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    DAMAGE DETECTION FOR ROTARY ANGLE MEASUREMENT SENSORS
    1.
    发明公开
    DAMAGE DETECTION FOR ROTARY ANGLE MEASUREMENT SENSORS 审中-公开

    公开(公告)号：EP4495013A3

    公开(公告)日：2025-03-12

    申请号：EP24209542.0

    申请日：2021-09-20

    Applicant: ROSEMOUNT AEROSPACE INC.

    Inventor： NASLUND, Brian Brent ,  KANE, Brian D. ,  SCHAUB, Steven ,  MATHEIS, Brian Daniel

    IPC: G01P13/02 ,  G01P21/02 ,  B64D45/02 ,  B64D43/02 ,  G01D3/08 ,  G01P15/00 ,  B64D45/00

    Abstract: An angle of attack sensor includes a mounting plate (68); a vane (12) supported from the mounting plate and extending from a first side of the mounting plate, wherein the vane is rotatable about a vane axis; a housing (36) extending from a second side of the mounting plate in a direction opposite to the vane; a resolver (64) coupled to the vane; and an electronics module (72) mounted within the housing, the electronics module comprising: at least one processor (88); a communication device (92); and computer-readable memory (90), encoded with instructions that, when executed by the at least one processor, cause the electronics module to: receive, from the resolver, a signal indicative of an angular position of the vane about the vane axis; compare the signal to a first damage criterion; and output, using the communication device, a first fault signal to a consuming system of an aircraft that is indicative of a damage event based on a comparison of the signal to the first damage criterion..

    ACOUSTIC AIR DATA SYSTEMS
    2.
    发明公开
    ACOUSTIC AIR DATA SYSTEMS 审中-公开

    公开(公告)号：EP3730947A1

    公开(公告)日：2020-10-28

    申请号：EP19214956.5

    申请日：2019-12-10

    Applicant: ROSEMOUNT AEROSPACE INC.

    Inventor： SLY, Jamie ,  SHANNON, Daniel W. ,  MATHEIS, Brian Daniel ,  ELL, Todd A. ,  KUNIK, William ,  KOUSHIK, Surdarshan N.

    IPC: G01P5/24 ,  G01P13/02 ,  B64D43/02

    Abstract: An ultrasonic air data system (100) can include a pole (103) having a length (103) longer than a boundary layer thickness (105) of a boundary layer flow (107) such that at least a distal end of the pole is configured to extend outwardly from an aircraft surface to be at least partially outside of the boundary layer flow. The system can include a transmitter (111) disposed on or in the pole at or near the distal end of the pole such that the transmitter is located at least partially outside of the boundary layer flow when in use, wherein the transmitter is configured to output a transmitter signal. The system can include one or more receivers (115) disposed downstream of the pole as defined by the boundary layer flow and configured to receive the transmitter signal.

    AIRCRAFT FREESTREAM DATA SYSTEMS
    3.
    发明公开
    AIRCRAFT FREESTREAM DATA SYSTEMS 审中-公开

    公开(公告)号：EP3633388A1

    公开(公告)日：2020-04-08

    申请号：EP19201552.7

    申请日：2019-10-04

    Applicant: ROSEMOUNT AEROSPACE INC.

    Inventor： MATHEIS, Brian Daniel ,  SLY, Jamie ,  EGBERG, James Barron

    IPC: G01P5/24 ,  G01P13/02 ,  G01P21/02

    Abstract: An aircraft freestream data system can include a first ultrasonic air data system (UADS) (101) configured to sense local acoustic properties at a first location on an aircraft, a first local air data module (103) operatively connected to the first UADS and configured to determine first local air data of the first location and to output first local air data, and a freestream data module (105) operatively connected to the first local air data module. The freestream data module can be configured to receive the first local air data from the local air data module, determine one or more freestream air data parameters based on at least the first local air data, and output the one or more freestream air data parameters to one or more aircraft consuming systems.

    AUTOMATED SUPER-COOLED WATER-DROPLET SIZE DIFFERENTIATION USING AIRCRAFT ACCRETION PATTERNS
    4.
    发明公开
    AUTOMATED SUPER-COOLED WATER-DROPLET SIZE DIFFERENTIATION USING AIRCRAFT ACCRETION PATTERNS 审中-公开
    使用飞机增量模式自动超冷却水滴尺寸差异

    公开(公告)号：EP3263460A1

    公开(公告)日：2018-01-03

    申请号：EP17178461.4

    申请日：2017-06-28

    Applicant: Rosemount Aerospace Inc.

    Inventor： LoPresto, Vincent R. ,  MATHEIS, Brian Daniel

    IPC: B64D15/20 ,  G08B19/02

    CPC classification number: B64D15/20 ,  B64D45/00 ,  B64D47/08 ,  G01N15/0227 ,  G08B19/02

    Abstract: Apparatus and associated methods relate to determining, based on a spatial extent of ice accretion, whether an atmosphere contains super-cooled water droplets that equal and/or exceed a predetermined size. A convex-shaped housing is mounted to an aircraft and exposed to an airstream. The convex-shaped housing has a testing region that is monitored for ice accretion by an ice detector. A boundary locator determines a specific location to be tested within the testing region. The determined specific location corresponds to a calculated boundary that separates an ice-accretion region from an ice-free region if the atmosphere contains super-cooled water droplets up to the predetermined size. If the ice detector detects ice accretion at the determined specific location, an alert is generated. The alert can advantageously inform a pilot of an atmosphere containing super-cooled water droplets that equal or exceed the predetermined size.

