Snecma

Arianegroup Sas

Airbus Safran Launchers Sas

Jacques Lelong

Noël David

Robert Gazave

Nicolas Ravier

Michel Fiolek

Frédérick Millon

Romain Stephant

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

A divergent segment includes a stationary divergent portion and a movable divergent portion suitable for occupying a retracted position and a deployed position. The threaded rod has a head supported by a support secured to the stationary divergent portion in cooperation with a rotary drive for driving the threaded rod in rotation, and a tip suitable for being inserted in a holder sleeve secured to the stationary divergent portion. The threaded rod cooperates with a nut secured to the movable divergent portion so that rotation of the rod causes the movable divergent portion to move. The tip presents an enlargement having at least one groove passing axially therethrough.

Threaded rod for system for deploying a deployable divergent segment of a thruster

Growing community of inventors

Puiseux En Bray, France

Jacques Lelong