公开(公告)号：EP4554020A1

公开(公告)日：2025-05-14

申请号：EP24204935.1

申请日：2024-10-07

Applicant: ROSEMOUNT AEROSPACE INC.

Inventor： HALAMA, Gary E. ,  ACOTT, Phillip

IPC: H01S5/00 ,  H01S3/23

Abstract: In accordance with at least one aspect of this disclosure, a method for seeding an optical beam (106) includes, emitting an optical beam (106) from an energy source towards an optical amplifier along an optical axis, and rotating one or more optical elements disposed with in the beam path of the optical beam (106) between the energy source and the optical amplifier about the optical axis to a align the optical beam with a reference beam.

公开(公告)号：EP4495013A3

公开(公告)日：2025-03-12

申请号：EP24209542.0

申请日：2021-09-20

Applicant: ROSEMOUNT AEROSPACE INC.

Inventor： NASLUND, Brian Brent ,  KANE, Brian D. ,  SCHAUB, Steven ,  MATHEIS, Brian Daniel

IPC: G01P13/02 ,  G01P21/02 ,  B64D45/02 ,  B64D43/02 ,  G01D3/08 ,  G01P15/00 ,  B64D45/00

Abstract: An angle of attack sensor includes a mounting plate (68); a vane (12) supported from the mounting plate and extending from a first side of the mounting plate, wherein the vane is rotatable about a vane axis; a housing (36) extending from a second side of the mounting plate in a direction opposite to the vane; a resolver (64) coupled to the vane; and an electronics module (72) mounted within the housing, the electronics module comprising: at least one processor (88); a communication device (92); and computer-readable memory (90), encoded with instructions that, when executed by the at least one processor, cause the electronics module to: receive, from the resolver, a signal indicative of an angular position of the vane about the vane axis; compare the signal to a first damage criterion; and output, using the communication device, a first fault signal to a consuming system of an aircraft that is indicative of a damage event based on a comparison of the signal to the first damage criterion..

公开(公告)号：EP4509372A1

公开(公告)日：2025-02-19

申请号：EP24190952.2

申请日：2024-07-25

Applicant: ROSEMOUNT AEROSPACE INC.

Inventor： NOUDURI, Phani Srinivas ,  VENKATARAMU, Raghavendra

IPC: B60S1/34 ,  B60S1/18 ,  B60S1/16 ,  H02K7/06

Abstract: In accordance with at least one aspect of this disclosure, a system (100) includes a wiper drive shaft (116) configured to drive a wiper arm (106) between a start position (110) and an end sweep position (112). The wiper drive shaft (116) includes external threads (132) defined therein and at a distal end (134) thereof. An axial length of the external threads (132) along the wiper drive shaft (116) defines the start position (110) and the end sweep position (112), and a total desired sweep angle between the start position (110) and end sweep position (112). The wiper drive shaft (116) includes a first hard stop groove (136) and a second hard stop groove (138), each defined at a respective first axial offset and a second axial offset from the external threads (132) to define a first hard stop position (140) and second hard stop position (142).

公开(公告)号：EP4494949A1

公开(公告)日：2025-01-22

申请号：EP24188300.8

申请日：2024-07-12

Applicant: ROSEMOUNT AEROSPACE INC.

Inventor： BOJJANAPALLI, Muralidhar Rao ,  HIRIYANNAIAH, Santosh

IPC: B60S1/08 ,  B60S1/18 ,  B60S1/34 ,  B60S1/16

Abstract: A windshield wiper system for an aircraft includes a wiper arm (12) and a wiper shaft (14) with a first end (34) connected to a base of the wiper arm. An electric motor (20) is coupled to the wiper shaft to rotationally drive the wiper shaft. The windshield wiper system also includes a brake system (24). The brake system includes an electromagnet (38) comprising an energized mode and a de-energized mode. The brake system also includes an anti-rotation assembly with a first element and a second element. The first element is connected directly to the wiper shaft. The second element is rotationally stationary relative the wiper shaft and the first element. The second element is configured to interlock with the first element to prevent rotation of the first element and the wiper shaft when both the electromagnet is in the de-energized mode and the wiper arm is in a park position.

公开(公告)号：EP4461652A3

公开(公告)日：2025-01-08

申请号：EP24202125.1

申请日：2019-12-13

Applicant: ROSEMOUNT AEROSPACE INC.

Inventor： ANDERSON, Kaleb ,  SCHWARTZ, Richard Alan ,  MADSEN, Michael William

IPC: G01P13/02 ,  B64D43/02

Abstract: A vane shaft for an angle of attack sensor, the vane shaft comprising: a body portion (50); a top portion (52) connected to an end of the body portion, the top portion being configured to connect to a vane assembly; a bore (54) extending through the body portion and the top portion; and a first vent hole (60A) extending through the body portion from the bore to an exterior surface of the vane shaft adjacent to the top portion

公开(公告)号：EP4450339A3

公开(公告)日：2024-12-11

申请号：EP24171673.7

申请日：2024-04-22

Applicant: ROSEMOUNT AEROSPACE INC.

