Satellite having a simplified, streamlined, and economical structure, and method for implementing same

Patent metadata

Field	Value
Publication number	US-9446863-B2
Application number	US-201113642694-A
Country	US
Kind code	B2
Filing date	Apr 19, 2011
Priority date	Apr 28, 2010
Publication date	Sep 20, 2016
Grant date	Sep 20, 2016

Abstract

The invention relates to a satellite having a structure that includes a circular launching interface ring and at least two main planar apparatus-holding walls that are substantially parallel to the axis of the ring and rigidly connected to one another and to the ring. Each wall directly bears on the ring by a base of the wall, and each wall is rigidly and directly attached to the ring by at least one somewhat point-by-point connection on at least one point or area of tangency or intersection with the base of the wall and the ring.

First claim

The invention claimed is:

1. A satellite having a structure comprising:
a circular launcher interface ring intended to be removably secured to an analogous ring secured to a satellite launcher, and
at least two planar equipment-holding primary walls extending substantially parallel to a longitudinal satellite axis of said circular launcher interface ring and rigidly connected to each other and to said circular launcher interface ring,
wherein each primary wall bears directly on an upper face of said circular launcher interface ring by a base of said primary wall, said base facing said circular launcher interface ring, and each primary wall is rigidly and directly attached to said circular launcher interface ring by at least one somewhat point-by-point connection to at least one point or area of tangency or of intersection between said base of said primary wall and said circular launcher interface ring.

2. The satellite according to claim 1 , said structure comprises at least three planar primary walls, rigidly attached and adjacent two by two to form a prismatic compartment having an axis substantially parallel to said axis of said circular launcher interface ring and having a cross-section, perpendicular to axis of said circular launcher interface ring that is polygonal.

3. The satellite according to claim 1 , wherein said structure also comprises an equipment-holding platform arranged between said primary walls but without any contact with said primary walls, and directly bearing on said circular launcher interface ring to which said equipment holding platform is rigidly and directly attached so as to be planar, independently of attachments of said primary walls to said circular launcher interface ring.

4. The satellite according to claim 3 , wherein said equipment-holding platform is attached to said circular launcher interface ring by connections that are also somewhat point-by-point or linear, on arcs of said circular launcher interface ring left free by said attachments between said primary walls and said circular launcher interface ring.

5. The satellite according to claim 3 , wherein said equipment-holding platform supports at least one propulsion sub-assembly and a sub-assembly for piloting and orbit and attitude control of the satellite.

6. The satellite according to claim 1 , said structure also comprises planar secondary walls, substantially parallel or perpendicular to said primary walls, rigidly attached to at least one of other secondary walls and primary walls to form new compartments and increase the surface area and volume available to house equipment.

7. The satellite according to claim 1 , wherein said structure also comprises additional planar walls, substantially parallel to said axis of said circular launcher interface ring, rigidly attached to each other and each of said additional walls being attached by a base to an end of one of said primary walls, said end facing away from said circular launcher interface ring, such that said additional walls form a compartment, having an axis parallel to said axis of said circular launcher interface ring, and said additional walls being attached by somewhat point-by-point connections above said primary walls.

8. The satellite according to claim 1 , wherein an end of said primary walls which faces away from said circular launcher interface ring is attached directly, by at least one somewhat point-by-point connection per primary wall, to a circular satellite interface ring, wherein is intended to be removably secured to a second satellite interface ring of another satellite stackable onto said satellite for a group launch.

9. The satellite according to claim 1 , wherein at least one somewhat point-by-point connection attaching said circular launcher interface ring, to a primary wall or to a platform being at least one of an equipment holding, stiffening and payload support platform, comprises or is at least associated with a shock and vibration isolator.

10. The satellite according to claim 3 , wherein an assembly consisting of said equipment-holding platform attached to said circular launcher interface ring, forms a module that can be removed without disassembling any other part of the satellite, the disassembly of said assembly making it possible to open up the satellite to perform actions inside.

11. The satellite according to claim 8 , wherein said satellite interface ring is of the same diameter as said circular launcher interface ring.

12. The satellite according to claim 8 , wherein at least one somewhat point-by-point connection attaching said satellite interface ring to a primary wall comprises or is at least associated with a shock and vibration isolator.

Assignees

• Cheynet De Beaupre Rene
• Airbus Defence & Space Sas

Inventors

• Cheynet De Beaupre Rene

Classifications

• B64G1/641 Primary

  Interstage or payload connectors (docking systems B64G1/646) · CPC title

• B64G1/10

  Artificial satellites; Systems of such satellites; Interplanetary vehicles (space shuttles B64G1/14) · CPC title

• B64G2001/1092

  Operations & Transport · mapped topic

• B64G1/223

  Modular spacecraft systems · CPC title