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公开(公告)号：EP3637112A1
公开(公告)日：2020-04-15
申请号：EP19202182.2
申请日：2019-10-09
Applicant: ROSEMOUNT AEROSPACE INC.
Inventor： SHANNON, Daniel W. , TEERLINCK, Karen A. , MANTESE, Joseph V. , SLY, Jaime
IPC: G01P5/24
Abstract: An ultrasonic air data system (UADS) can include a body (101) configured to mount to an aircraft, an acoustic signal shaping feature (103) associated with the body (101), and an acoustic source (105) operatively connected to the acoustic signal shaping feature (103), the acoustic source (105) configured to emit a directional acoustic signal. The acoustic signal shaping feature (103) can be configured to reshape the directional acoustic signal from the acoustic source (105) into an at least partially reshaped signal. The system can include one or more acoustic receivers (107) disposed on or at least partially within the body (101) for receiving the reshaped signal.
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公开(公告)号：EP3594696A1
公开(公告)日：2020-01-15
申请号：EP19186094.9
申请日：2019-07-12
Applicant: ROSEMOUNT AEROSPACE INC.
Inventor： SLY, Jaime , NASLUND, Brian Brent
Abstract: A system and method for an aircraft (50) includes a low profile pneumatic sensing system and an acoustic sensing system. The low profile pneumatic sensing system includes a pneumatic sensor (30; 52a, 52b) positioned to sense first sensed data of an airflow about an exterior of the aircraft (50) and does not extend beyond a boundary layer of the aircraft (50). The first sensed data is used to determine first air data parameters. The acoustic sensing system is configured to emit acoustic signals about the exterior of the aircraft (50) and sense the acoustic signals as second sensed data. The second sensed data is used to determine second air data parameters.
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公开(公告)号：EP3460524A1
公开(公告)日：2019-03-27
申请号：EP18195405.8
申请日：2018-09-19
Applicant: Rosemount Aerospace Inc.
Inventor： SLY, Jaime , MILLER, Mark Sherwood
Abstract: A system (12) for an aircraft (10) includes an optical sensor, at least one aircraft sensor, and a controller (18). The optical sensor is configured to emit a laser outside the aircraft (10), and the at least one aircraft sensor is configured to sense at least one aircraft condition. The controller (18) is configured to determine a first operational state of the aircraft (10) based upon the at least one aircraft condition and determine a second operational state of the aircraft (10) based on the at least one aircraft condition, and operate the optical sensor to emit the laser at a first intensity during the first operational state and a second intensity during the second operational state, wherein the second intensity is greater than the first intensity.
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公开(公告)号：EP4001924A1
公开(公告)日：2022-05-25
申请号：EP21209595.4
申请日：2021-11-22
Applicant: ROSEMOUNT AEROSPACE INC.
Inventor： SLY, Jaime , MATHEIS, Brian Daniel , ANDERSON, Kaare Josef
Abstract: An optical ice detector and airspeed probe includes an ice detection module (40) and an airspeed module (42). The ice detection module detects the presence or absence of ice, water, or ice and water particles, and the airspeed module determines a line-of-sight speed along a directional vector, each based on backscatter light returns emitted from a common collimated light source. An electronics module (78) determines an airspeed of an aircraft based on the line-of-sight speed determined by the airspeed module and at least one aircraft parameter received from the air data system.
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公开(公告)号：EP3882639A1
公开(公告)日：2021-09-22
申请号：EP21163820.0
申请日：2021-03-19
Applicant: Rosemount Aerospace Inc.
Inventor： ELL, Todd Anthony , SLY, Jaime
Abstract: An acoustic air data system includes first and second acoustic transmitters, T 1 , T 2 , an array of acoustic receivers, and control circuitry (16). The array is positioned to receive first and second acoustic signals. The control circuitry determines time difference of arrival (TDOA) of the first and second acoustic signals. The control circuitry determines, for each of a first and second set of acoustic receiver pairs, a signal velocity of the first and second acoustic signals, respectively, based on a distance between an inner acoustic receiver and an outer acoustic receiver and a corresponding TDOA for each pair of acoustic receivers. The control circuitry estimates one or more of wind angle, speed of sound, Mach number, and true airspeed of the airflow about the exterior of the vehicle based on parameters of a best fit circle.
