Aircraft probe with integral air temperature sensor

Details Aircraft probe with integral air temperature sensor Aircraft probe with integral air temperature sensor

1998-10-20

2000-06-20

Bennett, G. Bradley

Thermal measuring and testing

Temperature measurement

With fluid flow deflector

374135, 374143, 73180, G01K 114, G01K 1302, G01K 1710, G01C 2100

Patent

active

060769637

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.

REFERENCES:
patent: 2588840 (1952-03-01), Howland
patent: 4152938 (1979-05-01), Danninger
patent: 4821566 (1989-04-01), Johnston et al.
patent: 5544526 (1996-08-01), Baltins et al.
patent: 5628565 (1997-05-01), Hagen et al.
patent: 5653538 (1997-08-01), Phillips
patent: 6012331 (2000-01-01), Menzies et al.

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