Abstract: A composite sandwich structure comprises a core sandwiched between composite laminate facesheets. The core includes a plurality of core sections spliced together at joints that incorporate integral features for arresting the propagation of irregularities in the facesheets.

Abstract: A composite sandwich structure comprises a core sandwiched between composite laminate facesheets. The core includes a plurality of core sections spliced together at joints that incorporate integral features for arresting the propagation of irregularities in the facesheets.

Abstract: A composite sandwich structure comprises a core sandwiched between composite laminate facesheets. The core includes a plurality of core sections spliced together at joints that incorporate integral features for arresting the propagation of irregularities in the facesheets.

Abstract: A composite sandwich structure comprises a core sandwiched between composite laminate facesheets. The core includes a plurality of core sections spliced together at joints that incorporate integral features for arresting the propagation of irregularities in the facesheets.

Abstract: An airplane comprises a twin-deck fuselage in which an upper deck support structure is utilized for carry-through of a mid-mount main wing box. The main landing gear of the airplane is mounted to the fuselage and is stowed in a non-pressurized area below the main wing box (enabled due to an optimized wing box geometry). A pressurized passageway/cargo/galley complex separates the main landing gear box and the main wing box. The upper deck is continuous, while the lower deck is separated by the wheel wells into two distinct fore and aft areas (for either cargo or passengers). The airplane further comprises an integrated vertical fin and an aft-extended pressurized deck area for reduced double-deck wetted area. More specifically, the double-deck pressurized fuselage structure is extended to form a blending structure to which a structural box of the vertical fin is attached.

Abstract: An airplane comprises a twin-deck fuselage in which an upper deck support structure is utilized for carry-through of a mid-mount main wing box. The main landing gear of the airplane is mounted to the fuselage and is stowed in a non-pressurized area below the main wing box (enabled due to an optimized wing box geometry). A pressurized passageway/cargo/galley complex separates the main landing gear box and the main wing box. The upper deck is continuous, while the lower deck is separated by the wheel wells into two distinct fore and aft areas (for either cargo or passengers). The airplane further comprises an integrated vertical fin and an aft-extended pressurized deck area for reduced double-deck wetted area. More specifically, the double-deck pressurized fuselage structure is extended to form a blending structure to which a structural box of the vertical fin is attached.

Abstract: An integrated floor for an aircraft fuselage includes a composite panel forming a floor surface and composite beams bonded to the floor panel. The beams extend longitudinally within the fuselage and support the floor.

Abstract: A composite sandwich structure comprises a core sandwiched between composite laminate facesheets. The core includes a plurality of core sections spliced together at joints that incorporate integral features for arresting the propagation of irregularities in the facesheets.

Abstract: Techniques for providing fastener-free primary structural joint for sandwich panels are disclosed. In one embodiment, a technique includes positioning a first panel having a first edge portion proximate a second panel having a second edge portion such that the first and second edge portions cooperatively form an interior recess on an interior side of the first and second panels, applying adhesive to at least one of the recessed interior side of the panel assembly and a plug configured to occupy the interior recess, inserting the plug into the interior recess, the plug including a cap that extends beyond the interior recess and overlaps adjacent portions of the first and second panels, applying adhesive to at least one of a splice and an exterior side opposite from the interior side, and attaching the splice on the exterior side.

Abstract: A composite sandwich structure comprises a core sandwiched between composite laminate facesheets. The core includes a plurality of core sections spliced together at joints that incorporate integral features for arresting the propagation of irregularities in the facesheets.

Abstract: An aircraft seat assembly configured in accordance with an example embodiment of the invention utilizes composite materials to achieve significant weight savings relative to conventional seat designs. The seat assembly includes a lightweight composite support structure, a lightweight composite seat base, and a seat back assembly that employs a lightweight inner frame. The seat cushion and the seat back cushion may utilize a sealed pneumatic element that self-inflates to provide increased air cushioning during flight. The seat assembly can leverage inexpensive manufacturing techniques such that the seat assembly can be economically produced for use as an economy class seat.

Abstract: An integrated floor for an aircraft fuselage includes a composite panel forming a floor surface and composite beams bonded to the floor panel. The beams extend longitudinally within the fuselage and support the floor.

Abstract: Techniques for providing fastener-free primary structural joint for sandwich panels are disclosed. In one embodiment, a technique includes positioning a first panel having a first edge portion proximate a second panel having a second edge portion such that the first and second edge portions cooperatively form an interior recess on an interior side of the first and second panels, applying adhesive to at least one of the recessed interior side of the panel assembly and a plug configured to occupy the interior recess, inserting the plug into the interior recess, the plug including a cap that extends beyond the interior recess and overlaps adjacent portions of the first and second panels, applying adhesive to at least one of a splice and an exterior side opposite from the interior side, and attaching the splice on the exterior side.

Abstract: A pilot rest system for use in a flight deck of an aircraft comprising a sleeping area, which comprises two parts, the first part being the space beneath one or more observer seats and the second part being a seat-free area adjacent to said seats. A curtain is preferably provided to enclose the second part of the sleeping area to ensure privacy and keep the sleep area dark if desired. The rest system can further comprise a mini-lavatory and a mini-galley in the flight deck.

Abstract: A pilot rest system for use in a flight deck of an aircraft comprising a sleeping area, which comprises two parts, the first part being the space beneath one or more observer seats and the second part being a seat-free area adjacent to said seats. A curtain is preferably provided to enclose the second part of the sleeping area to ensure privacy and keep the sleep area dark if desired. The rest system can further comprise a mini-lavatory and a mini-galley in the flight deck.

Abstract: An aircraft seat assembly configured in accordance with an example embodiment of the invention utilizes composite materials to achieve significant weight savings relative to conventional seat designs. The seat assembly includes a lightweight composite support structure, a lightweight composite seat base, and a seat back assembly that employs a lightweight inner frame. The seat cushion and the seat back cushion may utilize a sealed pneumatic element that self-inflates to provide increased air cushioning during flight. The seat assembly can leverage inexpensive manufacturing techniques such that the seat assembly can be economically produced for use as an economy class seat.

Abstract: Aircraft having cab portions with integrated windshields are disclosed. The cab portion can include a rounded nose and a windshield positioned above and aft of a forward extremity of the rounded nose. A contour of the cab portion extending from the nose over the windshield aft of the nose can have a generally continuously smooth, unkinked shape. In particular embodiments, the portion of the contour corresponding to the windshield can be convex when viewed from a position external to the cab portion, and the shape of the windshield can form a portion of a conical surface.

Abstract: Aircraft having cab portions with integrated windshields are disclosed. The cab portion can include a rounded nose and a windshield positioned above and aft of a forward extremity of the rounded nose. A contour of the cab portion extending from the nose over the windshield aft of the nose can have a generally continuously smooth, unkinked shape. In particular embodiments, the portion of the contour corresponding to the windshield can be convex when viewed from a position external to the cab portion, and the shape of the windshield can form a portion of a conical surface.