Wall component for an aircraft

摘要

The present disclosure relates to a wall component for an aircraft for forming an outer wall comprising at least one first wall element, at least one second wall element and at least one connecting device for connecting the first wall element to the second wall element. On wall regions that are to be directed towards each other, the first and the second wall element comprise connecting regions. Furthermore, a joint element is provided, which comprises a joint region with a joint region surface that is to be arranged towards the outside of the aircraft, wherein the joint region is designed to be received with a matching fit into a recess formed by the connecting regions of the wall elements, and wherein the joint region surface, when the joint element is inserted, is flush with the outer surfaces of the wall elements.

主权项

1. A wall component for an aircraft for forming an outer wall, comprising:
at least one first wall element including a composite fiber material and having a first outer wall region and a first connecting region, the first outer wall region provided with a first outer surface in order to form a first surface area of the outer wall, and the first connecting region arranged on an edge region of the first wall element and configured such that it is set back relative to the first outer surface; at least one second wall element having a second outer wall region and a second connecting region, the second outer wall region provided with a second outer surface in order to form a second surface area of the outer wall, the second connecting region arranged on an edge region of the second wall element and configured such that it is set back relative to the second outer surface; and at least one connecting device for connecting the first wall element to the second wall element, the at least one connecting device including a one-piece joint element with a joint region for connecting the first connecting region to the second connecting region, the one-piece joint element further comprising a flange extending into a fuselage orthogonal to the first and second wall element, wherein the flange is configured to support an interior structure, and wherein the first connecting region and second connecting region are designed for connecting the at least one first wall element and at least one second wall element to one another on the edge regions to be directed toward one another and set back relative to the outer surfaces that serve for forming the outer wall in such a way that a depression is created when the first wall element and the second wall element are arranged adjacent to one another such that their connecting regions are directed toward one another, and the joint region is accommodated in the depression in a fitted fashion such that an outer joint region surface of the joint region forms the outer wall of the aircraft at the joint between the first and the second wall element and is arranged flush with the first outer surface, as well as the second outer surface, when the joint region is inserted into the depression.