中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

27 records (took 0.013 seconds)

    DAMAGE DETECTION FOR ROTARY ANGLE MEASUREMENT SENSORS
    11.
    发明公开
    DAMAGE DETECTION FOR ROTARY ANGLE MEASUREMENT SENSORS 审中-公开

    公开(公告)号：EP4495013A2

    公开(公告)日：2025-01-22

    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: B64D43/02

    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..

    SYNTHETIC AIR DATA OUTPUT GENERATION
    13.
    发明公开
    SYNTHETIC AIR DATA OUTPUT GENERATION 审中-公开
    一般合成器LUFTDATEN

    公开(公告)号：EP3179254A1

    公开(公告)日：2017-06-14

    申请号：EP16201353.6

    申请日：2016-11-30

    Applicant: Rosemount Aerospace Inc.

    Inventor： ANDERSON, Kaare Josef ,  MATHEIS, Brian Daniel ,  HONGERHOLT, Derrick D. ,  KUNIK, William

    IPC: G01P13/02 ,  G01P5/16 ,  G01P21/02 ,  G01C21/16

    CPC classification number: B64D43/02 ,  G01C21/165 ,  G01P5/16 ,  G01P13/025 ,  G01P21/025 ,  G06N3/04 ,  G07C5/0808

    Abstract: The method according to the invention includes receiving, over an aircraft data communications bus, a plurality of non-pneumatic inputs corresponding to aircraft operational parameters. The method further includes processing the plurality of non-pneumatic inputs through an artificial intelligence network to generate an air data output value, and outputting the air data output value to a consuming system for use when a pneumatic-based air data output value is determined to be unreliable.

    Abstract translation: 根据本发明的方法包括通过飞行器数据通信总线接收与飞行器操作参数相对应的多个非气动输入。 该方法还包括通过人造智能网络处理多个非气动输入，以产生空气数据输出值，并将空气数据输出值输出到消耗系统，以在将基于气动的空气数据输出值确定为 不可靠

    AIR DATA PROBE WITH IMPROVED PERFORMANCE WHEN OPERATING AT A HIGH ANGLE OF ATTACK
    15.
    发明公开
    AIR DATA PROBE WITH IMPROVED PERFORMANCE WHEN OPERATING AT A HIGH ANGLE OF ATTACK 审中-公开
    空气数据探头在高角度进行操作时性能得到改善

    公开(公告)号：EP3073276A2

    公开(公告)日：2016-09-28

    申请号：EP16162062.0

    申请日：2016-03-23

    Applicant: Rosemount Aerospace Inc.

    Inventor： JOHNSON, Paul Robert ,  CUSHER, Aaron A. ,  GOLLY, Timothy Thomas ,  MATHEIS, Brian Daniel ,  SEIDEL, Greg

    IPC: G01P5/165 ,  G01F1/46

    CPC classification number: G01F1/46 ,  B64D45/00 ,  G01P5/165

    Abstract: An air data probe (46) has a pitot tube with a tap (47) at a forward end (48) that defines an inner flow path. The inner flow path decreases in the cross-sectional area until reaching a throat (50). Bleed holes (52) or slots are provided to eliminate air recirculation and boundary layer separation. The outer surface of the tube may comprise a relatively flat portion and a bulged portion, or a long-nosed portion of smaller diameter and an enlarged portion.

    Abstract translation: 空气数据探测器（46）具有皮托管，该皮托管在限定内部流动路径的前端（48）处具有龙头（47）。 内部流动路径在横截面积中减小直到到达喉部（50）。 提供排放孔（52）或槽以消除空气再循环和边界层分离。 管的外表面可以包括相对平坦部分和凸出部分，或者具有较小直径的长鼻部分和扩大部分。

    DAMAGE DETECTION FOR ROTARY ANGLE MEASUREMENT SENSORS
    16.
    发明公开
    DAMAGE DETECTION FOR ROTARY ANGLE MEASUREMENT SENSORS 审中-公开

    公开(公告)号：EP4474292A2

    公开(公告)日：2024-12-11

    申请号：EP24207041.5

    申请日：2021-09-20

    Applicant: ROSEMOUNT AEROSPACE INC.

