An aeronautical cryogenic tank device for storing gas, having a spherical or annular shape about an axis, comprising an inner container (26) defining a liquefied gas storage chamber (28), an outer envelope (27) containing the inner container (26), an insulation chamber (29) defined between the inner container (26) and the outer envelope (27), the reduced-pressure insulation chamber (29) having scaling equal to or better than 10-9 millibar*litre/second, a removable collector (38) passing through the outer envelope (27) and the inner container (26) in a sealed manner, the collector (38) extending over a diameter or a diagonal of the inner container (26) and having a free end close to a bottom of the inner container (26), and a conduit supplied by the collector (38).

An acronautical gas storage cryogenic tank device, comprising an inner container (26) defining a liquefied gas storage chamber (28), an outer envelope (27) containing the inner container (26) and made of a plurality of demountable parts for accessing the inner container (26), the outer envelope (27) being made of a material resistant to temperatures from less than 60 C. to at least +80 C. an insulation chamber (29) defined between the inner container (26) and the outer envelope (27), the reduced-pressure insulation chamber (29) having helium-tightness equal to or better than 10*9) millibar*litre/second defined between the inner container (26) and the outer envelope (27), two connections of which at least one is a sliding connection, supporting the inner container (26) and borne by the outer envelope (27), a removable collector (42) passing through the outer envelope (27) and the inner container (26) in a sealed manner, and a flexible thermally insulating neck (42) forming a sealed interface between the collector on the one hand and, on the other hand, the outer envelope (27) and the inner container (26), the neck (42) being formed around a portion of the collector (38), the neck (42) passing through the insulation chamber (29) in order to allow the collector (38) to be demounted independently of the pressure in the insulation chamber (29).

The invention relates to a valve for pressurized fluid, the valve having a body incorporating a fluid circuit having an upstream end and a downstream end, the circuit having a seal valve, the seal valve enabling the circuit to be opened or closed, the valve having a member for controlling the seal valve, the seal valve being slidably mounted in the body so as to slide between a position in which the circuit is closed when the control member is in a rest position and a position in which the circuit is open when the control member is in an active position, the valve having a deformable member positioned between the seal valve and the control member. The invention also relates to a container or a set of containers for pressurized fluid comprising such a valve.

An aeronautical cryogenic tank device for storing gas, having a spherical or annular shape about an axis, comprising an inner container (26) defining a liquefied gas storage chamber (28), an outer envelope (27) containing the inner container (26), an insulation chamber (29) defined between the inner container (26) and the outer envelope (27), the reduced-pressure insulation chamber (29) having scaling equal to or better than 10-9 millibar*litre/second, a removable collector (38) passing through the outer envelope (27) and the inner container (26) in a sealed manner, the collector (38) extending over a diameter or a diagonal of the inner container (26) and having a free end close to a bottom of the inner container (26), and a conduit supplied by the collector (38).