Radiator with reduced insolation for satellite and satellite provided with such a radiator

Patent metadata

Field	Value
Publication number	US-9708081-B2
Application number	US-201415037479-A
Country	US
Kind code	B2
Filing date	Dec 19, 2014
Priority date	Dec 31, 2013
Publication date	Jul 18, 2017
Grant date	Jul 18, 2017

Abstract

A radiator for a satellite intended for being placed in geostationary orbit around the earth in a tilted plane relative to the plane of the ecliptic, includes at least one panel having at least one radiative surface, and including: a mounting foot supporting the panel; and control and motor elements for pivoting the mounting foot about an axis of rotation tilted relative to the radiative surface which is perpendicular to a radiation axis, the radiation axis and the axis of rotation being tilted relative to one another by a non-zero working angle, corresponding to the tilt angle of the plane of the orbit of the satellite relative to the plane of the ecliptic, the working angle being fixed, such that for any rotation of the mounting foot about the axis of rotation owing to the control and motor elements, the radiative surface remains parallel to the plane of the ecliptic.

First claim

The invention claimed is:

1. Radiator ( 1 ) for a satellite ( 2 ) intended to be stationed in geostationary orbit around the earth (T) in a plane that is tilted relative to the ecliptic plane, the radiator ( 1 ) comprising at least one panel ( 4 ) having at least one radiative surface ( 5 , 6 ), and comprising:
a support member ( 7 ) bearing the at least one panel ( 4 ),
control and motorization means ( 10 ) for pivoting the support member about an axis of rotation (R),
the radiator being characterized in that the axis of rotation (R) is tilted relative to the at least one radiative surface ( 5 , 6 ) and in that the at least one radiative surface ( 5 , 6 ) of the at least one panel ( 4 ) is perpendicular to an axis of radiation (S), the axis of radiation (S) and the axis of rotation (R) being tilted relative to each other by a non-zero operating angle (α), corresponding to the tilt angle of the orbit plane of the satellite ( 2 ) relative to the ecliptic plane, the operating angle (α) being fixed, such that for any rotation of the support member ( 7 ) about the axis of rotation (R) using the control and motorization means ( 10 ), the at least one radiative surface ( 5 , 6 ) remains parallel to the ecliptic plane.

2. Radiator ( 1 ) according to claim 1 , in which the at least one panel ( 4 ) is mounted pivoting about the axis of radiation (S), the radiator ( 1 ) also comprising a system ( 12 ) for guiding the range of rotation of the at least one panel ( 4 ) limiting the rotation of the at least one panel ( 4 ) about the of axis rotation (R), so as to keep the at least one panel in a given orientation relative to the satellite ( 2 ).

3. Radiator ( 1 ) according to claim 2 , in which the support member ( 7 ) comprises two portions ( 8 , 9 ), namely:
a first portion ( 8 ) capable of being mounted on a support face ( 3 , 16 ) of the satellite ( 2 ),
a second portion ( 9 ) on which the at least one panel ( 4 ) is mounted,
the at least one panel ( 4 ) being mounted on the second portion ( 9 ) via a bearing ( 13 ) in order to allow the rotation of the at least one panel ( 4 ) about the axis of radiation (S).

4. Radiator ( 1 ) according to claim 3 , in which the two portions ( 8 , 9 ) of the support member ( 7 ) are rectilinear and each an extension of the other, the first portion ( 8 ) extending along the axis of rotation (R) and the second portion extending along the axis of radiation (S).

5. Radiator ( 1 ) according to claim 2 , in which the system ( 12 ) for guiding the range of rotation comprises a rail ( 14 ), extending parallel to the axis of rotation (R) and a clamp ( 15 ) comprising arms, wherein the clamp is rigidly fixed to the at least one panel ( 4 ), the arms ( 26 , 27 ) of the clamp ( 15 ) engaging with the rail ( 15 ) in order to limit the range of rotation of the at least one panel ( 4 ) about the axis of rotation (R).

6. Radiator ( 1 ) according to claim 1 , in which the operating angle (α) is 23.5°.

7. Radiator ( 1 ) according to claim 1 , in which the operating angle (α) is greater than 23.5° for operation in tilted orbit, the radiator ( 1 ) then also comprising means for modulating the speed of rotation of the support member ( 7 ).

