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.

Disclosed is system and method for detecting formation of solid-state water on a surface of a body. The system comprises at least one microwave resonator sensor locatable on the body under the surface and an analyzer operably coupled to the at least one passive microwave resonator; the analyzer configured to measure at least one parameter of the response of the at least one microwave resonator sensor. The at least one parameter varies in relation to at least one of the permittivity and conductivity of the region above the surface calibrated to output a signal indicating and the analyzer is configured to output an indication when the at least one parameter indicates that solid-state water has formed on the surface. The method comprises measuring the at least one parameter at the analyzer and outputting a signal indicating the formation of solid-state water on the surface.

Disclosed is system and method for detecting formation of solid-state water on a surface of a body. The system comprises at least one microwave resonator sensor locatable on the body under the surface and an analyzer operably coupled to the at least one passive microwave resonator; the analyzer configured to measure at least one parameter of the response of the at least one microwave resonator sensor. The at least one parameter varies in relation to at least one of the permittivity and conductivity of the region above the surface calibrated to output a signal indicating and the analyzer is configured to output an indication when the at least one parameter indicates that solid-state water has formed on the surface. The method comprises measuring the at least one parameter at the analyzer and outputting a signal indicating the formation of solid-state water on the surface.

An icing detector includes an aircraft structure, an exposed member, an optical fiber sensor, and a measuring device. The exposed member is coupled to the aircraft structure and is exposed to an outside of the aircraft structure. The optical fiber sensor is coupled to the exposed member and is covered by one or both of the aircraft structure and the exposed member. The measuring device is configured to measure light received from the optical fiber sensor.

An icing detector includes an aircraft structure, an exposed member, an optical fiber sensor, and a measuring device. The exposed member is coupled to the aircraft structure and is exposed to an outside of the aircraft structure. The optical fiber sensor is coupled to the exposed member and is covered by one or both of the aircraft structure and the exposed member. The measuring device is configured to measure light received from the optical fiber sensor.

An aircraft lamp includes a light source unit, a lamp housing that houses the light source unit, and a power supply control unit that has a casing and includes a control circuit structure configured to control light emission of the light source unit. The control circuit structure is housed in the casing. The casing is disposed outside the lamp housing.

An anti-icing system at least includes: a precooler that exchanges heat between bleed air and outside air; and an anti-icing unit that receives the bleed air passed through the precooler. A bleed air flow rate adjusting section that adjusts a flow rate of the bleed air supplied to the anti-icing unit adjusts the flow rate of the bleed air to suppress pressure of the bleed air to a pressure upper limit or lower by using relationship r1 and relationship r2. The relationship r1 is a relationship between an altitude and a pressure upper limit of the bleed air. The relationship r2 is a relationship between the pressure upper limit and outside air temperature at which the temperature of the bleed air reaches allowable temperature of ducts and other members through which the bleed air flows. The relationship r2 is provided based on the altitude.

An anti-icing system at least includes: a precooler that exchanges heat between bleed air and outside air; and an anti-icing unit that receives the bleed air passed through the precooler. A bleed air flow rate adjusting section that adjusts a flow rate of the bleed air supplied to the anti-icing unit adjusts the flow rate of the bleed air to suppress pressure of the bleed air to a pressure upper limit or lower by using relationship r1 and relationship r2. The relationship r1 is a relationship between an altitude and a pressure upper limit of the bleed air. The relationship r2 is a relationship between the pressure upper limit and outside air temperature at which the temperature of the bleed air reaches allowable temperature of ducts and other members through which the bleed air flows. The relationship r2 is provided based on the altitude.

Systems and methods for machine-learning-based aircraft icing prediction use supervised and unsupervised learning to process real-time environmental data, such as onboard measurements of outside air temperature and dew point, to predict a risk of icing and determine whether to issue an icing risk alert to an onboard crewmember or a remote operator, and/or to recommend an icing avoidance maneuver. The systems and methods can use reinforcement learning to generate a confidence metric in the predicted risk of icing, to determine a time or distance to predicting icing, and/or to not issue an alert or recommend a maneuver in consideration of historical data in a “library of learning” and/or other flight data such as airspeed, altitude, time of year, and weather conditions. The predictive systems and methods are low-cost and low-power, do not require onboard weather radar, and can be effective for use in smaller aircraft that are completely icing-intolerant.

A system includes a plurality of sensors along a surface of an airfoil operable to measure a first set of ice thickness values at a first time and a second set of ice thickness values at a second time. The system further includes a processor configured to determine a first plurality of lift calculation variables and a second plurality of lift calculation variables. The processor also generates a threshold angle of attack value and updates the threshold angle of attack value at the second time, based on one or more differences between the first and second sets of ice thickness values and the first and second plurality of lift calculation variables. The processor is further configured to send, to a display, based on the updated threshold angle of attack, one or more changes to flight data to adjust the actual angle of attack of the airfoil.