Artificial Satellite

• US 10,118,717 B2
• Filed: 06/01/2016
• Issued: 11/06/2018
• Est. Priority Date: 06/02/2015
• Status: Active Grant

• Current Assignee: Airbus Defence & Space Sas (Airbus SE)
• Original Assignee: Airbus Defence & Space Sas (Airbus SE)
• Inventors: Walker, Andrew
• Primary Examiner(s): Badawi, Medhat
• Application Number:
  US15/565,703
• Publication Number:
  US 20180079534A1
• Time in Patent Office: 888 Days
• CPC Class Codes: B64G 1/10 Artificial satellites; Systems of such satellites; Interplanetary vehicles space shuttles B64G1/14
• CPC Class Codes: B64G 1/226 Special coatings for spacecraft
• CPC Class Codes: B64G 1/283 using reaction wheels
• CPC Class Codes: B64G 1/402 Propellant tanks; Feeding propellants
• CPC Class Codes: B64G 1/425 Power storage
• CPC Class Codes: B64G 1/503 Radiator panels
• CPC Class Codes: B64G 1/58 Thermal protection, e.g. heat shields

Abstract

Disclosed is an artificial satellite including a battery pack capable of dissipating heat, at least one radiator capable of conveying the heat dissipated by the battery pack into space, and a low-dissipation equipment item having an individual power flux density of less than 250 watts/m². The satellite includes a thermally insulating cover delimiting, together with the radiator, an interior isothermal zone in which thermal control takes place by radiation, the battery pack and the low-dissipation equipment being arranged in thermally insulating cover. The battery pack has an operating range of between 0° C. and 50° C. and preferably of between 10° C. and 30° C.

Claims

1. An artificial satellite comprising:

at least one battery pack configured to dissipate heat,

at least one radiator configured to convey the heat dissipated by the battery pack into space, and

at least one low-dissipation equipment item having an individual power flux density of less than 250 watts/m²,

wherein the artificial satellite comprises a thermally insulating cover delimiting, together with said radiator, an interior isothermal zone in which thermal control takes place by radiation, and

wherein said battery pack and said low-dissipation equipment are arranged in said thermally insulating cover, and said battery pack has an operating range of between 0°

C. and 50°

C.

2. The artificial satellite according to claim 1 wherein said battery pack is a Lithium battery pack.

3. The artificial satellite according to claim 1, wherein said low-dissipation equipment comprises a propellant storage and distribution system.

4. The artificial satellite according to claim 3, wherein said propellant storage and distribution system comprises at least one equipment item from among a tank, distribution pipes, valves, filters, and a portion of nozzles.

5. The artificial satellite according to claim 1, wherein said low-dissipation equipment comprises at least one reaction wheel.

6. The artificial satellite according to claim 1, wherein the thermally insulating cover is made of a flexible material.

7. The artificial satellite according to claim 1, which furthermore comprises heating equipment attached to said radiator.

8. The artificial satellite according to claim 1, which comprises:

a central structure,

at least one propellant tank secured to said central structure,

propellant distribution pipes attached at least in part to the central structure, and

valves installed on the pipes, and

wherein the insulating thermal cover comprises a sheath slipped over said central structure, said sheath containing;

said central structure, said tank, at least a portion of said pipes, and said valves.

9. The artificial satellite according to claim 8, wherein said sheath has a peripheral edge attached to an upper portion of the first radiator.

10. The artificial satellite according to claim 9, which comprises:

an anti-Earth face supporting the central structure,

wherein the thermal insulating cover comprises a substantially flat part of insulating material covering the anti-Earth face, wherein said part made of insulating material is secured to a lower portion of said at least one radiator so as to form, together with said sheath and said at least one radiator, a closed envelope.

11. The artificial satellite according to claim 1, wherein the low-dissipation equipment items of the satellite dissipate a heat flux of less than 40 watts.

12. The artificial satellite according to claim 2, wherein said low-dissipation equipment comprises a propellant storage and distribution system.

13. The artificial satellite according to claim 2, wherein said low-dissipation equipment comprises at least one reaction wheel.

14. The artificial satellite according to claim 3, wherein said low-dissipation equipment comprises at least one reaction wheel.

15. The artificial satellite according to claim 4, wherein said low-dissipation equipment comprises at least one reaction wheel.

16. The artificial satellite according to claim 2, wherein the thermally insulating cover is made of multi-layer insulation.

17. The artificial satellite according to claim 3, wherein the thermally insulating cover is made of multi-layer insulation.

18. The artificial satellite according to claim 2, which furthermore comprises heating equipment attached to said radiator.

19. The artificial satellite according to claim 1 wherein said battery pack has an operating range of between 10°

C. and 30°

C.

20. The artificial satellite according to claim 2 wherein said battery pack is a Lithium-Ion battery pack.