ROCKET MOTOR WITH COMPOSITE DIVERGENT NOZZLE SECTION

ROCKET MOTOR WITH COMPOSITE DIVERGENT NOZZLE SECTION

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...

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Hauptverfasser: ZORRILLA, Xavier, PICHON, Thierry, LONGUEVILLE, Laurent, HERRAIZ, Ivan
Format: Patent
Sprache:eng
Schlagworte:
BLASTING
COMBUSTION ENGINES
HEATING
HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
JET-PROPULSION PLANTS
LIGHTING
MECHANICAL ENGINEERING
WEAPONS
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creator ZORRILLA, Xavier
PICHON, Thierry
LONGUEVILLE, Laurent
HERRAIZ, Ivan
description 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.
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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. 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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. 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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.</abstract><oa>free_for_read</oa></addata></record>
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subjects BLASTING
COMBUSTION ENGINES
HEATING
HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
JET-PROPULSION PLANTS
LIGHTING
MECHANICAL ENGINEERING
WEAPONS
title ROCKET MOTOR WITH COMPOSITE DIVERGENT NOZZLE SECTION
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