| 摘要 |
<p>A rocket engine with an extendible exit cone including an exhaust nozzle for gas from a combustion chamber, the nozzle presenting a longitudinal axis having a first portion defining a nozzle throat and a stationary first exit cone segment, at least one extendible second exit cone segment of section greater than the section of the stationary first exit cone segment, and an extension mechanism for extending the extendible second exit cone segment, the mechanism being located outside the first and second exit cone segments. A rigid thermal protection shield is interposed between the extension mechanism and the stationary first exit cone segment. The thermal protection shield presents a convex wall on its face facing towards the stationary first exit cone segment.</p> |
