Double-lobe fuselage composite airplane

Claim 2

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.

Claim 3

A wide-body airplane fuselage, as set forth in claim 1, including: a main deck floor member extending horizontally outward from said vertical-plane bulkhead to the external shell of the two horizontally adjacent lobes for forming a horizontal partition in the interior thereof, and dividing each of said lobes into an upper main deck passenger compartment and a lower deck cargo compartment.

Claim 4

A wide-body airplane fusleage, as set forth in claim 1, wherein said continuous hinge joints comprise: hinge lugs formed integral with the edge of each of the joined composite material panels and being spaced apart along the edge of each of the joined panels such that the lugs of one panel edge will accommodate the lugs of the adjoining panel in a sequentially intermeshing relationship.

Claim 5

A wide-body airplane fuselage, as set forth in claim 3, wherein each of said continuous hinge joints comprise: a hinge pin having a concentric series of tubes, each tube being flexible in bending to allow for longitudinal misalignment during threading through holes in the hinge lugs and to accommodate variation in joining angle of the composite panels.

Claim 6

A wide-body composite material constructed airplane, comprising: a fuselage having a fore-body section, a center-body section and an aft-body section; said fore-body section having a flight crew cockpit; said center-body section having cylindrically contoured composite material panels forming an external shell for a pair of horizontally adjacent 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 pair of horizontally adjacent lobes; said composite material panels comprising a honeycomb core with a face sheet on both sides thereof; 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 pair of horizontally adjacent lobes for retaining them together in assembled relationship to complete the fuselage center-body construction; and aft-body section having engine nacelles strut mounted from the sides of the fuselage and a necked-in fuselage shape adjacent to said strut mounted engine nacelles for an aerodynamic cross-sectional design of least drag; and a wing having a high aspect ratio and being mounted to the lower portion of the fuselage such that no fuselage protrusion below the wing surface is evident.

Claim 7

A wide-body composite material constructed airplane, comprising: a fuselage having a fore-body section, a center-body section and an aft-body section; said fore-body section having a flight crew cockpit; said center-body section having cylindrically contoured composite material panels forming an external shell for a pair of horizontally adjacent 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 pair of horizontally adjacent lobes; said composite material panels comprising a honeycomb core with a face sheet on both sides thereof; 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 pair of horizontally adjacent lobes for retaining them together in assembled relationship to complete the fuselage center-body construction; and aft-body section having engine nacelles strut mounted from the sides of the fuselage and a necked-in fuselage shape adjacent to said strut mounted engine nacelles for an aerodynamic cross-sectional design of least drag; and a wing having a high aspect ratio and being mounted to the lower portion of the fuselage such that no fuselage protrusion below the wing surface is evident.

Claim 8

A wide-body airplane, as set forth in claim 5, including: a main deck floor member extending horizontally outward from said vertical-plane bulkhead to the external shell of the two horizontally adjacent lobes for forming a horizontal partition in the interior thereof, and dividing each of said lobes into an upper main deck passenger compartment and a lower deck cargo compartment.

Claim 9

A wide-body airplane, as set forth in claim 5, wherein said continuous hinge joints comprise: hinge lugs formed integral with the edge of each of the joined composite material panels and being spaced apart edge will accommodate the lugs of the adjoining panel in a sequentially along the edge of each of the joined panels such that the lugs of one panel intermeshing relationship.

Claim 10

A wide-body airplane, as set forth in claim 7, wherein each of said continuous hinge joints comprise: a hinge pin having a concentric series of tubes, each tube being flexible in bending to allow for longitudinal misalignement during threading through holes in the hinge lugs and to accommodate variation in joining angle of the composite panels.

Claim 11

A wide-body airplane, as set forth in claim 7, including: a main landing gear structurally mounted, aft of said wing, to a trunnion adjacent each exterior side wall of the double-lobe center-body section, such that the landing load path is directed into the side-wall structure of the fuselage and for retraction operation thereof, being pivotally swung straight in toward the centerline of the fuselage.

Claim 12

A wide-body airplane, as set forth in claim 9, including: a nose landing gear structurally mounted, forward of said wing, to a trunnion on the centerline of the double-lobe center-body section, such that the landing load path is directed into the centerline web structure of the fuselage and for retraction operation thereof, being pivotally swung straight rearwardly along the centerline of the fuselage and upwardly into the underside of the fuselage.

