Abstract: A thermal ice protection system including a spray tube for spraying engine bleed air on an interior surface of an aircraft wing leading edge. The engine bleed air impinges simultaneously at multiple locations on the interior surface heats the aircraft leading edge so as to inhibit the formation of ice on the aircraft leading edge at the predetermined ice susceptible areas. The spray tube is particularly intended to be used to heat a wing slat leading edge skin/surface without using a nose beam or other internal structure to direct the flow of the engine bleed air.

Abstract: Disclosed is a temperature sensor for measuring a temperature of a reference material. The temperature sensor includes a thermocouple, spring, and spring housing. The thermocouple is configured to measure the temperature of the reference material. The spring is operably coupled to the thermocouple and the spring housing is configured to accommodate the spring and thermocouple within the spring housing. Additionally, the spring housing is configured to attach to the reference material and the spring applies a force on the thermocouple in a direction towards the reference material.

Abstract: Disclosed is a temperature sensor for measuring a temperature of a reference material. The temperature sensor includes a thermocouple, spring, and spring housing. The thermocouple is configured to measure the temperature of the reference material. The spring is operably coupled to the thermocouple and the spring housing is configured to accommodate the spring and thermocouple within the spring housing. Additionally, the spring housing is configured to attach to the reference material and the spring applies a force on the thermocouple in a direction towards the reference material.

Abstract: A method includes receiving a plurality of temperature measurements from temperature sensors of an aircraft. The method includes determining whether a first count of one or more first temperature metrics that are within a temperature range is greater than a first threshold. The one or more temperature metrics are derived from the plurality of temperature measurements. The method includes initiating generating an icing output signal when the first count is greater than or equal to the first threshold.

Abstract: A method is provided that includes a number of operations performed in real-time during operation of a vehicle. That is, the method may include detecting fog on an interior surface of the window using one or more sensors according to a process, and automatically activating a fog protection system to reduce or prevent fog on the interior surface of the window in an instance in which fog is detected according to the process. For each sensor, the process may include receiving a measurement from the sensor. And from the measurement, the process may include identifying or calculating a dew-point temperature in a compartment of the vehicle including the window to an exterior thereof, and detecting fog on the interior surface of the window in an instance in which the dew-point temperature is near, at, or above a surface temperature of the interior surface of the window.

Abstract: A method includes receiving a plurality of temperature measurements from temperature sensors of an aircraft. The method includes determining whether a first count of one or more first temperature metrics that are within a temperature range is greater than a first threshold. The one or more temperature metrics are derived from the plurality of temperature measurements. The method includes initiating generating an icing output signal when the first count is greater than or equal to the first threshold.

Abstract: In one aspect, methods of detecting ice formation on an aircraft are described herein. In some implementations, a method of detecting ice formation on an aircraft comprises disposing an ice detector on an exterior surface of the aircraft, the ice detector comprising a probe surface and a pyroelectric material layer disposed on at least a portion of the probe surface. The method further comprises generating a charge on a surface of the pyroelectric material layer of the ice detector to increase the local freezing point of water on the surface of the pyroelectric material layer.

Abstract: A method is provided that includes a number of operations performed in real-time during operation of a vehicle. That is, the method may include detecting fog on an interior surface of the window using one or more sensors according to a process, and automatically activating a fog protection system to reduce or prevent fog on the interior surface of the window in an instance in which fog is detected according to the process. For each sensor, the process may include receiving a measurement from the sensor. And from the measurement, the process may include identifying or calculating a dew-point temperature in a compartment of the vehicle including the window to an exterior thereof, and detecting fog on the interior surface of the window in an instance in which the dew-point temperature is near, at, or above a surface temperature of the interior surface of the window.

Abstract: A method is provided that includes a number of operations performed in real-time during flight of the aircraft. That is, the method may include monitoring a continuous electrical signal output by a sensor on a surface of the aircraft, where a magnitude of the electrical signal may be related to an amount of ice buildup. The method may include calculating a liquid water content (LWC) value as a function of a rate of change of the electrical signal, and iteratively calculating a total water exposure (TWE) value as a function of the LWC value. The TWE value may represent a total water exposure of the aircraft from a time of an initial event, and may be calculated as a running total over a plurality of iterations. And the method may include performing a remedial or alert action in an instance in which the TWE value reaches a TWE threshold.

Abstract: In one aspect, methods of detecting ice formation on an aircraft are described herein. In some implementations, a method of detecting ice formation on an aircraft comprises disposing an ice detector on an exterior surface of the aircraft, the ice detector comprising a probe surface and a pyroelectric material layer disposed on at least a portion of the probe surface. The method further comprises generating a charge on a surface of the pyroelectric material layer of the ice detector to increase the local freezing point of water on the surface of the pyroelectric material layer.

Abstract: Methods and systems for providing secondary power to aircraft systems. In one embodiment, an aircraft system architecture for providing power to an environmental control system includes an electric generator operably coupled to a jet engine. The jet engine can be configured to provide propulsive thrust to the aircraft, and the electric generator can be configured to receive shaft power from the jet engine. The environmental control system can be configured to provide outside air to a passenger cabin of the aircraft in the absence of bleed air from the jet engine.

Abstract: Methods and systems for providing secondary power to aircraft systems. In one embodiment, an aircraft system architecture for providing power to an environmental control system includes an electric generator operably coupled to a jet engine. The jet engine can be configured to provide propulsive thrust to the aircraft, and the electric generator can be configured to receive shaft power from the jet engine. The environmental control system can be configured to provide outside air to a passenger cabin of the aircraft in the absence of bleed air from the jet engine.

Abstract: Methods and systems for providing secondary power to aircraft systems. In one embodiment, an aircraft system architecture for providing power to an environmental control system includes an electric generator operably coupled to a jet engine. The jet engine can be configured to provide propulsive thrust to the aircraft, and the electric generator can be configured to receive shaft power from the jet engine. The environmental control system can be configured to provide outside air to a passenger cabin of the aircraft in the absence of bleed air from the jet engine.

Abstract: Methods and systems for providing secondary power to aircraft systems. In one embodiment, an aircraft system architecture for providing power to an environmental control system includes an electric generator operably coupled to a jet engine. The jet engine can be configured to provide propulsive thrust to the aircraft, and the electric generator can be configured to receive shaft power from the jet engine. The environmental control system can be configured to provide outside air to a passenger cabin of the aircraft in the absence of bleed air from the jet engine.