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：US10724915B2

公开(公告)日：2020-07-28

申请号：US15990485

申请日：2018-05-25

Applicant: THALES

Inventor： Jean-Pierre Schlotterbeck ,  Jean-Philippe Pineau

IPC: G01P5/26 ,  G01P21/00 ,  G01C5/06 ,  G01L19/00 ,  G01S17/88 ,  G01L27/00 ,  G01P13/02 ,  G01P21/02 ,  G01P5/14 ,  G01S17/58

Abstract: A static pressure measurement probe system comprises: a base to be fixed onto the cockpit of an aircraft; at least one local pressure tapping formed through the base and coupled to a pressure measurement sensor; for each local pressure tapping, at least two assemblies each comprising an optical window that is transparent to a laser radiation and a laser anemometry probe configured to take anemometry measurements in an imaginary cylinder centred on the local pressure tapping and of a diameter less than 3 cm and of a height less than 4 cm counted from the outer end of the local pressure tapping, so that the measurements are within the airflow limit layer.

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：US20130145862A1

公开(公告)日：2013-06-13

申请号：US13708970

申请日：2012-12-08

Applicant: THALES

Inventor： Henri Leblond ,  Yves Jaulain ,  Jean-Philippe Pineau

IPC: G01P5/165

CPC classification number: G01P5/165 ,  G01P5/10

Abstract: A probe for measuring the total pressure of a flow and a method for implementing the probe is provided. The probe is intended to be fitted in an aircraft. The probe comprises a Pitot tube and means for reheating the probe assembly. The probe also comprises means for measuring a local temperature of regions of the Pitot tube likely to accumulate particles conveyed by the flow independently of the means for determining the average temperature of the probe. If the temperature delivered by the means for measuring a local temperature of regions of the Pitot tube likely to accumulate particles conveyed by the flow is less than the first reference temperature, then an additional reheating of regions of the Pitot tube likely to accumulate particles conveyed by the flow is triggered.

Abstract translation: 提供了用于测量流量的总压力的探针和用于实现探针的方法。 探头用于安装在飞机上。 探头包括皮托管和用于再加热探针组件的装置。 探头还包括用于测量皮托管的区域的局部温度的装置，其可能积聚由流动传送的颗粒，独立于用于确定探针的平均温度的装置。 如果通过用于测量皮托管的区域的局部温度的方法传递的温度可能积聚由流动传送的颗粒的温度小于第一参考温度，则皮托管的区域的另外再加热可能会积聚由 流量被触发。

公开(公告)号：US09116162B2

公开(公告)日：2015-08-25

申请号：US13708970

申请日：2012-12-08

Applicant: THALES

Inventor： Henri Leblond ,  Yves Jaulain ,  Jean-Philippe Pineau

IPC: G01P13/00 ,  G01P5/165 ,  G01P5/10

CPC classification number: G01P5/165 ,  G01P5/10

Abstract: A probe for measuring the total pressure of a flow and a method for implementing the probe is provided. The probe is intended to be fitted in an aircraft. The probe comprises a Pitot tube and means for reheating the probe assembly. The probe also comprises means for measuring a local temperature of regions of the Pitot tube likely to accumulate particles conveyed by the flow independently of the means for determining the average temperature of the probe. If the temperature delivered by the means for measuring a local temperature of regions of the Pitot tube likely to accumulate particles conveyed by the flow is less than the first reference temperature, then an additional reheating of regions of the Pitot tube likely to accumulate particles conveyed by the flow is triggered.

Abstract translation: 提供了用于测量流量的总压力的探针和用于实现探针的方法。 探头用于安装在飞机上。 探头包括皮托管和用于再加热探针组件的装置。 探头还包括用于测量皮托管的区域的局部温度的装置，其可能积聚由流动传送的颗粒，独立于用于确定探针的平均温度的装置。 如果通过用于测量皮托管的区域的局部温度的方法传递的温度可能积聚由流动传送的颗粒的温度小于第一参考温度，则皮托管的区域的另外再加热可能会积聚由 流量被触发。

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.