Patent ID: 6289671
Filing Date: 2001-09-18
Classification: F02K

Abstract:
A plug for a liquid-propellant rocket engine chamber nozzle, the plug comprising:an axial rod having a first end with a stopper and a second end, wherein the rod is positioned substantially along a longitudinal axis of the plug;a system for maintaining the plug in a nozzle throat, said system comprising a sleeve fixedly attached on said second end of said axial rod, a plurality of structural ribs extending in a radial direction from said sleeve, a plurality of spring-loaded levers each being securely hinged on an end of a respective one of said structural ribs and a plurality of rollers each arranged on an end portion of a respective one of said levers, said levers being positioned for causing contact of said rollers with a wall of said nozzle throat;a movement limiter comprising a cross slide movable on said axial rod for interaction with said sleeve of said maintaining system, a shell and a plurality of structural elements connecting said cross slide and said shell; anda sealing valve comprising a disc slidably mounted on said axial rod, a first loaded spring positioned on said axial rod between said stopper and said disc and a second loaded spring positioned between said disc and said cross slide.