公开(公告)号：US10667330B2

公开(公告)日：2020-05-26

申请号：US15094882

申请日：2016-04-08

Applicant: THALES

Inventor： Claude Sarno ,  Romain Hodot

IPC: H05B3/00 ,  B64D43/02 ,  G01P5/165 ,  B33Y80/00 ,  B64D15/00

Abstract: An aerodynamic measurement probe comprises a part to be sited in the region of the skin of an aircraft and means for heating the part. The heating means comprise a thermodynamic loop comprising a closed circuit in which a heat-transfer fluid circulates, the closed circuit comprising an evaporator and a zone in which the heat-transfer fluid can be condensed in the appendage in order to heat it. Outside the evaporator, the circuit in which the fluid circulates is formed by a tubular duct of open cross section.

公开(公告)号：US10472074B2

公开(公告)日：2019-11-12

申请号：US15220524

申请日：2016-07-27

Applicant: THALES

Inventor： Adrien Desjardins ,  Frederic Martin ,  Claude Sarno ,  Romain Hodot ,  Jean-Philippe Pineau

IPC: B64D15/06 ,  B64D43/02 ,  G01P5/165 ,  F28D15/02 ,  B33Y10/00 ,  B33Y50/02 ,  B33Y80/00 ,  B64F5/00 ,  F25B39/00 ,  B64D15/12 ,  F28D21/00 ,  F25B39/02

Abstract: The invention relates to an aircraft provided with at least one piece of aeronautic equipment fastened to the outside skin of the aircraft and a heater for heating the piece of aeronautic equipment. The heater is in the form of a thermodynamic closed circuit loop circulating heat-transfer fluid and including an evaporator and a heat source located inside the aircraft and a condenser located in the piece of aeronautic equipment or an appendage thereto. Fasteners in the form of tubular tabs include tubular channels for circulating the heat-transfer fluid.

公开(公告)号：US20190203982A1

公开(公告)日：2019-07-04

申请号：US16232779

申请日：2018-12-26

Applicant: THALES

Inventor： Romain HODOT ,  Claude Sarno

IPC: F25B21/02 ,  H01L35/32 ,  G01P1/02

CPC classification number: F25B21/02 ,  F25B2321/0212 ,  G01P1/023 ,  G05D23/1919 ,  G05D23/24 ,  H01L35/32

Abstract: The present invention relates to a thermal control device of a component, the control device including: a power source, a converter able to convert a temperature variation into a resistance variation, and a cooling module including two faces, a first face at a first temperature and a second face at a second temperature, the difference between the first temperature and the second temperature depending on the current supplying the cooling module, the first face being in, contact with the component, the cooling module, the converter and the power source being arranged electrically so that the current supplying the converter decreases with a temperature increase and the current supplying the cooling module remains constant.

公开(公告)号：US10329024B2

公开(公告)日：2019-06-25

申请号：US15220417

申请日：2016-07-27

Applicant: THALES

Inventor： Romain Hodot ,  Claude Sarno ,  Frederic Martin ,  Jean-Philippe Pineau

IPC: B64D15/06 ,  B64D15/12 ,  B64D43/02 ,  F28D15/02 ,  G01P5/165 ,  G01P13/02 ,  B33Y10/00 ,  B33Y50/02 ,  B33Y80/00 ,  B64F5/00 ,  F28D15/04 ,  B64D33/08 ,  F28D21/00

Abstract: A heater of a piece of aeronautic equipment is intended to be arranged at the skin of an aircraft. The equipment includes a part intended to be arranged at the skin of the aircraft and elements for heating the part. The heating element include a thermodynamic loop including a closed circuit in which a heat transfer fluid circulates, the closed circuit including an evaporator and a zone in which a condensation of the heat transfer fluid can occur in the appendage to heat it. Outside the evaporator, the circuit in which the fluid circulates is formed by a tubular channel with an empty section. At least part of the equipment is made from a material with a low heat conductivity.

