公开(公告)号：US11772830B2

公开(公告)日：2023-10-03

申请号：US16824857

申请日：2020-03-20

Applicant: THALES

Inventor： Claude Sarno ,  Romain Hodot ,  Philippe Oconte

IPC: B64G1/50 ,  B64D15/02 ,  B64G1/36 ,  B64G1/58

CPC classification number: B64G1/506 ,  B64D15/02 ,  B64G1/36 ,  B64G1/58

Abstract: This aeronautical equipment for an aircraft, comprising a part configured to be positioned at the level of a skin of the aircraft and means for reheating this part comprising a closed-circuit thermodynamic loop in which a phase-change heat transfer fluid circulates, is wherein it includes means for monitoring the fluid pressure in the loop in order to detect and report a malfunction of the equipment.

公开(公告)号：US20190276307A1

公开(公告)日：2019-09-12

申请号：US16293330

申请日：2019-03-05

Applicant: Thales

Inventor： Bertrand LEVERRIER ,  Claude Sarno ,  Claude Rougeot ,  Romain Hodot

IPC: B81B7/00 ,  B81B7/02

Abstract: The present invention relates to an electronic system comprising an electronic system comprising an electromechanical microsystem and a hermetic box encapsulating said microsystem. The box includes a fastening plane. The electromechanical microsystem includes a sensitive part and at least two beams connecting the sensitive part to the fastening plane.The beams are thermally coupled to the sensitive part and are electrically coupled to one another. The system further includes a thermal regulator of the electromechanical microsystem including an electrical circuit including at least two ends connected to the beams, and a circuit controller able to generate an electrical current in the electrical circuit to modify the temperature of the sensitive part.

公开(公告)号：US09975639B2

公开(公告)日：2018-05-22

申请号：US15220644

申请日：2016-07-27

Applicant: THALES

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

IPC: G01F1/46 ,  B64D15/06 ,  B64D15/12 ,  B64D43/02 ,  G01P5/165 ,  B33Y80/00 ,  F28D15/04 ,  B33Y50/02 ,  B22F3/105 ,  B22F5/10 ,  F28D21/00

CPC classification number: B64D15/06 ,  B22F3/1055 ,  B22F5/10 ,  B22F2202/13 ,  B22F2203/00 ,  B33Y50/02 ,  B33Y80/00 ,  B64D15/12 ,  B64D43/02 ,  F28D15/043 ,  F28D2021/0021 ,  G01F1/46 ,  G01P5/165 ,  Y02P10/295

Abstract: A piece of aeronautic equipment intended to equip an aircraft, the equipment piece (25) including at least one part intended to be arranged at a skin (27) outside of the aircraft and heating elements for that part, which 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 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 the part of the piece of equipment arranged outside the aircraft is made by additive manufacturing and includes a fastening base (120) for fastening on the skin of the aircraft from which support elements (130) for a Pitot tube (140) provided with lateral static pressure taps (150) extend.

公开(公告)号：US10035603B2

公开(公告)日：2018-07-31

申请号：US15221170

申请日：2016-07-27

Applicant: THALES

Inventor： Claude Sarno ,  Romain Hodot

IPC: B33Y50/02 ,  B33Y80/00 ,  B64D33/08 ,  F28D21/00 ,  B64D15/06 ,  B64D15/12 ,  B64D43/02 ,  G01P5/165 ,  F28D15/02 ,  B33Y10/00 ,  G01F1/46

CPC classification number: B64D15/06 ,  B33Y10/00 ,  B33Y50/02 ,  B33Y80/00 ,  B64D15/12 ,  B64D33/08 ,  B64D43/02 ,  F28D15/0266 ,  F28D2021/0021 ,  G01F1/46 ,  G01P5/165

Abstract: An aircraft provided with at least one piece of aeronautic equipment, the equipment (25) including a part intended to be arranged at a skin (27) of the aircraft and elements for heating the part, characterized in that the heating elements include a thermodynamic loop including a closed circuit in which a heat transfer fluid circulates, the closed circuit including an evaporator (14) associated with functional elements (70) of the aircraft forming a heat source giving off heat during their operation and a zone in which a condensation of the heat transfer fluid can occur in the appendage to heat it, and in that outside the evaporator, the circuit in which the fluid circulates is formed by a tubular channel with an empty section.

公开(公告)号：US09849993B2

公开(公告)日：2017-12-26

申请号：US15220428

申请日：2016-07-27

Applicant: THALES

Inventor： Claude Sarno ,  Romain Hodot

IPC: G01F1/68 ,  B64D15/06 ,  B64D15/12 ,  B64D43/02 ,  F28D15/02 ,  G01P5/165 ,  B33Y10/00 ,  B64F5/10 ,  B33Y80/00 ,  B33Y50/02 ,  B64D33/08 ,  F28D21/00

CPC classification number: B64D15/06 ,  B33Y10/00 ,  B33Y50/02 ,  B33Y80/00 ,  B64D15/12 ,  B64D33/08 ,  B64D43/02 ,  B64F5/10 ,  F28D15/02 ,  F28D15/0266 ,  F28D2021/0021 ,  G01P5/165

Abstract: An aircraft provided with at least two pieces of aeronautic equipment, a first piece of equipment (25) including a part intended to be arranged at a skin (27) of the aircraft and elements for heating the part, characterized in that the heating elements include a thermodynamic loop including a closed circuit in which a heat transfer fluid circulates, the closed circuit including an evaporator (14) associated with functional elements (80) of the second piece of equipment (81) of the aircraft forming a heat source giving off heat during their operation and a zone in which a condensation of the heat transfer fluid can occur in the appendage to heat it, and in that outside the evaporator (14), the circuit in which the fluid circulates is formed by a tubular channel with an empty section.

