A droop panel linkage for aircraft includes a lever arm, a main lever, a main tube and at least one drive strut. The lever arm is pivotally attached at a first end to a flap and is pivotally connected at a second end to a first end of the main lever. A second end of the main lever is provided with a first engagement element for engaging with a second engagement element incorporated into or associated with the main tube. The main tube is pivotally connected to a proximal end of the drive strut. A distal end of the drive strut is pivotally attached to the droop panel.
DROOP PANEL LINKAGE
VERBINDUNG FÜR DACHSCHRÄGEPLATTEN
DISPOSITIF DE LIAISON À PANNEAU BASCULANT
2017-09-13
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |
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