A fuselage (3) for an aircraft (1) is described. The fuselage has a control element (20) with an integrated engine outlet (23). The control element (20) is integrated at a rear end (2) of the fuselage (3), so that the control element (20) terminates flush with an outer skin (4) of the fuselage in a circumferential direction of the fuselage (3). An outer wall (40) of the control element (20) surrounds the engine outlet (23) so that the engine outlet (23) is directed towards an open rear side (6) of the control element (20). The control element (20) is connected to the fuselage (3) such that the control element (20) jointly the engine outlet (23) is pivotable about a rotation axis (26) with respect to the fuselage (3). The rotation axis (26) runs transversely to a longitudinal direction (8) of the fuselage (3) and the control element (20) functions as a tailplane when pivoting about the rotation axis (26).
FUSELAGE FOR AN AIRCRAFT WITH FUSELAGE-INTEGRATED TAILPLANE
RUMPF FÜR EIN FLUGZEUG MIT RUMPFINTEGRIERTEM HÖHENLEITWERK
FUSELAGE D'UN AÉRONEF AVEC STABILISATEUR INTÉGRÉ DANS LE FUSELAGE
2025-01-08
Patent
Electronic Resource
English
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