An electrically-powered downlock actuation system for a landing gear that does not convert rotary motor output into linear motion during the actuation process, but instead uses the rotary motor (214) output to directly drive a locking mechanism (200) coupled to upper and lower landing gear braces (202,204). The electrically-powered downlock actuation system (200) may include an electric motor (214), a gearbox (216) (optional), a clutch (optional) and a fixed link (220) to replace a hydraulically powered downlock actuation system. Further, the electrically-powered downlock actuation system (200) may be controlled with motor control electronics that cooperate with one or more sensors arranged to detect a position of an output shaft.
Electrically powered downlock actuation system
Elektrisch angetriebenes Sicherungsbetätigungssystem
Système d'actionnement électrique de verrou
2021-03-10
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |