A heated composite structure and a method for forming a heated composite structure. The structure includes carbon fibers embedded within a thermoplastic matrix. The carbon fibers are connected with first and second electrodes that are configured to be connected with an electric source such that applying current to the electrodes causes current to flow through the embedded carbon fibers to provide resistive heating sufficient to heat the composite structure to impede formation of ice on the composite structure.

Apparatus and associated methods relate to determining liquid-water concentration in a cloud atmosphere based on a frequency of resonance of a magnetostrictive resonator and/or a temporal variation of the resonant frequency of the magnetostrictive resonator. The magnetostrictive resonator is configured to resonate at a resonant frequency indicative of a measure of ice accumulation upon an exterior surface of the magnetostrictive resonator. When in liquid-water ambient, however, the magnetostrictive resonator has a resonant frequency less than a baseline resonant frequency. When in the liquid-water ambient, the magnetostrictive resonator also has temporal variations in resonant frequency that exceed one part in ten thousand. Using one or both of these resonant-frequency responses to liquid-water ambient, a signal indicative of liquid-water content can be generated.

Apparatus and associated methods relate to determining liquid-water concentration in a cloud atmosphere based on a frequency of resonance of a magnetostrictive resonator and/or a temporal variation of the resonant frequency of the magnetostrictive resonator. The magnetostrictive resonator is configured to resonate at a resonant frequency indicative of a measure of ice accumulation upon an exterior surface of the magnetostrictive resonator. When in liquid-water ambient, however, the magnetostrictive resonator has a resonant frequency less than a baseline resonant frequency. When in the liquid-water ambient, the magnetostrictive resonator also has temporal variations in resonant frequency that exceed one part in ten thousand. Using one or both of these resonant-frequency responses to liquid-water ambient, a signal indicative of liquid-water content can be generated.

Methods and systems are generally described that inhibit debris (such as ice) accretions and/or remove debris (such as ice) accretions from the exterior surface of an aircraft. In some embodiments, the invention is a system for an aircraft comprising: a component of the aircraft having a surface; a plurality of piezo-kinetic actuators each positioned proximate to a portion of the surface; and a control unit coupled to the plurality of actuators, the control unit configured to actuate one or more of the actuators at one or more frequencies; wherein the actuators are each configured to introduce a displacement of the surface in three dimensions to inhibit a formation of ice on at least the portion of the surface and to break up existing ice formations on at least the portion of the surface.

Methods and systems are generally described that inhibit debris (such as ice) accretions and/or remove debris (such as ice) accretions from the exterior surface of an aircraft. In some embodiments, the invention is a system for an aircraft comprising: a component of the aircraft having a surface; a plurality of piezo-kinetic actuators each positioned proximate to a portion of the surface; and a control unit coupled to the plurality of actuators, the control unit configured to actuate one or more of the actuators at one or more frequencies; wherein the actuators are each configured to introduce a displacement of the surface in three dimensions to inhibit a formation of ice on at least the portion of the surface and to break up existing ice formations on at least the portion of the surface.

A de-icing assembly includes an aircraft with an airfoil. A de-icer is disposed on a leading edge of the airfoil. A tab extends from the de-icer in an aft direction from an aft edge of the de-icer. The de-icer and the tab are adhesively attached onto an outer skin of the airfoil. A supercooled large droplet sensor is built into the tab. The supercooled large droplet sensor is positioned in a location aft of the aft edge of the de-icer.

A de-icing assembly includes an aircraft with an airfoil. A de-icer is disposed on a leading edge of the airfoil. A tab extends from the de-icer in an aft direction from an aft edge of the de-icer. The de-icer and the tab are adhesively attached onto an outer skin of the airfoil. A supercooled large droplet sensor is built into the tab. The supercooled large droplet sensor is positioned in a location aft of the aft edge of the de-icer.

A system for detecting icing includes an optical sensor configured to view at least a portion of an exterior surface or component of an aircraft and to output sensor data indicating at least one optical quality of the exterior surface or component, and an icing detection module. The icing detection module is configured to receive the sensor data from the optical sensor, compare the sensor data to predetermined quality data indicating at least one known optical quality of the exterior surface or component without icing, and determine the presence of icing on the exterior surface or component based on a difference between the sensor data and the predetermined quality data.

A system for detecting icing includes an optical sensor configured to view at least a portion of an exterior surface or component of an aircraft and to output sensor data indicating at least one optical quality of the exterior surface or component, and an icing detection module. The icing detection module is configured to receive the sensor data from the optical sensor, compare the sensor data to predetermined quality data indicating at least one known optical quality of the exterior surface or component without icing, and determine the presence of icing on the exterior surface or component based on a difference between the sensor data and the predetermined quality data.

A method of determining ice accretion on a surface of an aircraft can include supplying a known power to a heating element formed in a patch, wherein the patch includes a temperature sensor. A controller module can compare a sensed thermal signature with a threshold signature and determine the presence of ice accretion on the aircraft.