Abstract: Disclosed is a drive device, in particular for a flying vehicle such as an aircraft or a spacecraft, comprising at least one engine and a device for cooling the engine, the device for cooling the engine comprising a cryogenic refrigerator, i.e. refrigerating to a temperature between ?100° C. and ?273° C.

Abstract: The invention relates to a cryogenic tank comprising an inner shell intended to contain the cryogenic fluid, an outer shell arranged around the inner shell and delimiting a space between the two shells under vacuum, the outer shell extending in a longitudinal direction and having a plurality of reinforcing ribs distributed in planes that are perpendicular to the longitudinal direction, the ribs being formed by deformations, for example by knurling, on one and the same wall of the outer shell, wherein the tank also includes at least one reinforcing element for reinforcing at least part of at least one of the ribs, the reinforcing element comprising a strip rigidly connected to the two portions of the wall situated at the base and on either side of the rib.

Abstract: Method for cryogenic cooling of a first fluid by heat exchange with at least one second fluid in a heat exchanger, the first fluid and/or the second fluid being at a temperature between ?100° C. and ?273° C., wherein the heat exchanger is of the type with polymer microtubes, i.e. comprising a plurality of microtubes made of polymer and having a diameter of between 0.1 mm and 1 cm, one of the first and second fluids being circulated inside said microtubes while the other fluid is circulated around said microtubes.

Abstract: An aircraft propulsion unit is described. The unit may include a gas generator with a fan surrounded by a casing. A nacelle may extend around the casing and define an annular compartment with the casing wherein some equipment may be housed. An air inlet may be configured so a ventilation air flow penetrates inside the compartment. An air outlet may be configured so a ventilation air flow is evacuated from the compartment. The propulsion unit may also include an air flow adjustment regulator. The air flow adjustment regulator may be configured to maintain a nominal value of the ventilation air flow circulating through at least one of the air inlet and of the air outlet under nominal operating conditions, and to reduce the value of this ventilation air flow when a fire is detected inside the compartment.

Abstract: An aircraft propulsion unit is described. The unit may include a gas generator with a fan surrounded by a casing. A nacelle may extend around the casing and define an annular compartment with the casing wherein some equipment may be housed. An air inlet may be configured so a ventilation air flow penetrates inside the compartment. An air outlet may be configured so a ventilation air flow is evacuated from the compartment. The propulsion unit may also include an air flow adjustment regulator. The air flow adjustment regulator may be configured to maintain a nominal value of the ventilation air flow circulating through at least one of the air inlet and of the air outlet under nominal operating conditions, and to reduce the value of this ventilation air flow when a fire is detected inside the compartment.