公开(公告)号：EP2728364A1

公开(公告)日：2014-05-07

申请号：EP13190036.7

申请日：2013-10-24

Applicant: Rosemount Aerospace Inc.

Inventor： Seidel, Greg ,  Golly, Timothy Thomas

IPC: G01P5/165

CPC classification number: G01F1/46 ,  G01P5/165

Abstract: A pitot tube (10) includes a substantially cylindrical body portion (12) and a tip portion (14) extending along a pitot tube axis (16) from the body portion (12). The tip portion (14) includes an inlet opening (20) and a radially tapering outer surface (26) extending from the body portion (12) toward the inlet opening (20). Another pitot tube (10) includes a substantially cylindrical body portion (12) and a tip portion (14) extending along a pitot tube axis (16) from the body portion. The tip portion (14) includes an inlet opening (20). One or more electrical coils (34) including one or more coil wraps (46) are located at an interior (30) of the pitot tube (10). One or more bulkeads (58) are located between a forwardmost coil wrap (46A) and a drainage feature (58) to limit travel of particles ingested into the interior (30).

Abstract translation: 皮托管（10）包括基本上圆柱形的主体部分（12）和从主体部分（12）沿皮托管轴线（16）延伸的末端部分（14）。 尖端部分（14）包括从主体部分（12）朝向入口（20）延伸的入口（20）和径向渐缩的外表面（26）。 另一个皮托管（10）包括基本上圆柱形的主体部分（12）和从主体部分沿皮托管轴线（16）延伸的尖端部分（14）。 尖端部分（14）包括入口（20）。 一个或多个包括一个或多个线圈圈（46）的电线圈（34）位于皮托管（10）的内部（30）处。 一个或多个隔板（58）位于最前面的线圈包裹（46A）和排水构件（58）之间，以限制摄入到内部（30）中的颗粒的行进。

公开(公告)号：EP2692643A2

公开(公告)日：2014-02-05

申请号：EP13179161.8

申请日：2013-08-02

Applicant: ROSEMOUNT AEROSPACE INC.

Inventor： Garnett, Harold E ,  Webb, Matthew M ,  Skoglund, Jason L

IPC: B64D15/12 ,  B64D15/22

CPC classification number: B64D15/22 ,  B64D15/14

Abstract: A method for managing icing conditions on a rotary aircraft via one or more ice protection controllers. The method includes steps for receiving an icing condition signal from an icing rate sensor (125) at an ice protection controller (205), determining, in response to the icing condition signal, a de-icing signal based at least in part a liquid water content (LWC). The method further includes steps for transmitting, via a digital communication bus (350) disposed in at least part of a slip ring assembly (107; 230), the de-icing signal to a upper distributor (215) to cause the upper distributor to transmit power to one or more heating elements (220) for a respective rotor blade.

Abstract translation: 一种用于通过一个或多个防冰控制器管理旋翼飞机上的结冰条件的方法。 该方法包括用于在防冰控制器（205）处接收来自结冰速率传感器（125）的结冰状况信号的步骤，响应于结冰状况信号来确定至少部分地基于液态水的除冰信号 内容（LWC）。 该方法还包括以下步骤：经由设置在滑环组件（107; 230）的至少一部分中的数字通信总线（350）将除冰信号传输到上部分配器（215），以使上部分配器 将功率传输到用于相应转子叶片的一个或多个加热元件（220）。

公开(公告)号：EP2665013A1

公开(公告)日：2013-11-20

申请号：EP13167694.2

申请日：2013-05-14

Applicant: ROSEMOUNT AEROSPACE INC.

Inventor： Haukom, Michael James ,  Horsager, Thomas Jay ,  Thompson, Jesse Kelly

IPC: G06F21/84

CPC classification number: G06F21/84

Abstract: An example apparatus (600) includes a non-certified computing platform (102; 302; 400; 602), a certified computing platform (102; 302; 400; 604) and a user interface (404). The non-certified computing platform (102; 302; 400; 602) includes first hardware (606) and is configured to host non-certified software. The certified computing platform (102; 302; 400; 604) is separate and distinct from the non-certified computing platform (102; 302; 400; 602), and it includes second hardware (616) and is configured to host certified software in a partitioned environment. The user interface (404) is coupled to both platforms and includes a display (416; 628) coupled to both the first hardware (606) and second hardware (616) via a controllable switch (630). According to this example, the non-certified computing platform (102; 302; 400; 602) and certified computing platform (102; 302; 400; 604) are configured to host the non-certified software and certified software such that both are capable of operating concurrently.

Abstract translation: 的示例性装置（600）包括非认证计算平台（102; 302; 400; 602）（102; 302; 400; 604），经过认证的计算平台和用户接口（404）。 非认证计算平台（102; 302; 400; 602）包括第一硬件（606）和被配置为承载非认证软件。 （102; 302; 400; 604）的认证的计算平台是从非认证计算平台（102; 302; 400; 602）分开且不同，并且它包括第二硬件（616）和被配置为承载认证的软件在 分区环境。 用户接口（404）被耦合到两个平台，并且包括显示器（416; 628）经由一个可控开关（630）耦合到所述第一两个硬件（606）和第二硬件（616）。 。根据本实施例，在非认证计算平台（102; 302; 400; 602）和认证计算平台（102; 302; 400; 604）被配置为承载所述非认证的软件和认证的软件搜索没有两者都能够 经营兼任。

公开(公告)号：EP2330035A3

公开(公告)日：2013-10-16

申请号：EP10251876.8

申请日：2010-10-29

Applicant: ROSEMOUNT AEROSPACE INC.

