Actuator assemblies and methods of moving a control surface (50) of an aircraft utilizing the same are disclosed herein. The actuator assemblies (100) include a base structure (110) and an actuated arm (120) that is pivotally coupled to the base structure (110). The actuator assemblies (100) also include a drive assembly (130) that is operatively attached to the base structure (110) and includes an output shaft (132). The actuator assemblies (100) further include a linear actuator (140) that includes an actuator shaft (150) and an actuated body (160). The actuator shaft (150) is coupled to and configured to rotate with the output shaft (132) about an actuator shaft axis of rotation (152). The actuator assemblies (100) also include a linkage (180) that is pivotally coupled to the actuated arm (120). In addition, the linkage (180) is operatively attached to the actuated body (160) via a joint (170). The joint (170) defines a plurality of joint axes (172) of rotation that are spaced apart from the actuator shaft axis of rotation (152) of the actuator shaft (150).
ACTUATOR ASSEMBLIES FOR CONTROL SURFACES OF AN AIRCRAFT AND METHOD OF UTILIZING THE SAME
AKTUATORANORDNUNGEN FÜR STEUERFLÄCHEN EINES FLUGZEUGS UND VERFAHREN ZUR VERWENDUNG DAVON
ENSEMBLES ACTIONNEURS POUR DES SURFACES DE COMMANDE D'UN AÉRONEF ET PROCÉDÉ D'UTILISATION DE CEUX-CI
2019-07-10
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |
European Patent Office | 2020
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