公开(公告)号：WO2020234544A1

公开(公告)日：2020-11-26

申请号：PCT/FR2020/050840

申请日：2020-05-20

Applicant: LIEBHERR-AEROSPACE TOULOUSE SAS

Inventor： MAURY, Damien ,  LOSSOUARN, David ,  MANCHO, Jean-Luc ,  BREGOLI, Mickael ,  ANGELIQUE, Romain

IPC: F02C7/14 ,  F01D17/14 ,  F01D25/12 ,  F02C7/18 ,  B64D13/08

Abstract: L'invention concerne un régulateur, configuré pour recevoir un flux d'air chaud via une entrée (12) d'air, pour traiter cet air chaud et pour transmettre l'air chaud traité vers une sortie (14) d'air configurée pour alimenter un actionneur (16) pneumatique, comprenant au moins un élément (36, 37) électrique et/ou mécanique sensible à la température, et un corps (100) de régulateur. Le régulateur est aractérisé en ce que le corps de régulateur est composé d'une enceinte (28) creuse conductrice de chaleur entourant au moins en partie un conduit (22) permettant le transport du flux d'air chaud, ladite cavité étant remplie au moins en partie d'un maillage métallique fabriqué par fabrication additive permettant la circulation de l'air de refroidissement, et en ce que l'élément (36, 37) électrique et/ou mécanique sensible à la température est agencé dans ou au contact du régulateur de sorte à être refroidi par l'air de refroidissement par conduction thermique.

公开(公告)号：WO2020138075A1

公开(公告)日：2020-07-02

申请号：PCT/JP2019/050593

申请日：2019-12-24

Applicant: 川崎重工業株式会社

Inventor： 春木　悠 ,  坂川　佳司 ,  袴田　和英 ,  三谷　亮介

IPC: B64D13/08 ,  B64D33/10 ,  B64D47/00 ,  F28D1/02

Abstract: 外板冷却システムは、外板及び内板を有する外殻と、内板の内側に設けられた熱源室と、外板と内板との間に設けられ、与圧気体及び熱源室からのリターン気体のうち少なくとも一方の気体が流入し、当該気体が外板を介して外部へ放熱することにより冷却気体となって流出する冷却路と、外板と内板との間に冷却路及び外板から熱的に絶縁されるように設けられ、与圧気体及び熱源室からのリターン気体のうち少なくとも一方の気体が通過する非冷却路と、冷却路から出た冷却気体と非冷却路から出た非冷却気体とが流入し、それらが混合された混合気体となって熱源室へ流出する混合室と、混合室へ流れる冷却気体の流量を調整する流量調整弁とを備える。

公开(公告)号：WO2018183731A1

公开(公告)日：2018-10-04

申请号：PCT/US2018/025228

申请日：2018-03-29

Applicant: ROCKWELL COLLINS, INC.

Inventor： TSAI, Hsin-I ,  BURD, Peter John, Leslie ,  JOLLEY, Richard, Henry

IPC: B64D11/00 ,  B64D11/04 ,  B64D13/00 ,  B64D13/06 ,  B64D13/08 ,  B64D47/00

CPC classification number: B64D11/04 ,  F25B21/02 ,  F25B2321/0252 ,  F25B2700/21 ,  F25D15/00 ,  F25D23/12 ,  F25D25/025 ,  F28D9/0062 ,  F28F3/025 ,  Y02T50/46

Abstract: A solid state liquid-chilled bar unit for an aircraft galley includes a multilevel frame dimensioned to fit the galley and including stacked slots, each slot configured to fit a compartment. Warmer compartments include a liquid thermoelectric device (LTD) with "cold" and "hot" sides and a liquid heat exchanger (LHE) connected to the cold side. Scroll fans circulate air over a finned heat exchanger (on the LTD's hot side) to heat the compartment. Chiller compartments include LTDs with an LHE connected to the "hot" side, and may be bottle coolers or chiller drawers. Bottle coolers chill bottles or other containers via conductive contact with the LTD "cold" side, while chiller drawers chill air by circulating it over a finned heat exchanger on the "cold" side. Unchilled drawers store food, drink, or supplies at or near the ambient cabin temperature.

