A total air temperature probe positionable on a surface of an aircraft for measuring total air temperature includes an inlet scoop which receives airflow from free stream airflow moving toward the inlet scoop from a first direction. A first portion of the airflow entering the inlet scoop exits the probe through a main exit channel. A second portion of the airflow enters a TAT sensor flow passage, which extends longitudinally along an axis. This axis is oriented to form an angle of less than 90 degrees with the first direction from which the free stream airflow moves toward the inlet scoop. A sensor assembly extends longitudinally in the sensor flow passage and measures a total air temperature of airflow through the sensor flow passage. By increasing the angle through which the internal air turns, better inertial extraction of ice and water particles is realized. As a result, sensor clogging from accreted ice is significantly reduced. A second improvement is achieved by repositioning the sensor element to be more in-line with the internal air flow direction. This helps lower DHE by minimizing heated boundary layer spillage onto the sensing element.

Total air temperature probe providing improved anti-icing performance and reduced deicing heater error

An air data sensing probe adapted for mounting to an aerodynamically-shaped airfoil or strut attached to an air vehicle. An inlet port located near the leading edge of the strut admits fluid, to a first cavity and then, in turn, to a second cavity, so that the total temperature of the fluid may be measured and a signal related thereto conveyed to suitable flight control gear. A first exhaust port located generally opposite the inlet port allows entrained particles to exit the probe and boundary layer fluid evacuation apertures formed through the strut across the interface between the two cavities permit only a substantially particle-free core sample of fluid on the temperature sensing element. The secondary cavity couples to the primary cavity at an angle so that inertial separation of entrained particles results. In a second embodiment, the air data sensing probe connects to a barrel-shaped probe head so that multiple parameters related to the fluid can be measured, such as total pressure, Pt, static pressure, Ps, and total temperature, Tt, of a fluid flowing relative to the air vehicle as well as angle-of-attack (AOA) of the air vehicle relative to the fluid.

Integral airfoil total temperature sensor

A total air temperature sensor probe samples the air stream surrounding an aircraft in flight, and includes a duct carrying a fluid flow a portion of which is diverted to a primary chamber mounting a total air temperature sensor. A secondary chamber has a secondary sensor for sensing a different property of a sampled air stream. The secondary chamber is open to receive air flow from passageways in the total air temperature probe.

Total air temperature probe providing a secondary sensor measurement chamber

Aircraft probe assemblies integrally include a total airstream temperature sensor (52). Preferred embodiments include at least one pressure sensing port (20) and a temperature sensing port which are in fluid communication with a pressure sensing chamber and a temperature sensing chamber, respectively. A temperature sensor may thus be disposed in the temperature sensing chamber so as to sense the temperature of the in-flight air flow. The temperature sensor is most preferably shielded thermally from the probe element. Specifically, the temperature sensor is most preferably coaxially surrounded by a generally cylindrical thermal shield structure (60) having airflow inlet (66a) and outlet (66b) apertures. The thermal shield thereby prevents the temperature of the probe element (which may be heated by an integral electrical resistance heater during potential in-flight icing conditions) from affecting the airflow temperature data obtained by the temperature sensor.

Aircraft probe with integral air temperature sensor

The invention concerns a probe (S) for measuring physical parameters of a fluid flow generally directed rearwards of the probe, the probe comprising a structure ( 10, 20 ) bearing at least a sensor (C). The invention is characterised in that said structure comprises a part ( 20 ) whereof a leading edge ( 22 ) extends generally frontwards of the sensor and has a shape adapted to generate a vortex, and the sensor extends in the axial region of said vortex.

Probed for measuring physical parameters of a fluid flow

Air data measurement apparatus for use on an aircraft, comprises a housing (1) open at both ends (2, 3) and divided into two chambers (8, 9) by a transverse wall (7). The leading end chamber (8) contains a total pressure sensor (11) and the trailing end chamber (9) contains a total temperature sensor assembly (15) whereby the apparatus functions to measure total temperature and pressure at a common point on an aircraft.

James Stewart Johnston

Papers

Air data measurement apparatus