Wingbox with removable fuel tank
An aircraft wingbox assembly is disclosed having a wingbox with an upper cover, a lower cover and a pair of spars; a plurality of ribs in the wingbox. The ribs divide the wingbox into bays. A fuel tank is in a first one of the bays. One of the spars includes a spar hole which is configured to enable the fuel tank to be removed from the first one of the bays through the spar hole.
1. An aircraft wingbox assembly, comprising:
a wingbox with an upper cover,
a lower cover and a pair of spars;
a plurality of ribs in the wingbox, wherein the ribs divide the wingbox into bays;
a fuel tank in a first one of the bays, wherein one of the spars comprises a spar hole which is configured to enable the fuel tank to be removed from the first one of the bays through the spar hole; and,
wherein each of the ribs is attached to both of the covers and to both of the spars.
2. The aircraft wingbox assembly according to claim 1 , further comprising a door covering the spar hole; and fasteners attaching the door to the spar.
3. The aircraft wingbox assembly according to claim 1 , wherein the first one of the bays is between a first one of the ribs and a second one of the ribs.
4. The aircraft wingbox assembly according to claim 1 , wherein the fuel tank comprises a tank wall and first and second tank lugs extending from the fuel tank wall; and the assembly further comprises: a first fastener attaching the first tank lug to the first one of the ribs; and a second fastener attaching the second tank lug to the second one of the ribs, wherein the fuel tanks and the spar hole are configured to enable the fuel tank including both of the tank lugs to pass through the spar hole.
5. The aircraft wingbox assembly according to claim 1 , wherein the fuel tank is a hydrogen fuel tank.
6. The aircraft wingbox assembly according to claim 1 , wherein the fuel tank comprises a rigid tank wall.
7. The aircraft wingbox assembly according to claim 1 , wherein the fuel tank contains a fuel which is a pressurised gas or a cryogenically cooled liquid.
8. The aircraft wingbox assembly according to claim 1 , wherein the spars are spaced apart in a chordwise direction, and a length of the fuel tank extends in the chordwise direction.
9. The aircraft wingbox assembly according to claim 1 , wherein the spars extend in a spanwise direction; and the bays are spaced apart in the spanwise direction.
10. The aircraft wingbox assembly according to claim 1 , wherein the fuel tank is a first fuel tank; the pair of spars comprise a forward spar and a rear spar; and the assembly further comprises: a fuel cell; a first fuel line coupling the first fuel tank to the fuel cell; a second fuel tank in a second one of the bays; and a second fuel line coupling the second fuel tank to the fuel cell, wherein the first fuel line is located behind the rear spar and the second fuel line is located in front of the front spar.
11. A method of disassembling the aircraft wingbox assembly according to claim 1 , the method comprising: removing the fuel tank from the first one of the bays through the spar hole.
12. The method according to claim 11 , further comprising removing a door covering the spar hole.
13. The method according to claim 11 , wherein the fuel tank is attached to the wingbox or to one or more of the ribs by one or more fasteners, and the method further comprises inserting a tool into the first one of the bays, and disengaging the fastener(s) with the tool.
14. The method according to claim 11 , wherein the fuel tank has a length, and the fuel tank moves along its length as it is removed through the spar hole.
15. The method according to claim 11 , wherein the fuel tank comprises a fuel tank wall which is not collapsed before the fuel tank is removed.
16. An aircraft wing comprising the aircraft wingbox assembly according to claim 1 .
17. An aircraft comprising the aircraft wingbox assembly according to claim 1 .
18. A spar of the aircraft wingbox of claim 1 , the spar comprising:
a spar web; a spar flange;
a spar hole in the spar web, wherein the spar hole is sized to enable a fuel tank to be removed through the spar hole; and,
wherein the spar hole has an edge which is circular, elliptical, oval, or polygonal.
19. The spar according to claim 18 , further comprising a door covering the spar hole; and fasteners attaching the door to the spar.
20. The spar according to claim 18 , wherein said spar flange comprises an upper spar flange for attaching the spar to an upper cover of the aircraft wingbox, and the spar further comprises a lower spar flange for attaching the spar to a lower cover of the aircraft wingbox.