Structural component and fuselage of an aircraft or spacecraft

Abstract

The invention relates to a load-bearing component (10) for strengthening the skin of an aircraft or spacecraft, such as a stringer or frame, wherein said component is designed as a closed profile (hollow profile) (3) such that a system medium (M) can be conducted through the structural component. To this end, the hollow profile (3) serves as load-bearing component.

Description

technical field [0001] The invention relates to structural elements of aircraft or spacecraft and fuselages having such structural elements. Background technique [0002] An important aspect in aircraft construction is the constant effort to save weight. This is achieved on the one hand by the use of particularly light materials, such as CFK materials, and on the other hand by the use of a basic structure which achieves greater flight safety or robustness at a lower weight. [0003] The basic structure of the fuselage in modern transport aircraft is therefore formed by the skin and the stringers and bulkheads for reinforcing or stiffening the skin. Furthermore, the stringers generally extend in the longitudinal direction of the aircraft fuselage and the bulkheads extend in the direction of rotation along the inner circumference of the skin. These structural elements form the primary structure of the aircraft into which secondary structures such as transmissions, equipment,...

AI Technical Summary

Problems solved by technology

[0004] Reducing the number of primary structures such as stringers and bulkheads leads to weight savings, but this imposes a burden on stability and thus flight safety

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