公开(公告)号：US20190337645A1

公开(公告)日：2019-11-07

申请号：US16303776

申请日：2017-05-23

Applicant: AIRBUS DEFENCE AND SPACE SAS

Inventor： Bernard DELTOUR ,  Sylvain LECONTE ,  Christophe BEREND

IPC: B64G1/50 ,  B64G1/22

Abstract: Disclosed is a spacecraft including a casing having a face, a radiator borne by the face, and a thermal insulation device borne by the radiator. The thermal insulation device includes: —a first screen device able to cover a first zone of the radiator, the first screen device including a thermally insulating and flexible sheet, and at least two springs capable of producing a constant reaction force, the springs being preformed in such a way as to wind up on themselves at rest and being fixed to the insulating sheet, the springs each having an end fixed to the radiator and a free end; and —a traction device able to pull on the free end of the springs to make the sheet cover the first zone and to release the free end in order to expose the first zone to space.

公开(公告)号：US10427805B2

公开(公告)日：2019-10-01

申请号：US15103121

申请日：2014-12-18

Applicant: AIRBUS DEFENCE AND SPACE SAS

Inventor： Guillaume Cecchini ,  Hervé Guenat ,  Claude-Emile Mahy

IPC: B64G1/22 ,  B64G1/44 ,  B64G1/66 ,  B64G1/40 ,  B64G1/62

Abstract: The invention relates to a space wing, produced by means of a diaphragm forming a polygonal surface provided with an inflatable structure which includes ribs extending over the diaphragm along diagonals of the diaphragm and passing through a central point of the diaphragm. The inflatable structure includes at least one film strip, the perimeter of which adheres onto the diaphragm such as to form an inflatable space with the diaphragm.

公开(公告)号：US10400804B2

公开(公告)日：2019-09-03

申请号：US15537232

申请日：2015-11-24

Applicant: AIRBUS DEFENCE AND SPACE SAS

Inventor： Rene Jean Cheynet De Beaupre ,  Patrick Camarasa

IPC: F16B11/00 ,  F16B5/01 ,  F16F15/08 ,  F16B5/02

Abstract: A device for the shock-absorbing attachment of two elements to be assembled, the attachment device including: an inner part that is tubular along an attachment axis; an outer part that is tubular along the attachment axis, and hollow, the inner part being accommodated in the outer part such that the outer surface of the inner part is facing the inner surface of the outer part; an elastomer layer between the outer part and the inner part, the elastomer layer, when seen in section in a longitudinal plane including the attachment axis, including: to either side of the attachment axis, at least three so-called longitudinal portions, and at least two so-called transverse portions.

公开(公告)号：US10392133B2

公开(公告)日：2019-08-27

申请号：US15748172

申请日：2016-07-28

Applicant: AIRBUS DEFENCE AND SPACE SAS

Inventor： Pierre Blanc-Pâques

IPC: B64G1/10 ,  G06Q10/06 ,  G06T1/00 ,  G06T7/00 ,  G06Q10/04

Abstract: A method for planning the acquisition of images of areas Z1, . . . , ZN of the Earth, by a spacecraft on a mission around the Earth. Each area Zi of the Earth being associated with a request Ri such that a visual accessibility time interval Ti corresponds to the area Zi. For each interval Ti, discrete acquisition opportunities for acquiring area Zi are determined such that a start date, a period of execution, a local kinematic constraint and a weight is associated with each of the discrete acquisition opportunities. The discrete acquisition opportunities for acquiring areas Zi are grouped into a set D. The discrete acquisition opportunities Di of the set D are categorized by ascending start date. The kinematic compatibility between the discrete acquisition opportunities of set D is assessed. An optimal sequence of discrete acquisition opportunities is determined having a maximum weight, and being kinematically compatible.

公开(公告)号：US20190230658A1

公开(公告)日：2019-07-25

申请号：US16336299

申请日：2017-09-29

Applicant: AIRBUS DEFENCE AND SPACE SAS

Inventor： BENJAMIN GADAT ,  VINCENT DESLANDES

IPC: H04W72/04 ,  H04B7/185 ,  H04J13/00 ,  H04W4/80 ,  H04B1/713

Abstract: A method for transmitting, by a terminal, a message destined for a receiver station of a wireless communication system. The message being transmitted on a shared channel on which the transmission of messages is performed at the start of predetermined time intervals, termed slots. Data to be included in the message to be transmitted is encoded. The encoded data is distributed between Nb sub-messages of the message to be transmitted, Nb being an integer number greater than or equal to two. A slot is selected for transmitting the message. Nb transmission frequencies are selected, each respectively associated with the Nb sub-messages of the message. The message is transmitted at the start of the selected slot, by successively transmitting the sub-messages on their respective associated transmission frequencies.

