Structural component and method for producing a structural component

An aircraft or spacecraft comprising a structural component, the structural component comprising a planar web segmented into stiffening sections,

• wherein the structural component is a frame element or a stringer element and is integrally formed therewith,
• wherein the stiffening sections are mutually co-planar,
• wherein at least a first stiffening section of the stiffening sections is configured as a rigid mesh section,
• wherein at least a second stiffening section of the stiffening sections is configured as a solid section,
• wherein a plurality of solid sections are connected with each other to form a stiffening framework, and
• wherein the plurality of solid sections of the stiffening framework surround a plurality of rigid mesh sections.

A method for forming an aircraft structural component for reinforcing a fuselage of an aircraft or spacecraft, the structural component being a frame element or a stringer element comprising a planar web segmented into stiffening sections, which are each mutually co-planar, at least a first stiffening section of the stiffening sections being configured as a rigid mesh section, at least a second stiffening section of the stiffening sections being configured as a solid section, a plurality of solid sections being connected with each other to form a stiffening framework, the plurality of solid sections of the stiffening framework surrounding a plurality of rigid mesh sections, the method comprising:

• using a computer-based system to operate upon data that corresponds to a geometric configuration of the structural component;
• predetermining an expected stress load of the structural component with the computer-based system;
• and
• integrally forming the structural component to segment the structural component into the stiffening sections;
• wherein the at least first stiffening section and the at least second stiffening section are arranged and formed using topology optimization, such that a stiffness of the structural component is optimized for a predetermined stress load of the structural component.