Abstract: A flap arrangement includes a basic body, a hinge arrangement, and a flap that by the hinge arrangement is movably held on the basic body. The hinge arrangement includes at least three bearing points spaced apart from each other and arranged on a shared hinge line, wherein two bearing points are rigidly connected to the basic body and to the flap, and wherein the remaining bearing points in each case allow local movement between the basic body and the flap in at least one first spatial direction perpendicularly to the hinge line. Thus, load-induced constraint forces between the basic body and the control surface can be prevented.

Abstract: A rudder system for an aircraft includes a center box, a rudder and actuators, wherein the rudder is pivoted around a hinge line relative to the center box. The actuators are arranged at an acute angle relative to the hinge line, and connected with at least one pivoted pivot lever, wherein the pivot lever is fastened to the rudder by way of a first push rod. This provides considerably more installation space in a vertical stabilizer of an aircraft for a center box, so that the latter can comprise a distinctly smaller wall thickness than usual in prior art to absorb air load-induced torsion and bending stresses.

Abstract: A wing box for an aircraft wing with a framework and a first shell. The framework is connected to the first shell such that a load acting on the first shell can be transferred by the framework.

Abstract: A rudder system for an aircraft includes a centre box, a rudder and actuators, wherein the rudder is pivoted around a hinge line relative to the centre box. The actuators are arranged at an acute angle relative to the hinge line, and connected with at least one pivoted pivot lever, wherein the pivot lever is fastened to the rudder by way of a first push rod. This provides considerably more installation space in a vertical stabilizer of an aircraft for a centre box, so that the latter can comprise a distinctly smaller wall thickness than usual in prior art to absorb air load-induced torsion and bending stresses.

Abstract: A flap arrangement includes a basic body, a hinge arrangement, and a flap that by the hinge arrangement is movably held on the basic body. The hinge arrangement includes at least three bearing points spaced apart from each other and arranged on a shared hinge line, wherein two bearing points are rigidly connected to the basic body and to the flap, and wherein the remaining bearing points in each case allow local movement between the basic body and the flap in at least one first spatial direction perpendicularly to the hinge line. Thus, load-induced constraint forces between the basic body and the control surface can be prevented.

Abstract: A support structure for an aircraft, includes one or several bar elements and one or several junction elements. At least one bar element includes a transition region which can be made to engage at least one junction element. When the transition region of the bar element engages at least one junction element, centric force transmission takes place between the bar element and the junction element.

Abstract: An attachment system for attaching a tail unit to an attachment surface of an aircraft is disclosed. An attachment surface may be a fuselage, for example. In an arrangement, the attachment system includes a mounting with a first bearing surface that is capable of resting against the tail unit, and a second bearing surface that is capable of resting against the attachment surface. The first bearing surface and the second bearing surface, of which there is at least one, include a common line of contact. In the arrangement, the planes of the first bearing surface and of the second bearing surface are at an angle that differs from 0° and 180°.

Abstract: A support structure for an aircraft, includes one or several bar elements and one or several junction elements. At least one bar element includes a transition region which can be made to engage at least one junction element. When the transition region of the bar element engages at least one junction element, centric force transmission takes place between the bar element and the junction element.

Abstract: A wing box for an aircraft wing with a framework and a first shell. The framework is connected to the first shell such that a load acting on the first shell can be transferred by the framework.

Abstract: An attachment system for attaching a tail unit to an attachment surface of an aircraft is disclosed. An attachment surface may be a fuselage, for example. In an arrangement, the attachment system includes a mounting with a first bearing surface that is capable of resting against the tail unit, and a second bearing surface that is capable of resting against the attachment surface. The first bearing surface and the second bearing surface, of which there is at least one, include a common line of contact. In the arrangement, the planes of the first bearing surface and of the second bearing surface are at an angle that differs from 0° and 180°.

Abstract: The present invention relates to a center box (5) for an aircraft wing, as well as to an aircraft comprising such a center box (5). The center box (5) essentially comprises two lateral surfaces (6), which in turn essentially comprise two internal and external skins (2, 1) that are arranged so as to be spaced apart from each other. In order to provide adequate stability to the lateral surface (6), the internal skin (2) and the external skin (1) are interconnected by way of a multitude of profiles (3).