Launcher stage comprising a temporary support structure for temporarily supporting nozzle sections allowing access to the core of the engine

Patent metadata

Field	Value
Publication number	US-9989015-B2
Application number	US-201314385888-A
Country	US
Kind code	B2
Filing date	Apr 12, 2013
Priority date	Apr 13, 2012
Publication date	Jun 5, 2018
Grant date	Jun 5, 2018

Abstract

A stage of a space launcher including an engine core, a tank secured above the engine core, and a nozzle including a first deployable nozzle section secured below the engine core, the nozzle further including a second and a third section configured to be situated extending from each other when the nozzle is in a deployed propulsion configuration. The stage further includes a structure for temporarily supporting nozzle sections mounted on the tank, configured to change the nozzle to a configuration for accessing the engine core wherein the nozzle sections are inserted into each other, with the third section bearing against a lower support of the temporary structure.

First claim

The invention claimed is:

1. A stage of a space launcher comprising:
in an upright position, an engine core, a tank secured above the engine core, and a deployable nozzle comprising a first deployable nozzle section secured below the engine core;
the deployable nozzle further comprising a second nozzle section borne by a structure enabling deployment of the deployable nozzle, along with a third nozzle section;
the first, second, and third nozzle sections are configured to be situated extending from each other when the deployable nozzle is in a deployed propulsion configuration, with the second nozzle section being situated extending from the first nozzle section, and the third nozzle section being situated extending from the second nozzle section, the second nozzle section bearing the third nozzle section;
the stage further comprising a temporary support structure for temporarily supporting the nozzle sections mounted on the tank, the temporary support structure being suspended from the tank and being configured to change the deployable nozzle to a configuration for accessing the engine core wherein the first deployable nozzle section at least partially enters the second nozzle section, and wherein the second nozzle section at least partially enters the third nozzle section, wherein a lower end of the third nozzle section bears against a lower support of the temporary support structure; and
the first, second, and third nozzle section are configured to be in a launch configuration in which an axial length of the deployable nozzle is reduced by raising the second nozzle section so that a lower end of the second nozzle section is axially situated approximately where an upper end of the first deployable nozzle section is secured to the engine core, the second nozzle section substantially blocking access to the engine core by encompassing the engine core in the launch configuration.

2. A stage according to claim 1 , wherein, in the configuration for accessing the engine core, the lower end of the second nozzle section also bears against the lower support of the temporary support structure.

3. A stage according to claim 1 , wherein, in the configuration for accessing the engine core, an upper end of each of the second and third nozzle sections is situated on a level with or below the upper end of the first deployable nozzle section connected to the engine core.

4. A stage according to claim 1 , wherein the temporary support structure comprises rods connecting the lower support to the tank.

5. A stage according to claim 1 , wherein the lower support is in a shape of a ring.

6. A stage according to claim 1 , wherein the temporary support structure further comprises an upper support situated above an upper end of each of the second and third nozzle sections in the configuration for accessing the engine core.

7. A stage according to claim 6 , wherein the temporary support structure further comprises a connection frame between the upper and lower supports, the connection frame being arranged around the third nozzle section.

8. A space launcher comprising at least one stage according to claim 1 .

9. A method for manufacturing the space launcher including a main stage and an upper stage according to claim 1 , the method comprising:
producing the upper stage, by changing the deployable nozzle to the configuration for accessing the engine core;
transporting the upper stage to a launch pad, with the deployable nozzle in the configuration for accessing the engine core; and
on the launch pad, mounting the upper stage onto the main stage, with the deployable nozzle in the configuration for accessing the engine core.

10. A method for manufacturing the space launcher according to claim 9 , further comprising, prior to a launch: placing the nozzle in a launch configuration, wherein the second nozzle section is arranged around the engine core, and the lower end of the second nozzle section bearing an upper end of the third nozzle section; and removing the temporary support structure.

Assignees

• Snecma

Inventors

• Condaminet Olivier
• Lecompte Guy
• Matura Philippe

Classifications

• F05D2260/96

  Preventing, counteracting or reducing vibration or noise · CPC title

• B64G1/002

  Launch systems · CPC title

• F05D2230/68

  using auxiliary equipment for lifting or holding · CPC title

• F02K9/976 Primary

  Deployable nozzles · CPC title

• F01D25/285

  Temporary support structures, e.g. for testing, assembling, installing, repairing; Assembly methods using such structures · CPC title