Satellite with cylindrical main body, stack comprising such a satellite and launch assembly for such a satellite

Patent metadata

Field	Value
Publication number	US-10689133-B2
Application number	US-201615764678-A
Country	US
Kind code	B2
Filing date	Sep 30, 2016
Priority date	Oct 2, 2015
Publication date	Jun 23, 2020
Grant date	Jun 23, 2020

Abstract

Disclosed is a satellite including a cylindrical main body, the main body having an inner wall defining an inner space and an outer wall, and extending along a main axis between a lower end surface and an upper end surface, at least one of the lower end surface and the upper end surface including an interface mechanism intended for engaging with a complementary interface mechanism of another satellite or of a launcher, the satellite also including at least one external device attached to the outer wall of the main body, the outer device extending to project transversely from the outer wall relative to the main axis.

First claim

The invention claimed is:

1. A satellite comprising:
a main body having a cylindrical shape, the main body having an inner wall delimiting an inner space and an outer wall extending along a main axis between a lower end surface and an upper end surface, the lower end surface comprising an interface mechanism configured to engage with a complementary interface mechanism of a launcher;
at least one internal item of equipment, fixed onto the inner wall of the main body and extending at least partially into the inner space in which the outer wall of the main body comprises at least a portion of plane surface, forming a facet, the internal item of equipment comprising an optical imaging instrument, and electronics associated with the optical instrument, the optical instrument comprising a sighting axis oriented parallel to the main axis of the main body; and
at least one external item of equipment fixed onto the outer wall of the main body, the external item of equipment extending as a transverse projection from the outer wall with respect to the main axis, the at least one external item of equipment being either a tank of propellants or an inertial actuator, the external item of equipment being fixed on the at least portion of plane surface that forms the facet.

2. The satellite according to claim 1 , wherein the main body comprises a cylinder having an average diameter corresponding to a standard diameter in the space field, chosen from the following values: 937 mm, 1194 mm, and 1666 mm.

3. The satellite according to claim 1 , wherein the upper end surface comprises an interface mechanism configured to engage with a complementary interface mechanism of the lower end surface of another satellite.

4. The satellite according to claim 1 , wherein the main body is produced from parts made from monolithic aluminium.

5. A launch assembly comprising:
a launcher comprising a nosecone defining a housing for at least one satellite and an interface ring, the lower end surface of the main body of the satellite comprising an interface mechanism in order to be firmly fixed to the interface ring of the launcher; and
at least one said satellite according to claim 1 .

6. The satellite according to claim 1 , wherein the interface mechanism is linear.

7. The satellite according to claim 6 , wherein the interface mechanism comprises a clamp band system.

8. A satellite stack comprising:
first and second said satellites according to claim 1 ,
wherein, in the first satellite, the upper end surface comprises an interface mechanism configured to engage with a complementary interface mechanism of the lower end surface the second satellite, the main axes of the main bodies of the first and second satellites being parallel,
the interface mechanism of the upper end surface of the first satellite being in contact along the main axes with the interface mechanism of the lower end surface of the body of the second satellite, the interface mechanisms engaging with one another in order to firmly fix the first and second satellites together.

9. The satellite stack according to claim 8 , wherein the internal item of equipment of the first satellite extends partially into the inner space of the second satellite.

10. The satellite of claim 1 , wherein the at least one external item of equipment is an inertial actuator.

11. The satellite of claim 10 , wherein the inertial actuator is a control momentum gyroscope.

12. The satellite of claim 10 , wherein the inertial actuator is a momentum wheel.

13. A satellite comprising:
a main body having a cylindrical shape, the main body having an inner wall delimiting an inner space and an outer wall extending along a main axis between a lower end surface and an upper end surface, the lower end surface comprising an interface mechanism configured to engage with a complementary interface mechanism of a launcher;
at least one internal item of equipment, fixed onto the inner wall of the main body and extending at least partially into the inner space in which the outer wall of the main body comprises at least a portion of plane surface, forming a facet, the internal item of equipment comprising an optical imaging instrument, and electronics associated with the optical instrument, the optical instrument comprising a sighting axis oriented parallel to the main axis of the main body; and
at least one external item of equipment fixed onto the outer wall of the main body, the external item of equipment extending as a transverse projection from the outer wall with respect to the main axis, the at least one external item of equipment being either a tank of propellants or an inertial actuator, the external item of equipment being fixed on the at least portion of plane surface that forms the facet,
wherein the internal item of equipment comprises a mounting plate fixed to the inner wall of the main body and extending at least partially outside the inner space, beyond the upper end surface of the main body, and
the optical instrument is rigidly fixed to the mounting plate.

14. The satellite according to claim 13 , wherein the sighting axis of the optical instrument is oriented towards the lower end surface of the main body.

Assignees

• Airbus Defence & Space Sas

Inventors

• CHEYNET DE BEAUPRE René
• Palayret Francis
• Bertheux Philippe

Classifications

• B64G1/10 Primary

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

• B64G1/642

  Clamps, e.g. Marman clamps · CPC title

• B64G1/643 Primary

  for arranging multiple satellites in a single launcher · CPC title

• B64G1/1021

  Earth observation satellites · CPC title

• B64G1/286

  using control momentum gyroscopes (CMGs) · CPC title