초록

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.

대표청구항 ▼

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

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; andan 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; andwherein 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; andtransferring 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.