公开(公告)号：US09097735B2

公开(公告)日：2015-08-04

申请号：US14189875

申请日：2014-02-25

Applicant: THALES

Inventor： Frederic Martin ,  Serge Desbiolles ,  Jacques Mandle

IPC: G01P5/165 ,  G01C21/00

CPC classification number: G01P5/165

Abstract: A probe for measuring the total pressure of an airflow is intended to equip an aircraft and a method of using the probe. The probe comprises a Pitot tube, two separate heating wires supplied separately and allowing each one to heat an external part of the probe, and means of distribution of a given maximum power to each of the two heating wires as a function of the current temperature of each of the two parts. A method consists in giving priority to the reaching of a predefined minimum temperature of a first of the two parts of the probe by allocating to the first part of the probe a predefined share of the given maximum power for as long as the temperature of the first part is below a predefined minimum temperature.

Abstract translation: 用于测量气流总压力的探头旨在装备飞行器和使用探头的方法。 探针包括皮托管，分开供应的两根单独的加热线，并允许每一根加热线加热探头的外部部分，以及将给定的最大功率分配给两根加热线中的每一根的功能，作为当前温度的函数 这两个部分分别。 一种方法在于通过将探测器的第一部分的预定义份额分配给给定最大功率的预定份额来优先考虑达到探测器两部分中的第一部分的预定义的最低温度，只要第一 部分低于预定的最低温度。

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：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：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：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.