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公开(公告)号：US20170029123A1
公开(公告)日：2017-02-02
申请号：US15220524
申请日：2016-07-27
申请人： THALES
摘要： The invention relates to an aircraft provided with at least one piece of aeronautic equipment (100), the equipment comprising at least one part intended to be arranged at a skin (27) of the aircraft, and means for fastening on said skin outside the aircraft and means for heating the part, characterized in that the fastening means comprise means in the form of tubular tabs (101, 102), in that the heating means comprise a thermodynamic loop comprising a closed circuit in which a heat transfer fluid circulates, the closed circuit comprising an evaporator associated with means forming a heat source arranged inside the aircraft 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, at least partially formed in the tubular tabs (101, 102) of the fastening means.
摘要翻译： 本发明涉及一种设置有至少一件航空设备（100）的飞行器，该设备包括旨在布置在飞机的皮肤（27）上的至少一个部分，以及用于紧固在飞机外部的所述皮肤上的装置 以及用于加热所述部件的装置，其特征在于，所述紧固装置包括管状突片（101,102）形式的装置，其特征在于，所述加热装置包括热力循环，所述热力回路包括传热流体循环的封闭回路， 电路包括与形成设置在飞行器内部的热源的装置相关联的蒸发器，以及传热流体的冷凝可以在附件中发生加热的区域，并且在蒸发器外部，流体循环的回路 由具有空的部分的管状通道形成，至少部分地形成在紧固装置的管状突出部（101,102）中。
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公开(公告)号：US20170029124A1
公开(公告)日：2017-02-02
申请号：US15220644
申请日：2016-07-27
申请人： THALES
CPC分类号： 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
摘要： 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.
摘要翻译： 一种旨在装备飞行器的航空设备，设备件（25）包括至少一部分，旨在布置在飞机外面的皮肤（27）和用于该部件的加热元件，其包括热力循环，包括 封闭回路，其中传热流体循环，封闭回路包括蒸发器和传热流体的冷凝可以在附件中发生加热的区域，在蒸发器外部，流体循环的回路由 具有空的部分的管状通道，布置在飞机外部的设备的至少一部分由添加剂制造制成，并且包括紧固基座（120），用于紧固在飞行器的皮肤上，用于支撑元件（130）用于 设置有侧向静压抽头（150）的皮托管（140）延伸。
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公开(公告)号：US20170029121A1
公开(公告)日：2017-02-02
申请号：US15220428
申请日：2016-07-27
申请人： THALES
发明人： Claude SARNO , Romain HODOT
CPC分类号： B64D15/06 , B33Y10/00 , B33Y50/02 , B33Y80/00 , B64D15/12 , B64D33/08 , B64D43/02 , B64F5/10 , F28D15/02 , F28D15/0266 , F28D2021/0021 , G01P5/165
摘要： 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.
摘要翻译： 飞机设置有至少两件航空设备，第一件设备（25），其包括旨在布置在飞行器的皮肤（27）上的部件和用于加热部件的元件，其特征在于，所述加热元件包括 包括传热流体循环的闭合回路的热力循环，所述闭合回路包括与所述飞行器的第二设备（81）的功能元件（80）相关联的蒸发器（14），所述第二设备（81）形成发热体 在其操作期间和附加部分中可能发生传热流体的冷凝以加热的区域，并且在蒸发器（14）的外部，流体循环的回路由具有空的管状通道形成 部分。
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公开(公告)号：US20170029125A1
公开(公告)日：2017-02-02
申请号：US15221059
申请日：2016-07-27
申请人： THALES
发明人： Claude SARNO , Romain HODOT
CPC分类号： B64D15/06 , B22F3/1055 , B22F5/10 , B29C67/00 , B33Y10/00 , B33Y50/02 , B33Y80/00 , B64D15/12 , B64D33/08 , B64D43/02 , B64F5/00 , F25B39/00 , F25B39/02 , F28D15/0266 , F28D2021/0021 , G01P5/165
摘要： A piece of aeronautic equipment intended to equip an aircraft, the equipment including a part intended to be arranged at a skin of the aircraft and elements for heating the part in an appendage, characterized in that the heating elements include elements forming an oscillating heat pipe (90) including at least one evaporator associated with elements forming a heat source and at least one zone in which a condensation of the heat transfer fluid can occur in the appendage to heat it.
摘要翻译： 一种用于装备飞行器的航空设备，该设备包括旨在布置在飞行器皮肤上的部件和用于加热附件中的部件的元件，其特征在于，所述加热元件包括形成振荡热管（ 90），其包括与形成热源的元件相关联的至少一个蒸发器和至少一个区域，其中传热流体的冷凝可以在附件中发生以加热。
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公开(公告)号：US20170029122A1
公开(公告)日：2017-02-02
申请号：US15220481
申请日：2016-07-27
申请人： THALES
CPC分类号： B64D15/06 , B33Y10/00 , B33Y50/02 , B33Y80/00 , B64D15/12 , B64D33/08 , B64D43/02 , B64F5/00 , F28D15/0266 , F28D15/043 , F28D2021/0021 , G01P5/165 , G01P13/025
摘要： 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.
