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1. EP3854691 - ICE DETECTION ARRANGEMENT

Office
European Patent Office
Application Number 20153740
Application Date 24.01.2020
Publication Number 3854691
Publication Date 28.07.2021
Publication Kind A1
IPC
B64D 15/20
BPERFORMING OPERATIONS; TRANSPORTING
64AIRCRAFT; AVIATION; COSMONAUTICS
DEQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLYING SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
15De-icing or preventing icing on exterior surfaces of aircraft
20Means for detecting icing or initiating de-icing
CPC
B64D 15/20
BPERFORMING OPERATIONS; TRANSPORTING
64AIRCRAFT; AVIATION; COSMONAUTICS
DEQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLYING SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
15De-icing or preventing icing on exterior surfaces of aircraft
20Means for detecting icing or initiating de-icing
B64D 15/22
BPERFORMING OPERATIONS; TRANSPORTING
64AIRCRAFT; AVIATION; COSMONAUTICS
DEQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLYING SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
15De-icing or preventing icing on exterior surfaces of aircraft
20Means for detecting icing or initiating de-icing
22Automatic initiation by icing detector
G08B 19/02
GPHYSICS
08SIGNALLING
BSIGNALLING OR CALLING SYSTEMS; ORDER TELEGRAPHS; ALARM SYSTEMS
19Alarms responsive to two or more different undesired or abnormal conditions, e.g. burglary and fire, abnormal temperature and abnormal rate of flow
02Alarm responsive to formation or anticipated formation of ice
Applicants GOODRICH CORP
Inventors DEBBADI KARTHIK
RIDOUANE EL HASSAN
CHABUKSWAR ROHAN
ZADELL ALEX
SELVARAJ SUGUMARAN
BOTURA GALDEMIR
GELAO GIANCARLO
Designated States
Priority Data 20153740 24.01.2020 EP
Title
(DE) EISDETEKTIONSANORDNUNG
(EN) ICE DETECTION ARRANGEMENT
(FR) AGENCEMENT DE D√ČTECTION DE GLACE
Abstract
(EN) An ice detection system for an aircraft surface, comprising a sensor assembly (10) comprising a plurality of temperature sensitive elements configured to be arranged at respective points on the aircraft surface, a control unit (20) arranged to receive signals indicative of a temperature sensed by each of the temperature sensitive elements, a signal conducting bus (50) to transmit the signals from the temperature sensitive elements to the control unit, and means for providing power to the sensor assembly, wherein the sensor assembly further comprises a multiplexer (40) arranged to multiplex the signals from the plurality of temperature sensitive elements into a single signal for transmission on the signal conducting bus to the control unit.