The main objective of the RESEARCH project is the definition of an electrical architecture for a Flight Control System capable of controlling the flight control surface on an aircraft with the help of electrically operated actuators, thus replacing the hydraulic actuators commonly used in current aircraft designs.
This architecture will be designed with the main objective of being electrical, in line with the main purpose of this call, and certifiable, with the intention of possible use in future aircraft.
The objective of the RESEARCH project is to find a robust architecture to meet the constraints imposed by safety regulations while keeping other system performances (as weight, reliability) as optimal as possible.