Apparatus and associated methods relate to determining, based on a spatial extent of ice accretion, a maximum size of super-cooled droplets contained in an atmosphere and/or if an atmosphere contains super-cooled water droplets that equal and/or exceed a predetermined size. A testing region on an exterior surface of an aircraft is monitored for ice accretion by an ice detector. A boundary calculator determines a specific location to be tested within the testing region. The determined specific location corresponds to a calculated boundary that separates an ice-accretion region from an ice-free region if the atmosphere contains super-cooled water droplets of no larger than the predetermined size. If the ice detector detects ice accretion at the determined specific location, an alert is generated. The alert can advantageously inform a pilot of the aircraft that the atmosphere contains super-cooled water droplets that equal or exceed the predetermined size.

Apparatus and associated methods relate to determining, based on a spatial extent of ice accretion, a maximum size of super-cooled droplets contained in an atmosphere and/or if an atmosphere contains super-cooled water droplets that equal and/or exceed a predetermined size. A testing region on an exterior surface of an aircraft is monitored for ice accretion by an ice detector. A boundary calculator determines a specific location to be tested within the testing region. The determined specific location corresponds to a calculated boundary that separates an ice-accretion region from an ice-free region if the atmosphere contains super-cooled water droplets of no larger than the predetermined size. If the ice detector detects ice accretion at the determined specific location, an alert is generated. The alert can advantageously inform a pilot of the aircraft that the atmosphere contains super-cooled water droplets that equal or exceed the predetermined size.

A Light Detecting and Ranging (LIDAR) based system detecting and quantifying ice accretions and shedding on an aircraft. This system can be used to detect ice, operate ice protection systems, and satisfy aircraft icing certification requirements. This system can also be used to determine the shape, thickness, type, and location of the ice accretions.

A Light Detecting and Ranging (LIDAR) based system detecting and quantifying ice accretions and shedding on an aircraft. This system can be used to detect ice, operate ice protection systems, and satisfy aircraft icing certification requirements. This system can also be used to determine the shape, thickness, type, and location of the ice accretions.

A sensor for detecting the level of accumulation of a material along an axis in a fluid environment, the sensor comprising (a) an optically transparent body having a third refractive index and an exposed surface defining a length extending at least partially in the direction of the axis; (b) at least one light delivery source for delivering light to the body such that the light is distributed along the length of the exposed surface; and at least one light receiver for receiving reflected light from the length of the exposed surface, wherein the amount of the reflected light depends on the level of the material accumulated along the length of the exposed surface

A method of monitoring for the in-flight accretion of matter involves an electric field sensor applying a time-varying electric field to an engine surface of an aircraft while the aircraft is in flight. The electric field sensor is thermally-coupled and thermally-matched to the engine surface. A sensor monitor receives, in substantially real-time from the electric field sensor, at least one measurement set that includes a measurement of a phase and a magnitude of a current detected by the electric field sensor and resulting from the time-varying electric field. The sensor monitor generates an assessment, in substantially real-time, of an instantaneous accumulation of matter on the engine surface from the at least one measurement set. The sensor monitor activates an alarm upon the assessment indicating an accumulation of matter on the engine surface.

A method of monitoring for the in-flight accretion of matter involves an electric field sensor applying a time-varying electric field to an engine surface of an aircraft while the aircraft is in flight. The electric field sensor is thermally-coupled and thermally-matched to the engine surface. A sensor monitor receives, in substantially real-time from the electric field sensor, at least one measurement set that includes a measurement of a phase and a magnitude of a current detected by the electric field sensor and resulting from the time-varying electric field. The sensor monitor generates an assessment, in substantially real-time, of an instantaneous accumulation of matter on the engine surface from the at least one measurement set. The sensor monitor activates an alarm upon the assessment indicating an accumulation of matter on the engine surface.

Methods, systems, and devices are disclosed for implementing an exemplary immersion mode ice spectrometer. In order to increase sample throughput and improve accuracy of Ice Nucleating Particle (INP) freezing temperature measurement, the exemplary immersion mode ice spectrometer both increases sample cooling rates and monitors changes in optical properties of water droplets during freezing.

Methods, systems, and devices are disclosed for implementing an exemplary immersion mode ice spectrometer. In order to increase sample throughput and improve accuracy of Ice Nucleating Particle (INP) freezing temperature measurement, the exemplary immersion mode ice spectrometer both increases sample cooling rates and monitors changes in optical properties of water droplets during freezing.

Methods and systems are described for a moisture and icing detection system for an aircraft with an exterior component. The moisture and icing detection system includes a flexible sensor film comprising a water sensor and temperature sensor for application to an exterior surface of the exterior component. The moisture and icing detection system also includes a sensor head in electric communication with water sensor and temperature sensor of the flexible sensor film that generates an icing condition warning if the water sensor indicates the presence of water or ice on the flight surface and the temperature sensor indicates temperatures less than the freezing temperature of water. The icing condition warning may then be acted upon through a control action initiated by the moisture and icing and detection system.