公开(公告)号：US10211946B2

公开(公告)日：2019-02-19

申请号：US15741762

申请日：2016-07-08

Applicant: AIRBUS DEFENCE AND SPACE SAS

Inventor： Nicolas Jacquey ,  Bernard Pezet ,  Xavier Deplancq

IPC: H04B1/12 ,  H04K3/00 ,  H04B7/185

Abstract: A method for suppressing a spurious signal in a payload signal supplied by a receiving antenna of a payload of a satellite. The satellite also includes an array of measurement antennas supplying measurement signals. The measurement signals are combined with the payload signal. Reference weighting coefficients for weighting the measurement signals are determined as a function of the combined signals. A reference beam is formed by combining the measurement signals weighted based on the reference weighting coefficients. Anti jamming weighting coefficients for weighting the payload signal and the reference beam are determined. An anti jammed beam is formed by combining the payload signal and the reference beam weighed based on the corresponding anti jamming weighting coefficients.

公开(公告)号：US10207824B2

公开(公告)日：2019-02-19

申请号：US15103834

申请日：2014-12-15

Applicant: AIRBUS DEFENCE AND SPACE SAS ,  THALES ,  CENTRE NATIONAL D'ETUDES SPATIALES CNES

Inventor： Jérôme Lemaire ,  Yann Miegeville

IPC: B64G1/44 ,  B64G1/22 ,  B64G1/50 ,  B64G1/66 ,  F28D15/00 ,  F28D15/02 ,  F28F1/00 ,  F28D21/00

Abstract: A photovoltaic generator deployable for a satellite stabilized on three axes. The photovoltaic generator includes an assembly of planar panels articulated with respect to each other, and an attachment arm to the structure of the body of the satellite. In a first or launch position of the photovoltaic generator, the planar panels are folded one over the other. In a second or deployed position of the photovoltaic generator, the planar panels are fully deployed with at least a part of the planar panels being photovoltaic panels. At least one planar panel consists of a thermal radiator, with the radiative face thereof being orientated to be opposite the face of the photovoltaic panels carrying the photovoltaic sensors when the photovoltaic generator is in the deployed position. This radiative face is termed the “shade” face, and the face opposite the panel shaped radiator is termed the “sun” face.

公开(公告)号：US20180265227A1

公开(公告)日：2018-09-20

申请号：US15764678

申请日：2016-09-30

Applicant: AIRBUS DEFENCE AND SPACE SAS

Inventor： René CHEYNET DE BEAUPRE ,  Francis PALAYRET ,  Philippe BERTHEUX

IPC: B64G1/64 ,  B64G1/10 ,  B64G1/26 ,  B64G1/28

Abstract: Disclosed is a satellite including a cylindrical main body, the main body having an inner wall defining an inner space and an outer wall, and extending along a main axis between a lower end surface and an upper end surface, at least one of the lower end surface and the upper end surface including an interface mechanism intended for engaging with a complementary interface mechanism of another satellite or of a launcher, the satellite also including at least one external device attached to the outer wall of the main body, the outer device extending to project transversely from the outer wall relative to the main axis.

公开(公告)号：US20180265226A1

公开(公告)日：2018-09-20

申请号：US15534710

申请日：2015-12-15

Applicant: AIRBUS DEFENCE AND SPACE SAS

Inventor： Fabrice MENA

IPC: B64G1/50

CPC classification number: B64G1/503 ,  B64G1/506

Abstract: The invention relates to a spacecraft (1) comprising: a housing (2) 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 (16) and a second radiator (18) supported by the first surface and the second surface, respectively, the first radiator (16) and the second radiator (18) each having a main inner surface, a main outer surface opposite the main inner surface and side surfaces (19). The spacecraft (1) further comprises a first auxiliary radiator (32) and a first auxiliary heat-transfer device (34) thermally connecting said first auxiliary radiator (32) to the main inner surface of the second radiator (36), the first auxiliary radiator (18) being arranged in a first portion of the outer space (13), said first portion being defined by the main outer surface of the first radiator and by the first planes (48, 50, 52, 54) containing the side surfaces (19) of the first radiator.

公开(公告)号：US20180237168A1

公开(公告)日：2018-08-23

申请号：US15750980

申请日：2016-08-10

Applicant: AIRBUS DEFENCE AND SPACE SAS

Inventor： Philippe CAEL ,  Andrew WALKER ,  Fabrice MENA

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

CPC classification number: B64G1/1007 ,  B64G1/10 ,  B64G1/226 ,  B64G1/44 ,  B64G1/503 ,  B64G2001/1092

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.