| Issue |
Volume 6, 2013
Progress in Flight Dynamics, Guidance, Navigation, Control, Fault Detection, and Avionics
|
|
|---|---|---|
| Page(s) | 347 - 362 | |
| Section | Fault detection and control | |
| DOI | https://doi.org/10.1051/eucass/201306347 | |
| Published online | 02 December 2013 | |
Flight dynamics analysis and control of transport aircraft subject to failure
1
Istanbul Technical University Department of Aeronautical Engineering Istanbul 34469, Turkey
2
Anadolu University Faculty of Aeronautics and Astronautics Eskisehir 26470, Turkey
After a structural damage or component failure during any flight mode, aircraft dynamics are dramatically altered. A quick and adequate stabilization effort is crucial. Flight dynamics for several failure scenarios are analyzed. Necessary amounts of control deflections for postfailure trim are calculated. These trim values are used as control input in an open loop manner and validity of this approach is tested via flight simulations. Alternatively, a closed loop flight control system, which does not need the postfailure trim values, is also designed. This closed loop controller is based on a linearized aircraft model whereas flight simulations are based on nonlinear aircraft dynamics.
© 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.