公开(公告)号：EP3264103B1

公开(公告)日：2019-10-02

申请号：EP17173396.7

申请日：2017-05-30

Applicant: Rosemount Aerospace Inc.

Inventor： BENNING, Kevin ,  HEUER, Weston

IPC: G01P5/165 ,  B64D15/20 ,  G01K13/02

公开(公告)号：EP3766782A1

公开(公告)日：2021-01-20

申请号：EP19213983.0

申请日：2019-12-05

Applicant: ROSEMOUNT AEROSPACE INC.

Inventor： LOPRESTO, Vincent R. ,  HEUER, Weston

IPC: B64D15/12 ,  G01P5/165 ,  B64D43/02 ,  G01P13/02 ,  B64D15/20 ,  G08B19/02

Abstract: A method including providing power to an aircraft probe (102) anti-ice system, monitoring an actual power demand of the aircraft probe anti-ice system, monitoring an air data parameter and atmospheric conditions surrounding an aircraft (110) and calculating an expected power demand of the aircraft probe anti-ice system based on the air data parameters and the atmospheric conditions, comparing the actual power demand of the aircraft probe anti-ice system to the expected power demand, and performing a corrective action if the actual power demand and the expected power demand are different by more than an acceptable amount.

公开(公告)号：EP3264103A1

公开(公告)日：2018-01-03

申请号：EP17173396.7

申请日：2017-05-30

Applicant: Rosemount Aerospace Inc.

Inventor： BENNING, Kevin ,  HEUER, Weston

IPC: G01P5/165 ,  B64D15/20

CPC classification number: G01P5/165 ,  B64D15/20 ,  G01K13/028

Abstract: A system includes a device having a first surface configured to be exposed to airflow about an exterior of an aircraft, the device including a first self-compensating heater (28) configured to heat the first surface, a first current monitor configured to sense a first measurement value representing electrical current flow through the first self-compensating heater (28), one or more processors, and computer-readable memory encoded with instructions that, when executed by the one or more processors, cause the system to receive aircraft flight condition data and produce an icing condition signal based upon the first measurement value and the aircraft flight condition data.

Abstract translation: 一种系统包括具有第一表面和第二表面的装置，所述第一表面配置成暴露于围绕飞机外部的气流，所述装置包括配置成加热第一表面的第一自补偿加热器（28），配置成感测第一表面 表示流过第一自补偿加热器（28）的电流的测量值，一个或多个处理器和编码有指令的计算机可读存储器，所述指令在由一个或多个处理器执行时使系统接收飞行器飞行条件数据 并基于第一测量值和飞机飞行状态数据产生结冰状态信号。