Commenced in January 2007
Frequency: Monthly
Edition: International
Paper Count: 30184
Siding Mode Control of Pitch-Rate of an F-16 Aircraft

Authors: Ekprasit Promtun, Sridhar Seshagiri

Abstract:

This paper considers the control of the longitudinal flight dynamics of an F-16 aircraft. The primary design objective is model-following of the pitch rate q, which is the preferred system for aircraft approach and landing. Regulation of the aircraft velocity V (or the Mach-hold autopilot) is also considered, but as a secondary objective. The problem is challenging because the system is nonlinear, and also non-affine in the input. A sliding mode controller is designed for the pitch rate, that exploits the modal decomposition of the linearized dynamics into its short-period and phugoid approximations. The inherent robustness of the SMC design provides a convenient way to design controllers without gain scheduling, with a steady-state response that is comparable to that of a conventional polynomial based gain-scheduled approach with integral control, but with improved transient performance. Integral action is introduced in the sliding mode design using the recently developed technique of “conditional integrators", and it is shown that robust regulation is achieved with asymptotically constant exogenous signals, without degrading the transient response. Through extensive simulation on the nonlinear multiple-input multiple-output (MIMO) longitudinal model of the F-16 aircraft, it is shown that the conditional integrator design outperforms the one based on the conventional linear control, without requiring any scheduling.

Keywords: Sliding-mode Control, Integral Control, Model Following, F-16 Longitudinal Dynamics, Pitch-Rate Control.

Digital Object Identifier (DOI): doi.org/10.5281/zenodo.1072217

Procedia APA BibTeX Chicago EndNote Harvard JSON MLA RIS XML ISO 690 PDF Downloads 2798

References:


