Separation device for cryogenic propellant tanks of rocket stages
AssigneeArianegroup SAS
InventorKei Philipp BEHRUZI
Life of this patent
Estimating the term…
Abstract
A separation device for a cryogenic propellant tank of a rocket stage, wherein a secondary flow leading to the micropropulsion unit is structurally separated from a primary flow leading to a main engine, wherein a fan-shaped internal structure, through which the cryogenic liquid has to flow in order to reach the micropropulsion unit, is arranged in the inlet region of the secondary flow, wherein the internal structure is designed in such a way that it fills with liquid under zero gravity conditions and under only low acceleration, as well as during the operation of the micropropulsion unit under acceleration.
Claims10
A separation device for installation in a propellant tank of a rocket stage for cryogenic liquid propellants, the separation device comprising:
- a base body having at least one first region configured to be fluidically connected to a first outlet line of the propellant tank and at least one second region configured to be fluidically connected to a second outlet line of the propellant tank;
- and
- at least one liquid collector arranged in the second region and having an inlet opening for receiving a propellant from a tank interior and an outlet opening for discharging the propellant,
- wherein the at least one liquid collector has an internal structure configured such that the propellant enters the at least one liquid collector based on capillary forces.
Dependencies are inferred from the claim text.