A probe system includes a heater and a control circuit. The heater includes a resistive heating element routed through the probe. An operational current is provided to the resistive heating element to provide heating for the probe. The control circuit is configured to monitor the operational current over time and determine a half-life estimate of the resistive heating element based upon an exponential function of the operational current over time.

A total air temperature sensor includes a nose having an airfoil cross section with a leading edge and trailing edge, a sensor housing spaced from and downstream of the nose defining a stagnation chamber with at least one inlet, and a temperature sensor positioned within the sensor housing.

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 total air temperature sensor can include an airfoil portion. The airfoil portion can an inlet and an outlet through which a diverted airflow path can flow. The total air temperature sensor can include a temperature sensor located within a housing defining the total air temperature sensor and a sheath surrounding the temperature sensor. The temperature sensor can be configured to take a total temperature of the diverted airflow path.

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 detector includes a scoop portion. The scoop portion includes a top surface extending continuously from a forward tip to an aft end, a bottom surface opposite from the top surface, and a receiving portion therebetween. The bottom surface includes an aperture. The top surface includes a detent formed therein opposite from the aperture across the receiving portion. The detent is configured and adapted to receive at least a portion of a sensor. A method includes additively manufacturing a scoop portion and brazing a strut portion to the scoop portion. The scoop portion includes an upper surface, a lower surface, and a receiving portion therebetween.

An air data probe includes a probe body including a probe wall. The probe body is formed from a first material by direct energy metal deposition. An insert is positioned in the probe wall. The insert is formed from a second material different from the first material. The insert is encapsulated in the probe wall via the direct energy metal deposition. A method of forming an air data probe includes forming one or more thermally conductive inserts, and encapsulating the one or more inserts into a wall of an air data probe via direct energy metal deposition. The air data probe is formed from a first material and the one or more inserts are formed from a second material different from the first material.

A total air temperature probe includes a housing defining a total air temperature sensor flow passage and a sensor assembly positioned within the total air temperature sensor flow passage. The sensor assembly includes an element flow tube, and a sensing element within the element flow tube. An upper portion of the element flow tube is an entrance including a plurality of protrusions that extend in an upstream direction.

A total air temperature probe includes a probe head having an airflow inlet, a main airflow outlet, a main probe head wall extending from the airflow inlet to the main airflow outlet, and a flow separation bend wall positioned between the airflow inlet and the main airflow outlet. The flow separation bend wall is opposite the main probe head wall across a primary flow passage defined through the probe head from the airflow inlet to the main airflow outlet. A flow separation trip feature is defined on an interior surface of the main probe head wall for tripping a boundary layer flow separation in flow in the primary flow passage, e.g., for reduction of deicing heater error.

A system includes a device having a first surface configured to be exposed to airflow about an exterior of an aircraft, the device including a first self-compensating heater configured to heat the first surface, a first current monitor configured to sense a first measurement value representing electrical current flow through the first self-compensating heater, one or more processors, and computer-readable memory encoded with instructions that, when executed by the one or more processors, cause the system to receive aircraft flight condition data and produce an icing condition signal based upon the first measurement value and the aircraft flight condition data.