Abstract: 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.

Abstract: 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 he machined to fit dimensions and measurements corresponding to the internal support structures of the wing assembly.

Abstract: Examples include an apparatus configured for attaching a rib of an aircraft wing to a panel of the aircraft wing, the apparatus including: an insert that is configured to be attached, via an interference fit, to a hole in the rib; a shear tie including a socket at a first end of the shear tie, where the shear tie is configured to be attached to the panel at a second end of the shear tie; a ball stud including a shaft and a ball that is opposite the shaft, where the shaft is configured to be attached to the insert and the ball is configured to be positioned within the socket; and a fastener that is configured to secure the ball within the socket, thereby attaching the ball stud to the shear tie.

Abstract: A fastening system to couple a first aircraft structure and a second aircraft structure is disclosed. The fastening system includes a fastener, a nutplate having a body defining an opening to receive the fastener, a flange extending from the body to engage an outer surface of the first structure, and a first sleeve protruding from the flange in a direction away from the body, the first sleeve to couple to a first bore formed in the first structure and prevents rotation of the nutplate relative to the first structure.

Abstract: A solid laminate stringer includes a base segment that forms a first generally trapezoidal cross section. The solid laminate stringer also includes a transition segment abutting the base segment, with concave sides that are continuous with the sides of the base segment. The solid laminate stringer also includes a top segment abutting the transition segment, where the top segment forms a second generally trapezoidal cross section with sides that are continuous with the concave sides of the transition segment. The solid laminate stringer may also include a first overwrap layer covering the top segment, the transition segment, and at least a portion of the base segment. The solid laminate stringer may also include a second overwrap layer overlapping at least a portion of the first overwrap layer covering the base segment.

Abstract: Examples include an apparatus configured for attaching a rib of an aircraft wing to a panel of the aircraft wing, the apparatus including: an insert that is configured to be attached, via an interference fit, to a hole in the rib; a shear tie including a socket at a first end of the shear tie, where the shear tie is configured to be attached to the panel at a second end of the shear tie; a ball stud including a shaft and a ball that is opposite the shaft, where the shaft is configured to be attached to the insert and the ball is configured to be positioned within the socket; and a fastener that is configured to secure the ball within the socket, thereby attaching the ball stud to the shear tie.

Abstract: A solid laminate stringer includes a base segment that forms a first generally trapezoidal cross section. The solid laminate stringer also includes a transition segment abutting the base segment, with concave sides that are continuous with the sides of the base segment. The solid laminate stringer also includes a top segment abutting the transition segment, where the top segment forms a second generally trapezoidal cross section with sides that are continuous with the concave sides of the transition segment. The solid laminate stringer may also include a first overwrap layer covering the top segment, the transition segment, and at least a portion of the base segment. The solid laminate stringer may also include a second overwrap layer overlapping at least a portion of the first overwrap layer covering the base segment.

Abstract: Aircraft wings and aircraft including such aircraft wings are disclosed. An example apparatus includes an aircraft wing having a first panel; a second panel; ribs coupled between the first and second panels; and stiffeners coupled between the ribs in a spanwise direction and to the first panel, the coupling between the stiffeners and the first panel to deter axial loads from being received by the stiffeners, the stiffeners to increase a compressional stability of the first panel, wherein the coupling between the stiffeners and the first panel are indirect couplings formed via clips, the couplings formed via the clips deter the axial loads from being received by the stiffeners while increasing the compressional stability of the first panel.

Abstract: A solid laminate stringer includes a base segment that forms a first generally trapezoidal cross section. The solid laminate stringer also includes a transition segment abutting the base segment, with concave sides that are continuous with the sides of the base segment. The solid laminate stringer also includes a top segment abutting the transition segment, where the top segment forms a second generally trapezoidal cross section with sides that are continuous with the concave sides of the transition segment. The solid laminate stringer also includes a first overwrap layer covering the top segment, the transition segment, and at least a portion of the base segment. The solid laminate stringer also includes a second overwrap layer overlapping at least a portion of the first overwrap layer covering the base segment.

Abstract: A solid laminate stringer includes a base segment that forms a first generally trapezoidal cross section. The solid laminate stringer also includes a transition segment abutting the base segment, with concave sides that are continuous with the sides of the base segment. The solid laminate stringer also includes a top segment abutting the transition segment, where the top segment forms a second generally trapezoidal cross section with sides that are continuous with the concave sides of the transition segment. The solid laminate stringer also includes a first overwrap layer covering the top segment, the transition segment, and at least a portion of the base segment. The solid laminate stringer also includes a second overwrap layer overlapping at least a portion of the first overwrap layer covering the base segment.

Abstract: A window frame assembly for an aircraft, includes a window frame of composite material, adapted for attachment in a window opening of an aircraft, having an outer flange with an exterior surface and an interior surface, a metal erosion shield attached to the exterior surface of the outer flange, and a polymer adapter ring, attached to the interior surface of the outer flange. The window frame has a substantially constant thickness, and the erosion shield has a substantially constant cross-sectional shape. The adapter ring has a sloped engagement surface configured for supporting a window pane assembly.

Abstract: Aircraft wings and aircraft including such aircraft wings are disclosed. An example apparatus includes an aircraft wing having a first panel; a second panel; ribs coupled between the first and second panels; and stiffeners coupled between the ribs in a spanwise direction and to the first panel, the coupling between the stiffeners and the first panel to deter axial loads from being received by the stiffeners, the stiffeners to increase a compressional stability of the first panel, wherein the coupling between the stiffeners and the first panel are indirect couplings formed via clips, the couplings formed via the clips deter the axial loads from being received by the stiffeners while increasing the compressional stability of the first panel.

Abstract: A window frame assembly for an aircraft, includes a window frame of composite material, adapted for attachment in a window opening of an aircraft, having an outer flange with an exterior surface and an interior surface, a metal erosion shield attached to the exterior surface of the outer flange, and a polymer adapter ring, attached to the interior surface of the outer flange. The window frame has a substantially constant thickness, and the erosion shield has a substantially constant cross-sectional shape. The adapter ring has a sloped engagement surface configured for supporting a window pane assembly.