An aircraft assembly (20) includes an aircraft control surface (24) having a first skin (50), a second skin (52) and a support structure laterally between and connected to the first skin (50) and the second skin (52). The support structure includes a spar (60C), a first stiffener and a second stiffener. The spar extends spanwise within the aircraft control surface (24). The first stiffener extends longitudinally within the aircraft control surface to the spar. The second stiffener extends longitudinally within the aircraft control surface (24) to the spar (60C). An actuator receptacle projects longitudinally into the aircraft control surface (24) from a base (42) of the aircraft control surface (24) to the spar. The actuator receptacle extends spanwise within the aircraft control surface (24) between the first stiffener and the second stiffener.
AIRCRAFT CONTROL SURFACE WITH LINEAR ACTUATOR
FLUGZEUGSTEUERFLÄCHE MIT LINEARANTRIEB
GOUVERNE D'AÉRONEF À ACTIONNEUR LINÉAIRE
2023-08-16
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |