Framework wing box for a wing
View Patent ↗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.
1. An aircraft wing assembly comprising a wing box and a fuselage region of an aircraft, wherein the wing box comprises:
a framework comprising a plurality of junction elements and a plurality of tubular bar elements, the tubular bar elements being connected to each other at the end points with the corresponding junction elements;
an exterior shell forming a hollow space comprising the framework; and
an interior shell spaced apart from the exterior shell and enveloped by the exterior shell,
wherein the interior shell is connected to the junction elements;
wherein the exterior shell and the interior shell are connected to the fuselage region, such that a load is transferred from the exterior and interior shells to the fuselage region; and
wherein the interior shell extends only partially over the exterior shell.
2. The aircraft wing assembly of claim 1 , wherein the load is transferable in a straight line to a bottom region of the fuselage region by the framework.
3. A method for transferring forces from a wing box of an aircraft wing to a fuselage region of the aircraft, comprising:
providing an exterior shell and an interior shell at a distance from the exterior shell, wherein the interior shell extends only partially over the exterior shell and is enveloped by the exterior shell;
forming a hollow space with the exterior shell comprising a framework, the framework comprising a plurality of junction elements and a plurality of tubular bar elements, the tubular bar elements being connected to each other at the end points with the corresponding junction elements;
connecting the framework to the exterior shell and the interior shell, wherein the interior shell is connected to the junction elements;
connecting the exterior shell and the interior shell to the fuselage region;
absorbing a load from the exterior shell; and
transferring the load to the fuselage region by the exterior shell, the interior shell and the framework.
4. The method of claim 3 , further comprising transferring the load in a straight line to a bottom region of the fuselage with the framework.