A method and a device are disclosed for determining icing on an aircraft, as well as an aircraft. The method can include acquiring a current flight state of the aircraft, acquiring current flight conditions of the aircraft, estimating an estimated power feed of a power supply of the aircraft for the current flight state under the current flight conditions, comparing the estimated power feed with an actual power feed of the power supply of the aircraft, and determining a presence of icing on the aircraft when a probability of an existence of icing conditions exceeds a predetermined probability threshold and the estimated power feed exceeds the actual power feed by a predetermined amount.

The method of controlling an autonomous anti-icing apparatus includes: a first step of collecting and storing ice formation environment data; a second step of calculating a calculated value of an aerodynamic parameter based on the ice formation environment data and the ice formation prediction data in real time to determine whether ice formation is present on a surface of the structure and calculating a degree of ice formation through the calculated value of the aerodynamic parameter; and a third step of allowing a calculation control unit to send a temperature control signal, which includes a heating period signal, to a power supply so that an electric heating part is heated when the ice formation is determined by comparing the degree of ice formation with a preset value.

The method of controlling an autonomous anti-icing apparatus includes: a first step of collecting and storing ice formation environment data; a second step of calculating a calculated value of an aerodynamic parameter based on the ice formation environment data and the ice formation prediction data in real time to determine whether ice formation is present on a surface of the structure and calculating a degree of ice formation through the calculated value of the aerodynamic parameter; and a third step of allowing a calculation control unit to send a temperature control signal, which includes a heating period signal, to a power supply so that an electric heating part is heated when the ice formation is determined by comparing the degree of ice formation with a preset value.

A fluid valve is provided including an inner shell and an outer shell. The inner shell includes a sidewall having a first opening and an interior surface defining an inner chamber. The outer shell includes a sidewall having a second opening and an exterior surface defining an outer chamber. The inner shell is positioned within the outer shell and the inner shell is movable relative to the outer chamber between a first position and a second position by a change in fluid conditions of a fluid supplied to the fluid valve. The first opening and the second opening overlap to define a passageway extending from the interior surface of the inner shell to the exterior surface of the outer shell. Relative movement of the inner shell from the first position toward the second position reduces a cross-sectional area of the passageway.

A method and apparatus for predicting conditions favorable for icing, includes sensing a value indicative of a thermal cycling period, comparing, the sensed thermal cycling period with a threshold value, determining, if the sensed thermal cycling period satisfies the threshold value, and indicating, by the controller module, that conditions favorable for icing are present when the sensed thermal cycling period satisfies the threshold value.

A method and apparatus for predicting conditions favorable for icing, includes sensing a value indicative of a thermal cycling period, comparing, the sensed thermal cycling period with a threshold value, determining, if the sensed thermal cycling period satisfies the threshold value, and indicating, by the controller module, that conditions favorable for icing are present when the sensed thermal cycling period satisfies the threshold value.

A device for deicing a wall of an aircraft, comprising a closed circuit. The closed circuit comprises at least one condenser, positioned in the environment of the wall that is to be deiced, and in which a heat-transfer fluid condenses, generating energy in the form of latent heat which is transmitted to the wall that is to be deiced, at least one evaporator positioned in the environment of a heat source sited remotely with respect to the wall, and in which the heat-transfer fluid evaporates, absorbing energy in the form of latent heat coming from the heat source. At least part of the closed circuit is facing, in contact with, or positioned in, the wall that is to be deiced, being made of a material transparent to electromagnetic fields.

A device for deicing a wall of an aircraft, comprising a closed circuit. The closed circuit comprises at least one condenser, positioned in the environment of the wall that is to be deiced, and in which a heat-transfer fluid condenses, generating energy in the form of latent heat which is transmitted to the wall that is to be deiced, at least one evaporator positioned in the environment of a heat source sited remotely with respect to the wall, and in which the heat-transfer fluid evaporates, absorbing energy in the form of latent heat coming from the heat source. At least part of the closed circuit is facing, in contact with, or positioned in, the wall that is to be deiced, being made of a material transparent to electromagnetic fields.

A system includes an optical pressure sensor. A controller is operatively connected to receive input from the optical pressure sensor. An output connection is operatively connected to communicate output data from the controller. The controller includes machine readable 5 instructions configured to cause the controller to receive data from an optical pressure sensor, detect an accumulation of contaminant on the optical pressure sensor, and initiate a corrective action through the output connection in response to detecting the accumulation of contaminant.

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.