[1] R.J. Adams, J.M. Buffington, and S.S Banda. Design of nonlinear control laws for high-angle-of-attack flight. Jnl. Guidance, Control, and Dynamics, 17(4):737-745, 1994.
[2] G.J. Balas. Flight control law design: An industry perspective. European Jnl. of Ctrl., 9(2-3):207-226, 2003.
[3] C. Barbu, S. Galeani, A.R. Teel, and L. Zaccarian. Non-linear antiwindup for manual flight control. Intl. Jnl. of Ctrl., 78(14):1111-1129, 2005.
[4] R. Bhattacharya, Balas. G., M. Kaya, and A. Packard. Nonlinear receding horizon control of an F-16 aircraft. Jnl. Guidance, Control, and Dynamics, 25(5):924-931, 2002.
[5] J.M. Biannic and P. Apkarian. Parameter varying control of a high performance aircraft. In Proc. AIAA, Guidance, Navigation and Control Conference, pages 69-87, 1996.
[6] Y.J. Huang, T.C. Kuo, and H.K. Way. Robust vertical takeoff and landing aircraft control via integral sliding mode. Control Theory and Applications, IEE Proceedings-, 150:383-388, 2003.
[7] Y. Huo, M. Mirmirani, P. Ioannou, and R. Colgren. Adaptive linear quadratic design with application to F-16 fighter aircraft. In AIAA Guidance, Navigation, and Control Conference and Exhibit, August 2004.
[8] E.M. Jafarov and R. Tasaltin. Robust sliding-mode control for the uncertain MIMO aircraft model F-18. IEEE Trans. Aerospace Electronic Sys., 36(4):1127-1141, 2000.
[9] T. Keviczky and G. Balas. Receding horizon control of an F-16 aircraft: A comparative study. Control Engg. Practice, 14(9):1023-1034, 2006.
[10] H.K. Khalil. Universal integral controllers for minimum phase nonlinear systems. IEEE Trans. Aut. Ctrl., 45(3):490-494, 2000.
[11] D.A. Lawrence and W.J. Rugh. Gain scheduling dynamic linear controllers for a nonlinear plant. Automatica, 31(3):381-390, 1995.
[12] T. Lee and Y. Kim. Nonlinear adaptive flight control using backstepping and neural networks controller. Jnl. Guidance, Control, and Dynamics, 24(4):675-682, 2001.
[13] B. Lu. Linear Parameter-Varying Control of an F-16 Aircraft at High Angle of Attack. PhD thesis, North Carolina State University, 2004.
[14] B. Lu, F. Wu, and S. Kim. LPV antiwindup compensation for enhanced flight control performance. Jnl. Guidance, Control and Dynamics, 28:495-505, 2005.
[15] J-F. Magni, S. Bennani, and J. Terlouw (Eds). Robust Flight Control: A Design Challenge. Lecture Notes in Control and Information Sciences - Vol 224. Springer, 1998.
[16] L.T. Nguyen, M.E. Ogburn, W.P. Gillert, K.S. Kibler, P.W. Brown, and P.L. Deal. Simulator study of stall/post-stall characteristics of a fighter airplane with relaxed longitudinal static stability. NASA Technical Paper 1538, 1979.
[17] E. Promtun. Sliding Mode Control of F-16 Longitudinal Dynamics. MS. Thesis, San Diego State University, San Diego, USA, 2007.
[18] E. Promtun and S. Seshagiri. Sliding mode control of pitch-rate of an F-16 aircraft. In 17th IFAC World Congress, Seoul, S. Korea, July 2008.
[19] W.C. Reigelsperger and S.S. Banda. Nonlinear simulation of a modified F-16 with full-envelope control laws. Control Engineering Practice, 6:309-320, 1998.
[20] Richard S. Russell. Non-linear F-16 simulation using Simulink and Matlab. Technical report, University of Minnesota, June 2003.
[21] R. Rysdyk and A.J. Calise. Robust nonlinear adaptive flight control for consistent handling qualities. IEEE Trans. Aut. Ctrl., 13(6):896-910, 2005.
[22] S. Seshagiri and H.K. Khalil. Robust output feedback regulation of minimum-phase nonlinear systems using conditional integrators. Automatica, 41(1):43-54, 2005.
[23] S. Seshagiri and E. Promtun. Sliding mode control of F-16 longitudinal dynamics. In 2008 American Control Conference, Seattle, Washington, U.S.A, June 2008.
[24] J.S. Shamma and J.S. Cloutier. Gain-scheduled bank-to-turn autopilot design using linear parameter varying transformations. Jnl. Guidance Control and Dynamics, 9(5):1056-1063, 1996.
[25] Y. Shtessel, J. Buffington, and S. Banda. Tailless aircraft flight control using multiple time scale reconfigurable sliding modes. IEEE Trans. Ctrl. Sys. Tech., 10(2):288-62, 2002.
[26] S.A. Snell, D.F. Enns, and Jr. W.L. Garrard. Nonlinear inversion flight control for a supermaneuverable aircraft. Jnl. Guidance, Control, and Dynamics, 15(4):976-984, 1992.
[27] Lars Sonneveldt. Nonlinear F-16 model description. Technical report, Delft University of Technology, The Netherlands, June 2006.
[28] M.S. Spillman. Robust longitudinal flight control design using linear parameter-varying feedback. Jnl. Guidance, Control, and Dynamics, 23(1):101-108, 2000.
[29] B.L. Stevens and F.L. Lewis. Aircraft Control and Simulation. John Wiley & Sons, Inc., 2 edition, 2003.
[30] H. Vo and S. Seshagiri. Robust control of F-16 lateral dynamics (accepted). In 2008 IEEE IECON08, Orlando, Florida, U.S.A, Nov 2008.
[31] A. Young, C. Cao, N. Hovakimyan, and E. Lavretsky. An adaptive approach to nonaffine control design for aircraft applications. In AIAA Guidance, Navigation, and Control Conference and Exhibit, Keystone, CO, USA, August 2006.
[32] K.D. Young, V.I. Utkin, and U. Ozguner. A control engineer-s guide to sliding mode control. IEEE Trans. Ctrl. Sys. Tech., 7(3):328-342, 1999.