公开(公告)号：EP2946978B1

公开(公告)日：2020-09-30

申请号：EP15168821.5

申请日：2015-05-22

Applicant: Rosemount Aerospace Inc.

Inventor： REID, Alexander N. ,  WEBB, Matthew

IPC: B60S1/34

公开(公告)号：EP2946978A1

公开(公告)日：2015-11-25

申请号：EP15168821.5

申请日：2015-05-22

Applicant: Rosemount Aerospace Inc.

Inventor： REID, Alexander N. ,  WEBB, Matthew

IPC: B60S1/34

Abstract: A wiper arm assembly (14) has a load member (28), a wiper arm (24), and a blade load cam (32) with a cam slot (36). The load member (28) mates with a joint (40) disposed between first and second ends of the wiper arm (20). Changes in length of the load member (28) impose a force (L) in a lengthwise direction of the load member (28). The wiper arm (24) is configured to rotate relative to the blade load cam (32) about an axis proximate to the first end of the wiper arm (24). The cam slot (36) is configured to vary the length of the load member (28) as a function of a wiper angle in which the wiper angle is defined as the angle between the wiper arm (24) and a starting position of the wiper arm (24).

Abstract translation: 刮水臂组件（14）具有负载部件（28），一刮水器臂（24），和叶片负载凸轮（32）配有一个凸轮槽（36）。 负载部件（28）紧密配合的雨刮臂（20）的第一和第二端之间设置在接头（40）。 在负载部件（28）在负载部件（28）的长度方向施加的力（L）的长度的变化。 刮水器臂（24）被配置成相对于叶片负载凸轮（32）关于在轴接近所述刮水臂（24）的第一端部旋转。 凸轮槽（36）被配置为改变所述负载部件（28）为其中刮水角被定义为刮水器臂（24）之间的角度的擦拭角度的函数的长度和擦拭器的起始位置 臂（24）。

公开(公告)号：EP4467456A1

公开(公告)日：2024-11-27

申请号：EP24176981.9

申请日：2024-05-21

Applicant: ROSEMOUNT AEROSPACE INC.

Inventor： ROMAN, Jamison K. ,  WEBB, Matthew

IPC: B64D15/20 ,  G01N29/24 ,  H10N35/80 ,  G01P5/165 ,  B33Y10/00 ,  B33Y80/00

Abstract: An ice detection sensor apparatus (100) includes a strut body (102) extending along a longitudinal axis (A). The strut body (102) includes an axially extending wall (104) extending around the longitudinal axis (A) to surround an interior space (106), and an axial-facing end wall (108) connected to an axial end of the axially extending wall (104). The axial-facing end wall (108) partially bounds the interior space (106). A magneto strictive oscillator sensing element (118) extends from the interior space (106), through the axial-facing end wall (108). The sensing element (118) is engaged to the axial-facing end wall (108) for oscillation along the longitudinal axis (A) relative to the axial-facing end wall (108). A permanent magnet (PMG) element (122) is integral with, e.g., monolithic with, the strut body (102).

公开(公告)号：EP4292938A1

公开(公告)日：2023-12-20

申请号：EP23179626.9

申请日：2023-06-15

Applicant: ROSEMOUNT AEROSPACE INC.

Inventor： ROMAN, Jamison ,  WEBB, Matthew ,  SCHWEITZER, Jeremiah

IPC: B64D15/00 ,  B64D15/12 ,  B33Y80/00 ,  B64D15/20 ,  B22F10/00 ,  B33Y10/00 ,  B22F7/06

Abstract: A strut of a magnetostrictive oscillator includes a strut body (26) which includes an airfoil with a first end (28), a second end (30), a leading edge (52), a trailing edge (54), a first side (56), and a second side (58). The strut further includes a heater element (38) within the first side and second side, wherein the heater element connects from the first side to the second side. The strut further includes an electrically insulative layer (40) between the heater element and the strut body. The heater element and the electrically insulative layer are integral with the strut body.

公开(公告)号：EP3487261A1

公开(公告)日：2019-05-22

申请号：EP18205736.4

申请日：2018-11-12

Applicant: ROSEMOUNT AEROSPACE INC.

Inventor： WEBB, Matthew ,  CHONG, Peter Mann-Lai

IPC: H05B1/02

Abstract: A surface heating system of an external surface of a vehicle system includes a heater (16) and a heater controller (12). The heater (16) is configured to provide heat to the external surface. The heater controller (12) is configured to control a heater power of the heater (16) based upon an air temperature of air external to the vehicle, a liquid water content of the air, and a speed of the vehicle.

公开(公告)号：EP4301118A1

公开(公告)日：2024-01-03

申请号：EP23179336.5

申请日：2023-06-14

Applicant: Rosemount Aerospace Inc.

Inventor： ROMAN, Jamison K. ,  WEBB, Matthew ,  SCHWEIZER, Jeremiah

IPC: H10N35/01 ,  B33Y80/00 ,  B64D15/20 ,  H10N35/80

Abstract: A probe head of a magnetostrictive oscillator includes a probe head body which includes a hollow cylindrical portion with a first end (14), a second end (16), a radially inner side, and a radially outer side. The probe head body further includes a hemispherical portion connected to the first end (14) of the hollow cylindrical portion. The probe head further includes a heater element (38) within the radially outer side of the hollow cylindrical portion and an electrically insulative layer around the heater element (38). The heater element (38) and the electrically insulative layer are integral with the probe head body.

公开(公告)号：EP4183687A1

公开(公告)日：2023-05-24

申请号：EP22208662.1

申请日：2022-11-21

Applicant: ROSEMOUNT AEROSPACE INC.

Inventor： NASLUND, Brian Brent ,  BURNS, Jeremy S. ,  WEBB, Matthew ,  SKOGLUND, Jason Lee ,  LOPRESTO, Vincent R. ,  JACKSON, Darren G.

IPC: B64D15/14 ,  B64D15/22 ,  B64D45/00

Abstract: A method of monitoring an ice protection system (10) of a rotorcraft or an aircraft includes applying heat to rotating blades of the rotorcraft or the aircraft according to a heater duty cycle and determining an anticipated ice shed time for ice to shed from the rotating blades. Torque of the rotating blades is sensed, and an actual ice shed time for ice to shed from the rotating blades is determined based on the sensed torque. A status of the ice protection system (10) is determined based on the anticipated ice shed time and the actual ice shed time, and the status of the ice protection system (10) is output for consumption by a consuming system (70).

公开(公告)号：EP3564129A1

公开(公告)日：2019-11-06

申请号：EP19172127.3

申请日：2019-05-01

Applicant: ROSEMOUNT AEROSPACE INC.

Inventor： LOPRESTO, Vincent R. ,  WEBB, Matthew

IPC: B64D15/20

Abstract: Apparatus and associated methods relate to differentiating ice accretion caused by different supercooled water droplets on an airfoil (12) of an aircraft. A sensor (22) having a sensing surface region (42) is mounted at a mounting location of the airfoil (12) such that the sensing surface region (42) is flush with a surrounding adjacent surface of the airfoil (12). Water particles of sizes less than or equal to a predetermined threshold do not impinge the sensor surface region (42) at the mounting location when the aircraft is in flight. A sensor driver provides an excitation signal to the sensor (22). A signal detector (43) detects a sensor signal responsive to the provided excitation signal. The sensor signal is indicative of water particles exceeding the predetermined threshold impinging the sensing surface region (42). In some embodiments, the sensing surface region (42) is mechanically coupled to a resonant cavity (22C). In other embodiments, the sensor (22) is a surface resistance sensor configured to sense surface resistance.