United Aircraft Corporation (OAK) proposed a new wing frame design where some spars were replaced with composite panels. This solution reduces the structure's weight and simplifies assembly; the documentation was published in the FIPS database.
The development is based on two U-shaped carbon fiber panels. They are joined at the edges using fasteners and an adhesive layer, forming a closed load-bearing wing structure.
In the classical scheme, spars bear the main loads and require a complex set of reinforcing elements. In the new architecture, some of these functions are redistributed to composite panels.
This allows for the elimination of some structural elements and reduces the number of individual parts in the wing structure.
In areas forming the aerodynamic profile, three-layer panels are used. A honeycomb core is placed between the skins, which increases stiffness without significantly increasing weight.
Local reinforcement is achieved by changing the number of composite layers at attachment points. This maintains strength while reducing the weight of the structure.
Each panel is manufactured in a single technological cycle. This reduces the number of operations, speeds up assembly, and lowers production labor intensity.
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