公开(公告)号：WO2018144080A8

公开(公告)日：2018-08-09

申请号：PCT/US2017/056849

申请日：2017-10-17

Applicant: GENERAL ELECTRIC COMPANY

Inventor： HURT, Matthew, John ,  CARITA, Robert, Gregory ,  BRINSON, Thomas, Edward ,  CERNY, Matthew, Robert ,  MISRA MARTINEZ, Amit, Kumar ,  PARKER, David, Vickery ,  PEREZ VALADEZ, Alejandro, Yatzail

IPC: F02C6/08 ,  F02C9/18 ,  B64D13/08

Abstract: Systems and methods for integrated power and thermal management in a turbine-powered aircraft are provided. The systems may include rotationally-independent first and second auxiliary power unit shafts, a power turbine, a first compressor, a second compressor, a cooling turbine, and an electrical motor-generator. The power turbine may be rotatably disposed on the first auxiliary power unit shaft. The first compressor may be rotatably disposed on the first auxiliary power unit shaft. The second compressor may be rotatably disposed on the second auxiliary power unit shaft. The cooling turbine may be rotatably disposed on the second auxiliary power unit shaft. The electrical motor-generator may disposed on the first auxiliary power unit shaft to alternatively supply a motive force input to the first auxiliary power unit shaft and an electrical power output to the aircraft.

公开(公告)号：WO2017077305A1

公开(公告)日：2017-05-11

申请号：PCT/GB2016/053416

申请日：2016-11-03

Applicant: BAE SYSTEMS PLC

Inventor： VICKERS, Mark, Gordon ,  SHARPE, Douglas, John

IPC: G05D23/13 ,  B64D13/08 ,  F02C6/08

CPC classification number: G05D23/1931 ,  B64D13/08 ,  F02C6/08 ,  G05D23/24

Abstract: An aircraft environmental control system (4) for controlling a temperature of a fluid, the control system (4) comprising: a first temperature sensor (30) configured to measure a first temperature and to generate a first signal, the first temperature being a temperature of the fluid, the first signal being indicative of the measured first temperature; an amplifier (76) configured to amplify the first signal; one or more processors (64) configured to, using the amplified first signal, generate a control signal for controlling the temperature of the fluid; and a second temperature sensor (68) configured to measure a second temperature, the second temperature being a temperature of an operational environment of the amplifier (76); wherein the one or more processors (64) are further configured to, responsive to the determining that the measured second temperature satisfies one or more predetermined criteria, modify a gain of the amplifier (76)and wherein: the aircraft environmental control system (4) further comprises a baseline signal generation module (70) configured to generate a baseline signal, the baseline signal being independent of the measured temperature of the operational environment of the amplifier (76);the amplifier (76) is further configured to amplify the baseline signal; and the one or more processors (64) are further configured to, responsive to the determining that measured second temperature satisfies the one or more criteria, modify the gain of the amplifier (76) using the amplified baseline signal.

Abstract translation: 一种用于控制流体温度的飞行器环境控制系统（4），所述控制系统（4）包括：第一温度传感器（30），其被配置为测量第一温度并且生成第一温度 信号，第一温度是流体的温度，第一信号指示测得的第一温度; 放大器（76），其被配置为放大所述第一信号; 一个或多个处理器（64），被配置为使用放大的第一信号产生用于控制流体温度的控制信号; 以及配置成测量第二温度的第二温度传感器（68），所述第二温度是所述放大器（76）的操作环境的温度; 其中所述一个或一个以上处理器进一步经配置以响应于所述测得的第二温度满足一个或一个以上预定标准的所述确定而修改所述放大器的增益，且其中：所述飞行器环境控制系统（4） 进一步包括被配置为生成基线信号的基线信号生成模块（70），所述基线信号独立于所述放大器（76）的操作环境的测量温度;所述放大器（76）还被配置为放大所述基线信号 ; 并且所述一个或多个处理器（64）还被配置为响应于测量的第二温度满足所述一个或多个标准的确定，使用所述放大的基线信号修改所述放大器（76）的增益。

公开(公告)号：WO2017053786A1

公开(公告)日：2017-03-30

申请号：PCT/US2016/053426

申请日：2016-09-23

Applicant: FISHER CONTROLS INTERNATIONAL LLC

Inventor： JACKSON, Trenton, F.

