公开(公告)号：EP3511721A1

公开(公告)日：2019-07-17

申请号：EP19150553.6

申请日：2019-01-07

Applicant: ROSEMOUNT AEROSPACE INC.

Inventor： WINTER, John D.

IPC: G01P5/26 ,  G01L11/02 ,  G01P13/02 ,  G01P21/02 ,  G01S17/58

Abstract: A set of aircraft air data parameter outputs is generated based on laser sensor data and inertial sensor data. Directional light is emitted in one or more directions into air about an exterior of an aircraft, and returns of the emitted directional light in the one or more directions is sensed. Laser sensor data representing velocity of the aircraft in the one or more directions, static pressure of the air, and static air temperature of the air is generated based on the sensed returns. Acceleration and rotational rate of the aircraft is sensed in three axes. The set of aircraft air data parameter outputs is generated based on the laser sensor data and the inertial sensor data. The set of aircraft air data parameter outputs includes aircraft static air pressure, aircraft static air temperature, aircraft true airspeed, aircraft angle of attack, and aircraft angle of sideslip.

公开(公告)号：EP3598093A1

公开(公告)日：2020-01-22

申请号：EP19187284.5

申请日：2019-07-19

Applicant: ROSEMOUNT AEROSPACE INC.

Inventor： WINTER, John D. ,  SCHWARTZ, Wesley J. ,  JACKSON, Darren G.

IPC: G01K13/02

Abstract: A system (100) for correcting an air temperature (AT) reading can include a water content sensor (101) configured to measure a water content in an airflow and to output a water content signal (101a) indicative thereof, an AT sensor (103) configured to measure an air temperature and output an AT signal (103a) indicative thereof, and a correction module (105) operatively connected to the water content sensor (101) and the AT sensor (103). The correction module (105) can be configured to receive the water content signal (101a) and the AT signal (1013a) and to correct the AT signal (103a) based on the water content to output a corrected AT signal (105a).

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：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).