Kalman Filtering for Improvement Surface-to-Air Missile Guidance
Subject Areas : Control Engineering
1 - Department of Electrical & Computer Engineering , Torbat Heydarieh Branch, Islamic Azad University, Torbat Heydarieh, Iran
Keywords: Extended Kalman Filter, Bearing-only Tracking, Homing Missile, Pure Proportional Navigation,
Abstract :
Homing missiles are classified as Surface-to-air missiles. These missiles are used for air targets like airplane or helicopter combat. To counteract these missiles, fighter aircrafts use pseudo targets to deviate the course of the missiles. These pseudo targets in the form of Flyer Decoys, Jamming or Clutter are effective means to disable such missiles. In early versions of guidance systems, missiles turn-off their guidance systems temporarily. This can help in limited situations. However, in this paper an advanced guidance system based on Extended Kalman Filters is proposed. It is shown that using the estimated values of the variables from Kalman Filter, can modify the course of missile fight leading to the target. Due to the bearing-only nature of the system, it shown that initial conditions are very important in the estimation process. To reduce the effect of initial conditions, a set of Extended Kalman Filter is introduced. Simulation results are provided to show the effectiveness of the proposed methodology.
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[2] H. Shi, Z. Chen, J. Zhu and M. Kuang, “Model Predictive Guidance for Active Aircraft Protection from a Homing Missile,” IET Control Theory & Applications, vol. 16, no. 2, pp. 208-218, January 2022, doi: 10.1049/cth2.12218.
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[5] J. H. Oh and I. J. Ha, “Capturability of the 3-Dimensional Pure PNG Law,” IEEE Transactions on Aerospace and Electronic Systems, vol. 35, no. 2, April 1999, doi: 10.1109/7.766931.
[6] S. H. Song and I. J. Ha, “A Lyapunov-Like Approach to Performance Analysis of 3-Dimensional Pure PNG Laws,” IEEE Transactions on Aerospace and Electronic Systems, vol. 30, no. 1, January 1994, doi: 10.1109/7.250424.
[7] R. G. Brown and P. Y. C. Hwang, Introduction to Random Signals and Applied Kalman Filter, John Wiley & Sons, Inc., 1997 (Third Edition).
[8] Y. Kim and J. H. Seo, "The realization of the three dimensional guidance law using modified augmented proportional navigation," Proceedings of 35th IEEE Conference on Decision and Control, December 1996, pp. 2707-2712, vol. 3, doi: 10.1109/CDC.1996.573514.
[9] P. L. Vergez, “Tactical Missile Guidance with Passive Seekers Under High Off-Boresight Launch Conditions,” AIAA Journal of Guidance, Control and Dynamics, vol. 21, no. 3, May-June 1998, doi: 10.2514/2.4259.
[10] P. L. Vergez and R. K. Liefer, “Target Acceleration Modeling for Tactical Missile Guidance,” AIAA Journal of Guidance, Vol. 7, No. 3, May-June 1984, doi: 10.2514/3.19861.
[11] C. K. Chui and G. Chen, Kalman Filtering, Springer-Verlag, 1987.
[12] H. W. Sorenson, Kalman Filtering : Theory and Application, IEEE Press, 1985.
[13] N. Peach, “Bearings-Only Tracking Using a Set of Range-Parameterised Extended Kalman Filters,” IEE Proc. Control Theory Application, vol. 142, no. 1, January 1995, doi: 10.1049/ip-cta:19951614.
_||_[1] N. F. Palumbo, R. A. Blauwkamp and J. M. Lloyd, “Modern Homing Missile Guidance Theory and Techniques,” Johns Hopkins APL Technical Digest, vol. 29, no. 1, 2010.
[2] H. Shi, Z. Chen, J. Zhu and M. Kuang, “Model Predictive Guidance for Active Aircraft Protection from a Homing Missile,” IET Control Theory & Applications, vol. 16, no. 2, pp. 208-218, January 2022, doi: 10.1049/cth2.12218.
[3] C. F. Lin, Integrated, Adaptive, and Inteligent Navigation, Guidance, and Control Systems Design. Prentice-Hall, 1991.
[4] C. F. Lin, Modern Navigation, Guidance, and Control Processing, Prentice-Hall. Inc., 1991.
[5] J. H. Oh and I. J. Ha, “Capturability of the 3-Dimensional Pure PNG Law,” IEEE Transactions on Aerospace and Electronic Systems, vol. 35, no. 2, April 1999, doi: 10.1109/7.766931.
[6] S. H. Song and I. J. Ha, “A Lyapunov-Like Approach to Performance Analysis of 3-Dimensional Pure PNG Laws,” IEEE Transactions on Aerospace and Electronic Systems, vol. 30, no. 1, January 1994, doi: 10.1109/7.250424.
[7] R. G. Brown and P. Y. C. Hwang, Introduction to Random Signals and Applied Kalman Filter, John Wiley & Sons, Inc., 1997 (Third Edition).
[8] Y. Kim and J. H. Seo, "The realization of the three dimensional guidance law using modified augmented proportional navigation," Proceedings of 35th IEEE Conference on Decision and Control, December 1996, pp. 2707-2712, vol. 3, doi: 10.1109/CDC.1996.573514.
[9] P. L. Vergez, “Tactical Missile Guidance with Passive Seekers Under High Off-Boresight Launch Conditions,” AIAA Journal of Guidance, Control and Dynamics, vol. 21, no. 3, May-June 1998, doi: 10.2514/2.4259.
[10] P. L. Vergez and R. K. Liefer, “Target Acceleration Modeling for Tactical Missile Guidance,” AIAA Journal of Guidance, Vol. 7, No. 3, May-June 1984, doi: 10.2514/3.19861.
[11] C. K. Chui and G. Chen, Kalman Filtering, Springer-Verlag, 1987.
[12] H. W. Sorenson, Kalman Filtering : Theory and Application, IEEE Press, 1985.
[13] N. Peach, “Bearings-Only Tracking Using a Set of Range-Parameterised Extended Kalman Filters,” IEE Proc. Control Theory Application, vol. 142, no. 1, January 1995, doi: 10.1049/ip-cta:19951614.