Hostname: page-component-7857688df4-fzltz Total loading time: 0 Render date: 2025-11-18T10:37:10.206Z Has data issue: false hasContentIssue false
  • English
  • Français

Cooperative guidance for active defence based on line-of-sight constraint under a low-speed ratio

Published online by Cambridge University Press:  08 June 2022

S. Liu Open the ORCID record for S. Liu [Opens in a new window] ,
Y. Wang ,
Y. Li ,
B. Yan Open the ORCID record for B. Yan [Opens in a new window]  and
T. Zhang
S. Liu
Affiliation:
Unmanned System Research Institute, Northwestern Polytechnical University, Xi’an, China
Y. Wang
Affiliation:
Shanghai Electro-Mechanical Engineering Institute, Shanghai, China
Y. Li
Affiliation:
Shanghai Electro-Mechanical Engineering Institute, Shanghai, China
B. Yan*
Affiliation:
School of Astronautics, Northwestern Polytechnical University, Xi’an, China
T. Zhang
Affiliation:
Unmanned System Research Institute, Northwestern Polytechnical University, Xi’an, China
*
*Corresponding author. Email: yanbinbin@nwpu.edu.cn
Get access Rights & Permissions [Opens in a new window]

Abstract

In this study, an active defence cooperative guidance (ADCG) law that enables cheap and low-speed airborne defence missiles with low manoeuverability to accurately intercept fast and expensive attack missiles with high manoeuverability was designed to enhance the capability of aircraft for active defence. This guidance law relies on the line-of-sight (LOS) guidance method, and it realises active defence by adjusting the geometric LOS relationship involving an attack missile, a defence missile and an aircraft. We use a nonlinear integral sliding surface and an improved second-order sliding mode reaching law to design the guidance law. This can not only reduce the chattering phenomenon in the guidance command, but it can also ensure that the system can reach the sliding surface from any initial position in a finite time. Simulations were carried out to verify the proposed law using four cases: different manoeuvering modes of the aircraft, different speed ratios of the attack and defence missiles, different reaching laws applied to the ADCG law and a robustness analysis. The results show that the proposed guidance law can enable a defence missile to intercept an attack missile by simultaneously using information about the relative motions of the attack missile and the aircraft. It is also highly robust in the presence of errors and noise.

Keywords

Active defenceCooperative guidanceNonlinear integral sliding modeLine-of-sight constraint

Information

Type
Research Article
Information
The Aeronautical Journal , Volume 127 , Issue 1309 , March 2023 , pp. 491 - 509
Check for updates
Copyright
© The Author(s), 2022. Published by Cambridge University Press on behalf of Royal Aeronautical Society

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.)