IPC: G05D23/13 ,  B64D13/08 ,  F25B9/04 ,  G01N30/30 ,  G05D23/19

CPC classification number: F25B9/04 ,  G05D23/134

Abstract: A process control apparatus includes a housing, a process control device disposed in the housing, and a temperature control device operably coupled to the housing for regulating a temperature of an atmosphere internal to the housing. The temperature control device includes a vortex tube and a flow control valve. The flow control valve is coupled to the vortex tube and includes a temperature sensing feature configured to sense a temperature of an atmosphere internal to the housing and configured to move a control element of the flow control valve based on the sensed temperature between a plurality of positions to selectively direct the flow of fluid from the first and second vortex outlets to the atmosphere internal to the housing.

Abstract translation: 过程控制装置包括壳体，设置在壳体中的过程控制装置和可操作地联接到壳体的温度控制装置，用于调节壳体内部的气氛的温度。 温度控制装置包括涡流管和流量控制阀。 流量控制阀联接到涡流管并且包括温度感测特征，其被配置为感测壳体内部的气氛的温度并且被配置为基于在多个位置之间的感测温度来移动流量控制阀的控制元件 以选择性地将流体从第一和第二涡流出口引导到壳体内部的大气。

公开(公告)号：WO2016135101A1

公开(公告)日：2016-09-01

申请号：PCT/EP2016/053679

申请日：2016-02-22

Applicant: AIRBUS OPERATIONS GMBH

Inventor： SIEBEN, Martin

IPC: B64D11/00 ,  B64D11/04 ,  B64D13/00 ,  B64D13/08 ,  B64D13/06

CPC classification number: B64D11/0007 ,  B64D11/04 ,  B64D13/006 ,  B64D13/08 ,  B64D2011/0046 ,  B64D2013/0629 ,  Y02T50/56

Abstract: A system for manufacturing a kitchen arrangement for a cabin of a vehicle exhibits a primary module (4) with an electrical energy supply device, a cooling device, and at least one supply connection for supplying the primary module (4) with a requisite. The system further exhibits at least one auxiliary module (6) that can be coupled with the primary module (4). The cooling device is set up to provide a stream of cooled fluid to a fluid outlet (44). At least one outer boundary surface (8) of the primary module (4) exhibits an electrical connection coupled with the electrical energy supply device and a fluid connection (48) coupled with the fluid outlet (44). The at least one outer boundary surface is adjusted for coupling with an auxiliary module having a correspondingly shaped boundary surface.

Abstract translation: 一种用于制造车辆舱室的厨房装置的系统，其具有主要模块（4），其具有电能供应装置，冷却装置和用于向主模块（4）供应必要的至少一个供应连接。 该系统还具有至少一个辅助模块（6），其可以与主模块（4）耦合。 冷却装置设置成向流体出口（44）提供冷却流体流。 主模块（4）的至少一个外边界表面（8）呈现与电能供应装置耦合的电连接以及与流体出口（44）耦合的流体连接（48）。 调整至少一个外边界表面以与具有相应形状的边界表面的辅助模块联接。

公开(公告)号：WO2015054009A1

公开(公告)日：2015-04-16

申请号：PCT/US2014/058700

申请日：2014-10-01

Applicant: B / E AEROSPACE, INC.

Inventor： BURD, Peter John Leslie

IPC: F25D19/00 ,  B64D11/04 ,  B64D13/08

CPC classification number: B64D11/04 ,  B64D13/08 ,  B64D2013/0629 ,  F25D19/003 ,  F25D2317/067

Abstract: A chilled air plenum system for aircraft galleys adapted to be connected to a food cart bay for a food cart includes an air return plenum having a return airflow duct with a plurality of midline primary apertures and a plurality of secondary lateral side edge apertures for receiving return airflow from the food cart. The return airflow duct also includes a central lower resilient back stop and lateral side edge resilient back stops to prevent a cart from impacting the rear of the food cart bay. The return air plenum can be at least partially integrated into a galley back wall structure.

