Aircraft control surface includes a span-wise extending spar having at least one aperture. A displacement guide is adjacent to the aperture. A span-wise extending airfoil is mounted to the spar and extends chord-wise between leading and trailing edges. A resiliently deformable airfoil top skin is mounted to the spar via a leaf spring. The top skin is bendable relative to the spar and extends chord-wise from the spar to a top skin rear edge. A resiliently deformable airfoil bottom skin is disposed beneath the top skin. Part of the bottom skin is displaceable chord-wise through the aperture and is guidable therethrough by the displacement guide. The bottom skin extends chord-wise from the spar to a bottom skin rear edge joined to the top skin rear edge to form the airfoil trailing edge. An actuator is connected to and configured to displace the bottom skin chord-wise to displace the trailing edge.
AIRFOIL WITH FLEXIBLE TRAILING EDGE
SCHAUFEL MIT FLEXIBLER HINTERKANTE
PROFIL AÉRODYNAMIQUE AVEC BORD DE FUITE FLEXIBLE
2024-01-10
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |
Divergent-Trailing-Edge Airfoil
NTRS | 1988
|Leading edge - Trailing edge airfoil interactions
AIAA | 1995
|