    Abstract translation: 装置和相关方法涉及基于积冰的空间范围确定大气是否包含等于和/或超过预定尺寸的过冷水滴。 一个凸形的外壳安装在飞机上并暴露在气流中。 凸形外壳具有测试区域，该测试区域由冰检测器监测冰积聚。 边界定位器确定测试区域内要测试的特定位置。 如果大气包含达到预定尺寸的过冷水滴，则确定的特定位置对应于计算的边界，该边界将冰积累区域与无冰区域分开。 如果冰检测器在确定的特定位置检测到积冰，则生成警报。 警报可以有利地向飞行员通知包含等于或超过预定尺寸的过冷水滴的气氛。

    AIR DATA PROBE WITH MEANS FOR REDUCING BOUNDARY LAYER SEPARATION
    5.
    发明公开
    AIR DATA PROBE WITH MEANS FOR REDUCING BOUNDARY LAYER SEPARATION 审中-公开
    LUFTDATENSONDE MIT MITTELN ZUR VERMINDERUNG DERGRENZSCHICHTABLÖSUNG

    公开(公告)号：EP2947465A1

    公开(公告)日：2015-11-25

    申请号：EP15168478.4

    申请日：2015-05-20

    Applicant: Rosemount Aerospace Inc.

    Inventor： DOOLITTLE, Charles Jae ,  FOSTER, Roger Duane ,  MATHEIS, Brian Daniel

    IPC: G01P5/165

    CPC classification number: G01P5/165 ,  G01L15/00

    Abstract: An air data probe includes a probe head (102;202;302;402;602) and a raised portion (106;206;306;406;606). The probe head defines a longitudinal axis (A) and includes a forward tip (104;204;304;404;604) and a probe head surface (107;207;307;407;607). The raised portion is defined in the probe head surface aft of the forward tip. The raised portion is raised radially relative to the probe head surface. The raised portion is configured and adapted to trip a fluid boundary layer passing over the probe head to transition from laminar to turbulent for reducing boundary layer separation for consistent readings at high altitudes and/or high mach numbers. A method of manufacturing an air data probe includes forming a probe head and applying a raised portion to a surface of the probe head aft of the forward tip. Applying the raised portion to the surface of the probe head includes using brazing, additive manufacturing, adhesives and/or any other suitable technique.

    Abstract translation: 空气数据探头包括探头（102; 202; 302; 402; 602）和凸起部分（106; 206; 306; 406; 606）。 探针头限定纵向轴线（A）并且包括前向尖端（104; 204; 304; 404; 604）和探针头表面（107; 207; 307; 407; 607）。 凸起部分被限定在前端后部的探针头表面中。 凸起部分相对于探针头表面径向地升高。 凸起部分被配置和适于使通过探针头的流体边界层跳过以从层流到湍流转变，以便减少边界层分离，从而在高海拔和/或高马赫数下保持一致的读数。 制造空气数据探头的方法包括形成探针头并将凸起部分施加到前尖端后面的探针头的表面。 将凸起部分应用于探头的表面包括使用钎焊，添加剂制造，粘合剂和/或任何其它合适的技术。

    AIRCRAFT FREESTREAM DATA SYSTEMS
    7.
    发明公开
    AIRCRAFT FREESTREAM DATA SYSTEMS 审中-公开

    公开(公告)号：EP4220186A1

    公开(公告)日：2023-08-02

    申请号：EP23161581.6

    申请日：2019-10-04

    Applicant: ROSEMOUNT AEROSPACE INC.

    Inventor： MATHEIS, Brian Daniel ,  EGBERG, James Barron ,  SLY, James

    IPC: G01P5/24 ,  G01P13/02 ,  G01P21/02

    Abstract: An aircraft freestream data system can include a first ultrasonic air data system (UADS) (101) configured to sense local acoustic properties at a first location on an aircraft, a first local air data module (103) operatively connected to the first UADS and configured to determine first local air data of the first location and to output first local air data, and a freestream data module (105) operatively connected to the first local air data module. The freestream data module can be configured to receive the first local air data from the local air data module, determine one or more freestream air data parameters based on at least the first local air data, and output the one or more freestream air data parameters to one or more aircraft consuming systems.

    ACOUSTIC AIR DATA SENSING SYSTEM WITH SKIN FRICTION SENSOR
    8.
    发明公开
    ACOUSTIC AIR DATA SENSING SYSTEM WITH SKIN FRICTION SENSOR 审中-公开

    公开(公告)号：EP3712620A1

    公开(公告)日：2020-09-23

    申请号：EP19213156.3

    申请日：2019-12-03

    Applicant: ROSEMOUNT AEROSPACE INC.

    Inventor： MATHEIS, Brian Daniel ,  SHANNON, Daniel W. ,  KOUSHIK, Surdarshan N.

    IPC: G01P5/24 ,  G01P5/04 ,  G01P5/10 ,  G01P13/02 ,  G01P13/00 ,  G01H5/00

    Abstract: An acoustic air data sensing system includes an acoustic transmitter, a plurality of acoustic receivers, and a skin friction sensor. The acoustic transmitter is located to transmit an acoustic signal into airflow about an exterior of a vehicle. Each of the acoustic receivers is located at a respective angle from a wind angle reference line and a respective distance from the acoustic transmitter. The skin fiction sensor is positioned in a boundary layer region of the airflow that interacts with the acoustic receivers and transmitter. Based on time of flight values of the acoustic signal from the transmitter to each of the receivers and a skin friction measurement from the skin friction sensor as inputs to a transformation matrix, the acoustic air data sensing system outputs, from the transformation matrix, the true airspeed, the relative wind angle, and the speed of sound for operational control of the vehicle.

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