Abstract: A mechanical flight control system of an aircraft provided with an actuator and a force-measuring device, the actuator comprising at least one electric motor and one duplex calculator per motor, each duplex calculator comprising a control channel, a monitoring channel and two input interfaces, the force-measuring device comprising a plurality of measurement channels each comprising a sensor, an electronic module and an output interface connected to one of the input interfaces. the electronic module is connected to the sensor in order to generate an analog measurement signal and is configured to digitize the analog measurement signal, at least one of the measurement channels applying a delta-sigma modulation, and then to convert it into a digital transfer signal carrying a transfer value representative of a force in the mechanical flight control system.

Abstract: An architecture for transmitting data within an avionics system fitted to a vehicle, the architecture comprising a first field bus and a first avionics bus. According to the invention, the architecture comprises at least two primary channels each comprising: a primary field interface enabling communication between each primary channel via the first field bus, the field interfaces being interconnected with the first field bus; and a first avionics interface compatible with the first avionics bus. The architecture comprises at least one primary computer provided with a second avionics interface in communication via the first avionics bus with only one first avionics interface among the first avionics interfaces.