1
Department of Electrical and Computer Engineering, K. N T University of Technology
2
imam hossein university
Abstract
The conventional methods for designing autopilots deal conservatively with uncertainties such that the autopilot should be slowed down to the extent in which the system can maintain its desired performance in the presence of a certain uncertainty. However, there will be no guarantee of good performance in the presence of all uncertainties while the capabilities of the system will not be used properly. In the proposed method, using the extended state observer, the lumped uncertainties along with the system’s states will be estimated, and using feedback linearization approach, along with the nonlinear terms will be removed from the control loop. What remains is a simple linear system that is easier to control. In this method, uncertainties is treated without conservatism and consequently performance is improved in different conditions. Finally, for comparing the results of proposed method with linear autopilot a 1000 times Mont Carlo running with specific condition has been used and is shown that the proposed method is better than the conventional method in performance.
Balakrishnan, S. N., Tsourdos, A., and White, B. A. “Advances in Missile Guidance, Control, and Estimation”, CRC Press, 2012.##
Williams, D. E., Friedland, B., and Madiwale, A. N. “Modern Control Theory for Design of Autopilots for Bank-to-Turn Missiles”, J. Guid. Control Dyn., Vol. 10, No. 3, pp.378-386, 1987.##
Sun, M., Gao, Z., Du, S., and Chen. Z. "On Active Disturbance Rejection Based Framework for Flight Control: Principle and Applications”, Progress in Flight Dynamics, Guidance, Navigation, and Control, Vol. 10, No. 10, pp. 87-104, 2018.##
Adams, R. J., Buffington, J. M., Sparks, A. G., and Banda, S. S. “Robust Multivariable Flight Control”, Springer Science & Business Media, 2012.##
Adams, R. J., and Banda S. S. “Robust Flight Control Design using Dynamic Inversion and Structured Singular Value Synthesis”, IEEE T. Contr. Syst. T., Vol. 1, No. 2, pp.80-92, 1993.##
Kim, B. S., and Calise A. J. “Nonlinear Flight Control using Neural Networks”, J. Guid. Control Dyn. Vol. 20, No. 1, pp.26-33, 1997.##
Han, J. Q. “From PID to Active Disturbance Rejection Control”, IEEE T, Ind. Electron. Vol. 56, No. 3, pp.900-906, 2009.##
Wu, Z.-H., and Guo, B.-Z. “Active Disturbance Rejection Control to MIMO Nonlinear Systems with Stochastic Uncertainties: Approximate Decoupling and Output-Feedback Stabilisation", Int. J. Control, pp.1-20, 2018.##
Panchal, B., Subramanian, K., and Talole S. E. “Robust Missile Autopilot Design using Two Time-Scale Separation”, IEEE T. Aero. Elec. Sys., Vol. 54, No. 3, pp.1499-1510, 2018.##
Hedrick, J. K., and Gopalswamy, S. “Nonlinear Flight Control Design via Sliding Methods”, J. Guid. Control Dyn., Vol. 13, No. 5, pp.850-858, 1990.##
Benvenuti, L., Di Benedetto, M. D., and Grizzle, J. W. “Approximate Output Tracking for Nonlinear Non‐Minimum Phase Systems with an Application to Flight Control” Int. J. Robust Nonlin., Vol. 4, No. 3 pp.397-414, 1994.##
Hauser, J., Sastry, S., and Meyer, G. “Nonlinear Control Design for Slightly Non-Minimum Phase Systems: Application to V/STOL Aircraft”, Automatica Vol. 28, No. 4, pp. 665-679, 1992.##
Romano, L. J., and Singh, S. N. “IO Map Inversion, Zero Dynamics and Flight Control”, IEEE T. Aero. Elec. Sys., Vol. 26, No. 6, pp. 1022-1029, 1990.##
Isidori, A., Sastry, S. S., Kototovic, P. V., and Byrnes, C. I. “Singularly Perturbed Zero Dynamics of Nonlinear Systems”, IEEE T. Automa. Contr., Vol. 37, No. 10, pp.1625-1631, 1992.##
Lian, K. Y., Fu, L. C., and Liao, T. L. “Robust Output Tracking for Nonlinear Systems with Weakly Non-Minimum Phase”, Int. J. Control, Vol. 58, No. 2, pp.301-316, 1993.##
Lee, J.-I., and Ha, I.-J. “Autopilot Design for Highly Maneuvering STT Missiles via Singular Perturbation-Like Technique”, IEEE T. on Cont. Syst. T., Vol. 7.##
Khan Kalantary, S., & mohammadkhani, H. (2021). Robust Nonlinear Autopilot Design Based on Feedback Linearization and Extended State Observers for Interceptors. Aerospace Mechanics, 17(2), 1-12.
MLA
saeed Khan Kalantary; hassan mohammadkhani. "Robust Nonlinear Autopilot Design Based on Feedback Linearization and Extended State Observers for Interceptors", Aerospace Mechanics, 17, 2, 2021, 1-12.
HARVARD
Khan Kalantary, S., mohammadkhani, H. (2021). 'Robust Nonlinear Autopilot Design Based on Feedback Linearization and Extended State Observers for Interceptors', Aerospace Mechanics, 17(2), pp. 1-12.
VANCOUVER
Khan Kalantary, S., mohammadkhani, H. Robust Nonlinear Autopilot Design Based on Feedback Linearization and Extended State Observers for Interceptors. Aerospace Mechanics, 2021; 17(2): 1-12.
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