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: 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 wing fold system of a wing of an aircraft. The system may include a first lock of a latch to prevent movement of a latch pin of the latch to prevent movement of an unfixed portion of the wing with respect to a fixed portion of the wing, the first lock may include a first cam configured to prevent the second lock from transitioning to a second engaged position until the first lock may be in a first engaged position via contact with a second cam of the second lock. A second lock of the latch, the second lock may include the second cam configured to prevent the first lock from transitioning away from the first engaged position until the second lock transitions away from the second engaged position.

Abstract: A wing fold system of a wing of an aircraft. The system may include a first lock of a latch to prevent movement of a latch pin of the latch to prevent movement of an unfixed portion of the wing with respect to a fixed portion of the wing, the first lock may include a first cam configured to prevent the second lock from transitioning to a second engaged position until the first lock may be in a first engaged position via contact with a second cam of the second lock. A second lock of the latch, the second lock may include the second cam configured to prevent the first lock from transitioning away from the first engaged position until the second lock transitions away from the second engaged position.

Abstract: A system for supporting a load across non-intersecting beams each having a web depending from an upper chord with an upper surface generally parallel with a chordal plane includes at least one crossing member intersecting the beams at intersection loci. At each intersection locus the beam presents a channel receiving a crossing member in a nesting orientation in an installed orientation. The crossing member includes a support expanse configured for an abutting relation with the upper chord to present the upper surface and a top surface of the crossing member as coplanar in the installed orientation. The beam and the crossing member have aperture-pairs in register in the installed orientation. The apertures accommodate tension resisting members or compression resisting members coupled with the upper chord and traversing the crossing member for resisting tension or compression forces on the upper chord in the installed orientation.

Abstract: A system for supporting a load across non-intersecting beams each having a web depending from an upper chord with an upper surface generally parallel with a chordal plane includes at least one crossing member intersecting the beams at intersection loci. At each intersection locus the beam presents a channel receiving a crossing member in a nesting orientation in an installed orientation. The crossing member includes a support expanse configured for an abutting relation with the upper chord to present the upper surface and a top surface of the crossing member as coplanar in the installed orientation. The beam and the crossing member have aperture-pairs in register in the installed orientation. The apertures accommodate tension resisting members or compression resisting members coupled with the upper chord and traversing the crossing member for resisting tension or compression forces on the upper chord in the installed orientation.

Abstract: An aircraft deck support system includes horizontal deck support beams connected to the aircraft's frames. Each deck support beam has a plurality of machined, generally T-shaped supports. Each T-shaped support includes either a horizontal recess or a raised surface formed in a deck support beam upper chord and a U-shaped aperture formed in a beam web. The T-shaped support matably receives a cross-support beam attachment flange perpendicularly aligned with the deck support beams. Each cross-support beam includes a web perpendicularly connected at an upper end to the attachment flange, and a stiffening flange at a web lower end. Both the web and the stiffening flange are freely suspended within the U-shaped aperture of the T-shaped support. When joined, the cross-support beam seats on the T-shaped support allowing both the cross-support beam and the deck support beam to develop maximum bending moments at a reduced structural weight.