公开(公告)号：EP3581943A2

公开(公告)日：2019-12-18

申请号：EP19180014.3

申请日：2019-06-13

Applicant: ROSEMOUNT AEROSPACE INC.

Inventor： BOELKE, Joel ,  NASLUND, Brian Brent ,  LANGEMO, Benjamin John

IPC: G01P15/16 ,  G01P21/02 ,  G01P13/02 ,  G01C5/00 ,  G01C5/06

Abstract: A system and method of augmenting an existing air data system includes a multi-function probe (MFP) (30; 58) having a portion extending into an oncoming airflow about an exterior of an aircraft (10). A plurality of pressure sensing ports in the portion includes at least first and second static pressure ports (P S1 ). A first electronics channel (34) of the MFP (30; 58) includes pressure sensors (46, 48, 50) communicating with the first and second static pressure ports (P S1 ) and is configured to determine first and second altitude values based on sensed static pressures at the first and second static pressure ports (P S1 ), respectively, that are independent of the existing air data system.

公开(公告)号：EP3460436A1

公开(公告)日：2019-03-27

申请号：EP18195813.3

申请日：2018-09-20

Applicant: Rosemount Aerospace Inc.

Inventor： NASLUND, Brian Brent

IPC: G01L19/08 ,  G01P1/00 ,  G01L19/14

Abstract: A sensor (112) is configured to attach to a main body (16) and includes a sensor body (114), a transducer (120), a transmitter (122), and a power source (118). The sensor body (114) is configured to provide a smooth transition with a surface of the main body (16). The transducer (120) is positioned within the sensor body (114) and is configured to provide a sensed output. The transmitter (122) is positioned within the sensor body (114) and is configured to transmit the sensed output. The power source (118) is positioned within the sensor body (114) and is configured to provide electrical power to the transducer (120) and the transmitter (122).

公开(公告)号：EP3739342A1

公开(公告)日：2020-11-18

申请号：EP19213776.8

申请日：2019-12-05

Applicant: ROSEMOUNT AEROSPACE INC.

Inventor： SCHWARTZ, Wesley J. ,  NASLUND, Brian Brent ,  WINTER, John D. ,  BOELKE, Joel

IPC: G01P5/16 ,  G01P13/02

Abstract: A aircraft health management system for identifying an anomalous signal from one or more air data systems (ADS) includes one or more of a frequency processor (120), configured to provide a spectral signal that is representative of a frequency content of the first ADS signal, a noise processor (124), configured to provide a noise signal that is representative of a noise level of the first ADS signal, and a rate processor (128), configured to provide a rate signal that is representative of a rate of change of the first ADS signal. The aircraft health management system also includes a comparator (132) configured to provide a differential signal between the first ADS signal and the second ADS signal, and a prognostic processor (142) configured to determine if the ADS signal is anomalous by comparing values representative of a flight condition signal, the differential signal, and the spectral, noise, and/or rate signals.

公开(公告)号：EP3627272A1

公开(公告)日：2020-03-25

申请号：EP19198108.3

申请日：2019-09-18

Applicant: ROSEMOUNT AEROSPACE INC.

Inventor： NASLUND, Brian Brent ,  WINTER, John D.

IPC: G05D1/08 ,  B64D43/02

Abstract: An anti-spin system (100) for an aircraft can include an anti-spin module (101) configured to execute a computer implemented method. The method can include receiving flight data from one or more aircraft flight data systems (103), determining if the aircraft is near stall or in a stall using the flight data, and determining if the aircraft is in uncoordinated flight while near stall or in a stall to determine if the aircraft is near spin or in a spin using the flight data. If the aircraft is determined to be near spin, the method includes at least one of sending an alert to a warning indicator in a cockpit to warn the pilot of a spin or near spin condition, or sending a signal to an automated control system (109) for inputting automatic control to the aircraft to avoid a spin by coordinating the aircraft or avoiding a stall while uncoordinated.

公开(公告)号：EP3581943A3

公开(公告)日：2019-12-25

申请号：EP19180014.3

申请日：2019-06-13

Applicant: ROSEMOUNT AEROSPACE INC.

Inventor： BOELKE, Joel ,  NASLUND, Brian Brent ,  LANGEMO, Benjamin John

IPC: G01P21/02 ,  G01P13/02 ,  G01P5/165 ,  G01C5/00 ,  G01C5/06

Abstract: A system and method of augmenting an existing air data system includes a multi-function probe (MFP) (30; 58) having a portion extending into an oncoming airflow about an exterior of an aircraft (10). A plurality of pressure sensing ports in the portion includes at least first and second static pressure ports (P S1 ). A first electronics channel (34) of the MFP (30; 58) includes pressure sensors (46, 48, 50) communicating with the first and second static pressure ports (P S1 ) and is configured to determine first and second altitude values based on sensed static pressures at the first and second static pressure ports (P S1 ), respectively, that are independent of the existing air data system.

