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A vessel, such as a wing-integrated aircraft fuel tank. The vessel can include a first surface portion, a second surface portion spaced apart from the first surface portion, and a core positioned between the first and second surface portions. The core can be sealably connected to the first and secon

A vessel, such as a wing-integrated aircraft fuel tank. The vessel can include a first surface portion, a second surface portion spaced apart from the first surface portion, and a core positioned between the first and second surface portions. The core can be sealably connected to the first and second surface portions and can be positioned to carry a load from at least one of the first and second surface portions to the other. The core can include a plurality of cells separated by cell walls, at least some of which have wall openings positioned to provide liquid communication between adjacent cells.

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1. An airfoil, comprising:a first surface portion; a second surface portion spaced apart from the first surface portion; a core positioned between the first and second surface portions, the core being sealably connected to the first and second surface portions and positioned to carry a load from at

1. An airfoil, comprising:a first surface portion; a second surface portion spaced apart from the first surface portion; a core positioned between the first and second surface portions, the core being sealably connected to the first and second surface portions and positioned to carry a load from at least one of the first and second surface portions to the other, the core including an aft portion, a forward portion, and a plurality of cells separated by cell walls, at least some of the cell walls having wall openings positioned to provide liquid communication between adjacent cells, the at least some of the cell walls having a first portion proximate to the first surface portion, a second portion proximate to the second surface portion, and a third portion between the first and second portions, the first, second, and third portions having at least one wall opening; and a collection chamber in the airfoil and positioned inboard the core to collect fluid flowing in a spanwise direction through the aft and forward portions of the core. 2. The airfoil of claim 1 wherein the cells have cell openings extending along cell axes generally transverse to at least one of the first and second surface portions.3. The airfoil of claim 1 wherein the core is generally rigid in a direction generally transverse to at least one of the first and second surface portions.4. The airfoil of claim 1 wherein the core is configured to contain aircraft fuel.5. The airfoil of claim 1 wherein the first surface portion and the second surface portion form part of an aircraft wing.6. The airfoil of claim 1 wherein the first surface portion, the second surface portion and the core form at least part of a vehicle fuel tank.7. The airfoil of claim 1 wherein the first surface portion, the second surface portion and the core form at least part of a fuel tank.8. The airfoil of claim 1 wherein the first surface portion, the second surface portion and the core form at least a portion of a fuel-tight volume, and wherein the vessel further comprises a fuel port in liquid communication with the fuel-tight volume.9. The airfoil of claim 1 wherein the wall openings have a diameter approximately 0.125 inch or greater.10. The airfoil of claim 1 wherein the core cells have a width generally transverse to at least one of the first and second surface portions, and wherein the wall openings have a diameter of approximately one quarter of the width or greater.11. An airfoil, comprising:a first wing portion having a first external surface and a first internal surface; a second wing portion having a second external surface and a second internal surface, the second internal surface being spaced apart from the first internal surface; a core positioned between the first and second wing portions, the core being sealably connected to the first and second wing portions to form a fuel volume, the core being positioned to carry a load from at least one of the first and second wing portions to the other, the core including an outboard portion, an inboard portion, an aft portion, a forward portion, and a plurality of cells separated by cell walls, at least some of the cell walls having wall openings positioned to provide liquid communication between adjacent cells, the wall openings being sized and configured such that fuel flow through the wall openings from the outboard portion to the inboard portion provides sufficient fuel for operation of an aircraft engine, wherein at least some of the cells in the aft portion are in fluid communication with at least some of the cells in the forward portion during the course of normal engine operation; and a fuel port in liquid communication with the fuel volume, the fuel port being coupleable to the aircraft engine. 12. The airfoil of claim 11, wherein the fuel port and the openings of the cell walls are sized to provide a fuel flow rate sufficient to power the aircraft engine at all power settings.13. The airfoil of claim 11 wherein the core, the first wing portion and the second wing panel portion form at least part of a fuel-tight volume.14. The airfoil of claim 11 wherein the core is generally rigid in a direction generally transverse to at least one of the first and second wing portions.15. The airfoil of claim 11 wherein the core is adhesively bonded to the first and second wing portions.16. The airfoil of claim 11 wherein the first and second wing portions are spaced apart from each other by distance of about 12 inches or less.17. The airfoil of claim 11 wherein the core includes a first core portion attached to the first wing portion, a second core portion attached to the second wing portion and a septum positioned between the first and second wing portions.18. The airfoil of claim 11 wherein the core includes a plurality of generally similar adjacent cells.19. The airfoil of claim 11, further comprising:an inboard side connected between the first and second wing portions; and an outboard side portion connected between the first and second wing panel portions and spaced apart from the inboard side panel portion. 