A total air temperature sensor can include a first airfoil having a heated first surface, a second airfoil having a second surface spaced from the first surface and defining a sensor chamber, a temperature sensor located within the chamber, and a sheath surrounding the temperature sensor.

An air data probe includes a body, a mount adjacent to the body, a primary low ice adhesion surface coating on a primary impact region of the air data probe, the primary impact region being positioned for direct impact with water drops, and a secondary low ice adhesion surface coating on a secondary impact region of the air data probe, the secondary impact region being positioned for indirect contact by water drops. The primary low ice adhesion surface coating has a different composition than the secondary low ice adhesion surface coating.

A probe system includes a heater and a control circuit. The heater includes a resistive heating element routed through the probe system. An operational voltage is provided to the resistive heating element to provide heating for the probe system. The control circuit is configured to provide the operational voltage and monitor a capacitance between the resistive heating element and a metallic sheath of the heater over time. The control circuit is further configured to determine a remaining useful life of the probe system based on the capacitance.

An air temperature sensor for use on an aircraft can include a housing defining an interior and having a trailing edge, a temperature sensor having a distal end and located within the interior, a support tube surrounding at least a portion the temperature sensor, an element shroud surrounding at least a portion of support tube, and a bushing isolating the trailing edge of the housing from the distal end of temperature sensor.

A total air temperature sensor can include a first airfoil having a heated first surface, a second airfoil having a second surface spaced from the first surface and defining a sensor chamber, a temperature sensor located within the chamber, and a sheath surrounding the temperature sensor.

A system for correcting an air temperature (AT) reading can include a water content sensor configured to measure a water content in an airflow and to output a water content signal indicative thereof, an AT sensor configured to measure an air temperature and output an AT signal indicative thereof, and a correction module operatively connected to the water content sensor and the AT sensor. The correction module can be configured to receive the water content signal and the AT signal and to correct the AT signal based on the water content to output a corrected AT signal.

A fluid sensing device includes an outer shell, a three-axis force and moment balance, a strut, and a centerbody. The outer shell has an inlet at a first end of the outer shell, an aft vent at an opposing second end of the outer shell, and an interior space connecting the inlet and the aft vent. The three-axis force and moment balance is positioned in the interior space of the outer shell. The strut is connected to the outer shell and the three-axis force and moment balance such that the strut supports the three-axis force and moment balance in the interior space. At least a portion of the centerbody is positioned in the interior space of the outer shell. The centerbody is connected to the three-axis force and moment balance such that the three-axis force and moment balance is configured to measure force, moment, and/or movement of the centerbody.

An air data probe includes a body, a mount adjacent to the body, a primary low ice adhesion surface coating on a primary impact region of the air data probe, the primary impact region being positioned for direct impact with water drops, and a secondary low ice adhesion surface coating on a secondary impact region of the air data probe, the secondary impact region being positioned for indirect contact by water drops. The primary low ice adhesion surface coating has a different composition than the secondary low ice adhesion surface coating.

An air data system for an aircraft includes a multi-function probe (MFP) and an inertial reference unit (IRU). The MFP is positioned to sense a pressure of airflow about an exterior of the aircraft. A first electronics channel of the MFP is electrically coupled to the IRU to generate air data parameter outputs based on the pressure sensed by the MFP and inertial data sensed by the IRU.

A total air temperature probe includes a housing including an inlet scoop, an outlet, a main airflow passage extending from the inlet scoop to the outlet, an exit that extends through the housing, and a total air temperature sensor flow passage and a sensor assembly positioned in the total air temperature sensor flow passage. The main airflow passage includes an upper inlet surface extending from the inlet scoop, a lower inlet surface opposite the upper inlet surface and extending from the inlet scoop, an upper outlet surface extending from the upper inlet surface to the outlet, and a lower outlet surface opposite the upper outlet surface and extending from a split point in the housing to the outlet. The total air temperature sensor flow passage branches off from the main airflow passage and extends to the exit. The upper outlet surface is consistently concave toward the outlet.