Integrated Guidance, Control and Maneuver for Anti-Vessel Missiles Based on Backstepping Method

Abstract:

Integrated guidance, control and maneuver for anti-vessel missiles against vessel targets was studied. Firstly, the integrated guidance and autopilot model of the yaw plane was formulated, the guidance and control law was designed based on the backstepping method and sliding mode control theory. For the unavailable information of the vessel target, an estimating method was given. Integration of guidance and maneuver was realized based on a new guidance law. Finally, to verify the effectiveness and rightness of the integrated design scheme, the simulation of some anti-vessel missile against maneuvering targets had been made, the simulation results showed that high accuracy performance of guidance and control system can be got.

• Periodical: Applied Mechanics and Materials (Volume 69)
• Pages: 126-131
• DOI: https://doi.org/10.4028/www.scientific.net/AMM.69.126
• Online since: July 2011
• Authors: Cong Ying Li, Jin Yong Yu, Lei Han, Wen Guang Zhang
• Keywords: Anti-Vessel Missile, Backstepping, Sliding Mode Control (SMC), Trajectory Maneuver

References

[1] Ghose, D., LectureNotes on Guidance Laws and Their Applications, Automatic Control Research Center, Seoul National Univ., Republic of Korea, July 1996, Chaps. 5–7.

[2] Zarchan, P., Tactical and Strategic Missile Guidance, AIAA, Reston, VA, 1997, p.161–180.

[3] Cho, H. J., Ryoo, C. K., and Tahk, M. J., Closed-Form Optimal Guidance Law for Missiles of Time-Varying Velocity, Journal of Guidance, Control, and Dynamics, Vol. 19, No. 5, 1996, p.1017–1023.

DOI: 10.2514/3.21740

[4] Yaesh, I., and Ben-Asher, J. Z., Optimal Guidance with a Single Uncertain Time Lag, Journal of Guidance, Control, and Dynamics, Vol. 18, No. 5, 1995, p.981–988.

DOI: 10.2514/3.21494

[5] Song, S. H., and Ha, I. J., A Lyapunov-Like Approach to Performance Analysis of 3-Dimensional Pure PNG Laws, IEEE Transactions on Aerospace and Electric Systems, Vol. 30, No. 1, 1994, p.238–247.

DOI: 10.1109/7.250424

[6] Bezick, S., Rusnak, I., and Gray,W. S., Guidance of a Homing Missile via Nonlinear Geometric Control Methods, Journal of Guidance, Control, and Dynamics, Vol. 18, No. 3, 1995, p.441–448.

DOI: 10.2514/3.21407

[7] Yang, C. D., and Chen, H.Y., Nonlinear H1 Robust Guidance Law for Homing Missiles, Journal of Guidance, Control, and Dynamics, Vol. 21, No. 6, 1998, p.882–890.

DOI: 10.2514/2.4321

[8] Zhou, D., Mu, C., and Xu, W., Adaptive Sliding-Mode Guidance of a Homing Missile, Journal of Guidance, Control, and Dynamics, Vol. 22, No. 4, 1999, p.589–594.

DOI: 10.2514/2.4421

[9] Guidance of a Homing Missile, " Journal of Guidance, Control, and Dynamics, Vol. 22, No. 4, 1999, p.589–594.

[10] Babu, K. R., Sarma, I. G., and Swmy, K. N., Switched Bias Proportional Navigation for Homing Guidance Against Highly Maneuvering Target, Journal of Guidance, Control, and Dynamics, Vol. 17, No. 6, 1994, p.1357–1363.

DOI: 10.2514/3.21356

[11] P.K. Menon, E.J. Ohlmeyer, Integrated design of agile missile guidance and autopilot systems, Control Engineering Practice 9 (2001)1095-1106.

DOI: 10.1016/s0967-0661(01)00082-x

[12] Neil F. Palumbo, Todd D. Jackson, Integrated missile guidance and control: a state dependent riccati differential equation approach", Proceedings of the 1999 IEEE, International Conference on Control Applications, Kohala Coast-Island of Hawai'I, Hawai, I, USA, august 22-27, (1999).

DOI: 10.1109/cca.1999.806207

[13] Ernest Ohlmeyer, John E. Bibel and Steve Malyevac, Optimal design of integrated missile guidance and control, American Institute of Aeronautics and Astronautics, Inc.

DOI: 10.2514/6.1998-5519

[14] E. Devaud, J.P. Harcaut and H. Siguerdidjane, Various strategies to design a three-axes missile autopilot, AIAA 99-3976, pp.187-195.

DOI: 10.2514/6.1999-3976

[15] Jingqing Han, Wei Wang, Nonlinear tracking differentiator, Journal System Science and mathematics, 14(2), (1994), pp.177-183.