公开(公告)号：EP3460524A1

公开(公告)日：2019-03-27

申请号：EP18195405.8

申请日：2018-09-19

Applicant: Rosemount Aerospace Inc.

Inventor： SLY, Jaime ,  MILLER, Mark Sherwood

IPC: G01S17/93 ,  G01S17/95 ,  G01S7/484 ,  G01S7/497 ,  G08G5/06

Abstract: A system (12) for an aircraft (10) includes an optical sensor, at least one aircraft sensor, and a controller (18). The optical sensor is configured to emit a laser outside the aircraft (10), and the at least one aircraft sensor is configured to sense at least one aircraft condition. The controller (18) is configured to determine a first operational state of the aircraft (10) based upon the at least one aircraft condition and determine a second operational state of the aircraft (10) based on the at least one aircraft condition, and operate the optical sensor to emit the laser at a first intensity during the first operational state and a second intensity during the second operational state, wherein the second intensity is greater than the first intensity.

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：EP3444618A1

公开(公告)日：2019-02-20

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

Abstract: An angle of attack sensor (10) includes a vane assembly (22) and a multi-piece faceplate (12) adjacent the vane assembly (22). The faceplate (12) includes a heated chassis (16) defining a pocket and a mounting plate (14) positioned adjacent the heated chassis (16) and having an opening (32). The vane assembly (22) has a portion that is positioned in the pocket of the heated chassis (16) and extends through the opening of the mounting plate (14).

公开(公告)号：EP3444617A1

公开(公告)日：2019-02-20

申请号：EP18189469.2

申请日：2018-08-17

Applicant: Rosemount Aerospace Inc.

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

IPC: G01P13/02

Abstract: An angle of attack sensor (10) includes a housing (32) having an open first end (34) and a closed second end (36), a heated chassis (24) positioned within the open first end (34) of the housing (32), a mounting plate (12) positioned on the heated chassis (24) adjacent the open first end (34) of the housing (32) such that an internal chamber is formed between the heated chassis (24) and the mounting plate (12), a transducer compartment (38) between the heated chassis (24) and the closed second end (36) of the housing (32), and a water management system located adjacent the internal chamber and the transducer compartment (38). The water management system includes an annular chamber positioned in the internal chamber (30), a first tube (60) at a first end of the annular chamber (54), and a second tube (62) at a second end of the annular chamber (54). The first tube (60) has a hole such that the first tube (60) is in fluid communication with the annular chamber (54) and the internal chamber (30), and the second tube (62) is in fluid communication with the annular chamber (54) and the transducer compartment (38).

公开(公告)号：EP2933621B1

公开(公告)日：2019-02-20

申请号：EP15163832.7

申请日：2015-04-16

Applicant: Rosemount Aerospace Inc.

Inventor： Fahimi, Saeed ,  Groeneveld, Kevin

IPC: G01L19/00 ,  G01L19/14 ,  H01R13/504 ,  H01R4/02

公开(公告)号：EP3435095A2

公开(公告)日：2019-01-30

申请号：EP18195270.6

申请日：2016-03-22

Applicant: Rosemount Aerospace Inc.

Inventor： GOLLY, Timothy T. ,  SEIDEL, Greg ,  JOHNSON, Paul R.

IPC: G01P5/165 ,  G01P13/02 ,  G01F1/46

Abstract: An air data probe 100 includes a probe head 102 defining a longitudinal axis between a forward tip 104 and aft base. The probe includes a port opening 125 in the forward tip. The probe includes a first conduit 128 in fluid communication with the port opening to guide fluid flow from the port opening to a first chamber 130, wherein the first chamber 130 is downstream from the port opening. The probe also comprises a second conduit 132, offset radially and circumferentially from the first conduit 128, in fluid communication with the first chamber 130 to guide fluid flow from the first chamber to a second chamber 134, wherein the second chamber 134 is downstream from the first chamber 130, wherein the offset between the first and second conduits is configured to prevent particle ingestion from the port opening from entering the fluid conduit.

公开(公告)号：EP3196618B1

公开(公告)日：2019-01-02

申请号：EP17152332.7

申请日：2017-01-20

Applicant: Rosemount Aerospace Inc.

Inventor： ZHANG, Weibin

IPC: G01L9/00 ,  G01L9/06 ,  G01L13/02 ,  G01L15/00

公开(公告)号：EP2700925B1

公开(公告)日：2018-12-12

申请号：EP13180447.8

申请日：2013-08-14

Applicant: ROSEMOUNT AEROSPACE INC.

Inventor： Herman, Chad ,  Larson, Howard E.

IPC: G01K13/02

CPC classification number: G01K1/20 ,  G01K13/028 ,  G01K2013/024

Abstract: A total air temperature probe (100) includes a probe head (102) having an airflow inlet (110), a main airflow outlet (112), a main probe head wall (108) and a flow separation bend wall (118). The flow separation bend wall (118) is opposite the main probe head wall (108) across a primary flow passage (120). A flow separation trip feature (122; 222) is defined on an interior surface of the main probe head wall (108) for tripping a boundary layer flow separation in flow in the primary flow passage (120), e.g., for reduction of deicing heater error.

公开(公告)号：EP3392613A2

公开(公告)日：2018-10-24

申请号：EP18167272.6

申请日：2018-04-13

Applicant: Rosemount Aerospace Inc.

Inventor： ELL, Todd Anthony

IPC: G01C21/16

CPC classification number: G01C23/00 ,  B64D43/00 ,  G01C21/16 ,  G01C25/00

Abstract: An air data computer (10A, 10B) senses acceleration and rotational rate of an aircraft with an inertial sensor assembly of the air data computer (10A, 10B). The air data computer (10A, 10B) determines first attitude information of the aircraft based on the acceleration and rotational rate sensed with the inertial sensor assembly. The air data computer (10A, 10B) receives second attitude information of the aircraft from a source external to the air data computer (10A, 10B), and determines attitude correction values based on the first attitude information and the second attitude information. The air data computer (10A, 10B) applies the attitude correction values to the first attitude information to produce error-corrected attitude information that is output from the air data computer (10A, 10B).

公开(公告)号：EP3392153A1

公开(公告)日：2018-10-24

申请号：EP18167063.9

申请日：2018-04-12

Applicant: Rosemount Aerospace Inc.

Inventor： PESIK, Joseph T. ,  ELL, Todd Anthony ,  RUTKIEWICZ, Robert

IPC: B64D47/08 ,  B64F1/00 ,  G08G5/00 ,  G08G5/04 ,  G08G5/06

Abstract: Apparatus and associated methods relate to using an image of a fiducial (62) located indicating a parking location for the aircraft (18) to provide docking guidance data to a pilot of an aircraft (18). The fiducial (62) has vertically-separated indicia (68, 70) and laterally-separated indicia (64, 66). A camera (54) is configured to mount at a camera location so as to be able to capture two-dimensional images (72A-I) of a scene external to the aircraft (18). The two-dimensional image (72A-I) includes pixel data generated by the two-dimensional array of light-sensitive pixels. A digital processor (56) identifies first and second sets of pixel coordinates corresponding to the two vertically-separated (68, 70) and the two laterally-separated (64, 66) indicia, respectively. The digital processor (56) then calculates, based at least in part on the identified first pixel coordinates corresponding to the two vertically-separated indicia (68, 70), a range (R) to the parking location.