Convex thermal shield for rocket engine with extendable divergent nozzle
US9169807B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Sep 6, 2010 |
| Grant date | Oct 27, 2015 |
| Priority date | — |
| Expiry date | Dec 28, 2032 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF02K9/976
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
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.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.