公开(公告)号：US10234475B2

公开(公告)日：2019-03-19

申请号：US15220488

申请日：2016-07-27

Applicant: THALES

Inventor： Claude Sarno ,  Romain Hodot ,  Marc Duval-Destin

IPC: G01P5/165 ,  B64D15/12 ,  B64D43/02 ,  F28D15/02 ,  B33Y80/00 ,  B33Y10/00 ,  B33Y50/02 ,  B22F3/105 ,  B22F5/10 ,  F28D21/00

Abstract: Manufacturing method by addition for at least one part of a piece of aeronautic equipment intended to equip an aircraft, the equipment piece including at least one part intended to be arranged at a skin of the aircraft and heating elements for that part, which include a thermodynamic loop including a closed circuit at least partially integrated, in which a heat transfer fluid circulates, the closed circuit including an evaporator and a zone in which condensation of the heat transfer fluid can occur in the appendage to heat it, outside the evaporator, the circuit being formed by a tubular channel with an empty section at least partially integral with the equipment piece, at least the part of the equipment piece arranged outside the aircraft is made by additive manufacturing and includes a base for fastening on the skin of the aircraft from which support elements for a Pitot tube extend.

公开(公告)号：US20150083674A1

公开(公告)日：2015-03-26

申请号：US14227184

申请日：2014-03-27

Applicant: THALES

Inventor： Claude Sarno ,  Philippe Oconte ,  Francois Morlet

IPC: H05K7/20 ,  H05K7/18

CPC classification number: H05K7/20136 ,  G11B33/128 ,  G11B33/142 ,  H05K7/1425 ,  H05K7/18 ,  H05K7/20581

Abstract: The invention relates to a rack intended to equip an aeronautical platform (10) comprising two parallel shelves (11, 12) positioned between a front face (13) and a rear face (14) of the platform (10), the rack (15) being intended to be inserted into the platform (10) by translation (16) from the front face (13) to the rear face (14), the rack (15) containing at least one electronic equipment item (18) extending primarily in a plane, the electronic equipment item (18) being positioned in a useful compartment (17) of the rack (15), the electronic equipment item (18) being cooled by forced convection. According to the invention, the electronic equipment item (18) is positioned in the useful compartment (15) in such a way that its main plane is parallel to the shelves (11, 12). The electronic equipment item (18) can be plugged into the rack (15) in the same direction as the direction (16) of insertion of the rack (15) into the platform (10). The rack (15) comprises means (22, 38) for guiding an air flow used for the cooling of the electronic equipment item (18), the air flow penetrating into the useful compartment (17) parallel to the plane of the electronic equipment item (18) and at right angles to the direction (16) of insertion of the rack (15) into the platform (10).

Abstract translation: 本发明涉及一种用于装备航空平台（10）的机架，该航空平台包括位于平台（10）的前表面（13）和后表面（14）之间的两个平行架（11,12），齿条（15） ）通过从前表面（13）到后表面（14）的平移（16）被插入到平台（10）中，所述齿条（15）包含至少一个电子设备项目（18），主要在 一个平面，电子设备项目（18）位于机架（15）的有用隔间（17）中，电子设备项目（18）被强制对流冷却。 根据本发明，电子设备项目（18）以其主平面平行于搁架（11,12）的方式定位在有用隔间（15）中。 电子设备项（18）可以沿与架（15）插入平台（10）的方向（16）相同的方向插入到机架（15）中。 齿条（15）包括用于引导用于电子设备物品（18）的冷却的空气流的装置（22,38），空气流平行于电子设备项目的平面穿入有用室（17） （18）并且与所述齿条（15）插入所述平台（10）中的方向（16）成直角。

公开(公告)号：US20150003017A1

公开(公告)日：2015-01-01

申请号：US14365084

申请日：2012-12-06

Applicant: THALES

Inventor： Christian Tantolin ,  Claude Sarno

IPC: H05K7/20

CPC classification number: H05K7/20009 ,  H01L23/38 ,  H01L2924/0002 ,  H05K1/0203 ,  H05K2201/062 ,  H05K2201/10219 ,  H01L2924/00

Abstract: A system for regulating the temperature of printed circuit boards comprises a first assembly of at least one Peltier element, for regulating the temperature of a second assembly of at least one electronic component or for harvesting thermal energy dissipated by the second assembly. At least one Peltier element of the first assembly is coupled to first heat-exchanging means that are coupled to at least one electronic component of the second assembly, and to second heat-exchanging means allowing thermal energy given off from at least one Peltier element of the first assembly to be dissipated.

Abstract translation: 用于调节印刷电路板的温度的系统包括至少一个珀耳帖元件的第一组件，用于调节至少一个电子部件的第二组件的温度或用于收集由第二组件耗散的热能。 第一组件的至少一个珀耳帖元件被耦合到耦合到第二组件的至少一个电子部件的第一热交换装置，以及允许从至少一个珀耳帖元件发出的热能的第二热交换装置 第一个要消散的组件。