Inventor： Heuer, Weston D.C. ,  Kane, Brian ,  Willcox, Charles

IPC: B64D15/20

CPC classification number: B64D15/20

Abstract: In an icing condition detection system, a circuit provides an output representing impending icing conditions as a function of power consumption of a single element detector. A thermal isolation pedestal includes a detector support end that supports the single element detector and an opposite strut mounting end. A thermal isolation controller controls a thermal isolation pedestal temperature to thermally isolate the single element detector from a strut mounting end.

公开(公告)号：EP2518529A3

公开(公告)日：2012-12-05

申请号：EP12164337.3

申请日：2012-04-16

Applicant: ROSEMOUNT AEROSPACE INC.

Inventor： Ray, Mark D

IPC: G01S17/95 ,  G01S7/499 ,  B64D15/20

CPC classification number: B64D15/20 ,  G01S7/499 ,  G01S17/95 ,  Y02A90/19

Abstract: An apparatus for detecting icing conditions on an aircraft. The apparatus including a laser system configured and operative to generate a light signal and direct the light signal into a cloud and a lens component configured and operative to collect echo signals from a cloud caused by the light signal directed into the cloud by the laser system. The apparatus further includes a beam splitter component configured and operative to redirect signals received and passing through the lens component into at least first and second paths. Further provided is a supercooled large droplet (SLD) detector positioned to receive the redirected signals from the beam splitter. The SLD includes a first signal detector component configured and operative to perform a first color measurement on the first redirected signal; and a second signal detector component configured and operative to perform a second color measurement on the second redirected signal wherein the SLD detector is configured and operative to use the first and second color measurements to determine liquid water content and droplet diameter distribution for the cloud in which the light signal was directed into by the laser system.

公开(公告)号：EP1593940B1

公开(公告)日：2012-08-22

申请号：EP04258108.2

申请日：2004-12-23

Applicant: ROSEMOUNT AEROSPACE INC.

Inventor： Myhre, Douglas C.

IPC: G01F1/684 ,  G01F1/688

CPC classification number: G01F1/6847 ,  G01F1/6888

公开(公告)号：EP2472269A3

公开(公告)日：2012-08-15

申请号：EP11250891.6

申请日：2011-11-11

Applicant: ROSEMOUNT AEROSPACE INC.

Inventor： Guo, Shuwen ,  Splvak, Alexander ,  Fink, Anita

IPC: G01P15/125

CPC classification number: G01P15/125 ,  G01P15/0802 ,  G01P2015/0814

Abstract: A system for determining in-plane acceleration of an object. The system includes an in-plane accelerometer with a substrate rigidly attached to an object, and a proof mass-formed from a single piece of material-movably positioned a predetermined distance above the substrate. The proof mass includes a plurality of electrode protrusions extending downward from the proof mass to form a gap of varying height between the proof mass and the substrate. The proof mass is configured to move in a direction parallel to the upper surfaces of each of the plurality of substrate electrodes when the object is accelerating, which results in a change in the area of the gap, and a change in capacitance between the substrate and the proof mass. The in-plane accelerometer can be fabricated using the same techniques used to fabricate an out-of-plane accelerometer and is suitable for high-shock applications.

公开(公告)号：EP2042429A3

公开(公告)日：2012-06-20

申请号：EP08014708.5

申请日：2008-08-19

Applicant: ROSEMOUNT AEROSPACE INC.

Inventor： Isebrand, Scott ,  Powell, James

IPC: B64D29/06 ,  E05C19/14

CPC classification number: B64D29/06 ,  E05B15/0205 ,  E05B17/22 ,  E05C19/145

Abstract: A sensor (100) includes a clevis insert (108) for reception within a first bore (106) of a clevis (102). The clevis insert (108) is configured to accommodate a latch pin (104). A strain sensing element (112) is operatively associated with the clevis insert (108) for detecting mechanical strain imparted to the clevis insert (108) when a force acts on the clevis insert (108) through the pin (104). The invention also provides a method of retrofitting a cowl latch assembly.

公开(公告)号：EP1936386B1

公开(公告)日：2012-05-30

申请号：EP07254949.6

申请日：2007-12-19

Applicant: ROSEMOUNT AEROSPACE INC.

Inventor： Alwin, Steve F. ,  Liffrig, Ronald Fritz ,  Sandnas, Matthew L.

IPC: B64D43/02 ,  G01P13/00

CPC classification number: B64C13/16 ,  B64D43/02 ,  G01K13/028

公开(公告)号：EP2354774A3

公开(公告)日：2011-12-28

申请号：EP10015707.2

申请日：2008-02-12

Applicant: ROSEMOUNT AEROSPACE INC.

Inventor： Myhre, Douglas

IPC: G01K1/14 ,  G01K13/00 ,  B22D11/08 ,  B22D11/18 ,  B22D11/20

CPC classification number: G01K1/146 ,  B22D11/225 ,  G01K13/00

Abstract: A temperature measurement system comprises a) a temperature sensor adapted and configured to measure a temperature of a body and b) means for biasing the temperature sensor in the direction of the body In response to heat exchange with the body, wherein the means for biasing includes a bimetallic member adapted and configured to extend from a first position in the absence of the thermal energy source to a second position when In the presence of the thermal energy source, and wherein the bimetallic member includes multiple bimetallic strips attached to each other end to end in an accordion configuration.

Abstract translation: 温度测量系统包括：a）温度传感器，其适于并构造成测量身体的温度;以及b）用于在身体的方向上偏置温度传感器的装置。响应于与身体的热交换，其中用于偏置的装置包括 双金属构件，所述双金属构件适于并构造成当存在热能源时从不存在热能源的第一位置延伸到第二位置，并且其中双金属构件包括多个彼此连接的双金属条带 在手风琴配置。