Abstract: The invention relates to a hybrid propulsion architecture (100) for an aircraft, comprising: —a first source (102) of a first energy type, —second sources (104) of a second energy type different from the first energy type, —electrical propulsion systems (106), —an electric power supply network (118) connecting the first and second sources (102, 104) to the electrical propulsion systems, such that each electrical propulsion system is powered by the first source and by one of the second sources, the architecture being characterised in that it further comprises: —means for segregating (120) the electrical propulsion systems, which means are arranged in the electric power supply network and configured to impose a direction of flow of the electric power from the first source to the electrical propulsion systems.

Abstract: Light signalling device, in particular intended to be mounted on board an aircraft, includes a plurality of light elements mounted on a support and surrounded by a translucent cover, said device including a means of reflecting the light emitted by the light elements disposed near to the light elements, at least one photometric sensor positioned between the support and the reflection means, and a means of comparing a light intensity detected by the photometric sensor with a reference light intensity.

Abstract: Light signalling device, in particular intended to be mounted on board an aircraft, includes a plurality of light elements mounted on a support and surrounded by a translucent cover, said device including a means of reflecting the light emitted by the light elements disposed near to the light elements, at least one photometric sensor positioned between the support and the reflection means, and a means of comparing a light intensity detected by the photometric sensor with a reference light intensity.