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as the electrical network of the future aircraft becomes more and more complex, there is a need to develop a smart controller that can enable fast and automatic decisions to be taken to protect the vital operations of the system. This work aims to show how a control strategy can be devised to ensure the safe operation of such an electrical power system (EPS). The case study presented in this paper demonstrates how a smart controller can be used to ensure the uninterrupted power supply to the high priority loads in the event of the failure of one to four power electronic converters. The control logics are developed using the finite state machine (FSM) method, and applied to a representative DC based EPS of the future aircraft. The results are verified in Simulink environment.

In recent years, electrical machines are employed in an ever-increasing number of safety-critical applications, which require high power density, along with a demanding level of reliability and/or fault-tolerance capability. Multi-phase machines are generally considered a suitable option for satisfying these constraints. Among them, the dual three-phase configuration claims the additional benefit of being operated through conventional power electronics converters and control strategies. Despite the undeniable advantages and their wide diffusion, the thermal modelling of dual three-phase machines still represents an open research topic. Thus, this paper proposes the thermal analysis of a dual three-phase permanent magnet synchronous machine, highlighting the thermal coupling between the two winding sets. An experimentally fine-tuned lumped parameter thermal network is initially presented. Then, due to its relatively high number of nodes, a reduced order thermal network using only 3 nodes is developed. Finally, both thermal networks are examined and compared under several load conditions, in terms of accuracy and computational burden.

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Weight reduction is a key driver in the aerospace sector. Every kilogram of weight reduction has significant benefits over the aircraft's life cycle. This paper introduces a smart power management technique which is able to reduce the overload on the main aircraft generators. If implemented this would allow the generator size to be reduced at the design stage as no overload capability would be required. The paper first introduces the theoretical and mathematical background of the smart power management controller, utilizing both Linear Temporal Logic and a Finite State Machine. A case study is then used to show the derivation of the controller and demonstrate how smart reconfiguration of power paths (e.g. peak request of power) can reduce the overload on the main aircraft generators.