AIRCRAFT PROBE WITH INTEGRAL AIR TEMPERATURE SENSOR

摘要

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.