TANK FOR A SPACECRAFT ENGINE

Cryogenic propellant tank (1) for a spacecraft engine, comprising an external enclosure (10) defining an internal volume, characterized in that the internal volume of the tank comprises a primary volume (V1) and a secondary volume (V2) connected to the primary volume (V1) via a valve (20) configured...

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Bibliographische Detailangaben
Hauptverfasser:	VUILLAMY, Didier, EDELINE, Emmanuel, ROZ, Gérard
Format:	Patent
Sprache:	eng
Schlagworte:	AIRCRAFT AVIATION BLASTING COSMONAUTICS FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED,LIQUEFIED, OR SOLIDIFIED GASES FIXED-CAPACITY GAS-HOLDERS HEATING LIGHTING MECHANICAL ENGINEERING PERFORMING OPERATIONS STORING OF DISTRIBUTING GASES OR LIQUIDS TRANSPORTING VEHICLES OR EQUIPMENT THEREFOR VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED ORSOLIDIFIED GASES WEAPONS
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Beschreibung
Zusammenfassung:	Cryogenic propellant tank (1) for a spacecraft engine, comprising an external enclosure (10) defining an internal volume, characterized in that the internal volume of the tank comprises a primary volume (V1) and a secondary volume (V2) connected to the primary volume (V1) via a valve (20) configured to selectively allow a passage of fluid from the primary volume (V1) to the secondary volume (V2), or to isolate the secondary volume (V2) from the primary volume (V1), the primary volume (V1) having a primary orifice (11) adapted to be connected to a first pressurization source (41), the secondary volume (V2) having a supply orifice (4) adapted to be connected to a supply line of a spacecraft engine (30), and a secondary orifice (12) adapted to be connected to a second pressurization source (42).