Load-Bearing Fairing Element for Aircraft Flap Mechanism

The patent combines multiple stiffening elements (first and second stiffening elements) into a single integrated bridge element that is produced as one piece. This merging eliminates the need for separate production and assembly of multiple components, reducing manufacturing complexity while maintaining the load-bearing function through the integrated structural design of the bridge element with its specific geometric features.

The patent segments the fairing element into functionally distinct but integrally connected parts: the bridge element, first cover panel, and second cover panel. These segments are designed to be produced separately as simplified components and then assembled through straightforward connection means, maintaining structural integrity while enabling more efficient manufacturing compared to producing a single complex integrated structure.

The patent employs thin-walled shell structures for the bridge element and cover panels that provide adequate load-bearing capacity through optimized geometric shapes and material distribution. The bridge element features a top surface and bottom surface with specific curvature and thickness variations that maintain structural strength while minimizing material usage and weight, consistent with aerodynamic design principles.

The patent merges multiple stiffening functions into the bridge element, which is produced as a single integrated component rather than assembling multiple separate stiffening elements. This merging simplifies the manufacturing process by eliminating individual production and connection steps for each stiffening element, while the bridge element's integrated design maintains the necessary load-bearing capacity through its unified structural configuration.