| Issue |
Volume 6, 2013
Progress in Flight Dynamics, Guidance, Navigation, Control, Fault Detection, and Avionics
|
|
|---|---|---|
| Page(s) | 175 - 188 | |
| Section | Guidance and control | |
| DOI | https://doi.org/10.1051/eucass/201306175 | |
| Published online | 02 December 2013 | |
Aircraft pitch attitude adaptive control via singular perturbation technique
Novosibirsk State Technical University 20 K. Marx Av., Novosibirsk 630092, Russia
The problem of aircraft pitch attitude control is treated in the presence of uncertain aerodynamics. The proposed design methodology guarantees desired pitch attitude transient performance indices by inducing of two-time-scale motions in the closed-loop system where the controller dynamics is a singular perturbation with respect to the system dynamics. The singular perturbation method is used in order to get explicit expressions for evaluation of the controller parameters. Stability of fast-motion transients for a large range of aerodynamic characteristics variations is maintained due to a high-frequency-gain online identification and gain tuning that are incorporated in the control loop. Numerical example and simulation results are presented.
© Owned by the authors, published by EDP Sciences, 2013
This is an Open Access article distributed under the terms of the Creative Commons Attribution License 2.0, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.