Flight dynamics analysis and control of transport aircraft subject to failure

Abstract

After a structural damage or component failure during any §ight mode, aircraft dynamics are dramatically altered. A quick and adequate stabilization e¨ort is crucial. Flight dynamics for several failure scenarios are analyzed. Necessary amounts of control de §ections 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 §ight simulations. Alternatively, a closed loop §ight 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 §ight simulations are based on nonlinear aircraft dynamics.