Safran Aircraft Engines

Snecma

Arianegroup Sas

Robert Gazave

Frédérick Millon

Didier Vuillamy

Jacques Lelong

A nozzle () for a space vehicle engine (M), the nozzle comprising a stationary portion () and a movable portion (), the nozzle () including a pneumatic deployment system () comprising: a deployment actuator () for deploying the movable portion () of the nozzle (); a high unlocking actuator (); a low unlocking actuator (); and an ejector (); the deployment system () including a feed system () configured so as to, sequentially: move the deployment actuator () from its support position towards its deployment position; move the high and low unlocking actuators () into their high and low unlocking positions; and actuate the ejector so as to eject the deployment system () from the nozzle ().

Spacecraft nozzle comprising an improved deployment system

An assembly comprising a duct () for passing a flow of cryogenic fluid, and a valve (); the assembly being characterized in that the duct () includes an interface for inserting the valve, the interface forming an internal abutment () and an external abutment (); the valve () being configured in such a manner as to be inserted into said insertion interface by sliding, the valve () comprising a valve body () presenting a first end () and a second end (), the valve body () being adapted to be bolted in said insertion interface in such a manner that the first end () and the second end () come into abutment respectively against the internal abutment () and against the external abutment (), the assembly including an internal sealing element () arranged between the internal abutment () and the first end (), and an external sealing element () arranged between the external abutment () and the second end ().

Interface for a valve for a cryogenic fluid duct

The rocket engine nozzle system comprises a set of individual nozzles distributed in a ring around a central core of axially symmetrical shape that presents a central axis. Each individual nozzle placed at the periphery of the central core comprises a circular section throat for receiving gas from a combustion chamber, and a diverging portion that is tangential to the central core. The diverging portion has an outlet section that presents first and second lateral sides that converge radially towards the central axis of the central core, a curved outer side having its convex side facing outwards, and an inner side situated in the vicinity of the central core.

Growing community of inventors

Panilleuse, France

Robert Gazave