Satellite with deployable payload modules

Patent metadata

Field	Value
Publication number	US-9650160-B2
Application number	US-201314046613-A
Country	US
Kind code	B2
Filing date	Oct 4, 2013
Priority date	Oct 5, 2012
Publication date	May 16, 2017
Grant date	May 16, 2017

Abstract

A telecommunication satellite with geostationary orbit comprises an upper module, a lower module, and a lateral module, disposed in a storage configuration between the upper module and the lower module, and deployed to an operational configuration of the satellite in the orbit by a rotation in relation to an axis Z oriented towards the earth in the operational configuration. The lateral module comprises two substantially plane and mutually parallel main surfaces, termed dissipative surfaces, able to dissipate by radiation a quantity of heat generated by facilities of the satellite; the dissipative surfaces being, in the operational configuration, held in a manner substantially parallel to the plane of the orbit, making it possible to limit the solar flux received by the dissipative surfaces and to optimize the quantity of heat dissipated by the lateral module.

First claim

The invention claimed is:

1. A telecommunication satellite with geostationary orbit comprising:
an upper module;
a lower module;
a lateral module, disposed in a storage configuration between the upper module and the lower module, and deployed to an operational configuration of the satellite in the orbit by a rotation in relation to an axis Z oriented towards the earth in the operational configuration;
at least one mission or service facility linked to the lateral module so as to move at least with the rotation of the lateral module in relation to the axis Z,
wherein the lateral module includes two substantially plane and mutually parallel main surfaces that define dissipative surfaces able to dissipate by radiation a quantity of heat generated by the satellite, and
wherein the dissipative surfaces, in the operational configuration, are held in a manner substantially parallel to the plane of the orbit, making it possible to limit the solar flux received by the dissipative surfaces and to optimize the quantity of heat dissipated by the lateral module.

2. The satellite according to claim 1 , wherein the lateral module comprises two articulations, linked respectively to the upper module and to the lower module, configured so as to allow the rotation of the said lateral module in relation to the Z axis, from the storage configuration to the operational configuration.

3. The satellite according to claim 1 , further comprising a rigid structure linking the upper module and the lower module.

4. The satellite according to claim 3 , wherein the lateral module includes at least one articulation linked to the rigid structure configured so as to allow the rotation of the lateral module in relation to the Z axis from the storage configuration to the operational configuration.

5. The satellite according to claim 1 ,
wherein the at least one mission or service facility is a telecommunication device including an antenna reflector, a motorized mechanism linking the antenna reflector to the lateral module, and a radiofrequency source fixed to the lateral module and able to emit or receive a beam of waves,
wherein the motorized mechanism is configured to hold, in the storage configuration, the reflector between the upper module and the lower module, and in a manner substantially parallel to one of the dissipative surfaces of the lateral module, and
wherein the motorized mechanism is configured to displace and hold the reflector, in the operational configuration, in a position allowing the reflection of a beam of waves between the radiofrequency source and a predefined zone of coverage of the terrestrial globe.

6. The satellite according to claim 5 , wherein the radiofrequency source of the telecommunication device is fixed against one of the dissipative surfaces of the lateral module.

7. The satellite according to claim 5 , wherein the radiofrequency source of the telecommunication device is fixed against a surface of the lateral module that is adjacent and substantially perpendicular to the dissipative surfaces.

8. The satellite according to claim 5 , wherein the lateral module comprises several telecommunication devices; the satellite further comprising means of communication between the telecommunication devices, the upper module and/or the lower module; the communication means comprising a physical link or a link in free space.

9. The satellite according to claim 1 , further comprising a substantially spindly mechanical reinforcement, linking the upper module and the lower module, and able to rigidify the satellite.

10. The satellite according to claim 1 , further comprising a set of solar generators held in the storage configuration against one of the dissipative surfaces of the lateral module.

11. The satellite according to claim 10 , wherein the set of solar generators is fixed to the lateral module, to the upper module or to the lower module.

12. The satellite according to claim 10 , wherein the set of solar generators is linked electrically to the lower module.

13. The satellite according to claim 1 , further comprising two lateral modules configured in such a way that, in the storage configuration, respective dissipative surfaces of the two lateral modules are substantially mutually parallel.

14. The satellite according to claim 1 , wherein the lateral module is deployed from the storage configuration to the operational configuration by a rotation of an angle substantially equal to 90 degrees.

15. The satellite according to claim 1 , wherein the lateral module is deployed from the storage configuration to the operational configuration by a rotation of an angle substantially equal to 180 degrees.

16. The satellite according to claim 1 , wherein the upper module and the lower module form two ends of a satellite structure along the Z axis.

17. The satellite according to claim 1 , wherein the at least one mission or service facility is linked to the lateral module by a motorized mechanism.

18. The satellite according to claim 1 ,
wherein the at least one mission or service facility is linked to the lateral module by a motorized mechanism configured to move the at least one mission or service facility relative to the lateral module between a respective storage configuration and a respective operational configuration, and
wherein the motorized mechanism is configured to hold the at least one mission or service facility in the respective storage configuration at least in part inside a volume delimited between the upper module and the lower module along the axis Z.

19. The satellite according to claim 1 ,
wherein the at least one mission or service facility is linked to the lateral module by a motorized mechanism configured to move the at least one mission or service facility relative to the lateral module between a respective storage configuration and a respective operational configuration, and
wherein the motorized mechanism is configured to hold the at least one mission or service facility in the respective storage configuration inside a volume delimited between the upper module and the lower module along the axis Z.

Assignees

• Thales Sa

Inventors

• Celerier Bruno

Classifications

• B64G1/2224

  about multiple axes · CPC title

• B64G1/54

  Protection against radiation · CPC title

• B64G2001/1092

  Operations & Transport · mapped topic

• G01S19/02

  Details of the space or ground control segments · CPC title

• B64G1/222

  for deploying structures between a stowed and deployed state · CPC title