Inventor： MARSHALL, Travis H. ,  REID, Alexander N. ,  SEIDEL, Greg A. ,  CHANDOLA, Nitin ,  SARKAR, Saugata ,  ACHARYA, Ranadip

IPC: B60S1/34 ,  B60S1/32

Abstract: A wiper apparatus includes a wiper axis interface (102) configured for mounting a wiper assembly to a wiper drive (106). A lower wiper arm (110) extends from the wiper axis interface to a wiper mount (112) that is configured to connect the lower arm to an upper arm (114). A first end (124) of the lower wiper arm proximate the wiper axis interface has a first airfoil profile and wall thickness. A second end (126) of the lower wiper arm proximate the wiper mount has a second airfoil profile and wall thickness. An intermediate portion (128) of the lower wiper arm extending between the first and second ends has a transitioning airfoil profile and thickness that transitions from the first airfoil profile and wall thickness to the second airfoil profile and wall thickness.

公开(公告)号：EP4461652A2

公开(公告)日：2024-11-13

申请号：EP24202125.1

申请日：2019-12-13

Applicant: ROSEMOUNT AEROSPACE INC.

Inventor： ANDERSON, Kaleb ,  SCHWARTZ, Richard Alan ,  MADSEN, Michael William

IPC: B64D43/02

Abstract: A vane shaft for an angle of attack sensor, the vane shaft comprising: a body portion (50); a top portion (52) connected to an end of the body portion, the top portion being configured to connect to a vane assembly; a bore (54) extending through the body portion and the top portion; and a first vent hole (60A) extending through the body portion from the bore to an exterior surface of the vane shaft adjacent to the top portion

公开(公告)号：EP4431348A1

公开(公告)日：2024-09-18

申请号：EP24163381.7

申请日：2024-03-13

Applicant: ROSEMOUNT AEROSPACE INC.

Inventor： BOJJANAPALLI, Muralidhar Rao ,  VENKATARAMU, Raghavendra

IPC: B60S1/08 ,  B60S1/16

CPC classification number: B60S1/08 ,  B60S1/163

Abstract: In accordance with at least one aspect of this disclosure, a system (100) includes a wiper arm (106) configured to sweep along a sweep zone (108) defined between a start position (110) and an end sweep position (112). A wiper drive shaft (116) is operatively connected at a proximal end (118) to the wiper arm to drive the wiper arm between the start position and the end sweep position. At least an angular encoder (120) is operatively connected to a distal end (122) of the wiper drive shaft configured to record an actual position of the wiper arm. A controller (128) is operatively connected to the encoder to receive position wiper arm position data therefrom.

公开(公告)号：EP4366094A2

公开(公告)日：2024-05-08

申请号：EP24160288.7

申请日：2018-05-11

Applicant: Rosemount Aerospace Inc.

Inventor： DEANGELO, Tim

IPC: H01R12/58

CPC classification number: H01R12/52 ,  H05K1/11 ,  H05K1/145 ,  H05K3/368 ,  H05K2201/1018920130101 ,  H05K2201/1029520130101 ,  H05K2201/201820130101 ,  B33Y80/00 ,  H01R12/58 ,  H05K1/144 ,  H05K3/366 ,  H05K2201/04220130101

Abstract: A circuit card assembly (10; 110; 210; 310) includes a first printed wiring board (28; 128; 228; 328) with a first receiving feature (38; 138; 238; 338) and a trace (12; 112; 212; 312) attached to the first printed wiring board (28; 128; 228; 328). The three dimensional trace (12; 112; 212; 312) is formed by layer-by-layer additive manufacturing. The three dimensional trace (12; 112; 212; 312) includes first (14; 114; 214; 314) and second ends. The first end (14; 114; 214; 314) of the three dimensional trace (12; 112; 212; 312) engages with the first receiving feature (38; 138; 238; 338) of the first printed wiring board (28; 128; 228; 328). The second end of the three dimensional trace (12; 112; 212; 312) is configured to engage with a second printed wiring board (40; 140; 240; 340).

公开(公告)号：EP4321874A1

公开(公告)日：2024-02-14

申请号：EP23190336.0

申请日：2023-08-08

Applicant: ROSEMOUNT AEROSPACE INC.

Inventor： SHERMAN, Andrew E. ,  NASLUND, Brian B. ,  KUNIK, William G.

IPC: G01P5/165 ,  G01P13/02 ,  G01P21/02 ,  B64F5/60

Abstract: A system includes a body, a sensor (50), a pressurized fluid source (46), and a blockage detection module (32). The body defines a cavity (44) open to an ambient environment at a port. The sensor communicates with the cavity to produce a signal representative of a fluid pressure within the cavity. The blockage detection module includes a pressure regulator (36) and a valve (38) disposed along a conduit (34) fluidly connecting the pressurized fluid source to the cavity. The blockage detection module includes a processor (40) and memory (42) encoded with instructions of a blockage detection method.