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Despite the advances in aircraft guidance and control systems technology,Loss of Control remains as the main cause of the fatal accidents of largetransport aircraft. Loss of Control is defined as excursion beyond theallowable flight envelope and is often a consequence of upset condition ifimproper maneuver is implemented by the pilot. Hence, extensive research inrecent years has focused on improving the current fault tolerant controlsystems and developing new strategies for loss of control prevention andrecovery systems. However, success of such systems requires the perception ofthe damaged aircraft's dynamic behavior and performance, and understanding ofits new flight envelope. This paper provides a comprehensive understanding oflateral control surfaces' failure effect on the NASA Generic Transport Model'smaneuvering flight envelope; which is a set of attainable steady statemaneuvers herein referred to as trim points. The study utilizes a massivedatabase of the Generic Transport Model's high-fidelity maneuvering flightenvelopes computed for the unimpaired case and wide ranges of aileron andrudder failure cases at different flight conditions. Flight envelope boundaryis rigorously investigated and the key parameters confining the trim points atdifferent boundary sections are identified. Trend analysis of the impairedflight envelopes and the corresponding limiting factors is performed whichdemonstrates the effect of various failure degrees on the remaining feasibletrim points. Results of the post-failure analysis can be employed in emergencypath planning and have potential uses in the development of aircraft resilientcontrol and upset recovery systems.

Evaluating the Effects of Control Surfaces Failure on the GTM