摘要翻译： 一种旨在装备飞行器的航空设备，设备（25）包括旨在布置在飞行器的皮肤（27）上的部件和用于加热部件的元件，其特征在于，加热元件包括热力循环，包括 闭合回路，其中传热流体循环，所述闭合回路包括与飞行器的功能元件（25a）相关联的蒸发器（14），所述蒸发器形成在其操作期间发热的热源以及热量冷凝的区域 传递流体可以在附件中发生以加热它，并且在蒸发器（14）的外部，流体循环的回路由具有空的部分的管状通道形成。
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公开(公告)号：US20190203982A1
公开(公告)日：2019-07-04
申请号：US16232779
申请日：2018-12-26
申请人： THALES
发明人： Romain HODOT , Claude Sarno
CPC分类号： F25B21/02 , F25B2321/0212 , G01P1/023 , G05D23/1919 , G05D23/24 , H01L35/32
摘要： 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.
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公开(公告)号：US20170030941A1
公开(公告)日：2017-02-02
申请号：US15220488
申请日：2016-07-27
申请人： THALES
发明人： Claude SARNO , Romain HODOT , Marc DUVAL-DESTIN
CPC分类号： G01P5/165 , B22F3/1055 , B22F5/10 , B33Y10/00 , B33Y50/02 , B33Y80/00 , B64D15/12 , B64D43/02 , F28D15/0266 , F28D2021/0021 , Y02P10/295
摘要： 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.
摘要翻译： 制造方法，通过添加用于装备飞行器的一件航空设备的至少一部分，该设备件包括旨在布置在飞行器的皮肤上的至少一个部件和用于该部件的加热元件，其包括热力学 循环，其包括至少部分集成的封闭回路，其中传热流体循环，闭合回路包括蒸发器和传热流体的冷凝可以在附件中发生加热，蒸发器外部的回路 由具有至少部分与设备件至少部分一体的空的部分的管状通道形成，设置在飞行器外部的至少一部分设备件通过添加剂制造制成，并且包括用于紧固在飞行器的皮肤上的基座， 皮托管的支撑元件延伸。
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公开(公告)号：US20170029126A1
公开(公告)日：2017-02-02
申请号：US15221170
申请日：2016-07-27
申请人： THALES
发明人： Claude SARNO , Romain HODOT
CPC分类号： B64D15/06 , B33Y10/00 , B33Y50/02 , B33Y80/00 , B64D15/12 , B64D33/08 , B64D43/02 , F28D15/0266 , F28D2021/0021 , G01F1/46 , G01P5/165
摘要： 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.
摘要翻译： 一种设置有至少一件航空设备的飞机，该设备（25）包括旨在布置在飞行器的皮肤（27）上的部件和用于加热该部件的元件，其特征在于，所述加热元件包括热力循环 包括其中传热流体循环的闭合回路，所述闭合回路包括与飞行器的功能元件（70）相关联的蒸发器（14），所述蒸发器形成在其操作期间发热的热源，并且其中冷凝 传热流体可以在附件中发生以加热它，并且在蒸发器外部，流体循环的回路由具有空的部分的管状通道形成。
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公开(公告)号：US20170029120A1
公开(公告)日：2017-02-02
申请号：US15220417
申请日：2016-07-27
申请人： THALES
CPC分类号： B64D15/06 , B33Y10/00 , B33Y50/02 , B33Y80/00 , B64D15/12 , B64D33/08 , B64D43/02 , B64F5/00 , F28D15/0266 , F28D15/043 , F28D2021/0021 , G01P5/165 , G01P13/025
摘要： A heating of a piece of aeronautic equipment intended to be arranged at the skin of the aircraft. The equipment (25) includes a part (30, 31) intended to be arranged at the skin (27) 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 (14) and a zone in which a condensation of the heat transfer fluid can occur in the appendage to heat it. Outside the evaporator (14), 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.
摘要翻译： 一架旨在安排在飞机皮肤上的航空设备的加热。 设备（25）包括旨在布置在飞行器的皮肤（27）上的部分（30,31）和用于加热部件的元件。 加热元件包括热力循环，其包括传热流体循环的封闭回路，包括蒸发器（14）的闭合回路和附加部分中可能发生传热流体的冷凝以加热的区域。 在蒸发器（14）的外部，流体循环的回路由具有空的部分的管状通道形成。 至少部分设备由具有低导热性的材料制成。
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公开(公告)号：US20160302259A1
公开(公告)日：2016-10-13
申请号：US15094882
申请日：2016-04-08
申请人： THALES
发明人： Claude SARNO , Romain HODOT
IPC分类号： H05B3/00
摘要： 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.
摘要翻译： 空气动力学测量探头包括位于飞行器皮肤区域中的部件和用于加热部件的装置。 加热装置包括热力循环，其包括传热流体在其中循环的闭合回路，闭合回路包括蒸发器和传热流体可以在其中的附属物中冷凝以便加热它的区域。 在蒸发器外部，流体循环的回路由开口横截面的管状管形成。
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