Towards More Resilient Flight Control Within the aviation community, especially for commercial transport aircraft design, all developments focus on ensuring and improving the required safety levels and reducing the risks that critical failures occur. Recent airliner accident and incident statistics (published in 2008), [8], show that about 16% of the accidents between 1993 and 2007 can be attributed to Loss of Control In-flight (LOC-I), caused by a piloting mistake (e.g. due to spatial disorientation), technical malfunctions or unusual upsets due to external disturbances. Loss of flight control is a subcategory of Loss of Control In-flight (LOC-I), where a technical malfunction is the initial event which causes control loss. LOC-I remains the second largest accident category after Controlled Flight Into Terrain (CFIT) which accounts for 23% of air accidents. However, a short term study for the year 2008 shows that loss of control comes at the top in the list of catastrophic accidents, according to the UK Civil Aviation Authority (UK-CAA). Data examined by the international aviation community shows that, in contrast to CFIT, the share of LOC-I occurrences is not significantly decreasing. Resilient flight control, or fault tolerant flight control (FTFC), allows improved survivability and recovery from adverse flight conditions induced by faults, damage and associated upsets. This can be achieved by ‘intelligent’ utilisation of the control authority of the remaining control effectors in all axes consisting of the control surfaces and engines or a combination of both. In this technique, control strategies are applied to restore stability and manoeuvrability of the vehicle for continued safe operation and a survivable recovery. The aim of the GARTEUR Flight Mechanics Action Group FM-AG(16) on Fault Tolerant Flight Control, of which this book is the culmination, was to facilitate the proliferation of new developments in fault tolerant control design within the European aerospace research community in practical and real-time operational applications. This addresses the need to improve the resilience and safety of future aircraft and aiding the pilot to recover from adverse conditions induced by (multiple) system failures and damage that would otherwise be potentially catastrophic. Up until now, faults or damage on board aircraft have been accommodated by hardware design using duplex, triplex or even quadruplex redundancy of critical components. However, the approach of the research presented in this book is to focus on new control law design methods to accommodate (unanticipated) faults and/or damage that dramatically change the configuration of the aircraft. These methods take into account a unique combination of robustness, reconfiguration and (real-time) adaptation of the control laws.


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