Claim 13

A wide-body airplane, comprising: a fuselage having a fore-body section, a center-body section and an aft-body section; said fore-body section comprsing a pilot's cockpit; said center-body section having cylindrically contoured honeycomb sandwich panels forming an external shell comprising two horizontally adjacent lobes of substantially equal radius of curvature and a vertical plane centerline web of honeycomb sandwich panel construction forming a structural interconnection between said two horizontally adjacent lobes; said honeycomb sandwhich panels comprising a honeycomb core with a face sheet on both sides thereof; 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 honeycomb sandwich panels, and forming longitudinal structural interconnections between said vertical-plane centerline web and said two horizontally adjacent lobes for retaining them together in assembled relationship to complete the fuselage center-body construction; said aft-body section comprising engine nacelles strut mounted to the sides of the fuselage, a V-tail mounted to the top of the fuselage, and a wedge-shaped tail cone mounted aft of the strut mounted engine nacelles and said V-tail; and a wing of high-aspect ratio having its semi-span root ends structurally fastened to said centerline web such that no fuselage protrusions below the wing undersurface is evident.

Claim 14

A wide-body airplane, comprising: a fuselage having a fore-body section, a center-body section and an aft-body section; said fore-body section comprsing a pilot's cockpit; said center-body section having cylindrically contoured honeycomb sandwich panels forming an external shell comprising two horizontally adjacent lobes of substantially equal radius of curvature and a vertical plane centerline web of honeycomb sandwich panel construction forming a structural interconnection between said two horizontally adjacent lobes; said honeycomb sandwhich panels comprising a honeycomb core with a face sheet on both sides thereof; 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 honeycomb sandwich panels, and forming longitudinal structural interconnections between said vertical-plane centerline web and said two horizontally adjacent lobes for retaining them together in assembled relationship to complete the fuselage center-body construction; said aft-body section comprising engine nacelles strut mounted to the sides of the fuselage, a V-tail mounted to the top of the fuselage, and a wedge-shaped tail cone mounted aft of the strut mounted engine nacelles and said V-tail; and a wing of high-aspect ratio having its semi-span root ends structurally fastened to said centerline web such that no fuselage protrusions below the wing undersurface is evident.

Claim 15

A wide-body airplane, as set forth in claim 11, including: a piano-hinge type joint having lugs formed integral with adjoining edges of composite material panels and dimensioned to interface along their hinge axis for forming said structural interconnection between said vertical plane centerline web and said two horizontally adjacent lobes of said center-body section.

Claim 16

A wide-body airplane, as set forht in claim 11, including: a main landing gear structurally mounted, aft of said wing, to a trunnion adjacent to each exterior side wall of the double-lobe center-body section, such that the landing load path is directed into the side-wall structure of the fuselage and for retraction operation thereof, being pivotally swung straight in toward the centerline of the fuselage.

Claim 17

A wide-body airplane, as set forth in claim 11, including: a nose landing gear structurally mounted, forward of said wing, to a trunnion on the centerline of the double-lobe center-body section, such that the landing load path is directed into the centerline web structure of the fuselage, and for retraction operation thereof, being pivotally swung straight along the centerline of the fuselage and upwardly into the underside of the fuselage.

Claim 18

A wide-body airplane, as set forth in claim 11, wherein: said aft-body section has a necked-in fuselage shape adjacent to said strut mounted engine nacelles for aerodynamically integrating said strut mounted engine nacelles into a cross-sectional fuselage design of least drag.

Claim 19

A wide-body airplane as set forth in claim 11, wherein: said center-body section has a horizontal partition extending from said vertical plane centerline web, horizontally outward to the lobe side walls of the fuselage for forming a main deck floor member in the interior of the two horizontally adjacent lobes of said center-body section, and vertically dividing each side-by-side lobe into an upper main deck passenger compartment and a lower deck cargo compartment.

Claim 20

A wide-body airplane, as set forth in claim 16, including: a piano-hinge type joint having lugs formed integral with adjoining edges of composite material panels and dimensioned to interface along their hinge axis for forming a structural interconnection between said horizontal partition extending from said vertical plane centerline web and said two horizontally adjacent lobes of said center-body section.