Abstract: Composite assemblies are described that include composite spars that are co-cured with one or more sacrificial members on their flanges, forming an integrated sacrificial surface for the composite spars. In one embodiment, the composite assembly includes a composite spar having a web and flanges that project from sides of the web. The composite assembly further includes a sacrificial member of composite materials co-cured with the composite spar on an outer surface of at least one of the flanges. In addition, the sacrificial member has an outer surface that has been machined into conformance with an inner surface of at least one skin panel for an aircraft structure to form a contact surface with the at least one skin panel.

Abstract: Foldable aircraft wings are disclosed. An example aircraft includes a foldable wing having a fixed wing portion, a foldable wing portion and a hinge to pivotally couple the foldable wing portion relative to the fixed wing portion. The hinge includes a wing transition portion including wing hinge ribs and wing stub ribs, respective ones of the wing hinge ribs coupled to corresponding respective ones of the wing stub ribs. The hinge also includes a tip transition portion including tip hinge ribs, where respective ends of the tip hinge ribs positioned between corresponding respective ones of the wing hinge ribs and the wing stub ribs.

Abstract: Composite assemblies are described that include composite spars that are co-cured with one or more sacrificial members on their flanges, forming an integrated sacrificial surface for the composite spars. In one embodiment, the composite assembly includes a composite spar having a web and flanges that project from sides of the web. The composite assembly further includes a sacrificial member of composite materials co-cured with the composite spar on an outer surface of at least one of the flanges. In addition, the sacrificial member has an outer surface that has been machined into conformance with an inner surface of at least one skin panel for an aircraft structure to form a contact surface with the at least one skin panel.

Abstract: Composite assemblies are described that include composite spars that are co-cured with one or more sacrificial members on their flanges, forming an integrated sacrificial surface for the composite spars. In one embodiment, the composite assembly includes a composite spar having a web and flanges that project from sides of the web. The composite assembly further includes a sacrificial member of composite materials co-cured with the composite spar on an outer surface of at least one of the flanges. In addition, the sacrificial member has an outer surface that has been machined into conformance with an inner surface of at least one skin panel for an aircraft structure to form a contact surface with the at least one skin panel.

Abstract: A breakaway support configured to selectively release an actuator from a fitting and a method of providing the breakaway support. The breakaway support includes a race positioned between the actuator and the fitting. The second end of the actuator is connected to the fitting via a ball joint is positioned within the race. The ball joint permits the actuator to pivot about the ball joint in a vertical plane between a first position and a second position. The breakaway support includes a first knuckle that causes the actuator to release from the fitting when the actuator moves in a first direction beyond the first position. A portion of the fitting or a second knuckle may cause the actuator to release from the fitting when the actuator moves in a second direction beyond the second position. A portion of the actuator may break to release the actuator from the fitting.

Abstract: Foldable aircraft wings are disclosed. An example aircraft includes a foldable wing having a fixed wing portion, a foldable wing portion and a hinge to pivotally couple the foldable wing portion relative to the fixed wing portion. The hinge includes a wing transition portion including wing hinge ribs and wing stub ribs, respective ones of the wing hinge ribs coupled to corresponding respective ones of the wing stub ribs. The hinge also includes a tip transition portion including tip hinge ribs, where respective ends of the tip hinge ribs positioned between corresponding respective ones of the wing hinge ribs and the wing stub ribs.

Abstract: A breakaway support configured to selectively release an actuator from a fitting and a method of providing the breakaway support. The breakaway support includes a race positioned between the actuator and the fitting. The second end of the actuator is connected to the fitting via a ball joint is positioned within the race. The ball joint permits the actuator to pivot about the ball joint in a vertical plane between a first position and a second position. The breakaway support includes a first knuckle that causes the actuator to release from the fitting when the actuator moves in a first direction beyond the first position. A portion of the fitting or a second knuckle may cause the actuator to release from the fitting when the actuator moves in a second direction beyond the second position. A portion of the actuator may break to release the actuator from the fitting.

Abstract: An inspection system is presented. The inspection system comprises a remotely controllable imaging assembly and a scale reticle. The remotely controllable imaging assembly includes a camera and a lens system. The lens system includes a tunable-focus lens and a magnifying lens between the camera and the tunable-focus lens. The scale reticle is positioned within a sight line of the camera of the imaging assembly such that the scale reticle is between the imaging assembly and a target.

Abstract: An inspection system is presented. The inspection system comprises a remotely controllable imaging assembly and a scale reticle. The remotely controllable imaging assembly includes a camera and a lens system. The lens system includes a tunable-focus lens and a magnifying lens between the camera and the tunable-focus lens. The scale reticle is positioned within a sight line of the camera of the imaging assembly such that the scale reticle is between the imaging assembly and a target.