Aircraft shock strut having a fluid level monitor

Details Aircraft shock strut having a fluid level monitor Aircraft shock strut having a fluid level monitor

B - Operations, Transporting

64

C

B64C 25/58 (2006.01) F16F 9/32 (2006.01) G01F 23/292 (2006.01)

Patent

CA 2500458

A system for monitoring a liquid level in an aircraft shock strut (10) includes a cylinder (32) having an internal chamber (42) sealed by a piston telescopically movable within the cylinder. The chamber contains a gas and a liquid, and a sensor assembly (35) is provided for monitoring a condition of a level of the liquid in the chamber. The sensor assembly includes at least one probe (80, 82) within the chamber, and a fitting assembly (72) allows one or more leads from the probe to pass through the wall of the strut while maintaining pressure in the chamber. The fitting assembly includes a plug molded to the one or more leads extending from the probe. The fitting assembly also includes a retainer for holding the plug in sealed relationship with a through passage in the strut.

La présente invention a trait à un système pour le contrôle d'un niveau de liquide dans une jambe à amortisseur d'aéronef (10) comportant un vérin (32) comprenant une chambre interne (42) obturée par un piston à déplacement télescopique au sein du vérin. La chambre contient un gaz et un liquide, et un ensemble capteur (35) destiné au contrôle d'un état du niveau du liquide dans la chambre. L'ensemble capteur comprend au moins une sonde (80, 82) au sein de la chambre, et un ensemble de raccordement (72) permet le passage d'un ou des cordons depuis la sonde à travers la paroi de la jambe tout en maintenant la pression dans la chambre. L'ensemble de raccordement comprend un tampon moulé à l'un ou aux cordons s'étendant à partir de la sonde. L'ensemble de raccordement comprend également un élément de retenue pour le maintien du tampon en relation étanche avec un passage traversant dans la jambe.

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