公开(公告)号：US09253918B2

公开(公告)日：2016-02-02

申请号：US14227184

申请日：2014-03-27

Applicant: THALES

Inventor： Claude Sarno ,  Philippe Oconte ,  Francois Morlet

IPC: H05K5/00 ,  H05K7/00 ,  G06F1/16 ,  B64C1/00 ,  B64C30/00 ,  G08B21/00 ,  H05K7/20 ,  G11B33/12 ,  G11B33/14 ,  H05K7/14 ,  H05K7/18

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

Abstract: A rack for an aeronautical platform comprising two parallel shelves positioned between a front face and a rear face of the platform, the rack being inserted into the platform by translation from the front face to the rear face the rack containing electronic equipment extending primarily in a plane, the electronic equipment being positioned in a useful compartment of the rack and cooled by forced convection. The electronic equipment is positioned in such a way that its main plane is parallel to the shelves. The rack comprises means for guiding an air flow used for the cooling of the electronic equipment item, the air flow penetrating into the useful compartment parallel to the plane of the electronic equipment item and at right angles to the direction of insertion of the rack into the platform.

Abstract translation: 一种用于航空平台的机架，包括位于所述平台的前表面和后表面之间的两个平行架，所述齿条通过从所述前表面到所述后表面平移而插入所述平台中，所述机架包含主要在平面中延伸的电子设备 ，电子设备被定位在机架的有用隔间中并被强制对流冷却。 电子设备的定位方式是使其主平面平行于货架。 机架包括用于引导用于电子设备项目的冷却的空气流的装置，空气流与电子设备项目的平面平行地插入有用室，并且与支架的插入方向成直角。 平台。

公开(公告)号：US20150241144A1

公开(公告)日：2015-08-27

申请号：US14625480

申请日：2015-02-18

Applicant: THALES

Inventor： Claude Sarno ,  Philippe Oconte ,  Romain Hodot

IPC: F28F9/007 ,  F28D1/02

CPC classification number: F28F9/007 ,  F28D1/02 ,  H05K7/20645 ,  H05K7/20681

Abstract: Heat regulation system (1) for at least one equipment item (2) embedded onboard an aircraft, includes a thermal regulation circuit (5) connected to the equipment item(s) (2). The thermal regulation circuit (5) includes a modular thermal regulation device (6) adapted to receive a modifiable number of thermal regulation modules (8).

Abstract translation: 用于至少一个嵌入在飞行器上的设备项目（2）的热调节系统（1）包括连接到设备项目（2）的热调节电路（5）。 热调节电路（5）包括适于接收可修改数量的热调节模块（8）的模块化热调节装置（6）。

公开(公告)号：US11300332B2

公开(公告)日：2022-04-12

申请号：US16232779

申请日：2018-12-26

Applicant: THALES

Inventor： Romain Hodot ,  Claude Sarno

IPC: F25B21/02 ,  G01P1/02 ,  H01L35/32 ,  G05D23/19 ,  G05D23/24

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：US10183753B2

公开(公告)日：2019-01-22

申请号：US15220481

申请日：2016-07-27

Applicant: THALES

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

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

Abstract: A piece of aeronautic equipment intended to equip an aircraft, the equipment (25) including a part intended to be arranged at a skin (27) of the aircraft and elements for heating the part, characterized in that the heating elements include a thermodynamic loop including a closed circuit in which a heat transfer fluid circulates, the closed circuit including an evaporator (14) associated with functional elements (25a) of the aircraft forming a heat source giving off heat during their operation and a zone in which a condensation of the heat transfer fluid can occur in the appendage to heat it, and in that outside the evaporator (14), the circuit in which the fluid circulates is formed by a tubular channel with an empty section.

公开(公告)号：US10994988B2

公开(公告)日：2021-05-04

申请号：US16293330

申请日：2019-03-05

Applicant: THALES

Inventor： Bertrand Leverrier ,  Claude Sarno ,  Claude Rougeot ,  Romain Hodot

IPC: B81B7/02 ,  B81B7/00

Abstract: The present invention relates to an electronic system comprising an electronic system comprising an electromechanical microsystem and a hermetic box encapsulating said microsystem. The box includes a fastening plane. The electromechanical microsystem includes a sensitive part and at least two beams connecting the sensitive part to the fastening plane. The beams are thermally coupled to the sensitive part and are electrically coupled to one another. The system further includes a thermal regulator of the electromechanical microsystem including an electrical circuit including at least two ends connected to the beams, and a circuit controller able to generate an electrical current in the electrical circuit to modify the temperature of the sensitive part.