公开(公告)号：US20190341996A1

公开(公告)日：2019-11-07

申请号：US16323750

申请日：2017-07-27

Applicant: AIRBUS DEFENCE AND SPACE SAS

Inventor： BENJAMIN GADAT ,  LYONEL BARTHE ,  THIBAULT MAISONNAT ,  ARNAUD COLLIN

IPC: H04B7/185 ,  H04L25/02 ,  H04L27/00 ,  H04B17/21

Abstract: A method for detecting useful signals in an overall signal. Each useful signal may be affected with a frequency drift. In the detection phase, frequency spectra for detecting the overall signal for multiple detection time windows are calculated and useful signals according to the detection frequency spectra are detected. In the estimation phase, for each useful signal detected: the frequency of the overall signal for multiple frequency drift values is reset. In the estimation phase, for each useful signal detected, a frequency spectrum is calculated for the estimation of the overall signal for each frequency drift value over an estimation time window having the useful signal detected and of a duration higher than the detection time window. In the estimation phase, for each useful signal detected, the frequency drift is estimated affecting the useful signal detected according to the estimation frequency spectra.

公开(公告)号：US10407186B2

公开(公告)日：2019-09-10

申请号：US15563271

申请日：2016-03-31

Applicant: AIRBUS DEFENCE AND SPACE SAS

Inventor： Nicolas Cuilleron ,  Philippe Laurens ,  Valerio Moro

IPC: B64G1/28 ,  B64G1/24 ,  B64G1/26

Abstract: A method of controlling the attitude of a spacecraft in spinning around itself with a non-zero total angular momentum HTOT. The spacecraft includes a set of inertia flywheels configured to form an internal angular momentum HACT. The axis of the total angular momentum HTOT is aligned with a principal axis of inertia of the spacecraft, in the course of which the inertia flywheels are controlled to form an internal angular momentum HACT. The following expression, in which J is the inertia matrix of the spacecraft: Hact×J−1(Htot⊗J−1Htot) is negative if the principal axis of inertia targeted is the axis of maximum inertia of the spacecraft and is positive if the principal axis inertia targeted is the axis of minimum inertia of the spacecraft.

公开(公告)号：US10228224B2

公开(公告)日：2019-03-12

申请号：US14908834

申请日：2014-07-31

Applicant: Airbus Defence and Space SAS

Inventor： Patrick Comtesse ,  Felipe Medina ,  Luc Preaud

IPC: F42B15/36 ,  B64G1/64 ,  F42B15/38

Abstract: A method and device enable the linear separation of two elements attached to each other through two connecting surfaces which are conical in this example, of a first element and a second element respectively, using thermite placed on the other side of the wall of the outer element, facing a connecting arrangement placed between both connecting surfaces. An electrical triggering of the thermite causes a quick and local warming-up, at the connecting arrangement which, after melting, enables both elements to be separated.

公开(公告)号：US10207825B2

公开(公告)日：2019-02-19

申请号：US15108780

申请日：2014-12-24

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

Inventor： Raphaël Hache ,  Bruno Trancart ,  Andrew Walker

IPC: B64G1/50 ,  B64G1/10 ,  B64G1/22 ,  B64G1/66

Abstract: A telecommunications satellite stabilized on three axes includes a set of dissipative equipment constituting a payload of the satellite. The satellite includes support data transmission antennas and is substantially parallelepipedal in shape with the panels forming two opposite faces, east and west faces. The panels form two additional opposite faces, north and south faces, and include radiator surfaces on their external faces. The radiator surfaces are configured to cool the electronic equipment of the satellite. The equipment installed on the north and south panels dissipate thermal power corresponding to less than 25% of the total dissipated power.

