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A new distributed control system for fuel management and other avionics applications is introduced. The system consists of a network of smart components such as sensors, valves, and pumps which are connected via a controlled area network bus (CANbus). Thus, no central fuel management computer is required, wiring is simplified, and the weight decreases. The heart of each smart component is a CAN-enabled microcontroller. All smart components share a copy of the same code inside its microcontroller, for easier certification. A distribution methodology has been developed based on a set of automata and on the employment of CANbus (as the communication protocol) for global state broadcasting.

This paper describes the development of a graphic computer tool that facilitates the generation of control software for a new distributed fuel management system for aircraft. The system has been the result of a three-year European Community Research Project. The goal was to move from a centralized control architecture to a fully distributed one, where each component of the system makes a decision by itself and the control of the whole system is a shared task. The interchange of information between components is performed via fieldbuses. The graphic computer tool developed is able to perform an automatic code generation starting from a graphic description of the system provided by the user. Thus, different aircraft fuel system configurations can be considered. According to the specific aircraft under study, they can include more or less tanks and components in the system. For each case, the control code of the distributed system can be quickly modified. It can, then, be integrated in each component device to operate in the system. This paper describes the main ideas of the new distributed avionic system and the graphical tool. Some experimental results in a laboratory plant simulator are also shown.

Aircrafts usually have several fuel tanks, and there are fuel transfers among these tanks along a flight. These transfers are controlled with valves, and may follow several alternative paths, since structural fuel system redundancies are provided for evident reasons. An on board program for the management and reconfiguration of the fuel system must be developed and tested. The article introduces an aircraft fuel management system simulation, which provides a platform for the study of the fuel system logic and sequencing that the on board program must implement for normal flights and for malfunction cases. The simulation environment can be easily modified and extended, for instance to consider the use of new components. A specific example is considered: an aircraft with six tanks in the wings and a tail tank. The article presents a two-layer model, the use of the model for simulation experiments, and some illustrative examples.