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公开(公告)号：US20240077260A1
公开(公告)日：2024-03-07
申请号：US18201051
申请日：2023-05-23
Applicant: Rosemount Aerospace Inc.
Inventor： Vincent R. LoPresto , Brian Daniel Matheis
Abstract: An aerodynamic friction energy deicing system can include a heat energy device configured to be operatively connected to an aircraft structure and to convert heat energy due to aerodynamic friction on the aircraft structure into another form or to store heat energy due to aerodynamic friction on the aircraft structure. The converted or stored energy can be used for any suitable purpose, e.g., for use in ice prevention and/or deicing and/or powering one or more aircraft systems.
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公开(公告)号：US20220091152A1
公开(公告)日：2022-03-24
申请号：US17026839
申请日：2020-09-21
Applicant: Rosemount Aerospace Inc.
Inventor： Brian Brent Naslund , Brian D. Kane , Steven Schaub , Brian Daniel Matheis
Abstract: An angle of attack sensor includes a rotatable vane extending away and support from a mounting plate, a housing extending way from an opposite side of the mounting plate, and a sensor 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 includes a processor, computer-readable memory, and a communication device. 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.
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公开(公告)号：US10723479B2
公开(公告)日：2020-07-28
申请号：US15897537
申请日：2018-02-15
Applicant: Rosemount Aerospace Inc.
Inventor： Kaare Josef Anderson , Brian Daniel Matheis , Derrick D. Hongerholt , William Kunik
Abstract: In one example, a method 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.
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公开(公告)号：US20190383848A1
公开(公告)日：2019-12-19
申请号：US16009989
申请日：2018-06-15
Applicant: Rosemount Aerospace Inc.
Inventor： Brian Daniel Matheis , Matthew Anderson , Greg Allen Seidel , Paul Llamas
IPC: G01P5/165
Abstract: An air data probe includes a body, a mount adjacent to the body, a primary low ice adhesion surface coating on a primary impact region of the air data probe, the primary impact region being positioned for direct impact with water drops, and a secondary low ice adhesion surface coating on a secondary impact region of the air data probe, the secondary impact region being positioned for indirect contact by water drops. The primary low ice adhesion surface coating has a different composition than the secondary low ice adhesion surface coating.
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15.发明申请公开(公告)号：US20170369177A1
公开(公告)日：2017-12-28
申请号：US15195833
申请日：2016-06-28
Applicant: Rosemount Aerospace Inc.
Inventor： Vincent R. LoPresto , Brian Daniel Matheis
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.
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Patent Agency Ranking
16.发明申请公开(公告)号：US20160282158A1
公开(公告)日：2016-09-29
申请号：US14665007
申请日：2015-03-23
Applicant: Rosemount Aerospace, Inc.
Inventor： Paul Robert Johnson , Aaron A. Cusher , Timothy Thomas Golly , Brian Daniel Matheis , Greg Seidel
Abstract: An air data probe has a pitot tube with a tap at a forward end that defines an inner flow path. The inner flow path decreases in the cross-sectional area until reaching a throat. The inner flow path has cross-sections that are generally cylindrical and also has sections of removed material. Other embodiment have unique shapes.
Abstract translation: 空气数据探头具有皮托管，其在前端具有限定内部流动路径的水龙头。 内部流路在横截面积减小直到达到喉部。 内部流动路径具有大致圆柱形的横截面并且还具有被去除的材料的部分。 其他实施例具有独特的形状。
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公开(公告)号：US11125770B2
公开(公告)日：2021-09-21
申请号：US16211913
申请日：2018-12-06
Applicant: Rosemount Aerospace Inc.
Inventor： Daniel W. Shannon , Brian Daniel Matheis
Abstract: An acoustic air data sensor for an aircraft includes an acoustic transmitter, an acoustic receiver, an acoustic signal generator, timing circuitry, speed of sound determination circuity, and communication circuitry. The acoustic transmitter is located to transmit an acoustic signal through an airflow stagnation chamber that is pneumatically connected to an exterior of the aircraft and configured to receive and stagnate airflow from the exterior of the aircraft. The acoustic receiver is positioned at a distance from the acoustic transmitter to receive the acoustic signal. The pulse generator causes the acoustic transmitter to provide the acoustic signal. The timing circuitry determines a time of flight of the acoustic signal from the acoustic transmitter to the acoustic receiver. The speed of sound determination circuity determines, based on the time of flight and the distance, a speed of sound through air in the stagnation chamber. The communication circuitry outputs the speed of sound.
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公开(公告)号：US10928413B2
公开(公告)日：2021-02-23
申请号：US16153358
申请日：2018-10-05
Applicant: Rosemount Aerospace Inc.
Inventor： Brian Daniel Matheis , Jaime Sly , James Barron Egberg
Abstract: An aircraft freestream data system can include a first ultrasonic air data system (UADS) configured to sense local acoustic properties at a first location on an aircraft, a first local air data module 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 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.
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公开(公告)号：US10578637B2
公开(公告)日：2020-03-03
申请号：US16009989
申请日：2018-06-15
Applicant: Rosemount Aerospace Inc.
Inventor： Brian Daniel Matheis , Matthew Anderson , Greg Allen Seidel , Paul Llamas
Abstract: An air data probe includes a body, a mount adjacent to the body, a primary low ice adhesion surface coating on a primary impact region of the air data probe, the primary impact region being positioned for direct impact with water drops, and a secondary low ice adhesion surface coating on a secondary impact region of the air data probe, the secondary impact region being positioned for indirect contact by water drops. The primary low ice adhesion surface coating has a different composition than the secondary low ice adhesion surface coating.
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公开(公告)号：US10416188B2
公开(公告)日：2019-09-17
申请号：US15649873
申请日：2017-07-14
Applicant: Rosemount Aerospace Inc.
Inventor： Charles Jae Doolittle , Mackenzie Whalen , James Barron Egberg , Aaron A. Cusher , Brian Daniel Matheis
Abstract: An air data probe includes a probe body and an air data sensing port disposed in the probe body. The probe body 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 is disposed in the probe body at a port location aft of the tip. The probe body 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.
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