Assemblies having a first structure (400), a second structure (402) movable relative to the first structure, and an actuator system (404) arranged therebetween and configured to control relative movement therebetween. The actuator system includes a drive shaft (410), a first element (406) configured to be driven in a first direction, and a second element (408) configured to be driven in a second direction. A spar (420) is fixedly connected to the first structure and a spar connection pivotably connects the first element to the spar at a fixed coupler. The drive shaft, the first element, and the second element are housed within the second structure. Rotation of the second element causes a translation motion of the drive shaft away from the first structure and rotation of the first element about the fixed coupler such that the second structure is translated and rotated relative to the first structure.
AIRCRAFT CONTROL SURFACE ACTUATION MECHANISM
BETÄTIGUNGSMECHANISMUS FÜR FLUGZEUGSTEUERFLÄCHEN
MÉCANISME D'ACTIONNEMENT DE SURFACE DE COMMANDE D'AÉRONEF
2023-06-21
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |
Aircraft control surface actuation systems and methods
Europäisches Patentamt | 2019
|