초록 ▼

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 tempe

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.

대표청구항 ▼

[ What is claimed is:] [1.] An aircraft sensor probe assembly comprising:an elongated probe element adapted to project outwardly from an aircraft along a projection axis and into an in-flight airflow stream, said probe element being mounted for rotational movement about said projection axis;a temper

[ What is claimed is:] [1.] An aircraft sensor probe assembly comprising:an elongated probe element adapted to project outwardly from an aircraft along a projection axis and into an in-flight airflow stream, said probe element being mounted for rotational movement about said projection axis;a temperature sensing chamber formed in said probe element said temperature sensing chamber having inlet and outlet airflow ports to allow a portion of the airflow stream to flow thereinto and therefrom, respectively; anda temperature sensor disposed in said temperature sensing chamber to sense the temperature of said airflow stream portion flowing into said temperature sensing chamber, whereinsaid inlet airflow port is aligned longitudinally with respect to said projection axis such that rotation of said probe element causes said inlet airflow port to be coincident with a stagnation line of an oncoming airstream. [15.] An aircraft probe assembly comprising:a hollow, generally conically shaped probe element having a pressure port and a temperature sensing port defined therein;a separator nested within said probe element and establishing a pressure chamber in fluid communication with said pressure port, and a temperature sensing chamber in fluid communication with said temperature sensing port, wherein said pressure chamber and said temperature sensing chamber are fluid-isolated from one another; anda temperature sensor disposed in said temperature sensing chamber. The aircraft probe assembly as in claim 15, wherein said pressure port and said temperature sensing port are elongate slots. The aircraft probe assembly as in claim 16, wherein said pressure port and said temperature sensing port are longitudinally aligned with one another. The aircraft probe assembly as in claim 15, 16 or 17, wherein said pressure port and said temperature sensing port are each aligned with a stagnation line on an exterior surface of said probe element. The aircraft probe assembly as in claim 15, wherein said temperature sensing chamber is located at an apical end of said elongate probe element.