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：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：US12077324B2

公开(公告)日：2024-09-03

申请号：US17785628

申请日：2020-12-09

Applicant: AIRBUS DEFENCE AND SPACE SAS

Inventor： Catherine Berthomieu ,  Carole Chossiere ,  Andrew Walker ,  Franck Levallois ,  Vincent Claudet

IPC: B64G1/64 ,  B64G1/10 ,  B64G1/22

CPC classification number: B64G1/64 ,  B64G1/10 ,  B64G1/223

Abstract: A method for assembling devices on a satellite structure is disclosed including attaching the devices to a first face of a plate drilled with a through-hole provided with a fluid connector, on a second face of the plate, depositing a continuous peripheral bead of polymerisable adhesive composition and depositing a plurality of discontinuous and disjointed inner beads of polymerisable adhesive composition, pressing the second face of the plate against a continuous face of the structure, performing suction so as to create a pressure differential between the plate and the structure, at least partially polymerising the polymerisable adhesive compositions so as to form adhesive joints between the plate and the structure, and interrupting the suction.

公开(公告)号：US10677533B2

公开(公告)日：2020-06-09

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 ,  B64G1/50 ,  F28F7/02 ,  F28D15/04 ,  F28F13/00 ,  F28D21/00

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：US11377236B2

公开(公告)日：2022-07-05

申请号：US17414275

申请日：2019-12-18

Applicant: AIRBUS DEFENCE AND SPACE SAS

Inventor： Andrew Walker

IPC: B64G1/50

Abstract: A method for attaching a heat-emitting device and a capillary heat pipe to a panel of a spacecraft wall is disclosed including the steps of: a) positioning a capillary heat pipe on a portion of the panel; attaching female attachment bodies to the panel, the female attachment bodies protruding relative to the capillary heat pipe; c) placing a thermally-conductive and self-curing paste over a portion of the capillary heat pipe or over a heat-emitting device; d) placing a heat-emitting device on the thermally-conductive and self-curing paste and on the female attachment bodies, said heat-emitting device bearing against and being in direct contact with the female attachment bodies, and e) attaching the heat-emitting device and said capillary heat pipe to the panel by attaching male attachment members to the female attachment bodies.

公开(公告)号：US11067341B2

公开(公告)日：2021-07-20

申请号：US16486853

申请日：2018-03-13

Applicant: AIRBUS DEFENCE AND SPACE SAS

Inventor： Andrew Walker

IPC: F28D15/04 ,  B01F13/00 ,  B64G1/50 ,  F28D21/00

Abstract: A heat transfer device is disclosed having a housing including a first main wall and a second main wall, the housing having a sealed internal cavity, a liquid contained in the internal cavity, and a mixer able to set the liquid in motion, the heat transfer device being able to be switched between a first state and a second state in which the liquid is in motion and transfers heat by convection between the first main wall and the second main wall, the thermal conductance between the first main wall and the second main wall in the first state being four times less than the thermal conductance between the first main wall and the second main wall in the second state.