Abstract: A system for heating an aircraft surface having a thermally disadvantaged zone includes a carbon nano-tube (CNT) sheet heating element having a power inlet configured to receive power from an external electrical power source and provide it to the CNT sheet heating element that extends across the thermally disadvantaged zone. The CNT sheet heating element is configured and arranged such upon application of power from the external electrical power source to the CNT sheet heating element, the CNT sheet heating element produces a first heat output in a first zone and a second heat output in the thermally disadvantaged zone with the second heat output being greater than the first heat output.

Abstract: A method and system for detecting and determining icing conditions. The method includes: creating a statistical model from test data in which set of data from n data inputs are each plotted as a point in n-dimensional space, and wherein the n-dimensional space is divided into a plurality of regions each representative of a different icing condition according to the data in that region; for a set of current data from n data inputs, using the model to classify the icing condition indicated by the current data, by: obtaining current data from n data inputs; providing the current data as input data to the model; determining the region of the model in which the current data set is located; and identifying the icing condition indicated by the current data set according to the determined region.

Abstract: A heater mat for heating an airfoil having a chord, a leading edge, and a trailing edge includes a first zone element configured to heat a first chord-wise segment of the airfoil. The system further includes a second zone element configured to heat a second chord-wise segment of the airfoil that is adjacent to the first chord-wise segment of the airfoil. The system further includes a first zone busbar located at the leading edge of the heater mat and electrically coupled to the first zone element.

Abstract: A heater mat for heating an airfoil having a chord, a leading edge, and a trailing edge includes a first zone element configured to heat a first chord-wise segment of the airfoil. The system further includes a second zone element configured to heat a second chord-wise segment of the airfoil that is adjacent to the first chord-wise segment of the airfoil. The system further includes a first zone busbar located at the leading edge of the heater mat and electrically coupled to the first zone element.

Abstract: A system for heating an aircraft component of an aircraft includes a heater mat located adjacent the aircraft component and to generate heat. The system further includes a controller coupled to the heater mat and configured to receive an aircraft speed of the aircraft and an outside air temperature (OAT), and to control the heater mat based on the OAT and the aircraft speed.

Abstract: A multi-layered ice detector apparatus includes a first heater strip, a second heater strip, and a plurality of temperature sensors. The first heater strip is configured to be mounted to a surface, the first heater strip forming a first heater layer of the multi-layered ice detector apparatus. The second heater strip is coupled in proximity to the first heater strip, the second heater strip forming a second heater layer of the multi-layered ice detector apparatus. The plurality of temperature sensors are coupled to at least one of the first heater strip and the second heater strip, wherein the plurality of temperature sensors are configured to detect a temperature profile of the multi-layered ice detector apparatus, wherein the temperature profile is indicative of an extent of icing.

Abstract: An ice detection system for an aircraft surface includes a sensor assembly comprising a plurality of temperature sensitive elements configured to be arranged at respective points on the aircraft surface, a control unit arranged to receive signals indicative of a temperature sensed by each of the temperature sensitive elements, a signal conducting bus 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 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.

Abstract: An ice protection system for controlling icing on an aircraft surface includes an OAT sensor configured to provide a signal indicative of an OAT, a LWC detector configured to provide a signal indicative of a LWC, an electrothermal device located on the aircraft surface, and an electronic control system configured to determine a critical temperature (TC) at or below which an anti-icing system will be used to preheat the aircraft surface, supply an electrical power having a calculated power level to the electrothermal device, and calculate the power level as being: zero if OAT>TC and LWC=0, controlled based on OAT and LWC if OAT>TC and LWC>0, controlled based on OAT and LWC if OAT<TC and LWC>0, and controlled based on OAT if OAT<TC and LWC=0.

Abstract: An ice protection system for controlling icing on an aircraft surface includes an OAT sensor configured to provide a signal indicative of an OAT, a LWC detector configured to provide a signal indicative of a LWC, an electrothermal device located on the aircraft surface, and an electronic control system configured to determine a critical temperature (TC) at or below which an anti-icing system will be used to preheat the aircraft surface, supply an electrical power having a calculated power level to the electrothermal device, and calculate the power level as being: zero if OAT>TC and LWC=0, controlled based on OAT and LWC if OAT>TC and LWC>0, controlled based on OAT and LWC if OAT<TC and LWC>0, and controlled based on OAT if OAT<TC and LWC=0.