A linear actuator driven flap mechanism for an aircraft wing is contained within a wing support and fairing of the aircraft wing. The rib frame of the flap mechanism is attached to the wingbox structure of the aircraft wing at a first and second point. The rib frame of the flap mechanism defines a width with a first and second web. A linear actuator and a motion linkage are positioned with the width between the first and second webs of the rib frame. The linear actuator is not mechanically driven rotary actuation or mechanically driven linear actuation. As a result of the compact construction, the flap mechanism can be employed in thinner, smaller aircraft wings being designed today.
Linear actuator driven flap mechanism
2025-03-18
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |