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US 8,985,514 B2Granted
Composite structural panels and aircraft fuselages
AssigneeThe Boeing Company
InventorRachel Cardin
Life of this patent
Estimating the term…
Abstract
Structural panel assemblies include first and second composite panels positioned in edgewise alignment, with at least one tab extending from a mating edge of the first panel and including an exterior surface in facing registration with a corresponding portion of an interior surface of the second composite panel. The corresponding portion includes a recessed area to interfit with the tab or is otherwise configured to receive the tab. The exterior surface of the tab is spaced from the corresponding portion, to receive a bonding material therebetween for bonding the composite panels.
Claims17
An aircraft fuselage assembly comprising:
- first and second skin sections each further comprising a plurality of plies of composite materials and having a mating edge, with the mating edges disposed in edgewise alignment with each other;
- and
- a plurality of tabs each extending longitudinally from the mating edge of the first skin section along an interior surface of the second skin section, each tab including an exterior surface in facing registration with a corresponding portion of the interior surface of the second skin section, each of said tabs further including at least one injection hole formed therethrough for injection of bonding material between said exterior surface and said corresponding portion for attaching the first and second skin sections;
- wherein at least one of said corresponding portions includes a recessed area adapted to matingly receive the exterior surface of at least one of the plurality of tabs;
- wherein at least one of the plurality of tabs includes a protrusion extending substantially orthogonally from the exterior surface thereof;
- and
- wherein the protrusion interfits with the recessed area disposed on the interior surface of the second skin section in facing registration with the exterior surface.
4 more elements
A vehicle shell assembly comprising:
- a first composite panel having a mating edge;
- a second composite panel having a corresponding mating edge positioned in edgewise alignment with the mating edge of the first composite panel;
- and at least one tab disposed on and extending longitudinally from the mating edge of the first composite panel,
- the tab including an exterior surface in facing registration with a corresponding portion of an interior surface of the second composite panel, the tab further including at least one injection hole formed therethrough
- for injection of bonding material between said exterior surface and said corresponding portion for attaching the first composite panel and the second composite
- wherein the corresponding portion includes a recessed area adapted to matingly receive the exterior surface of the tab;
- wherein the tab includes a protrusion extending substantially orthogonally from the exterior surface of the tab;
- and wherein the protrusion interfits with the recessed area.
5 more elements
An aircraft fuselage assembly comprising:
- first and second skin sections each further comprising a plurality of plies of composite materials and having a mating edge, with the mating edges disposed in edgewise alignment with each other;
- and
- a plurality of tabs each extending longitudinally from the mating edge of the first skin section along an interior surface of the second skin section, each tab including an exterior surface in facing registration with a corresponding portion of the interior surface of the second skin section, each of said tabs further including at least one injection hole formed therethrough for injection of bonding material between said exterior surface and said corresponding portion for attaching the first and second skin sections;
- wherein at least one of said corresponding portions includes a recessed area adapted to matingly receive the exterior surface of at least one of the plurality of tabs;
- wherein at least one of the plurality of tabs includes a protrusion extending substantially orthogonally from the exterior surface thereof;
- and
- wherein the protrusion forms a lip disposed on a distal end of the at least one tab.
4 more elements
Dependencies are inferred from the claim text.