The Boeing Company

Gregory A Cass

Khanh Mai Pham

Garrett C Hanson

Ian E Schroeder

Provided are stiffened stringer panels with integrated shim structures. An example composite panel comprises a skin member having an inner surface, and a stringer positioned on the inner surface. The stringer comprises a first flange portion and a second flange portion with the first flange portion and the second flange portion contacting the inner surface. The composite panel further comprises an integrated shim positioned on the first flange portion. The integrated shim may comprise a sacrificial material configured to be trimmed to the desired geometry. The sacrificial material may comprise a glass fiber reinforced plastic fabric pre-impregnated with resin. The integrated shim may be configured to interface with internal support structures of a wing assembly. The integrated shim may be configured to be machined to fit dimensions and measurements corresponding to the internal support structures of the wing assembly.

Stiffened composite panel with integrated shim

The construction of a stringer transition through a common base eliminates the need for plate fittings and their associated fasteners to connect opposing ends of a first stringer having a large cross-sectional area to a second stringer having a smaller cross-sectional area. A base of composite material is secured to a skin panel of an aircraft wing with the base aligned with and extending along the longitudinal length of the skin panel. The first stringer is secured to the base and the second stringer is secured to the base, with the first stringer and second stringer longitudinally aligned with the base and with a longitudinal spacing between the first stringer and the second stringer. The base connects the first stringer to the second stringer and only the base connects the first stringer to the second stringer.

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Seattle, WA, United States of America

Gregory A Cass