A method of detecting that ice has been shed from an external surface of a component is provided, the method comprising applying power to a heating means to provide heat to said external surface. The method further comprises sensing the temperature of the component and calculating the rate of change of temperature increase of the external surface over time. Further, the method comprises detecting a change in said rate of change of temperature increase over time, wherein said detected change in rate of change of temperature increase indicates that said ice has been shed from said external surface of said component.

A method for managing icing conditions on a rotary aircraft via one or more ice protection controllers. The method includes steps for receiving an icing condition signal from an icing rate sensor at an ice protection controller, determining, in response to the icing condition signal, a de-icing signal based at least in part a liquid water content (LWC). The method further includes steps for transmitting, via a digital communication bus disposed in at least part of a slip ring assembly, the de-icing signal to a upper distributor to cause the upper distributor to transmit power to one or more heating elements for a respective rotor blade.

A method for managing icing conditions on a rotary aircraft via one or more ice protection controllers. The method includes steps for receiving an icing condition signal from an icing rate sensor at an ice protection controller, determining, in response to the icing condition signal, a de-icing signal based at least in part a liquid water content (LWC). The method further includes steps for transmitting, via a digital communication bus disposed in at least part of a slip ring assembly, the de-icing signal to a upper distributor to cause the upper distributor to transmit power to one or more heating elements for a respective rotor blade.

Provided are embodiments for deicing an aircraft propeller having a plurality of blades of an aircraft. An example method includes performing a first heating, by a first plurality of heating elements connected to a first portion of each of the plurality of blades, for a first period of time, the first portion of each of the plurality of blades of the propeller defining a first deicing zone. The method further includes, subsequent to expiration of the first period of time, performing a second heating, by a second plurality of heating elements connected to a second portion of each of the plurality of blades, for a second period of time, the second portion of each of the plurality of blades of the propeller defining a second deicing zone.

An air date probe includes a strut assembly extending from a base, and a tube assembly coupled to the strut assembly. One or both of the strut assembly and the tube assembly comprises a self-regulating thin film heating arrangement. The self-regulating thin film heating arrangement includes at least one circuit including a positive temperature coefficient (PTC) heating element connected in series with a negative temperature coefficient (NTC) heating element.

A method for managing icing conditions on a rotary aircraft via one or more ice protection controllers. The method includes steps for receiving an icing condition signal from an icing rate sensor at an ice protection controller, determining, in response to the icing condition signal, a de-icing signal based at least in part a liquid water content (LWC). The method further includes steps for transmitting, via a digital communication bus disposed in at least part of a slip ring assembly, the de-icing signal to a upper distributor to cause the upper distributor to transmit power to one or more heating elements for a respective rotor blade.

A method for managing icing conditions on a rotary aircraft via one or more ice protection controllers. The method includes steps for receiving an icing condition signal from an icing rate sensor at an ice protection controller, determining, in response to the icing condition signal, a de-icing signal based at least in part a liquid water content (LWC). The method further includes steps for transmitting, via a digital communication bus disposed in at least part of a slip ring assembly, the de-icing signal to a upper distributor to cause the upper distributor to transmit power to one or more heating elements for a respective rotor blade.

Apparatus and methods for generating electrical power for powering a device associated with a bladed rotor driven by a gas turbine engine of an aircraft are disclosed. The apparatus includes a rotor shaft coupled the bladed rotor of the aircraft and driven by a turbine shaft of the engine via a speed-reducing gear train. A speed-augmenting power transfer device has an input coupled to the rotor shaft and an output for outputting a rotation speed higher than a rotation speed of the rotor shaft received at the input of the speed-augmenting power transfer device. An electric generator disposed in a hub of the bladed rotor is coupled to the output of the speed-augmenting power transfer device and configured to generate electrical power for the device associated with the bladed rotor.

Apparatus and methods for generating electrical power for powering a device associated with a bladed rotor driven by a gas turbine engine of an aircraft are disclosed. The apparatus includes a rotor shaft coupled the bladed rotor of the aircraft and driven by a turbine shaft of the engine via a speed-reducing gear train. A speed-augmenting power transfer device has an input coupled to the rotor shaft and an output for outputting a rotation speed higher than a rotation speed of the rotor shaft received at the input of the speed-augmenting power transfer device. An electric generator disposed in a hub of the bladed rotor is coupled to the output of the speed-augmenting power transfer device and configured to generate electrical power for the device associated with the bladed rotor.

There is provided an ice protection system for a rotary aircraft, including a rotor blade susceptible to an ice buildup having an inboard portion and an outboard portion, the length of the inboard portion and the length of the outboard portion define a total length of the rotor blade; a first deicing system coupled to the inboard portion of the rotor blade, the first deicing system including a plurality of spanwise zones; and a second deicing system coupled to the outboard portion of the rotor blade, the second deicing system including a plurality of chordwise zones. In one aspect, there is provided a deicing system for a rotary aircraft. In another aspect, there is a method to de-ice a rotor blade of an aircraft.