8. Radiator ( 1 ) according to claim 1 , in which the at least one panel ( 4 ) comprises two parallel radiative surfaces ( 5 , 6 ) oriented in opposite directions.

9. Radiator ( 1 ) according to claim 1 , in which the at least one panel ( 4 ) comprises a deflector placed over the entire periphery, projecting relative to the at least one radiative surface ( 5 , 6 ), in order to block some of the sun's rays.

10. Radiator ( 1 ) according to claim 1 , also comprising an attitude sensor linked to the control and motorization means ( 10 ) in order to pivot the support member ( 7 ), so as to verify and/or control the orientation of the at least one panel ( 4 ) relative to the sun.

11. Radiator ( 1 ) according to claim 1 , comprising fluid connection means capable of being connected with a satellite ( 2 ), the fluid connection means including at least one internal circuit ( 19 ) comprising two flexible pipes passing on the inside of the support member ( 7 ) of the radiator ( 1 ).

12. Radiator ( 1 ) according to claim 1 , comprising fluid connection means capable of being connected with a satellite ( 2 ), the fluid connection means including at least one external circuit ( 20 ) comprising two flexible pipes passing on the outside of the support member ( 7 ) of the radiator ( 1 ).

13. Satellite ( 2 ) capable of being placed in orbit around the earth, comprising at least one radiator ( 1 ) according to claim 1 , mounted on a support face ( 3 , 16 ) of the satellite ( 2 ), the support member ( 7 ) of the radiator ( 1 ) being fixed on the satellite ( 2 ) such that the axis of rotation (R) is perpendicular to a reference face of the satellite, the reference face being a north face ( 3 ) or a south face ( 17 ) of the satellite ( 2 ).

14. Satellite ( 2 ) according to claim 13 , in which the radiator ( 1 ) can adopt a folded position in which the at least one panel ( 4 ) is against the support face ( 3 , 16 ) of the satellite ( 2 ) on which it is fixed, and a deployed position in which the at least one panel ( 4 ) is brought into a position in which it is tilted relative to the support face ( 3 , 16 ) by the operating angle (α).

15. Radiator ( 1 ) according to claim 3 , in which the system ( 12 ) for guiding the range of rotation comprises a rail ( 14 ), extending parallel to the axis of rotation (R) and a clamp ( 15 ) comprising arms, wherein the clamp is rigidly fixed to the at least one panel ( 4 ), the arms ( 26 , 27 ) of the clamp ( 15 ) engaging with the rail ( 15 ) in order to limit the range of rotation of the at least one panel ( 4 ) about the axis of rotation (R).

16. Radiator ( 1 ) according to claim 4 , in which the system ( 12 ) for guiding the range of rotation comprises a rail ( 14 ), extending parallel to the axis of rotation (R) and a clamp ( 15 ) comprising arms, wherein the clamp is rigidly fixed to the at least one panel ( 4 ), the arms ( 26 , 27 ) of the clamp ( 15 ) engaging with the rail ( 15 ) in order to limit the range of rotation of the at least one panel ( 4 ) about the axis of rotation (R).

17. Radiator ( 1 ) according to claim 2 , in which the operating angle (α) is greater than 23.5° for operation in tilted orbit, the radiator ( 1 ) then also comprising means for modulating the speed of rotation of the support member ( 7 ).

18. Radiator ( 1 ) according to claim 3 , in which the operating angle (α) is greater than 23.5° for operation in tilted orbit, the radiator ( 1 ) then also comprising means for modulating the speed of rotation of the support member ( 7 ).

19. Radiator ( 1 ) according to claim 4 , in which the operating angle (α) is greater than 23.5° for operation in tilted orbit, the radiator ( 1 ) then also comprising means for modulating the speed of rotation of the support member ( 7 ).

20. Radiator ( 1 ) according to claim 5 , in which the operating angle (α) is greater than 23.5° for operation in tilted orbit, the radiator ( 1 ) then also comprising means for modulating the speed of rotation of the support member ( 7 ).

Assignees

• Airbus Defence & Space Sas

Inventors

• Cael Philippe

Classifications

• B64G1/58

  Thermal protection, e.g. heat shields · CPC title

• B64G1/1014

  Navigation satellites · CPC title

• B64G1/44

  using radiation, e.g. deployable solar arrays · CPC title

• B64G1/503 Primary

  Radiator panels · CPC title

• B64G1/1007

  Communications satellites · CPC title