Optimized torsion box for an aircraft

Abstract

The invention provides an aircraft lifting surface with a torsion box (13) of a composite material comprising an upper skin (21), a lower skin (23), a front spar (18), a rear spar (20), one or more intermediate spars (19, 19') and a plurality of transverse ribs (25, 25', ...) arranged between the rear spar (20) and its adjacent intermediate spar (19') and / or between the front spar (18) and the adjacent intermediate spar (19) for improving its structural behavior. The invention also provides a manufacturing method of said torsion box.

Description

technical field [0001] The invention relates to a torsion box of an aircraft, in particular to a torsion box of a lifting surface. Background technique [0002] The structure of an aircraft's lifting surface usually includes a torsion box. For example, an aircraft empennage (horizontal or vertical) is usually constructed from a leading edge, a torsion box and a trailing edge with control surfaces (flaps, elevator, rudder, etc.). [0003] The torsion box is the main structure responsible for supporting all the loads involved (aerodynamic, fuel, dynamic, etc.) and consists of several structural elements. [0004] Composites with an organic matrix and continuous fibers, especially carbon fiber reinforced plastics (CFRP), are today widely used in the aerospace industry in a wide variety of structural elements. In particular, all elements that make up the torsion boxes of aircraft empennages and other lifting surfaces can be manufactured using carbon fiber composites. [0005]...

AI Technical Summary

Problems solved by technology

The torsion box manufactured using the described method is expensive because the steps will be performed individually for each structural element

Furthermore, the costs associated with the assembly of the torsion boxes are high due to the long length and the high complexity of the tasks required to install and fit together all the structural elements

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