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：US20180320983A1

公开(公告)日：2018-11-08

申请号：US15772444

申请日：2016-11-16

Applicant: AIRBUS DEFENCE AND SPACE SAS

Inventor： Christian FLEMIN ,  Typhaine COQUARD ,  Andrew WALKER

IPC: F28D15/02 ,  F28D15/04 ,  F28F7/02 ,  B64G1/50

Abstract: Disclosed is a heat exchange device for effecting a heat exchange between a heat transfer fluid of a first network of capillary heat pipes and a heat transfer fluid of a second network of capillary heat pipes. The heat exchange device includes a solid block provided with a first channel and a second channel which are independent of one another, the first channel having at least one opening intended to be connected to a capillary heat pipe of the first network, the second channel having at least one opening intended to be connected to a capillary heat pipe of the second network, the first channel having a portion which lies near a portion of the second channel such that the heat transfer fluid of the first network is able to exchange heat with the heat transfer fluid of the second network via the heat exchanging portions.

公开(公告)号：US10118717B2

公开(公告)日：2018-11-06

申请号：US15565703

申请日：2016-06-01

Applicant: AIRBUS DEFENCE AND SPACE SAS

Inventor： Andrew Walker

IPC: B64G1/52 ,  B64G1/50 ,  B64G1/42 ,  B64G1/10 ,  B64G1/40 ,  B64G1/28

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.

公开(公告)号：US20180290768A1

公开(公告)日：2018-10-11

申请号：US15764667

申请日：2016-09-29

Applicant: AIRBUS DEFENCE AND SPACE SAS

Inventor： Frédéric FAYE ,  Eric BEAUFUME ,  Jacques COTTIER

IPC: B64G1/10 ,  B64G1/64 ,  B64G1/40 ,  G02B23/02 ,  G02B23/16

CPC classification number: B64G1/1021 ,  B64G1/10 ,  B64G1/402 ,  B64G1/405 ,  B64G1/641 ,  B64G2001/1028 ,  G02B23/02 ,  G02B23/16

Abstract: Disclosed is a satellite which includes: at least one optical photography instrument including a main lens having an optical axis and the optical instrument having a field of view; at least one launcher interface system, intended for being removably secured to a satellite interface system of a launcher of the satellite; a linking device between the launcher interface and the optical instrument extending substantially parallel to the optical axis of the main lens between an upper end and a lower end; the launcher interface system is connected to the linking device by the lower end and the optical axis of the optical instrument is directed from the upper end towards the lower end of the linking device, the launcher interface system being outside the field of view of the instrument.

公开(公告)号：US10086482B2

公开(公告)日：2018-10-02

申请号：US15501203

申请日：2015-07-24

Applicant: AIRBUS DEFENCE AND SPACE SAS ,  ETANCHEITE ET FROTTEMENT J.MASSOT

Inventor： Guy Aubert ,  Stéphane Deyber

IPC: F16F3/12 ,  F16F3/08 ,  F16F1/40 ,  F16F15/08 ,  B23P15/00 ,  B29C45/00 ,  B29C45/14 ,  B29C69/00 ,  B64G1/64 ,  F16F3/087 ,  B29K21/00 ,  B29K705/02 ,  B29L31/00

Abstract: Disclosed is a method of manufacturing a final piece including several materials, the final piece being produced at least according to the steps of: inserting an elastomer (5) in at least one insertion cavity (6) of an initial piece (2) so that the elastomer (5) is in contact and fixed with the initial piece (2); then cutting the initial piece (2) in at least two distinct parts (3, 4), so that the at least two distinct parts (3, 4) are fixed together but not in contact with each other, the at least two distinct parts (3, 4) being connected together by the elastomer (5). This may be applied to manufacturing a final piece including several parts, of various natures, connected together.

公开(公告)号：US20180251239A1

公开(公告)日：2018-09-06

申请号：US15748172

申请日：2016-07-28

Applicant: AIRBUS DEFENCE AND SPACE SAS

Inventor： PIERRE BLANC-PÂQUES

IPC: B64G1/10 ,  G06T7/00 ,  G06T1/00

CPC classification number: B64G1/1021 ,  B64G2001/1028 ,  G06Q10/04 ,  G06Q10/06 ,  G06T1/0007 ,  G06T7/0002 ,  G06T2207/30181

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.