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.

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 rotary blade includes a blade body, one or more heater elements, and a temperature sensing circuit. The one or more heater elements are connected to the blade body. The temperature sensing circuit is in thermal communication with the blade body and is electrically isolated from the one or more heater elements for determining actual temperature of the rotary blade independent of operation of the one or more heater elements.

A rotary blade includes a blade body, one or more heater elements, and a temperature sensing circuit. The one or more heater elements are connected to the blade body. The temperature sensing circuit is in thermal communication with the blade body and is electrically isolated from the one or more heater elements for determining actual temperature of the rotary blade independent of operation of the one or more heater elements.

A method of an embodiment includes receiving data from a sensor that is configured to supply data related to an ice layer thickness on a skin surface, calculating the ice layer thickness, comparing the ice layer thickness to a threshold thickness, vibrating the skin surface using at least one mechanical element for a sufficient duration, sufficient frequency, and sufficient displacement to result in removal of a first portion of the ice layer thereby resulting in at least a partially deiced skin surface, and heating the partially deiced skin surface using at least one heating element. The method of an embodiment further includes heating from a leading edge of the skin surface to a trailing edge of the skin surface and heating the surface to result in a sufficient temperature increase in the skin surface for removal of a second portion of the ice layer.

A method of an embodiment includes receiving data from a sensor that is configured to supply data related to an ice layer thickness on a skin surface, calculating the ice layer thickness, comparing the ice layer thickness to a threshold thickness, vibrating the skin surface using at least one mechanical element for a sufficient duration, sufficient frequency, and sufficient displacement to result in removal of a first portion of the ice layer thereby resulting in at least a partially deiced skin surface, and heating the partially deiced skin surface using at least one heating element. The method of an embodiment further includes heating from a leading edge of the skin surface to a trailing edge of the skin surface and heating the surface to result in a sufficient temperature increase in the skin surface for removal of a second portion of the ice layer.

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.

An electrothermal ice protection system (IPS) installed on an aircraft includes a sensor, a parting strip assembly, and a controller. The sensor monitors a direction of a local incident airflow that is imparted on the sensor. The parting strip assembly is coupled to the critical surface and includes a plurality of heating sections. The controller is in signal communication with the sensor and the parting strip assembly. The controller determines a direction of surface airflow incident on a critical surface of the aircraft based on the local incident airflow and selectively concentrates power to at least one targeted heating section among the plurality of heating sections with respect to non-targeted heating sections among the plurality of heating sections based on the direction of the surface airflow.

An electrothermal ice protection system (IPS) installed on an aircraft includes a sensor, a parting strip assembly, and a controller. The sensor monitors a direction of a local incident airflow that is imparted on the sensor. The parting strip assembly is coupled to the critical surface and includes a plurality of heating sections. The controller is in signal communication with the sensor and the parting strip assembly. The controller determines a direction of surface airflow incident on a critical surface of the aircraft based on the local incident airflow and selectively concentrates power to at least one targeted heating section among the plurality of heating sections with respect to non-targeted heating sections among the plurality of heating sections based on the direction of the surface airflow.