Rocket motor with composite divergent nozzle section

Patent metadata

Field	Value
Publication number	US-11035321-B2
Application number	US-201716311820-A
Country	US
Kind code	B2
Filing date	Jun 28, 2017
Priority date	Jun 29, 2016
Publication date	Jun 15, 2021
Grant date	Jun 15, 2021

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.

First claim

The invention claimed is:

1. A rocket nozzle presenting a longitudinal axis and comprising both a rocket combustion chamber made of metal material and presenting a downstream end and also a diverging portion made of composite material formed by a wall of conical shape extending between an upstream end and a downstream end, the upstream end of the composite material diverging portion being connected to the downstream end of the rocket combustion chamber; wherein the rocket nozzle further comprises an annular fastener mount made of metal material comprising a first portion that is separate from the combustion chamber and secured to the rocket combustion chamber and a second portion extending beyond the downstream end of the rocket combustion chamber in the direction of the longitudinal axis of the rocket nozzle, the first and second portions of the annular fastener mount being rigidly secured to each other, and wherein the upstream end of the composite material diverging portion is fastened to the second portion of the annular fastener mount by a plurality of fastener members, each comprising a fastener bolt, each fastener bolt passing through the conically-shaped wall of the composite material diverging portion near the upstream end of said wall; wherein the second portion of the annular fastener mount is separate from the rocket combustion chamber and the first portion; and the second portion of the annular fastener mount is fastened to the first portion of the annular fastener mount by fastener members.

2. The rocket nozzle according to claim 1 , wherein the rocket combustion chamber includes a cooling circuit for passing a flow of cooling fluid, the cooling circuit comprising at least a first annular channel for passing the flow of cooling fluid extending along the downstream end of the rocket combustion chamber and in the proximity of the fastener members.

3. The rocket nozzle according to claim 1 , wherein the rocket combustion chamber includes a cooling circuit for passing a flow of cooling fluid, the cooling circuit comprising at least a first annular channel for passing the flow of cooling fluid extending along the downstream end of the rocker combustion chamber and in the proximity of the fastener members.

4. The rocket nozzle according to claim 1 , wherein a gasket is interposed between an inside face of the second portion of the annular mount and an outside face of the wall of the diverging portion.

5. A rocket nozzle presenting a longitudinal axis and comprising both a rocket combustion chamber made of metal material and presenting a downstream end and also a diverging portion made of composite material formed by a wall of conical shape extending between an upstream end and a downstream end, the upstream end of the composite material diverging portion being connected to the downstream end of the rocket combustion chamber; wherein the rocket nozzle further comprises an annular fastener mount made of metal material comprising a first portion secured to the rocket combustion chamber and a second portion extending beyond the downstream end of the rocket combustion chamber in the direction of the longitudinal axis of the rocket nozzle, the first and second portions of the annular fastener mount being rigidly secured to each other, and wherein the upstream end of the composite material diverging portion is fastened to the second portion of the annular fastener mount by a plurality of fastener members, each comprising a fastener bolt, each fastener bolt passing through the conically-shaped wall of the composite material diverging portion near the upstream end of said wall, wherein the annular fastener mount is formed integrally with the rocket combustion chamber, the second portion of the annular fastener mount extending the first portion of said mount, wherein the rocket combustion chamber includes a cooling circuit for passing a flow of cooling fluid, the cooling circuit comprising at least a first annular channel for passing the flow of cooling fluid extending along the downstream end of the rocket combustion chamber and in the proximity of the fastener members, and wherein the first annular channel is upstream from the fastener members and the cooling circuit includes a second annular channel for passing a flow of cooling fluid that extends along a free end of the second portion of the annular mount, said second annular flow channel being present downstream from the fastener members.

6. The rocket nozzle according to claim 5 , wherein the cooling circuit includes a plurality of axial ducts communicating with the first and second annular channels, each axial duct being present between two adjacent fastener members.

7. The rocket nozzle according to claim 6 , wherein a plurality of stiffeners are present on an outside face of the rocket nozzle, the axial ducts communicating with the first and second annular channels being received in the stiffeners.

Assignees

• Arianegroup Sas

Inventors

• Pichon Thierry
• Zorrilla Xavier
• Herraiz Ivan
• Longueville Laurent

Classifications

• F05D2300/603

  Composites; e.g. fibre-reinforced · CPC title

• F02K9/972

  Fluid cooling arrangements for nozzles (F02K9/64 takes precedence) · CPC title

• F02K9/64

  having cooling arrangements · CPC title

• F02K9/97 Primary

  Rocket nozzles (thrust or thrust vector control F02K9/80) · CPC title

• F05D2300/10

  Metals, alloys or intermetallic compounds · CPC title