A landing gear system includes a landing gear collar and a strut assembly supported by the landing gear collar. The strut assembly includes a piston that is adjustable between a fully extended position and a fully compress position. The landing gear system further includes a rotary encoder and a controller. The rotary encoder rotates in response adjusting the piston and to outputs a data value in response to its rotation. The controller is in signal communication with the rotary encoder and determines a stroke of the piston based on the data value output from the rotary encoder.
CONFIGURABLE ROTARY ENCODER INCLUDING TWO POINT INFLIGHT AUTO CALIBRATION AND ERROR ADJUSTMENT
KONFIGURIERBARER DREHGEBER MIT AUTOMATISCHER ZWEIPUNKTKALIBRIERUNG UND FEHLERANPASSUNG WÄHREND DES FLUGS
ENCODEUR ROTATIF CONFIGURABLE COMPRENANT UN ÉTALONNAGE AUTOMATIQUE ET UN RÉGLAGE D'ERREUR EN VOL À DEUX POINTS
2024-08-07
Patent
Electronic Resource
English
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