An aircraft ice detection system is configured to determine a condition of a cloud and includes a radar transmitter, a radar receiver, optics and a splitter. The radar transmitter is configured to produce quasi-optical radiation. The optics are configured to direct the quasi-optical radiation from the radar transmitter to the cloud and receive reflected quasi-optical radiation from the cloud. The radar receiver is configured to receive the reflected quasi-optical radiation from the optics and the splitter is configured to direct the reflected quasi-optical radiation from the optics to the radar receiver.

An electrothermal ice protection system (IPS) installed on an aircraft includes a sensor, a parting strip assembly, and a controller. The sensor monitors a direction of a local incident airflow that is imparted on the sensor. The parting strip assembly is coupled to the critical surface and includes a plurality of heating sections. The controller is in signal communication with the sensor and the parting strip assembly. The controller determines a direction of surface airflow incident on a critical surface of the aircraft based on the local incident airflow and selectively concentrates power to at least one targeted heating section among the plurality of heating sections with respect to non-targeted heating sections among the plurality of heating sections based on the direction of the surface airflow.

An electrothermal ice protection system (IPS) installed on an aircraft includes a sensor, a parting strip assembly, and a controller. The sensor monitors a direction of a local incident airflow that is imparted on the sensor. The parting strip assembly is coupled to the critical surface and includes a plurality of heating sections. The controller is in signal communication with the sensor and the parting strip assembly. The controller determines a direction of surface airflow incident on a critical surface of the aircraft based on the local incident airflow and selectively concentrates power to at least one targeted heating section among the plurality of heating sections with respect to non-targeted heating sections among the plurality of heating sections based on the direction of the surface airflow.

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.

An ice resistant structure is provided which includes a self-supporting, structural platform, a retaining, protective layer and a subsurface anti-icing (AI) and/or de-icing (DI) layer. The retaining, protective layer is disposed over the self-supporting, structural platform. The subsurface anti-icing (AI) and/or de-icing (DI) layer is located between the self-supporting, structural platform and the retaining, protective layer. The subsurface Al and/or DI layer is a functional layer such that an Al and/or DI agent is released to a surface of the retaining protective layer by an activation mechanism responsive to a change in an environmental condition.

An ice resistant structure is provided which includes a self-supporting, structural platform, a retaining, protective layer and a subsurface anti-icing (AI) and/or de-icing (DI) layer. The retaining, protective layer is disposed over the self-supporting, structural platform. The subsurface anti-icing (AI) and/or de-icing (DI) layer is located between the self-supporting, structural platform and the retaining, protective layer. The subsurface Al and/or DI layer is a functional layer such that an Al and/or DI agent is released to a surface of the retaining protective layer by an activation mechanism responsive to a change in an environmental condition.

A method for testing water droplet shedding ability of a surface of an aircraft wing includes: blowing air toward a surface of a cylindrical member in an airflow direction perpendicular to an axial direction of the cylindrical member, the cylindrical member simulating the wing and having water-related surface characteristics that differ across a predetermined boundary position in a circumferential direction; supplying a water droplet to a portion of the surface of the cylindrical member on a leading edge side with respect to a flow of the air; and capturing an image of the water droplet that moves on the surface of the cylindrical member across the boundary position due to the flow of the air.

A method for testing water droplet shedding ability of a surface of an aircraft wing includes: blowing air toward a surface of a cylindrical member in an airflow direction perpendicular to an axial direction of the cylindrical member, the cylindrical member simulating the wing and having water-related surface characteristics that differ across a predetermined boundary position in a circumferential direction; supplying a water droplet to a portion of the surface of the cylindrical member on a leading edge side with respect to a flow of the air; and capturing an image of the water droplet that moves on the surface of the cylindrical member across the boundary position due to the flow of the air.

In order to provide a simplified inspection of an aircraft for the pilot, an aircraft inspection system is provided which includes at least one movable inspection unit, a position detection arrangement, and at least one data transfer interface. The at least one moveable inspection unit is moveable relative to an aircraft to be inspected. The at least one movable inspection unit includes at least one sensor for detecting a characteristic value, for verifying a characteristic and/or for determining a defect of an aircraft. The movable inspection unit is configured to generate monitoring data. When a defect or a characteristic value is detected, the position detection arrangement detects position data of the movable inspection unit in relation to the aircraft to be inspected, and assigns the position data to the monitoring data. The data transfer interface provides the position data with the assigned monitoring data as inspection data.

In order to provide a simplified inspection of an aircraft for the pilot, an aircraft inspection system is provided which includes at least one movable inspection unit, a position detection arrangement, and at least one data transfer interface. The at least one moveable inspection unit is moveable relative to an aircraft to be inspected. The at least one movable inspection unit includes at least one sensor for detecting a characteristic value, for verifying a characteristic and/or for determining a defect of an aircraft. The movable inspection unit is configured to generate monitoring data. When a defect or a characteristic value is detected, the position detection arrangement detects position data of the movable inspection unit in relation to the aircraft to be inspected, and assigns the position data to the monitoring data. The data transfer interface provides the position data with the assigned monitoring data as inspection data.