Abstract: Aircraft probe assemblies integrally include a total airstream temperature sensor. Preferred embodiments include at least one pressure sensing port 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 having airflow inlet and outlet 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.

Abstract: Improved multifunction probe designs include circumferentially separated pairs of sensing ports which may respectively be dedicated to angle of attack functionality and air data pressure sensing functionality. In one preferred embodiment, a multifunction aircraft probe is provided with a rotatable probe element which is adapted to project outwardly from an aircraft with which it is operatively mated. The probe element is provided with a centrally located (i.e., in substantial alignment with the probe's stagnation line) dynamic pressure sensing port, and outer and inner pairs of pneumatic sensing ports which are symmetrically circumferentially separated from one another and from the dynamic pressure sensing port. Most preferably, each of the outer pneumatic sensing ports is circumferentially spaced from the central dynamic pressure sensing port by a first angle (e.g., substantially 90.degree.