Abstract: A system and method include a first icing detector configured to detect a first icing condition in relation to one or more portions of an aircraft. The first icing detector is configured to output a first icing signal indicative of the first icing condition. A second icing detector is configured to detect a second icing condition in relation to the one or more portions of the aircraft. The second icing detector is configured to output a second icing signal indicative of the second icing condition. A control unit is in communication with the first icing detector and the second icing detector. The control unit is configured to receive the first icing signal from the first icing detector and the second icing signal from the second icing detector. The control unit is further configured to distinguish between presence of supercooled liquid water and ice crystal icing in response to receiving one or both of the first icing signal or the second icing signal.

Abstract: A system and method include a first icing detector configured to detect a first icing condition in relation to one or more portions of an aircraft. The first icing detector is configured to output a first icing signal indicative of the first icing condition. A second icing detector is configured to detect a second icing condition in relation to the one or more portions of the aircraft. The second icing detector is configured to output a second icing signal indicative of the second icing condition. A control unit is in communication with the first icing detector and the second icing detector. The control unit is configured to receive the first icing signal from the first icing detector and the second icing signal from the second icing detector. The control unit is further configured to distinguish between presence of supercooled liquid water and ice crystal icing in response to receiving one or both of the first icing signal or the second icing signal.

Abstract: A method for detecting an icing condition using an apparatus comprising a piezoelectric material and a vibration detector. The piezoelectric material has a surface proximate to a surface of a vehicle. The piezoelectric material is configured to vibrate. The vibration detector is configured to detect a change in vibrations in the piezoelectric material that indicates a presence of an icing condition on the surface of the piezoelectric material.

Abstract: A method for detecting an icing condition using an apparatus comprising a piezoelectric material and a vibration detector. The piezoelectric material has a surface proximate to a surface of a vehicle. The piezoelectric material is configured to vibrate. The vibration detector is configured to detect a change in vibrations in the piezoelectric material that indicates a presence of an icing condition on the surface of the piezoelectric material.

Abstract: A method and apparatus for detecting an icing condition. The apparatus comprises a piezoelectric material and a vibration detector. The piezoelectric material has a surface proximate to a surface of a vehicle. The piezoelectric material is configured to vibrate. The vibration detector is configured to detect a change in vibrations in the piezoelectric material that indicates a presence of an icing condition on the surface of the piezoelectric material.

Abstract: A method and apparatus for detecting an icing condition. The apparatus comprises a sensor system and an icing condition detector. The sensor system is configured to collect drops of water from air on an exterior of an aircraft and generate a number of images of the drops of water collected. The icing condition detector is configured to detect a presence of a number of types of icing conditions for the aircraft using the number of images from the sensor.

Abstract: A method and apparatus for detecting an icing condition. The apparatus comprises a piezoelectric material and a vibration detector. The piezoelectric material has a surface proximate to a surface of a vehicle. The piezoelectric material is configured to vibrate. The vibration detector is configured to detect a change in vibrations in the piezoelectric material that indicates a presence of an icing condition on the surface of the piezoelectric material.

Abstract: A thermal anti-ice system in an aircraft. A controlled valve receives air from a compressor bleed port of an engine of the aircraft. A self-regulating valve is fluidly connected between the controlled valve and an inlet of the engine. A first pressure sensor senses pressure between the valves. A second pressure sensor senses pressure between the self-regulating valve and the inlet. The system can be used to de-ice aircraft inlet lip skins made of composite materials that have comparatively lower design temperatures than other comparable materials.

Abstract: A thermal anti-ice system in an aircraft. A controlled valve receives air from a compressor bleed port of an engine of the aircraft. A self-regulating valve is fluidly connected between the controlled valve and an inlet of the engine. A first pressure sensor senses pressure between the valves. A second pressure sensor senses pressure between the self-regulating valve and the inlet. The system can be used to de-ice aircraft inlet lip skins made of composite materials that have comparatively lower design temperatures than other comparable materials.