In some applications, aircraft air data probes are heated to prevent rain, ice, or other moisture from attaching to the air data probe. The body of the air data probe and the components positioned within the body of the air data probe can be constructed from differing materials, resulting in differing coefficient of thermal expansions for each component. Retention features are added to a housing to prevent an epoxy potting from expanding outside its intended region and preventing damage to the electronic components within the housing.

In some applications, aircraft air data probes are heated to prevent rain, ice, or other moisture from attaching to the air data probe, ensuring proper functionality of the air data probe. But the elevated temperatures can have negative effects on the electronic components positioned within the air data probe. Therefore, thermal isolating features are added to a housing to thermally isolate the heated parts of the air data probe from the electronic components within the air data probe, which are required to stay relatively cool for proper functioning.

An air temperature sensor with a housing having a skin with a first and second portion, a temperature sensor having at least a portion extending through the housing, a set of fluid passageways defined within an interior of the housing, and a tube to receive bleed air from an aircraft engine located within the interior and to allow hot bleed air into the set of fluid passageways.

Sensor assemblies and methods of de-icing or preventing ice formation are provided. Compressed air may be supplied to a vortex tube. The vortex tube may separate the compressed air into a first stream and a second stream, the first stream hotter than the second stream. A sensor body may be warmed by the first stream, and the second stream may be directed away from the sensor body.

A probe includes a housing defining a flow passage for a first fluid and having an entrance port and an exit port, a sensor configured to sense a parameter of the first fluid and positioned within the flow passage, and a hoop ejector connected externally to the housing such that a channel of the hoop ejector surrounds the exit port. The hoop ejector has a plurality of holes configured to port a second fluid from the channel such that the first fluid is aspirated from the flow passage and out through the exit port.

A total air temperature sensor includes a probe head, a strut, and a turbulence inducing surface. The probe head has an airflow inlet and an airflow outlet. The strut defines a leading edge and an opposed trailing edge extending along a longitudinal axis, and connects between the probe head and an opposed probe mount. The turbulence inducing surface is defined in the strut aft the leading edge. The turbulence inducing surface is configured to trip a fluid boundary layer passing over the strut to transition from laminar to turbulent for moving flow separation toward the trailing edge to reduce acoustic noise emission from the total air 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 fluid sensing device includes an outer body having a fore side, an aft side, and an interior space, the outer body including a fluid inlet disposed at the fore side; an inner body extending at least partially out of the fluid inlet of the outer body along a longitudinal axis; one or more vents disposed aft of the fluid inlet to allow passage of fluid through the fluid sensing device; and at least one load sensor coupled to the inner body to measure a fluid drag force on the inner body, wherein the inner body is configured to induce the Coanda effect in at least a portion of a fluid contacting the inner body at an angle transverse to a longitudinal axis of the inner body.

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 system for detecting the presence of ice in a total-air-temperature probe with which an aircraft is equipped monitors the slope of total-air-temperature measurements carried out by the total-air-temperature probe, and monitors the slope of a temperature differential, which is the difference between a static-air-temperature value and a temperature value according to the ISA model, determined depending on the altitude of the aircraft. The presence of ice in the total-air-temperature probe is detected when the total air temperature measured by the total-air-temperature probe exhibits a positive slope higher than a first predefined positive threshold and when in addition the temperature differential simultaneously exhibits a positive slope higher than a second predefined positive threshold. Thus, the detection of the presence of ice is possible whatever the flight phase of the aircraft.