Abstract: A monolithic joint system for a fuselage to wing joint in an aircraft is provided. The joint system comprises a first vertical flange, a base plate, a second vertical flange, and damage containment features associated with at least one of these components. The first vertical flange is configured to connect to a fuselage section of the aircraft and the second vertical flange is configured to connect to a rib web of a wing, while the base plate attaches outboard wing to inboard wing box. The first vertical flange, the base plate, and the second vertical flange are formed from a continuous piece of material. The damage containment features are configured to slow propagation of an active crack tip in the joint system during operation of the aircraft. Thus, the illustrative embodiments provide a one-piece joint system for the fuselage to wing joint of an aircraft.

Abstract: Aircraft main landing gear drag brace backup fitting assemblies and related methods are described herein. An example aircraft wing disclosed herein includes a rear spar having a rear side and a front side opposite the rear side, a side-of-body rib coupled to the rear spar, a rib post disposed on the front side of the rear spar, where the rib post is to couple a second rib to the rear spar, a side-of-body fitting coupled to the side-of-body rib, an intercostal member coupled between the side-of-body fitting and the rib post, and a drag brace fitting disposed on the rear side of the rear spar. The drag brace fitting is coupled to the rib post and the side-of-body fitting via a first plurality of fasteners extending through the rear spar.

Abstract: A monolithic joint system for a fuselage to wing joint in an aircraft is provided. The joint system comprises a first vertical flange, a base plate, a second vertical flange, and damage containment features associated with at least one of these components. The first vertical flange is configured to connect to a fuselage section of the aircraft and the second vertical flange is configured to connect to a rib web of a wing, while the base plate attaches outboard wing to inboard wing box. The first vertical flange, the base plate, and the second vertical flange are formed from a continuous piece of material. The damage containment features are configured to slow propagation of an active crack tip in the joint system during operation of the aircraft. Thus, the illustrative embodiments provide a one-piece joint system for the fuselage to wing joint of an aircraft.

Abstract: Aircraft main landing gear drag brace backup fitting assemblies and related methods are described herein. An example aircraft wing disclosed herein includes a rear spar having a rear side and a front side opposite the rear side, a side-of-body rib coupled to the rear spar, a rib post disposed on the front side of the rear spar, where the rib post is to couple a second rib to the rear spar, a side-of-body fitting coupled to the side-of-body rib, an intercostal member coupled between the side-of-body fitting and the rib post, and a drag brace fitting disposed on the rear side of the rear spar. The drag brace fitting is coupled to the rib post and the side-of-body fitting via a first plurality of fasteners extending through the rear spar.

Abstract: A stiffened panel comprises a composite panel, and a stiffener including a base flange on the composite panel. The base flange is tapered towards the panel. The stiffened panel further comprises a composite overwrap layer on only the composite panel and a tapered surface of the base flange.

Abstract: A stiffened panel comprises a composite panel, and a stiffener including a base flange on the composite panel. The base flange is tapered towards the panel. The stiffened panel further comprises a composite overwrap layer on only the composite panel and a tapered surface of the base flange.