Suboptimal Guidance and Control Design for a Missile with Onboard Strapdown Seeker

Abstract:

Dynamic inversion control in conjunction with nonlinear suboptimal three dimensional (3-D) guidance law, in terminal phase, is implemented in both the pitch and yaw plane for a short range surface to surface missile with onboard active strapdown seeker. The implemented guidance and control laws intercept the target with a minimum miss distance in addition to meeting the various constraints such as line of sight, seeker field-of-view (FOV), and impact angle. This is achieved using approximate solution to Hamilton-Jacobi-Bellman (HJB) equation [1]. Dynamic inversion control is implemented in two time scales for the inner loop body rate and outer loop angles. Various nonlinearities including that due to the coupling effect between pitch and yaw channels are accounted for in the six-degree-of-freedom (6-DOF) formulation.

• Periodical: Applied Mechanics and Materials (Volumes 110-116)
• Pages: 2513-2520
• DOI: https://doi.org/10.4028/www.scientific.net/AMM.110-116.2513
• Online since: October 2011
• Authors: Netra Singh, Manoranjan Sinha
• Keywords: Dynamic Inversion Control, Field of View, Line of Sight (LOS), Multiple Time Scale, Nonlinear Suboptimal Iteration Guidance, Six-Degrees-Of-Freedom, Strapdown Seeker, Three-Dimensional

References

[1] Xin, Ming and Balakrishnan, S.N., A New Method for Suboptimal Control of A Class of Nonlinear Systems, Optimal Control Applications and Methods, Vol. 26, No. 2, 2005, pp.55-83.

DOI: 10.1002/oca.750

[2] Zarchan, P., Tactical and Strategic Missile Guidance, 4th Ed. Progress in Astronautics and Aeronautics, Vol. 157, AIAA.

[3] Siouris, G., Missile Guidance and Control Systems, Springer, New York, NY, (2004).

[4] Roskam, J., Aircraft Flight Dynamics and Automatic Flight Controls (Part I), DAR Corporation, Lawrence, KS, (2003).

[5] P. N. Dwivedi, A. Bhattacharya and P. Kumar, Nonlinear Autopilot Design via Sliding Mode: Two Different Approaches, AIAA Guidance, Navigation and Control Conference and Exhibit, 21 - 24 August, 2006, Keystone, Colorado.

[6] Ito, D., Georgie, J., Valasek, J., and Ward, D. T., Re-entry Vehicle Flight Controls Design Guidelines: Dynamic Inversion, NASA TP 2002-210771, Texas A&M University, (2002).

[7] A. Das, R. Das, S. Mukhopadhyay, and A. Patra, Nonlinear autopilot and observer design for a surface-to-surface, skid-to-turn missile, IEEE INDICON Conference, Chennai, India, December (2005).

DOI: 10.1109/indcon.2005.1590178

[8] Snell, S. A., Enns, D. F., and Garrard Jr., W. L., Nonlinear Inversion Flight Control for a Supermaneuverable Aircraft, Journal of Guidance, Control and Dynamics, Vol. 15, No. 4, July - Aug. 1992, pp.976-984.

DOI: 10.2514/3.20932