公开(公告)号：US10155597B2

公开(公告)日：2018-12-18

申请号：US15750980

申请日：2016-08-10

Applicant: AIRBUS DEFENCE AND SPACE SAS

Inventor： Philippe Cael ,  Andrew Walker ,  Fabrice Mena

IPC: B64G1/50 ,  B64G1/10 ,  B64G1/22 ,  B64G1/44

Abstract: Disclosed is an artificial satellite including one face from the North face and the South face supporting at least one main radiator having an outer face turned towards space and an inner face opposite the outer face. The satellite includes a bearing structure carrying the North face, the South face, the East face and the West face. At least one part of the at least one main radiator protrudes from at least one face from the East face and the West face. The inner face of the at least one protruding part is covered with a high infrared emissivity material. The value of the dimension of the at least one protruding part is between 19% and 50% of the value of the distance between the East and West faces.

公开(公告)号：US10144534B2

公开(公告)日：2018-12-04

申请号：US15534710

申请日：2015-12-15

Applicant: AIRBUS DEFENCE AND SPACE SAS

Inventor： Fabrice Mena

IPC: B64G1/50

Abstract: Disclosed is a spacecraft including:—a housing defining an inner space and an outer space, the housing having a first surface and a second surface opposite the first surface; a first radiator and a second radiator supported by the first surface and the second surface, respectively, the first radiator and the second radiator each having a main inner surface, a main outer surface opposite the main inner surface and side surfaces. The spacecraft further includes a first auxiliary radiator and a first auxiliary heat-transfer device thermally connecting the first auxiliary radiator to the main inner surface of the second radiator, the first auxiliary radiator being arranged in a first portion of the outer space, the first portion being defined by the main outer surface of the first radiator and by the first planes containing the side surfaces of the first radiator.

公开(公告)号：US20170341781A1

公开(公告)日：2017-11-30

申请号：US15535900

申请日：2015-12-15

Applicant: AIRBUS DEFENCE AND SPACE SAS

Inventor： Fabrice Mena ,  Patrick Coutal

IPC: B64G1/50 ,  B64G1/44 ,  B64G1/22

CPC classification number: B64G1/503 ,  B64G1/222 ,  B64G1/446 ,  B64G1/50 ,  B64G1/506

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.

公开(公告)号：US09828116B1

公开(公告)日：2017-11-28

申请号：US15535900

申请日：2015-12-15

Applicant: AIRBUS DEFENCE AND SPACE SAS

Inventor： Fabrice Mena ,  Patrick Coutal

IPC: B64G1/50 ,  B64G1/44 ,  B64G1/22

CPC classification number: B64G1/503 ,  B64G1/222 ,  B64G1/446 ,  B64G1/50 ,  B64G1/506

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.

公开(公告)号：US11254452B2

公开(公告)日：2022-02-22

申请号：US16448215

申请日：2019-06-21

Applicant: Airbus Defence and Space SAS ,  Airbus Defence and Space Netherlands B.V

Inventor： Fabrice Mena ,  Bruin Benthem

IPC: B64G1/58 ,  B64G1/22 ,  B64G1/10 ,  B64G1/44 ,  B64G1/50

Abstract: A radiative fin for a spacecraft is disclosed having an end fitting of heat conductive material, configured to be mounted on the spacecraft, a flexible radiative laminate, connected to the end fitting at one end and having an opposite free end, at least one pyrolytic graphite sheet, and at least one heat emission layer in contact with the pyrolythic graphite sheet on at least part of the surface of the pyrolythic graphite sheet, and a flexible rod, extending from the end fitting along at least part of a side of the flexible radiative laminate and being affixed to the latter. The flexible rod is adapted to occupy a folded position and a deployed position and to exert, while in the folded position, a deployment torque adapted to bring the flexible rod back to the deployed position.

公开(公告)号：US11299296B2

公开(公告)日：2022-04-12

申请号：US16308247

申请日：2017-06-09

Applicant: AIRBUS DEFENCE AND SPACE SAS

Inventor： Fabrice Mena ,  Jean-Christophe Dunat

IPC: B64G1/50 ,  B64G1/10

Abstract: Disclosed is a spacecraft including: a housing defining an exterior space, the housing having a first face and a second face; and first and second radiators carried by the first and second faces, the first and second radiators each having an inner main face, an outer main face, and side faces. The spacecraft includes a first auxiliary radiator and a first auxiliary heat transfer device thermally connecting the first auxiliary radiator to the inner main face of the second radiator, the first auxiliary radiator being arranged in a first portion of the exterior space defined by the outer main face of the first radiator and by first planes containing the side faces of the first radiator. The first auxiliary heat transfer device includes a heat conducting device. The first auxiliary radiator is composed solely of one or two radiating panels supporting the heat conducting device.