Spacecraft

Patent metadata

Field	Value
Publication number	US-9828116-B1
Application number	US-201515535900-A
Country	US
Kind code	B1
Filing date	Dec 15, 2015
Priority date	Dec 17, 2014
Publication date	Nov 28, 2017
Grant date	Nov 28, 2017

Abstract

The invention relates to a spacecraft comprising a body having two opposite faces; a first radiator carried by at least one face; the first radiator having an outer face; a first supporting arm extending substantially perpendicularly to the outer face of the first radiator; a drive motor suitable for rotating the first supporting arm about its longitudinal axis a first assembly carried by the first supporting arm, said first assembly comprising a plurality of slats stationary with respect to the first supporting arm; said slats being attached one above the other and separated from each other by a free space.

First claim

The invention claimed is:

1. A spacecraft comprising:
a body having a face +Y and a face −Y opposite the face +Y;
a first radiator carried by at least one face out of the face +Y and the face −Y; said first radiator having an outer face;
a first supporting arm extending substantially perpendicularly to the outer face of the first radiator, said first supporting arm having a longitudinal axis;
a drive motor suitable for rotating the first supporting arm about said longitudinal axis of the first supporting arm, the speed of rotation of the first supporting arm being substantially equal to the speed of revolution of the sun around the spacecraft;
a first assembly carried by the first supporting arm, said first assembly having at least one absorption face suitable for absorbing a portion of the incident solar radiation during the vernal and autumnal equinoxes, said first assembly being suitable for transmitting heat generated by said portion of the incident solar radiation absorbed to the first radiator; said absorption face being inclined with respect to the outer face of the first radiator by an angle substantially between 20° and 26°,

wherein said first assembly comprises at least two slats attached one above the other and separated from each other by a free space, said at least two slats being stationary with respect to the first supporting arm.

2. The spacecraft according to claim 1 , wherein said first radiator is carried by the face −Y and wherein said at least two slats of the first assembly are substantially parallel to the direction of the solar radiation during the summer solstice.

3. The spacecraft according to claim 1 , further comprising:
a second radiator carried by the other face out of the face −Y and the face +Y, said second radiator having an outer face;
a second supporting arm extending substantially perpendicularly to the outer face of the second radiator, said second supporting arm having a longitudinal axis;
a drive motor suitable for rotating the second supporting arm about said longitudinal axis of the second supporting arm, the speed of rotation of the second supporting arm being substantially equal to the speed of revolution of the sun around the spacecraft;
a second assembly carried by the second supporting arm, said second assembly having at least one absorption face inclined with respect to the outer face of the second radiator by an angle substantially between 20° and 26°,

and wherein said second assembly comprises a plurality of slats stationary with respect to the second supporting arm; since said slats are attached one above the other and separated from each other by a free space, and said slats of the second assembly are substantially parallel to the direction of the solar radiation during the winter solstice.

4. The spacecraft according to claim 1 , further comprising at least one solar panel, and wherein at least one of said first supporting arm and said second supporting arm supports said at least one solar panel.

5. The spacecraft according to claim 1 , wherein said slats comprise a polyimide film and rods suitable for rigidifying said polyimide film.

6. The spacecraft according to claim 1 , wherein said absorption face has a coating having high solar absorptivity.

7. The spacecraft according to claim 1 , wherein the outer face of said radiator has a non-specular coating.

8. The spacecraft according to claim 1 , wherein each of said at least two slats has a thickness of less than one millimeter.

9. The spacecraft according to claim 1 , wherein said at least two slats of the first assembly are parallel to each other.

10. The spacecraft according to claim 6 , wherein said coating is a black coating.

Assignees

• Airbus Defence & Space Sas

Inventors

• Mena Fabrice
• Coutal Patrick

Classifications

• B64G1/506

  Heat pipes · CPC title

• B64G1/446

  Thermal solar power generation · CPC title

• B64G1/503 Primary

  Radiator panels · CPC title

• B64G1/50

  for temperature control · CPC title

• B64G1/222

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