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

    IPC: B64D43/02

    Abstract: An angle of attack sensor includes a rotatable vane (12) away and support from a mounting plate (68), a housing (36) extending way from an opposite side of the mounting plate, and a sensor (10) coupled to the vane. The angle of attack sensor communicates with an electronics module enclosed within the housing or mounted remotely with respect to the angle of attack sensor. The electronics module (72) includes a processor (88), computer-readable memory (90), and a communication device (92). The computer-readable memory is encoded with instructions that, when executed by the processor, cause the electronics module to perform steps of a damage detection method.

    DETERMINING ALTITUDE OF AN AIRCRAFT DURING FLIGHT BASED ON VORTEX SHEDDING
    18.
    发明公开
    DETERMINING ALTITUDE OF AN AIRCRAFT DURING FLIGHT BASED ON VORTEX SHEDDING 审中-公开

    公开(公告)号：EP3822580A1

    公开(公告)日：2021-05-19

    申请号：EP20208432.3

    申请日：2020-11-18

    Applicant: ROSEMOUNT AEROSPACE INC.

    Inventor： DAUP, Michael Robert ,  NASLUND, Brian Brent ,  MATHEIS, Brian Daniel

    IPC: G01C5/00 ,  G01P5/01 ,  G01P5/24

    Abstract: Apparatus and associated methods relate to determining altitude of an aircraft during flight based on properties of vortex shedding. A vortex-shedding projection (14) is projected into the airstream adjacent to the exterior surface of the aircraft so as to cause vortex-shedding turbulence (36) of the airstream. One or more downstream sound-pressure detectors (16A - 16G), which are attached to the exterior surface of the aircraft downstream from the vortex-shedding projection, detect(s) a vortex-shedding frequency f of the vortex-shedding turbulence caused by the vortex-shedding projection. A processor (18) determines the altitude of the aircraft based, at least in part, on the vortex-shedding frequency f of the vortex-shedding turbulence as detected by the one or more downstream sound-pressure detectors.

    AIR DATA PROBE WITH TURBULENCE-PRODUCING GEOMETRY
    20.
    发明公开
    AIR DATA PROBE WITH TURBULENCE-PRODUCING GEOMETRY 审中-公开
    带有湍流产生几何的大气数据探针

    公开(公告)号：EP3270169A2

    公开(公告)日：2018-01-17

    申请号：EP17179943.0

    申请日：2017-07-06

    Applicant: Rosemount Aerospace Inc.

    Inventor： DOOLITTLE, Charles Jae ,  WHALEN, Mackenzie ,  EGBERG, James Barron ,  CUSHER, Aaron A. ,  MATHEIS, Brian Daniel

    IPC: G01P5/165 ,  G01P13/02

    CPC classification number: G01P5/165 ,  G01L19/0007 ,  G01L19/02 ,  G01L19/14 ,  G01P13/025

    Abstract: An air data probe (10) includes a probe body (18) and an air data sensing port (20) disposed in the probe body (18). The probe body (18) includes a barrel region, a tapered head region extending forward from the barrel region, and a tip at a forward-most end of the tapered head region. The air data sensing port (20) is disposed in the probe body (18) at a port location aft of the tip. The probe body (18) has a turbulence-producing geometry originating at the tip that produces a turbulent boundary layer of airflow that extends from the tip to the port location.

    Abstract translation: 大气数据探头（10）包括探头主体（18）和布置在探头主体（18）中的大气数据传感端口（20）。 探针主体（18）包括筒状区域，从筒状区域向前延伸的锥形头部区域以及锥形头部区域的最前端处的尖端。 空气数据感测端口（20）设置在探针主体（18）中的尖端后方的端口位置处。 探头体（18）具有产生湍流的几何形状，该湍流产生几何形状起始于尖端，产生从尖端延伸到端口位置的湍流的气流边界层。

Patent Agency Ranking