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Adaptive integrated guidance and control for impact angle constrained interception with actuator saturation

Published online by Cambridge University Press:  07 August 2019

X. L. Ai Open the ORCID record for X. L. Ai [Opens in a new window] ,
Y. C. Shen  and
L. L. Wang
X. L. Ai*
Affiliation:
School of Aerospace Engineering, Beijing Institute of Technology, Beijing, 100081, China
Y. C. Shen
Affiliation:
Beijing Institute of Electronic System Engineering, Beijing, 100854, China
L. L. Wang
Affiliation:
Beijing Institute of Space Long March Vehicle, Beijing, 100076, China
*
bitaixiaolin@163.com
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Abstract

This paper considers the integrated guidance and control (IGC) problem for impact angle constrained interception against manoeuvring targets with actuator saturation constraint. Based on the backstepping technique, an adaptive IGC law is presented to address this problem, where a fixed-time differentiator is proposed to estimate the derivatives of virtual control inputs to avoid the inherent problem of “explosion of complexity” suffered by the typical backstepping. Furthermore, an auxiliary first-order filter is introduced into the IGC law to cope with the actuator saturation constraint. The stability of the closed-loop system is strictly proved. Finally, the superiority of the proposed IGC law is verified by comparison simulations.

Keywords

Integrated guidance and controlImpact angle constraintActuator saturationAerodynamic uncertaintiesManoeuvring targets
Type
Research Article
Information
The Aeronautical Journal , Volume 123 , Issue 1267 , September 2019 , pp. 1437 - 1453
Copyright
© Royal Aeronautical Society 2019 