Abstract translation: 用于适于连接到用于食品车的食品车间隔架的用于飞机厨房的冷却空气通风系统包括具有多个中线主孔的返回气流管道和用于接收返回的多个次级侧向侧边缘孔的回气通风室 来自食物车的气流。 回流通风管还包括中央的下部弹性后挡块和侧向侧边缘弹性后挡块，以防止推车撞击食物车托架的后部。 返回空气增压室可以至少部分地集成到厨房后壁结构中。

公开(公告)号：WO2013083436A1

公开(公告)日：2013-06-13

申请号：PCT/EP2012/073719

申请日：2012-11-27

Applicant: AIRBUS OPERATIONS GMBH

Inventor： ALTAY, Mehmet

IPC: B64D15/12 ,  B64C1/18 ,  B64D13/08

CPC classification number: H05B1/0236 ,  B64C1/1453 ,  B64C1/18 ,  B64D13/08 ,  B64D15/12 ,  B64D2221/00 ,  B64G1/428 ,  B64G1/50 ,  H04B3/548 ,  H04B2203/5458

Abstract: The present invention relates to a heating system (10) for an aircraft or spacecraft with a control device (5) which comprises at least one power line data transmission transceiver (5a; 5b) and one sensor controller (7), and at least one remote component (1) which comprises a sensor element (4) and a heating element (2), the at least one power line data transmission transceiver (5a; 5b) being connected to the at least one remote component (1) via a connecting cable (8a; 8b), the control device (5) being designed to supply the at least one heating element (2) with power via the connecting cable (8a; 8b) and the sensor controller (7) being designed to exchange first control signals with the sensor element (4) via the connecting cable (8a; 8b).

Abstract translation: 本发明涉及一种用于具有控制装置（5）的飞机或航天器的加热系统（10），该控制装置包括至少一个电力线数据传输收发器（5a; 5b）和一个传感器控制器（7），以及至少一个 远程组件（1），其包括传感器元件（4）和加热元件（2），所述至少一个电力线数据传输收发器（5a; 5b）通过连接到所述至少一个远程组件（1）连接 电缆（8a; 8b），所述控制装置（5）被设计成经由所述连接电缆（8a; 8b）向所述至少一个加热元件（2）供电;以及所述传感器控制器（7）被设计成交换第一控制 通过连接电缆（8a; 8b）与传感器元件（4）发出信号。

公开(公告)号：WO2012095645A1

公开(公告)日：2012-07-19

申请号：PCT/GB2012/050013

申请日：2012-01-06

Applicant: BAE SYSTEMS plc ,  SMITH, Stephen, John, Richard ,  WATT, Kieran, James

Inventor： SMITH, Stephen, John, Richard ,  WATT, Kieran, James

IPC: B64D13/08 ,  B64D15/06

CPC classification number: B64D13/00 ,  B64D13/06 ,  B64D13/08 ,  B64D15/02 ,  B64D2013/0614 ,  B64D2013/0633 ,  B64F1/362 ,  Y02T50/56

Abstract: A method and apparatus for a turboprop-powered medium altitude long endurance (MALE) aircraft, comprising: a heat exchanger (51) comprising a heat-storage material, for example a heat-storage wax; and an air recirculation path (26); wherein the heat exchanger (51) is arranged to cool air recirculating around the air recirculation path (26) which is arranged to provide cooling to the MALE aircraft, for example to an equipment bay (18). The heat-storage material may be cooled by ground-based cooling apparatus when the aircraft is on the ground and/or by ram air when the aircraft is in flight. The heat-storage material may have a melting point selected so as to be rendered solid during ground- based cooling and/or ram air cooling, and/or selected so as to undergo melting whilst cooling the air recirculating around the air recirculation path (26).

Abstract translation: 一种用于涡轮螺旋桨发动机的中等高度长寿命（MALE）飞行器的方法和装置，包括：热交换器（51），其包括蓄热材料，例如储热蜡; 和空气再循环路径（26）; 其中所述热交换器（51）布置成冷却围绕所述空气再循环路径（26）再循环的空气，所述空气再循环路径被布置成向所述MALE飞机提供冷却，例如到设备隔间（18）。 当飞机在飞行中时，飞机在地面上和/或冲压空气时，储热材料可以被地面冷却装置冷却。 储热材料可以具有选择的熔点，以便在基于地面的冷却和/或冲压空气冷却期间变得固体，和/或选择以在冷却围绕空气再循环路径（26）再循环的空气的同时进行熔化 ）。