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Design and construction of a composite material airplane having a high aspect-ratio wing and a horizontal double-lobe fuselage cross-section for cargo and/or passenger accommodations. The fuselage comprises a double-lobe shell of contoured honeycomb core composite panels and an interior vertical pla

Design and construction of a composite material airplane having a high aspect-ratio wing and a horizontal double-lobe fuselage cross-section for cargo and/or passenger accommodations. The fuselage comprises a double-lobe shell of contoured honeycomb core composite panels and an interior vertical plane centerline web forming a divider between the lobes. Piano-hinge type joints are utilized for multi-panel junctures to provide uniform load distribution across the junctures. The piano-hinge juncture utilizes hinge lugs which are dimensioned to interface sequentially along the hinge axis, and the hinge lugs are interconnected by a tubular hinge pin.

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A wide-body composite material constructed airplane fuselage, comprising: a fore-body section, a center-body section, and an aft-body section; and center-body section having cylindrically contoured composite material panels forming an external shell of two horizontally ajdacent lobes with equal radi

A wide-body composite material constructed airplane fuselage, comprising: a fore-body section, a center-body section, and an aft-body section; and center-body section having cylindrically contoured composite material panels forming an external shell of two horizontally ajdacent lobes with equal radius-of-curvature in cross-section; a vertical plane bulkhead being of composite material panel construction and forming a longitudinal centerline interconnection between said two horizontally adjacent lobes; said composite material panels comprising a honeycomb core with a face sheet on both sides thereof; and continuous hinge joints for transmitting and redistributing structural loads from each of the face sheets through an edge intersecting, centrally positioned, common hinge axis of adjoining composite material panels, and forming longitudinal structural interconnections between said vertical-plane bulkhead and said two horizontally adjacent lobes for assembly into the center-body section of the fuselage.