公开(公告)号：EP3632753A1

公开(公告)日：2020-04-08

申请号：EP19201314.2

申请日：2019-10-03

Applicant: ROSEMOUNT AEROSPACE INC.

Inventor： VENKATAMUNIBHASKARAN, Ramesh ,  THIRUNARAYANA, Ashok Kumar

IPC: B60S1/08 ,  G01S13/95

Abstract: An aircraft windshield wiper control system (30) includes an aircraft weather radar system (22) mounted in an aircraft (10) and that detects precipitation in a travel path of an aircraft (10) and an integrated avionics module (24) that receives aircraft weather information from the aircraft weather radar system (22). The system (30) also includes an aircraft wiper blade motor (50), a wiper blade motor drive and a wiper control module (26) that receives aircraft weather information from the integrated avionics module (24) and generates a wiper control signal, based on the received information that controls operation of the wiper blade motor drive to cause motion of the aircraft wiper blade motor (50).

公开(公告)号：EP3444618B1

公开(公告)日：2020-04-08

申请号：EP18189477.5

申请日：2018-08-17

Applicant: Rosemount Aerospace Inc.

Inventor： REID, Alexander N. ,  SCHWARTZ, Richard Alan ,  KRUEGER, William B. ,  DeAngelo, Timothy ,  FREEMAN, Kenneth

IPC: G01P13/02

公开(公告)号：EP2869316B1

公开(公告)日：2020-03-25

申请号：EP14189930.2

申请日：2014-10-22

Applicant: ROSEMOUNT AEROSPACE INC.

Inventor： Rozman, Gregory I. ,  Gieras, Jacek F.

IPC: H01F38/18 ,  H01F27/28 ,  H02P9/30 ,  H02P25/02

公开(公告)号：EP3614152A1

公开(公告)日：2020-02-26

申请号：EP19203208.4

申请日：2018-01-29

Applicant: ROSEMOUNT AEROSPACE INC.

Inventor： Essawy, Magdi ,  McTighe, James Joseph

IPC: G01P5/165 ,  G01P13/02 ,  G01K13/02 ,  G01K15/00 ,  G01R31/00 ,  H05B3/56

Abstract: A probe system configured to receive a radio-frequency (RF) signal from a radio-frequency (RF) antenna (30) includes a heater (14) and a control circuit (16). The heater includes a resistive heating element routed through the probe system. An operational voltage is provided to the resistive heating element to provide heating for the probe system and the resistive heating element has an element capacitance. The control circuit is configured to determine an antenna response of the resistive heating element and determine a remaining useful life of the probe system based on the antenna response over time.

公开(公告)号：EP3613673A1

公开(公告)日：2020-02-26

申请号：EP19190596.7

申请日：2019-08-07

Applicant: ROSEMOUNT AEROSPACE INC.

Inventor： BOELKE, Joel

IPC: B64D15/12 ,  H05B1/02

Abstract: A system (10) includes a heating element (20), a signal injector (14), and a signal receiver (28). The heating element (20) is coupled between a first node (18) and a second node (22). The signal injector (14) is communicatively coupled the heating element (20) via the first node (18). The signal generator is configured to provide a test signal to the heating element (20). The signal receiver (28) is communicatively coupled to the heating element (20) via the second node (22). The signal receiver (28) is configured to receive the test signal from the heating element (20) and to determine a capacitance of the heating element (20) based upon the received test signal.

公开(公告)号：EP3611516A1

公开(公告)日：2020-02-19

申请号：EP19190617.1

申请日：2019-08-07

Applicant: ROSEMOUNT AEROSPACE INC.

Inventor： NASLUND, Brian Brent ,  ANDERSON, Matthew Paul ,  LANGEMO, Benjamin John ,  SHERMAN, Andrew

IPC: G01P5/165 ,  G01P13/02

Abstract: An aircraft probe (12) includes a base (24), a strut (22) that extends from the base (24), at least one port (26, 28, 30), and an electronics assembly insertable into the strut (22) and removable from the strut (22). The electronics assembly includes at least one pressure sensor (42a, 42b, 42c) that is pneumatically connected to the at least one port (26, 28, 30) to sense a first pressure when in the inserted position.

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

IPC: G01P13/02 ,  G01P5/24 ,  G01P5/16 ,  B64D43/02

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.

公开(公告)号：EP3594075A1

公开(公告)日：2020-01-15

申请号：EP19186155.8

申请日：2019-07-12

Applicant: ROSEMOUNT AEROSPACE INC.

Inventor： SRINIVAS, Nouduri Phani ,  SANTYAR, Srivatsa

IPC: B60S1/18 ,  B60S1/26

Abstract: A windshield wiper system (WWS) (10) includes a brushless direct current (BLDC) motor (20) with a motor output shaft gear (22), a gear train (30) and an internally cut sector gear (40). The gear train (30) includes a first gear (31), which has a first diameter (D1) and engages with the motor output shaft gear (22), and a second gear (32), which has a second diameter (D2) that is shorter than the first diameter (D1) and rotates with the first gear (31). The internally cut sector gear (40) is coupled with an output shaft (50) and formed to define an internal geared groove (41) that engages with the second gear (32).

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：EP3567369A1

公开(公告)日：2019-11-13

申请号：EP19183630.3

申请日：2018-08-28

Applicant: ROSEMOUNT AEROSPACE INC.

Inventor： ROMAN, Jamison K. ,  HEUER, Weston Daniel Clarence

IPC: G01N29/24 ,  G01B11/30

Abstract: A method of improving the measurement accuracy of digital ice rate sensors (20) by providing an enhanced surface finish on magnetostrictive oscillator detector probes, further comprising a method of statistical process control, comprising the steps of:
measuring external surface roughness on each of the magnetostrictive oscillator detector probes and at least one parameter of a metal plating bath, wherein the at least one parameter is selected from the group consisting of bath temperature, soak time, and chemical concentration, and wherein the measuring occurs on at least a sample of the magnetostrictive oscillator detector probes;
recording the external surface roughness and the at least one parameter;
evaluating a series of the external surface roughness and the at least one parameter; and
determining a trend in the series.