System for reducing the dynamic behavior of the movable segment of a deployable nozzle for a rocket engine

Patent metadata

Field	Value
Publication number	US-9494110-B2
Application number	US-201214119648-A
Country	US
Kind code	B2
Filing date	May 15, 2012
Priority date	May 23, 2011
Publication date	Nov 15, 2016
Grant date	Nov 15, 2016

Abstract

A deployable nozzle for a rocket engine, the nozzle including at least a stationary divergent segment and a movable divergent segment that is coaxial about the stationary divergent segment and configured to move along the stationary divergent segment from a retracted position towards a deployed position. The deployable nozzle further includes a transverse stiffener that is prestressed in tension and that extends transversely relative to the movable divergent segment in a vicinity of a downstream end of the movable divergent segment between at least two points at a periphery of an inside wall of the movable divergent segment.

First claim

The invention claimed is:

1. A deployable nozzle for a rocket engine, the nozzle comprising:
at least a stationary divergent segment;
a movable divergent segment that is coaxial about the stationary divergent segment and is configured to move along the stationary divergent segment from a retracted position towards a deployed position; and
a transverse stiffener that is prestressed in tension and that extends transversely relative to the movable divergent segment in a vicinity of a downstream end of the movable divergent segment between at least two points at a periphery of an inside wall of the movable divergent segment.

2. A deployable nozzle according to claim 1 , wherein the transverse stiffener extends in a transverse plane of the movable divergent segment.

3. A deployable nozzle according to claim 1 , wherein the transverse stiffener comprises at least one tie extending diametrically and having two ends, each end being connected to a point of the periphery of the inside wall of the movable divergent segment.

4. A deployable nozzle according to claim 1 , wherein the transverse stiffener comprises at least two ties extending radially from a primary central body.

5. A deployable nozzle according to claim 1 , wherein the transverse stiffener comprises adjustment means for adjusting a prestress tension.

6. A deployable nozzle according to claim 1 , wherein the transverse stiffener comprises at least one cord made of polymer fibers.

7. A deployable nozzle according to claim 1 , wherein the transverse stiffener comprises fastener means for fastening to the movable divergent segment and secured to the movable divergent segment.

8. A deployable nozzle according to claim 1 , wherein, in the retracted position, the transverse stiffener cooperates with a downstream end portion of the stationary divergent segment.

9. A deployable nozzle according to claim 1 , wherein the stationary divergent segment and the movable divergent segment include, in a vicinity of their downstream ends, complementary centering means that cooperate with each other in the retracted position.

10. A deployable nozzle according to claim 9 , wherein the transverse stiffener carries an annular centering skirt that cooperates with a downstream end portion of the stationary divergent segment in the retracted position by mutually engaging therewith.

11. A deployable nozzle according to claim 9 , wherein the transverse stiffener comprises at least two ties extending radially from a primary central body while the downstream end of the stationary divergent segment carries a secondary central body with which the primary central body cooperates in the retracted position by mutual engagement therewith.

12. A deployable nozzle according to claim 11 , wherein the stationary divergent segment includes a further transverse stiffener prestressed in tension comprising at least two ties extending radially in a vicinity of a downstream end of the stationary divergent segment, between at least two points of a periphery of an inside wall of the stationary divergent segment from the secondary central body.

13. A rocket engine comprising at least one deployable nozzle according to claim 1 .

Assignees

• David Noël
• Pyre Alain
• Snecma

Inventors

• David Noël
• Pyre Alain

Classifications

• F02K9/976 Primary

  Deployable nozzles · CPC title

• F05D2260/96

  Preventing, counteracting or reducing vibration or noise · CPC title

• F05D2300/433

  Polyamides, e.g. NYLON · CPC title

• F05D2300/614

  Fibres or filaments · CPC title