Article purchase

Temporarily unavailable

References

Yan, X. and Lyu, S. A two-side cooperative interception guidance law for active air defense with a relative time-to-go deviation, Aerospace Sci. Technol., 2020, 100, 105787.CrossRefGoogle Scholar
Zhao, Z.T., Huang, W., Yan, L. and Yang, Y.G. An overview of research on wide-speed range waverider configuration, Progr. Aerospace Sci., 2020, 113, 100606.CrossRefGoogle Scholar
Zhang, T., Yan, X., Huang, W., Che, X. and Wang, Z. Multidisciplinary design optimization of a wide speed range vehicle with waveride airframe and RBCC engine, Energy, 2021, 235, 121386.CrossRefGoogle Scholar
Weiss, M., Shima, T., Castaneda, D. and Rusnak, I. Combined and cooperative minimum-effort guidance algorithms in an active aircraft defense scenario, J. Guidance Control Dyn., 2017, 40, (5), pp 1241–1254.CrossRefGoogle Scholar
Garcia, E., Casbeer, D.W., Fuchs, Z.E. and Pachter, M. Cooperative missile guidance for active defense of air vehicles, IEEE Trans. Aerospace Electron. Syst., 2017, 54, (2), pp 706–721.CrossRefGoogle Scholar
Han, T., Hu, Q. and Xin, M. Three-dimensional approach angle guidance under varying velocity and field-of-view limit without using line-of-sight rate, IEEE Trans. Syst. Man Cybern. Syst., 2022, Published Online, doi: 10.1109/TSMC.2022.3150299 CrossRefGoogle Scholar
Han, T., Shin, H.-S., Hu, Q., Tsourdos, A. and Xin, M. Differentiator-based incremental three-dimensional terminal angle guidance with enhanced robustness, IEEE Trans. Aerospace Electron. Syst., 2022, Published Online, doi: 10.1109/TAES.2022.3158639 CrossRefGoogle Scholar
Shima, T. Optimal cooperative pursuit and evasion strategies against a homing missile, J. Guidance Control Dyn., 2011, 34, (2), pp 414–425.CrossRefGoogle Scholar
Shaferman, V. and Shima, T. Cooperative multiple-model adaptive guidance for an aircraft defending missile, J. Guidance Control Dyn., 2010, 33, (6), pp 1801–1813.CrossRefGoogle Scholar
Prokopov, O. and Shima, T. Linear quadratic optimal cooperative strategies for active aircraft protection, J. Guidance Control Dyn., 2013, 36, (3), pp 753–764.CrossRefGoogle Scholar
Perelman, A., Shima, T. and Rusnak, I. Cooperative differential games strategies for active aircraft protection from a homing missile, J. Guidance Control Dyn., 2011, 34, (3), pp 761–773.CrossRefGoogle Scholar
Saurav, A., Kumar, S.R. and Maity, A. Cooperative guidance strategies for aircraft defense with impact angle constraints, AIAA Scitech 2019 Forum, 2019, p 0356.Google Scholar
Rubinsky, S. and Gutman, S. Three-player pursuit and evasion conflict, J. Guidance Control Dyn., 2014, 37, (1), pp 98–110.CrossRefGoogle Scholar
Naiming, Q.I., Qilong, S.U.N. and Jun, Z.H.A.O. Evasion and pursuit guidance law against defended target, Chin. J. Aeronaut., 2017, 30, (6), pp 1958–1973.Google Scholar
Qilong, S.U.N., Naiming, Q.I., Longxu, X.I.A.O. and Haiqi, L.I.N. Differential game strategy in three-player evasion and pursuit scenarios, J. Syst. Eng. Electron., 2018, 29, (2), pp 352–366.Google Scholar
Ratnoo, A. and Shima, T. Line-of-sight interceptor guidance for defending an aircraft, J. Guidance Control Dyn., 2011, 34, (2), pp 522–532.CrossRefGoogle Scholar
Yamasaki, T., Balakrishnan, S.N. and Takano, H. Geometrical approach-based defense-missile intercept guidance for aircraft protection against missile attack, Proc. Inst. of Mech. Eng. Part G J. Aerospace Eng., 2012, 226, (8), pp 1014–1028.Google Scholar
Ratnoo, A. and Shima, T. Line of sight guidance for defending an aircraft, AIAA Guidance, Navigation, and Control Conference, 2010, p 7877.CrossRefGoogle Scholar
Liu, S., Liu, W., Yan, B., Liu, S. and Yin, Y. Impact time control guidance law for large initial lead angles based on sliding mode control, J. Phys. Conf. Ser., 2021, 2031, (1), 012050.Google Scholar
Han, T., Hu, Q., Shin, H.S., Tsourdos, A. and Xin, M. Sensor-based robust incremental three-dimensional guidance law with terminal angle constraint, J. Guidance Control Dyn., 2021, 44, (11), pp 2016–2030.Google Scholar
Liu, S., Yan, B., Liu, R., Dai, P., Yan, J. and Xin, G. Cooperative guidance law for intercepting a hypersonic target with impact angle constraint, Aeronaut. J., 2022, 126, (1300), 1026–1044.CrossRefGoogle Scholar
Liu, S., Yan, B., Zhang, T., Dai, P. and Yan, J. Guidance law with desired impact time and FOV constrained for antiship missiles based on equivalent sliding mode control, Int. J. Aerospace Eng., 2021. doi: 10.1155/2021/9923332 CrossRefGoogle Scholar
Shin, H.S., Tsourdos, A. and Li, K.B. A new three-dimensional sliding mode guidance law variation with finite time convergence, IEEE Trans. Aerospace Electron. Syst., 2017, 53, (5), pp 2221–2232.CrossRefGoogle Scholar
Song, J. and Song, S. Three-dimensional guidance law based on adaptive integral sliding mode control, Chin. J. Aeronaut., 2016, 29, (1), pp 202–214.CrossRefGoogle Scholar
Sinha, A. and Kumar, S.R. Supertwisting control-based cooperative salvo guidance using leader–follower approach, IEEE Trans. Aerospace Electron. Syst., 2020, 56, (5), pp 3556–3565.CrossRefGoogle Scholar
Liu, S., Yan, B., Zhang, X., Liu, W. and Yan, J. Fractional-order sliding mode guidance law for intercepting hypersonic vehicles, Aerospace, 2022, 9, (2), p 53.CrossRefGoogle Scholar
Shtessel, Y., Taleb, M. and Plestan, F. A novel adaptive-gain supertwisting sliding mode controller: Methodology and application, Automatica, 2012, 48, (5), pp 759–769.CrossRefGoogle Scholar
Qian, D. and Yi, J. Hierarchical Sliding Mode Control for Under-Actuated Cranes, Springer, 2016, Heidelberg, Berlin.CrossRefGoogle Scholar
Lian Fu, L. Application and ordinary solution of a kind of first order differential equation, J. Huangshi Inst. Technol., 2011, 27, (4), pp 41–42 (in Chinese).Google Scholar
Bhat, S.P. and Bernstein, D.S. Geometric homogeneity with applications to finite-time stability, Math. Control Signals Syst., 2005, 17, (2), pp 101–127.CrossRefGoogle Scholar
Chalanga, A., Kamal, S., Fridman, L.M., Bandyopadhyay, B. and Moreno, J.A. Implementation of super-twisting control: Super-twisting and higher order sliding-mode observer-based approaches, IEEE Trans. Indus. Electron., 2016, 63, (6), pp 3677–3685.CrossRefGoogle Scholar
Shima, T. and Golan, O.M. Linear quadratic differential games guidance law for dual controlled missiles, IEEE Trans. Aerospace Electron. Syst., 2007, 43, (3), pp 834–842.CrossRefGoogle Scholar
Shinar, J. and Steinberg, D. Analysis of optimal evasive maneuvers based on a linearized two-dimensional kinematic model, J. Aircraft, 1977, 14, (8), pp 795–802.CrossRefGoogle Scholar
Supplementary material: File

Liu et al. supplementary material

Liu et al. supplementary material

Download Liu et al. supplementary material(File)
File 5.1 MB