Method for arranging a plurality of spacecraft under the fairing of a launcher, assembly resulting from such a method and dispenser suited to such an assembly

Patent metadata

Field	Value
Publication number	US-10407190-B2
Application number	US-201615097943-A
Country	US
Kind code	B2
Filing date	Apr 13, 2016
Priority date	Apr 17, 2015
Publication date	Sep 10, 2019
Grant date	Sep 10, 2019

Abstract

A method for arranging a plurality of spacecraft comprises the following steps: arranging a first layer of spacecraft around a dispenser; fixing the spacecraft of the first layer to the dispenser using mechanical interfaces extending in a radial direction; arranging a second layer of spacecraft around the first layer and the dispenser, the spacecraft of the second layer being arranged that they extend beyond, in a longitudinal direction of the fairing, the spacecraft of the first layer which are interposed between them and the dispenser; fixing the spacecraft of the second layer to the dispenser using mechanical interfaces extending in a radial direction over a distance greater than that of the mechanical interfaces of the first layer; and arranging the assembly thus obtained, under the fairing of a launcher. Assembly of spacecraft that can be obtained by the method and a dispenser suited to the assembly is provided.

First claim

The invention claimed is:

1. A method for arranging a plurality of spacecraft under a fairing of a launcher, comprising the steps of:
arranging a first layer of spacecraft around a dispenser having a longitudinal axis;
fixing the spacecraft of the first layer to the dispenser using mechanical interfaces extending in a radial direction of the dispenser;
arranging a second layer of spacecraft around the first layer and the dispenser, the spacecraft of the second layer being arranged in such a way that they extend beyond, in a longitudinal direction of the fairing, the spacecraft of the first layer which are interposed between them and the dispenser such that the entirety of at least one spacecraft of the first layer of spacecraft is interposed between the dispenser and the second layer of spacecraft;
fixing the spacecraft of the second layer to the dispenser using mechanical interfaces extending in the radial direction over a distance greater than that of the mechanical interfaces of the first layer; and
arranging the assembly thus obtained, comprising the dispenser and the spacecraft, under the fairing of the launcher with the longitudinal axis of the dispenser aligned with the longitudinal axis of the fairing.

2. The method of claim 1 , wherein both the first layer and the second layer comprise a plurality of stages spaced in a longitudinal direction of the dispenser, each stage being made up of a plurality of spacecraft arranged in a ring around the dispenser, each stage of the second layer surrounding a corresponding stage of the first layer.

3. The method of claim 1 , wherein the spacecraft are substantially mutually identical, the spacecraft of the second layer being angled, with respect to those of the first layer, around respective radially-oriented axes.

4. The method of claim 3 , wherein
the spacecraft have a shape that is elongate along a main axis and
the spacecraft of the first layer are arranged with their main axis oriented perpendicular to a longitudinal direction of the dispenser and those of the second layer are arranged with their main axis oriented in the longitudinal direction of the dispenser and perpendicular to the radial direction of the dispenser.

5. An assembly of spacecraft comprising:
a dispenser having a longitudinal axis;
a first set of spacecraft arranged around the dispenser to form a first layer of spacecraft, the spacecraft being fixed to the dispenser by mechanical interfaces extending from the dispenser in a radial direction of the dispenser; and
a second set of spacecraft arranged around the first layer and the dispenser to form a second layer of spacecraft, the spacecraft of the second layer being arranged so that they extend beyond, in the direction of the longitudinal axis, the spacecraft of the first layer which are interposed between them and the dispenser such that the entirety of at least one spacecraft of the first layer of spacecraft is interposed between the dispenser and the second layer of spacecraft, and the second set of spacecraft being fixed to the dispenser by mechanical interfaces extending in the radial direction over a distance greater than that of the mechanical interfaces of the first layer.

6. The assembly of claim 5 , wherein both the first layer and the second layer of spacecraft comprise a plurality of stages spaced in the direction of the longitudinal axis of the dispenser, each stage being made up of a plurality of spacecraft arranged in a ring around the dispenser, each stage of the second layer surrounding a corresponding stage of the first layer.

7. The assembly of claim 5 , wherein the spacecraft are substantially mutually identical, the spacecraft of the second layer being angled, with respect to those of the first layer, around respective radially-oriented axes.

8. The assembly of claim 7 , wherein
the spacecraft have a shape that is elongate along a main axis, and
the spacecraft of the first layer are arranged with their main axis oriented perpendicular to a longitudinal direction of the dispenser and those of the second layer are arranged with their main axis oriented in the longitudinal direction of the dispenser and perpendicular to the radial direction of the dispenser.

9. A dispenser of spacecraft that implements the method of claim 1 , comprising:
a central body of a shape that is elongate along a longitudinal axis, and
a plurality of mechanical interfaces for anchoring spacecraft extending radially from the central body, the mechanical interfaces being arranged in stages spaced longitudinally, wherein
the dispenser has an alternation of sets of stages of mechanical interfaces extending radially over a first distance and of sets of stages of mechanical interfaces extending radially over at least a second distance greater than the first distance.

Assignees

• Thales Sa

Inventors

• Fernandez Gilles
• Sost Jean-Claude

Classifications

• B64G1/641 Primary

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

• B64G1/1085

  Swarms and constellations · CPC title

• B64G1/002

  Launch systems · CPC title

• B64G2001/643

  Operations & Transport · mapped topic

• B64G1/643

  for arranging multiple satellites in a single launcher · CPC title