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...

Ausführliche Beschreibung

Gespeichert in:

Bibliographische Detailangaben
Hauptverfasser:	ZORRILLA, Xavier, PICHON, Thierry, LONGUEVILLE, Laurent, HERRAIZ, Ivan
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	BLASTING COMBUSTION ENGINES HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MECHANICAL ENGINEERING WEAPONS
Online-Zugang:	Volltext bestellen
Tags:	Tag hinzufügen Keine Tags, Fügen Sie den ersten Tag hinzu!

Beschreibung
Zusammenfassung:	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.