20. The airfoil of claim 11, further comprising the aircraft engine carried by the first and/or second wing portion.21. An airfoil, comprising:a first wing portion having a first external surface and a first internal surface; a second wing portion having a second external surface and a second internal surface, the second internal surface being spaced apart from the first internal surface; a core positioned between the first and second wing portions, the core being sealably connected to the first internal surface and the second internal surface to form a fuel-tight volume, the core being positioned to carry a load from at least one of the first and second wing portions to the other, the core including an outboard portion, an inboard portion, an aft portion, a forward portion, and a plurality of at least generally similarly sized and shaped cells separated by cell walls, at least some of the cell walls having wall openings positioned to provide liquid communication between adjacent cells, the wall openings being sized and configured such that fuel flow through the wall openings from the outboard portion to the inboard portion provides sufficient fuel for operation of an aircraft engine; a collection chamber in the airfoil and positioned inboard the core to collect fluid flowing in a spanwise direction through the aft and forward portions of the core; and a fuel port in liquid communication with the collection chamber, the fuel port being coupleable to the aircraft engine. 22. The airfoil of claim 21 wherein the core includes at least one of a titanium, titanium alloy, aluminum, aluminum alloy and carbon fiber reinforced epoxy material.23. The airfoil of claim 21, further comprising:a first intermediate panel positioned between the first and second wing panel portions; and a second intermediate panel positioned between the first and second wing panel portions and spaced apart from the first intermediate panel, the first and second intermediate panels being sealably connected to the core. 24. The airfoil of claim 21, further comprising the aircraft engine carried by the first and/or second wing portion.25. An aircraft, comprising:a fuselage; a wing coupled to the fuselage, wherein the wing includes: a first surface portion; a second surface portion spaced apart from the first surface portion; a core positioned between the first and second surface portions, the core being sealably connected to the first and second surface portions to form at least part of a fuel-tight volume, the core being positioned to carry a load from at least one of the first and second surface portions to the other, the core including an aft portion, a forward portion, a plurality of cells separated by cell walls, at least some of the cell walls having wall openings positioned to provide liquid communication between adjacent cells, the at least some of the cell walls having a first portion proximate to the first surface portion, a second portion proximate to the second surface portion, and a third portion between the first and second portions, the first, second, and third portions having at least one wall opening, wherein at least some of the cells in the aft portion are in fluid communication with at least some of the cells in the forward portion during the course of normal engine operation; and fuel port in liquid communication with the fuel volume; at least one engine coupled to at least one of the wing and the fuselage; and a fuel conduit coupled between the fuel port and the at least one engine. 26. The aircraft of claim 25, further comprising:a first intermediate panel positioned between the first and second surface portions; and a second intermediate panel positioned between the first and second surface portions and spaced apart from the first intermediate panel, the first and second intermediate panels being sealably connected to the core. 27. The aircraft of claim 25, further comprising a fuel collection chamber in liquid communication with the core, wherein the fuel port is positioned in a wall of the fuel collection chamber.28. The airfoil of claim 25, the core includes at least one of a titanium, titanium alloy, aluminum, aluminum alloy and carbon fiber reinforced epoxy material.29. A method for using an aircraft wing, comprising:disposing aircraft fuel in a fuel volume defined at least in part by an upper wing panel portion, a lower wing panel portion and a core sealably positioned between the upper and lower wing panel portions; applying aerodynamic loads to at least one of the upper and lower wing panel portions; transferring the aerodynamic loads from the at least one wing panel portion to the other through the core while the core remains at least approximately stationary relative to the upper and lower wing panel portions; passing the aircraft fuel from a first plurality of cells in the core to a second plurality of cells in the core through openings in walls between adjacent cells, the walls having a first portion proximate to the upper wing panel portion, a second portion proximate to the lower wing panel portion, and a third portion between the first and second portions, the first, second, and third portions having at least one opening; and collecting aircraft fuel passing in a spanwise direction through aft and forward portions of the core in a collection chamber positioned in the wing and inboard the core. 30. The method of claim 29, further comprising conveying the fuel to an aircraft engine.31. The method of claim 29, further comprising inspecting the core without opening an access panel in any of the upper and lower wing panel portions.32. The method of claim 29, wherein passing the aircraft fuel includes passing the aircraft fuel through the openings in the first, second, and third portions.