Nonlinear Non-minimum Phase Flight Vehicle Control Using Dynamic Sliding Manifold

Authors

1 Mechanical Engineering Department, Amirkabir University of Technology, Tehran, Iran

2 Corresponding Author, Mechanical Engineering Department, Amirkabir University of Technology, Tehran, Iran

3 Aerospace Engineering Department, KNToosi University of Technology, Tehran, Iran

Abstract

Design and synthesis of a nonlinear non-minimum phase supersonic flight vehicle longitudinal dynamics control for g commands output tracking are presented. The non-minimum nature of the resulting input/output pair necessitates using a modified switching manifold in sliding mode control theory. Dynamic sliding manifold is designed to compensate for unstable internal dynamics of the system associated with the coupling between the moment generating actuators and the aerodynamic forces on the flight vehicle. The employed method is simple to implement in practical applications and enables the sliding mode control design to exhibit the desired dynamic properties during the entire output-tracking process independent of matched perturbations and accommodates to unmatched perturbations. Results of simulations are presented to demonstrate the performance, robustness, and stability of the considered autopilot.

Keywords

References

 
[1]     Isidori, A. “Nonlinear Control Systems, Springer,” (1995).
 
[2]    Utkin, V. I., Guldner, J., and Shi J., “Sliding Modes in Electromechanical Systems,” Taylor and Francis, London, (1998).
 
[3]    Shkolnikov, I. A., and Shtessel, Y., “Tracking in a Class of Non-minimum Phase Systems with Nonlinear Internal Dynamics via Sliding Mode Control using Method of System Center,” Automatica, Vol. 38,pp. 837-842, (2002).
 
[4]    Byrnes, C. I., and Isidori, A., “Output Regulation for Nonlinear Systems: An Overview,” International Journal of Robust and Nonlinear Control, Vol. 10, pp. 323-337, (2000).
 
[5]    Shkolnikov, I. A., and Shtessel, Y., “Tracking Controller Design for a Class of Non-minimum Phase Systems via the Method of System Center,” IEEE Transaction on Automatic Control, Vol. 46, No. 10, pp. 1639-1643, (2001).
 
 
[6]    Gopalswmy, S., and Hedrick, J. K., “Tracking Nonlinear Non-minimum Phase System using Sliding Control,” International Journal of Control, Vol. 57, No. 5, pp. 1141-1158, (1993).
 
[7]    Devasia, S., Chen, D., and Paden, B., “Nonlinear Inversion-based Output Tracking,” IEEE Transaction on Automatic Control, Vol. 41, pp. 930-942, (1996).
 
[8]    Mehrabian, A. R., and Roshanian, J., “Skid-to-turn Missile Autopilot Design using Scheduled Eigenstructure Assignment Technique,” Journal of Aerospace Engineering, Imech Part G, Vol. 220, pp. 225-239, (2006).
 
[9]    Nichols, R. A., Richert, R. T., and Rugh, W. J., “Gain Scheduling for H∞ Controllers: A Flight Control Example,” IEEE Transaction on Control Systems Technology, Vol. 1, No. 2, pp.69-79, (1993).
 
[10]  Shtessel, Y. B., “Nonlinear Output Tracking in Conventional and Dynamic Sliding Manifolds,” IEEE Transaction on Automatic Control, Vol. 42, No. 9, pp. 1282-1286, (1997).
 
[11]  Zhu, J. J., and Mickle, M. C., “Missile Autopilot Design using a New Linear Time-varying Control Technique,” Journal of Guidance, Control, and Dynamics, Vol. 20, No. 1, pp. 150-157, (1997).
 
[12]  US Standard Atmosphere, (US government printing office, Washington, D. C), (1976).
 
[13]  Oesterom, M., and Babuska, R., “Design of a Gain Scheduling Mechanism for Flight Control Laws by Fuzzy Clustering,” Control Engineering Practice, Vol. 14, No. 7, pp. 769-781, (2006).
 
[14]  Decarlo, R., Zak, S. H., and Matthews, G. P., “Variable Structure Control of Nonlinear Multivariable Systems: A Tutorial,” IEEE Proceedings, Vol. 76, No. 3, pp. 212-232, (1988)

Files

Share

How to cite

Statistics