Rumpf für ein Flugzeug mit Rumpfintegriertem Höhenleitwerk

Details

Veröffentlichungs-Nr.

EP4180332

Aktenzeichen

EP21207682

Anmeldetag

11. November 2021

Veröffentlichung

8. Januar 2025

Erteilung

8. Januar 2025

Rechtsraum

EP

IPC

B64D27/20B64D33/04B64D29/06B64C15/02B64C1/16F02K1/00B64C15/12

Abstract

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).

Anmelder

Firma

Airbus Defence and Space GmbH

Land

🇩🇪 Deutschland

Fachgebiete