公开(公告)号：EP3581942A1

公开(公告)日：2019-12-18

申请号：EP19179986.5

申请日：2019-06-13

Applicant: ROSEMOUNT AEROSPACE INC.

Inventor： NASLUND, Brian Brent ,  WINTER, John D. ,  BOELKE, Joel

IPC: G01P13/02 ,  G01P5/165 ,  B64D43/02

Abstract: An air data system for an aircraft (10) includes a multi-function probe (MFP) (12A, 12B, 12C) and an inertial reference unit (IRU) (14). The MFP (12A, 12B, 12C) is positioned to sense a pressure of airflow about an exterior of the aircraft (10). A first electronics channel (51) of the MFP (12A, 12B, 12C) is electrically coupled to the IRU (14) to generate air data parameter outputs based on the pressure sensed by the MFP (12A, 12B, 12C) and inertial data sensed by the IRU (14).

公开(公告)号：EP3581938A1

公开(公告)日：2019-12-18

申请号：EP19175352.4

申请日：2019-05-20

Applicant: Rosemount Aerospace Inc.

Inventor： NASLUND, Brian Brent ,  BOELKE, Joel ,  LANGEMO, Benjamin John ,  BENNING, Kevin

IPC: G01P5/165 ,  G01P13/02 ,  B64D43/02

Abstract: A system includes an air data computer (ADC) (48, 70, 88) having a single pneumatic port for receiving a pneumatic input, a plurality of electrical inputs for receiving one or more electrical signals, and an output. The ADC (48, 70, 88) can transmit, via the output, air data parameters based on the received pneumatic input and the received one or more electrical signals. In a further example embodiment, the system includes a first pressure sensing probe discrete from the ADC (48, 70, 88) and a pneumatic connection (52, 74, 92) joining a pressure sensing port of the first probe to the pneumatic input of the ADC (48, 70, 88). Second and third pressure sensing probes pneumatically coupled to respective pressure modules, which output electrical signals to the ADC (48, 70, 88), the electrical signals being representative of pressures sensed by the second and third pressure sensing probes, respectively.

公开(公告)号：EP3567374A1

公开(公告)日：2019-11-13

申请号：EP19173587.7

申请日：2019-05-09

Applicant: ROSEMOUNT AEROSPACE INC.

Inventor： SLY, Jaime ,  NASLUND, Brian Brent

IPC: G01P5/24 ,  G01P5/14 ,  G01P5/16 ,  G01P13/02

Abstract: An air data system for an aircraft (30) includes a multi-function probe (MFP) and an acoustic sensor system. The MFP is positioned to sense pressure of an airflow about an exterior of the aircraft (30). The pressure is used to generate first air data parameters for the aircraft (30). The acoustic sensor system is configured to emit acoustic signals about the exterior of the aircraft (30) and sense the acoustic signals as sensed data, which is used to generate second air data parameters.

公开(公告)号：EP3567373A1

公开(公告)日：2019-11-13

申请号：EP19173614.9

申请日：2019-05-09

Applicant: Rosemount Aerospace Inc.

Inventor： SLY, Jaime ,  NASLUND, Brian Brent

IPC: G01P5/16 ,  G01P5/24 ,  G01P13/02

Abstract: A system and method for an aircraft (30; 30') includes an air data system and an acoustic sensing system. The air data system includes a pitot tube (32a) positioned to sense a pitot pressure of an airflow about an exterior of the aircraft (30; 30'), and an angle of attack vane (36a) positioned to sense an angle of attack of the aircraft (30; 30'). The pitot pressure and the angle of attack are used to determine first air data parameters. The acoustic sensing system is configured to emit acoustic signals about the exterior of the aircraft (30; 30') and sense the acoustic signals as sensed data. The sensed data is used to determine second air data parameters.

公开(公告)号：EP3336558A1

公开(公告)日：2018-06-20

申请号：EP17207656.4

申请日：2017-12-15

Applicant: Rosemount Aerospace Inc.

Inventor： MILLER, Mark Sherwood ,  NASLUND, Brian Brent ,  KUNIK, William

IPC: G01P13/02 ,  G01P5/14 ,  G01P5/26 ,  G01P21/02 ,  G05D1/00

CPC classification number: G01P13/025 ,  B64D43/02 ,  G01K13/028 ,  G01P5/14 ,  G01P5/165 ,  G01P5/26 ,  G01P21/025

Abstract: A first air data system for providing first aircraft air data parameter outputs is formed by a first electronics channel of a first multi-function probe (MFP) (12A) that is electrically coupled with a first electronics channel of a second MFP (12B) to receive static pressure data from the second MFP (12B). A second air data system for providing second aircraft air data parameter outputs is formed by a second electronics channel of the second MFP (12B) that is electrically coupled with a second electronics channel of the first MFP (12A) to receive static pressure data from the first MFP (12A). A third air data system for providing third aircraft air data parameter outputs is formed by a laser air data sensor that is configured to emit directional light into airflow about the aircraft exterior and to generate the third aircraft air data parameter outputs based on returns of the emitted directional light.