An ice protection system adapted to protect at least one ice-susceptible flight surface of an aircraft includes a mechanical ice protection device attached to the flight surface. A controller controls a power source that causes the mechanical ice protection device to change in shape and, thereby, change an aerodynamic characteristic of the flight surface. This change in shape happens only when the current thickness of ice on the surface exceeds a minimum thickness and the minimum thickness is based on attitude of the aircraft.

A device for detecting a frosting intensity for an aircraft in flight includes a surface for collecting the frost and measuring means capable of measuring the thickness of the frost deposited on the frost collection surface. The device further includes calculation means configured to determine, at predetermined time intervals (T.sub.samp), the change in the thickness of the frost, and control means configured to generate an alarm signal when the difference in the thickness of the frost measured between two time intervals (T.sub.samp) is greater than a threshold value.

A device for detecting a frosting intensity for an aircraft in flight includes a surface for collecting the frost and measuring means capable of measuring the thickness of the frost deposited on the frost collection surface. The device further includes calculation means configured to determine, at predetermined time intervals (T.sub.samp), the change in the thickness of the frost, and control means configured to generate an alarm signal when the difference in the thickness of the frost measured between two time intervals (T.sub.samp) is greater than a threshold value.

An ice accretion apparatus comprises a column having a longitudinal axis, a side wall, and a central chamber having top and bottom ends. It also comprises a top unit which closes the top end of the chamber and includes a droplet discharge device for producing water droplets, a bottom unit which closes the bottom end of the chamber and includes a target, and chamber cooling means configured to cool the chamber during a test and thereby to cool the water droplets, whereby, in use during the test, a layer of accreted ice is built up on the target.

An ice accretion apparatus comprises a column having a longitudinal axis, a side wall, and a central chamber having top and bottom ends. It also comprises a top unit which closes the top end of the chamber and includes a droplet discharge device for producing water droplets, a bottom unit which closes the bottom end of the chamber and includes a target, and chamber cooling means configured to cool the chamber during a test and thereby to cool the water droplets, whereby, in use during the test, a layer of accreted ice is built up on the target.

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.

In some examples, a system includes a receiver configured to receive temperature data for a region of airspace from a data source external to the vehicle. The system also includes processing circuitry configured to determine one or more moisture values for the region of airspace based on radar returns received by a weather radar onboard the vehicle. The processing circuitry is further configured to determine a potential for icing at a location within the region of airspace based on the one or more moisture values and further based on the temperature data received from the data source. The processing circuitry is also configured to generate an output based on the determined potential for icing at the location.

In some examples, a system includes a receiver configured to receive temperature data for a region of airspace from a data source external to the vehicle. The system also includes processing circuitry configured to determine one or more moisture values for the region of airspace based on radar returns received by a weather radar onboard the vehicle. The processing circuitry is further configured to determine a potential for icing at a location within the region of airspace based on the one or more moisture values and further based on the temperature data received from the data source. The processing circuitry is also configured to generate an output based on the determined potential for icing at the location.

An aircraft wing may comprise an airfoil having deicing zone, an anti-icing zone, and an ice runback control zone. An aircraft wing may comprise an electro-thermal ice protection system disposed in the aircraft wing. The electro-thermal ice protection system may be disposed along the deicing, anti-icing, and ice runback control zones of the airfoil to improve aerodynamic performance of the aircraft and reduce ice formation along the wings of the aircraft.

An aircraft wing may comprise an airfoil having deicing zone, an anti-icing zone, and an ice runback control zone. An aircraft wing may comprise an electro-thermal ice protection system disposed in the aircraft wing. The electro-thermal ice protection system may be disposed along the deicing, anti-icing, and ice runback control zones of the airfoil to improve aerodynamic performance of the aircraft and reduce ice formation along the wings of the aircraft.