Rocket motor with composite divergent nozzle section
US11035321B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jun 28, 2017 |
| Grant date | Jun 15, 2021 |
| Priority date | — |
| Expiry date | Feb 3, 2038 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2300/603
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A nozzle presents a longitudinal axis, includes both a combustion chamber made of metal material and presenting a downstream end, and a diverging portion made of composite material formed by a wall of conical shape extending between an upstream and a downstream end. The upstream end of the composite material diverging portion is connected to the downstream end of the combustion chamber. The nozzle further includes an annular mount made of metal material including a first portion secured to the combustion chamber and a second portion extending beyond the downstream end of the combustion chamber along the longitudinal axis. The upstream end of the composite material diverging portion is fastened to the second portion of the annular mount by a plurality of fastener members, each including a fastener bolt, each fastener bolt passing through the conically-shaped wall of the composite material diverging portion near the upstream end of the wall.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.