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公开(公告)号：US11714098B2
公开(公告)日：2023-08-01
申请号：US16391192
申请日：2019-04-22
Applicant: Rosemount Aerospace Inc.
Inventor： Jaime Sly , Daniel W. Shannon , Brian Daniel Matheis , Todd Anthony Ell , William Kunik , Sudarshan N. Koushik
Abstract: An ultrasonic air data system can include a pole having a length longer than a boundary layer thickness of a boundary layer flow 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 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 disposed downstream of the pole as defined by the boundary layer flow and configured to receive the transmitter signal.
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公开(公告)号：US20210156882A1
公开(公告)日：2021-05-27
申请号：US16694303
申请日：2019-11-25
Applicant: Rosemount Aerospace Inc.
Inventor： Brian Hawley , Jaime Sly , Brian Daniel Matheis
Abstract: Apparatus and associated methods relate to detecting turbulence of an airstream over an airfoil surface of an aircraft using a sequence of acoustic transducers attached to the airfoil surface of the aircraft along a path. Each of the sequence of acoustic transducers is configured to detect acoustic waves indicative of airstream condition proximate the acoustic transducer. A processor is configured to determine, for each of the sequence of acoustic transducers, a level of turbulence of the airstream proximate the acoustic transducer.
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公开(公告)号：US09341533B2
公开(公告)日：2016-05-17
申请号：US14183665
申请日：2014-02-19
Applicant: Rosemount Aerospace Inc.
Inventor： Charles Jae Doolittle , Brian Daniel Matheis , Roger Duane Foster
Abstract: An air data probe includes a probe head defining a longitudinal axis with a forward tip, and a turbulence inducing surface defined in the probe head aft of the forward tip. The turbulence inducing surface is configured and adapted to trip a fluid boundary layer passing over the probe head to transition from laminar to turbulent to control or reduce boundary layer separation resulting in consistent readings at high altitudes.
Abstract translation: 空气数据探头包括限定具有前部尖端的纵向轴线的探针头和限定在前部尖端的探头头部中的湍流诱导表面。 湍流诱导表面被配置和适于使通过探针头的流体边界层跳过从层流到湍流转变，以控制或减少边界层分离，导致在高海拔处的一致读数。
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公开(公告)号：US09297714B2
公开(公告)日：2016-03-29
申请号：US14282629
申请日：2014-05-20
Applicant: Rosemount Aerospace Inc.
Inventor： Charles Jae Doolittle , Roger Duane Foster , Brian Daniel Matheis
Abstract: An air data probe includes a probe head and a raised portion. The probe head defines a longitudinal axis and includes a forward tip and a probe head surface. 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针头和凸起部分。 探针头限定纵向轴线并且包括前端和探针头表面。 凸起部分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。 凸起部分被构造和适于使通过探针头的流体边界层跳跃以从层流转变成湍流，以便减少边界层分离，以在高海拔和/或高马赫数处获得一致的读数。 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部尖端的探针头的表面。 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。
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公开(公告)号：US20140251000A1
公开(公告)日：2014-09-11
申请号：US14183665
申请日：2014-02-19
Applicant: ROSEMOUNT AEROSPACE INC.
Inventor： Charles Jae Doolittle , Brian Daniel Matheis , Roger Duane Foster
IPC: G01L15/00
Abstract: An air data probe includes a probe head defining a longitudinal axis with a forward tip, and a turbulence inducing surface defined in the probe head aft of the forward tip. The turbulence inducing surface is configured and adapted to trip a fluid boundary layer passing over the probe head to transition from laminar to turbulent to control or reduce boundary layer separation resulting in consistent readings at high altitudes.
Abstract translation: 空气数据探头包括限定具有前部尖端的纵向轴线的探针头和限定在前部尖端的探头头部中的湍流诱导表面。 湍流诱导表面被配置和适于使通过探针头的流体边界层跳过从层流到湍流转变，以控制或减少边界层分离，导致在高海拔处的一致读数。
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Patent Agency Ranking
公开(公告)号：US11802888B2
公开(公告)日：2023-10-31
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
CPC classification number: G01P13/025 , B64D43/02
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：US20210078722A1
公开(公告)日：2021-03-18
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：US10900990B2
公开(公告)日：2021-01-26
申请号：US16361005
申请日：2019-03-21
Applicant: Rosemount Aerospace Inc.
Inventor： Brian Daniel Matheis , Daniel W. Shannon , Sudarshan N. Koushik
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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公开(公告)号：US20200333371A1
公开(公告)日：2020-10-22
申请号：US16391192
申请日：2019-04-22
Applicant: Rosemount Aerospace Inc.
Inventor： Jaime Sly , Daniel W. Shannon , Brian Daniel Matheis , Todd Anthony Ell , William Kunik , Sudarshan N. Koushik
Abstract: An ultrasonic air data system can include a pole having a length longer than a boundary layer thickness of a boundary layer flow 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 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 disposed downstream of the pole as defined by the boundary layer flow and configured to receive the transmitter signal.
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公开(公告)号：US20140251001A1
公开(公告)日：2014-09-11
申请号：US14282629
申请日：2014-05-20
Applicant: Rosemount Aerospace Inc.
Inventor： Charles Jae Doolittle , Roger Duane Foster , Brian Daniel Matheis
IPC: G01L15/00
Abstract: An air data probe includes a probe head and a raised portion. The probe head defines a longitudinal axis and includes a forward tip and a probe head surface. 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针头和凸起部分。 探针头限定纵向轴线并且包括前端和探针头表面。 凸起部分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。 凸起部分被构造和适于使通过探针头的流体边界层跳跃以从层流转变成湍流，以便减少边界层分离，以在高海拔和/或高马赫数处获得一致的读数。 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部尖端的探针头的表面。 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。
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