and Tahk, M.J.Homing guidance law for cooperative attack of multiple missile. Journal of Guidance, Control, and Dynamics, 2010, 33, (1), pp 275–280.CrossRefGoogle Scholar
Taub, I. and Shima, T.Intercept angle missile guidance under time varying acceleration bounds. Journal of Guidance, Control and Dynamics, 2013, 36, (3), pp 686–699.CrossRefGoogle Scholar
Wang, X.F., Zheng, Y.Y. and Lin, H.Integrated guidance and control law for cooperative attack of multiple missiles. Aerospace Science and Technology, 2015, 42, pp 1–11.CrossRefGoogle Scholar
Zhang, Y, Wang, X. and Ma, G.Impact time control guidance law with large impact angle constraint. Proceedings of the Institution Mechanical Engineers, Part G: Journal of Aerospace Engineering Systems, 2015, 229, (11), pp 2119–2131.CrossRefGoogle Scholar
Lee, J.I., Jeon, I.S. and Tahk, M.J.Guidance law to control impact time and angle. IEEE Transactions on Aerospace and Electronic Systems, 2007, 43, (1), pp 301–310.Google Scholar
Li, X, Wang, L. and Fan, X.Two-stage control guidance of missile impact angle and flight time. Journal of National University of Defense Technology, 2017, 39, (6), pp 6–11.Google Scholar
Kumar, S.R. and Ghose, D.Impact time and angle control guidance. Proceedings of AIAA Guidance, Navigation and Control Conference, 2015, 2015, pp. 0616–0638.Google Scholar
Zhang, C., Song, J. and Hou, B.Cooperative guidance law with impact angle and impact time constraints for networked Missiles. Acta Armamentarii, 2016, 37, (3), pp 431–438.Google Scholar
Zhao, S.Y., Zhou, R., Wei, C. and Quanxin, D.Design of time constrained guidance laws via virtual leader approach. Chinese Journal of Aeronautics, 2010, 23, (1), pp 103–108.Google Scholar
LLv, T., Lv, Y. and Li, C.Finite time cooperative guidance law for multiple missiles with line-of-sight angle constraint. Acta Armamentarii, 2018, 39, (2), pp 305–314.Google Scholar
Wang, H., Shi, D. and Liu, H.Three-dimensional guidance law for missile of adjustable thrust with heat flux limit. Infrared and Laser Engineering, 2018, 47, (3), pp 140–150.Google Scholar
Chen, Y., Zhang, J. and Sun, W.Study of guidance law based on thrust control technology. Aero Weaponry, 2011, 5, pp 26–28.Google Scholar
Song, J., Song, S. and Xu, S.A cooperative guidance law for multiple to intercept maneuvering target. Journal of Astronautics, 2016, 37, (12), pp 1306–1314.Google Scholar
Mi, X., Zou, Y. and Li, S.Self-triggered DMPC design for cooperative multi-agent systems. IEEE Transactions on Industrial Electronics, 2019, 67, pp 512–520.CrossRefGoogle Scholar
Zhou, H., Song, S. and Song, J.Design of an observer-based sliding mode guidance law with finite time convergence. Journal of Central South University (Science and Technology), 2016, 47, (1), pp 91–99.Google Scholar
Liu, P., Sun, R. and Li, W.Homing guidance law with falling angle and flying time control. Journal of Harbin Institute of Technology, 2014, 21, (1), pp 55–61.Google Scholar