Fuselage for an aircraft with fuselage-integrated tailplane

A fuselage for an aircraft, the fuselage comprising:

• a shell surface;
• and
• a control element with an integrated engine outlet;
• wherein the control element is integrated at a rear end of the fuselage and is a rearward extension of the fuselage in a longitudinal direction of the fuselage, so that the control element terminates flush with an outer skin of the fuselage in a circumferential direction of the fuselage;
• wherein an outer wall of the control element surrounds the engine outlet, such that the engine outlet is directed towards an open rear side of the control element;
• wherein the fuselage transitions into the control element at a transition point, the fuselage and the control element having similar cross-sections at the transition point and, at the transition point, the width and height of the control element correspond to the width and height, respectively, of the fuselage;
• wherein the control element is connected to the fuselage such that the control element is pivotable together with the engine outlet about a rotation axis with respect to the fuselage;
• wherein the rotation axis runs transversely to the longitudinal direction of the fuselage and the control element functions as a tailplane when pivoting about the rotation axis;
• wherein the shell surface is static with respect to the fuselage and does not pivot about the rotation axis;
• wherein the control element is configured to be moved upwardly, from an initial state, to an upward state and moved downwardly, from the initial state, to a downward state;
• wherein the control element includes an upper control surface and a lower control surface;
• wherein, when the control element is moved to the upward state, the upper control surface is configured to slide under the shell surface and the lower control surface is covered by the shell surface;
• wherein, when the control element is moved to the downward state, the lower control surface is configured to slide under the shell surface and the upper control surface is covered by the shell surface;
• wherein the engine outlet has a convergent nozzle portion and a divergent nozzle portion arranged therebehind in the longitudinal direction;
• wherein the divergent nozzle portion has two control blades;
• and
• wherein adjusting of the two control blades of the divergent nozzle portion in the same direction generates a moment about a vertical axis of the aircraft resulting in a yaw movement of the aircraft.