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Patent Agency Ranking
公开(公告)号：EP3865880A1
公开(公告)日：2021-08-18
申请号：EP20213223.9
申请日：2020-12-10
Applicant: ROSEMOUNT AEROSPACE INC.
Inventor： SLY, Jaime , BOELMAN, Joshua
Abstract: Apparatus (12) and associated methods relate to determining airspeed and/or altitude based on acoustic waves caused by airflow. One or more acoustic transducers (14A-D) are positioned along an exterior surface of an aircraft. Each of the one or more acoustic transducers is configured to detect acoustic waves caused by the airflow. The acoustic waves detected are indicative of an airstream condition proximate the acoustic transducer, such as, for example, airspeed and/or altitude. A processor (64) is configured to determine airspeed and/or altitude of the aircraft based, at least in part, on the acoustic waves detected.
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公开(公告)号：EP3594938A1
公开(公告)日：2020-01-15
申请号：EP19185819.0
申请日：2019-07-11
Applicant: ROSEMOUNT AEROSPACE INC.
Inventor： SLY, Jaime , BOELMAN, Joshua
Abstract: An acoustic sensor system (10) for an aircraft (52) includes a transmitter (12) configured to emit acoustic signals external to the aircraft (52), and at least one microphone (14a-14n) positioned on an exterior of the aircraft (52) and configured to sense the acoustic signals as sensed data. The acoustic sensor system (10) is configured to direct the acoustic signals to the at least one microphone (14a-14n) such that a sound pressure level is attenuated perpendicular to the aircraft (52).
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公开(公告)号：EP4455747A1
公开(公告)日：2024-10-30
申请号：EP24171269.4
申请日：2024-04-19
Applicant: ROSEMOUNT AEROSPACE INC.
Inventor： WESSER, Aaron , ACOTT, Phillip , MILLER, Mark Sherwood , SLY, Jaime , BOELMAN, Joshua A.
Abstract: An optical apparatus (102) can be configured to cover an optical transceiver (104). At least a portion of the apparatus (102) can be configured to move relative to the transceiver (104) between a block state wherein the apparatus (102) is configured to block transmission from a transmitter (106) of the optical transceiver to a receiver (108) of the optical transceiver as well as block emission from the transmitter (106) to the atmosphere, and one or more transmit states wherein the apparatus (102) is configured to allow at least partial transmission from the transmitter (106) of the optical transceiver to a receiver (108) of the optical transceiver while blocking emission from the transmitter (106) to the atmosphere.
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公开(公告)号：EP3770609A1
公开(公告)日：2021-01-27
申请号：EP19215549.7
申请日：2019-12-12
Applicant: ROSEMOUNT AEROSPACE INC.
Inventor： SLY, Jaime , MILLER, Mark Sherwood
Abstract: An air data sensor (100) can include an acoustic transmitter (101) configured to output an acoustic signal into an airflow and a plurality of acoustic transducers configured to receive the acoustic signal output by the acoustic transducer. The air data sensor can also include a light source (107) configured to output a light beam into the airflow, and a light receiver (111) configured to receive scattered light from the light beam. The light source and the light receiver can be bistatic such that a measurement zone is formed away from the air data sensor.
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公开(公告)号：EP3594645A1
公开(公告)日：2020-01-15
申请号：EP19185811.7
申请日：2019-07-11
Applicant: ROSEMOUNT AEROSPACE INC.
Inventor： SLY, Jaime , BOELMAN, Joshua
Abstract: An acoustic sensor system for an aircraft (52), and method for operating the same, includes a transmitter (12), at least one microphone (14a-14n), and a control circuit (16). The transmitter (12) is configured to emit acoustic signals external to the aircraft. The at least one microphone (14a-14n) is positioned on an exterior of the aircraft (52) and configured to sense the acoustic signals as sensed data. The control circuit (16) is configured to receive the sensed data and control the transmitter (12) through a drive circuit (18), and is configured to detect an environmental condition and control the transmitter (12) to emit the acoustic signals at a reduced intensity based on the detected environmental condition.
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