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References

REFERENCES

Yan, H., Tan, S. and He, Y. A small-gain method for integrated guidance and control in terminal phase of re-entry. Acta Astronaut, 2017, 132, pp 282–292.CrossRefGoogle Scholar
Wang, X. and Wang, J. Partial integrated guidance and control with impact angle constraints. J Guidance Control Dyn, 2015, 38, (5), pp 925–936.CrossRefGoogle Scholar
Yang, C. and Yang, C. Analytical solution of three-dimensional realistic true proportional navigation. J Guidance Control Dyn, 2012, 19, (3), pp 569–577.CrossRefGoogle Scholar
Ohimeyer, E. Root-mean-square miss distance of proportional navigation missile against sinusoidal target. J Guidance Control Dyn, 2015, 19, (3), pp 563–568.CrossRefGoogle Scholar
Zhou, D., Mu, C. and Xu, W. Adaptive sliding-mode guidance for a homing missile. J Guidance Control Dyn, 1999, 22, (4), pp 589–594.CrossRefGoogle Scholar
Moon, J., Kim, K. and Kim, Y. Design of missile guidance law via variable structure control. J Guidance Control Dyn, 2001, 24, (4), pp 659–664.CrossRefGoogle Scholar
Lechevin, N. and Rabbath, C. Lyapunov-based nonlinear missile guidance. J Guidance Control Dyn, 2004, 27, (3), pp 1096–1102.CrossRefGoogle Scholar
Shima, T. Intercept-angle guidance. J Guidance Control Dyn, 2011, 34, (2), pp 484–492.CrossRefGoogle Scholar
Kumar, S., Rao, S. and Ghose, D. Sliding-mode guidance and control for all-aspect interceptors with terminal angle constraints. J Guidance Control Dyn, 2012, 35, (4), pp 1230–1246.CrossRefGoogle Scholar
Kumar, S., Rao, S. and Ghose, D. Non-singular terminal sliding mode guidance with impact angle constraints. J Guidance Control Dyn, 2014, 37, (4), pp 610–621.CrossRefGoogle Scholar
Zhang, Y., Tang, S. and Guo, J. Adaptive terminal angle constraint interception against manoeuvring targets with fast fixed-time convergence. Int J Robust Nonlinear Control, 2018, 28, pp 2996–3014.CrossRefGoogle Scholar
Zhang, Y., Tang, S. and Guo, J. An adaptive fast fixed-time guidance law with an impact angle constraint for intercepting manoeuvring targets. Chinese J Aeronaut, 2018, 31, (6), pp 1327–1344.CrossRefGoogle Scholar
Gurfil, P., Jodorkovskym, M. and Guelman, M. Finite time stability approach to proportional navigation systems analysis. J Guidance Control Dyn, 1998, 21, (6), pp 853–861.CrossRefGoogle Scholar
Chwa, D. and Choi, J. Adaptive nonlinear guidance law considering control loop dynamics. IEEE Trans Aerosp Electron Syst, 2003, 39, (40), pp 1134–1143.CrossRefGoogle Scholar
Sun, S., Zhou, D. and Hou, W. A guidance law with finite time convergence accounting for autopilot lag. Aerosp Sci Technol, 2013, 25, (1), pp 132–137.CrossRefGoogle Scholar
He, S., Lin, D. and Wang, J. Robust terminal angle constraint guidance law with autopilot lag for intercepting manoeuvring targets. Nonlinear Dyn, 2015, 81, (1), pp 881–892.CrossRefGoogle Scholar
Zhou, D., Qu, P. and Sun, S. A guidance law with terminal impact angle constraint accounting for missile autopilot. J Dyn Syst Meas Control, 2013, 135, (5), pp 1–10.CrossRefGoogle Scholar
Menon, P. and Ohlmeye, R.E. Integrated design of agile missile guidance and autopilot systems. Control Eng Practice, 2001, 9, (10), pp 1095–1106.CrossRefGoogle Scholar
Vaddo, S., Menon, P. and Ohlmeye, R.E. Numerical state-dependent Raccati equation approach for missile integrated guidance control. J Guidance Control Dyn, 2009, 32, (2), pp 699–703.CrossRefGoogle Scholar
Xin, M., Balakrishnan, S. and Ohlmeyer, E. Integrated guidance and control missiles with θ - $\theta -D$ method. IEEE Trans Control Syst Technol, 2006, 14, (6), pp 981–992.CrossRefGoogle Scholar
Padhi, R., Chawla, C. and Das, P. Partial integrated guidance and control of interceptors for high-speed ballistic targets. J Guidance Control Dyn, 2014, 37, (1), pp 149–163.CrossRefGoogle Scholar
Kim, J., Whang, I. and Kim, B. Finite horizon integrated guidance and control for terminal homing in vertical plane. J Guidance Control Dyn, 2016, 39, (5), pp 1104–1112.CrossRefGoogle Scholar
He, S., Lin, D. and Wang, J. Continuous second-order sliding mode based impact angle guidance law. Aerosp Sci Technol, 2015, 41, pp 199–208.CrossRefGoogle Scholar
Shima, T., Idan, M. and Golan, O. Sliding-mode control for integrated missile autopilot guidance. J Guidance Control Dyn, 2006, 29, (2), pp 250–260.CrossRefGoogle Scholar
Idan, M., Shima, T. and Golan, O. Integrated sliding mode autopilot-guidance for dual-control missiles. J Guidance Control Dyn, 2007, 30, (4), pp 1081–1089.CrossRefGoogle Scholar
Shin, H., Hwang, T., Tsopurdos, A., White, B. and Tahk, M. Integrated intercept missile guidance and control with terminal angle constraint. Proceedings of the 26th International Congress of the Aeronautical Sciences, 2008, IEEE, pp 1875–1884.Google Scholar
Yan, H., Wang, W., Yu, B. and Ji, H. Adaptive integrated guidance and control based on backstepping and input-to-state stability. Asian J Control, 2014, 16, (2), pp 602–608.CrossRefGoogle Scholar
Shen, Y., Yu, J., Luo, G., Ai, X. and Jia, Z. Observer-based adaptive sliding mode backstepping output-feedback DSC for spin-stabilised canard-controlled projectiles. Chinese J Aeronaut, 2017, 30, (3), pp 1115–1126.CrossRefGoogle Scholar
Hou, M., Liang, X. and Duan, G. Adaptive block dynamic surface control for integrated missile guidance and autopilot. Chinese J Aeronaut, 2013, 26, (3), pp 741–750.CrossRefGoogle Scholar
Ran, M., Wang, Q., Hou, D. and Dong, C. Backstepping design of missile guidance and control based on adaptive fuzzy sliding mode control. Chinese J Aeronaut, 2014, 27, (3), pp 634–642.CrossRefGoogle Scholar
He, S., Song, T. and Lin, D. Impact angle constrained integrated guidance and control for manoeuvring target interception. J Guidance Control Dyn, 2017, 40, (10), pp 2652–2660.CrossRefGoogle Scholar
Wang, X., Zheng, Y. and Lin, H. Integrated guidance and control law for cooperative attack of multiple missiles. Aerosp Sci Technol, 2015, 42, pp 1–11.CrossRefGoogle Scholar
Wang, W., Xiong, S., Wang, S., Song, S. and Lai, C. Three dimensional impact angle constrained integrated guidance and control for missiles with input saturation and actuator failure. Aerosp Sci Technol, 2016, 53, pp 169–187.CrossRefGoogle Scholar
He, S., Wang, W. and Wang, J. Three-dimensional multivariable integrated guidance and control design for maneuvering targets interception. J Franklin Inst, 2016, 353, pp 4330–4350.CrossRefGoogle Scholar
He, S., Wang, W. and Wang, J. Adaptive backstepping impact angle control with autopilot dynamics and acceleration saturation consideration. Int J Robust Nonlinear Control, 2017, 27, pp 3777–3893.Google Scholar
Basin, M., Yu, P. and Shtessel, Y. Finite- and fixed-time differentiators utilising HOSM techniques. IET Control Theory Appl, 2017, 11, (8), pp 1144–1152.CrossRefGoogle Scholar