Wingbox with fuel tank attached to ribs
An aircraft wingbox assembly is disclosed having a wingbox including 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; and a fuel tank in the wingbox. All or part of the fuel tank is located in a first one of the bays between a first one of the ribs and a second one of the ribs. The fuel tank includes a tank wall and first and second tank lugs extending from the fuel tank wall. A first fastener attaches the first tank lug to the first one of the ribs; and a second fastener attaches the second tank lug to the second one of the ribs.
1. An aircraft wingbox assembly, comprising:
a wingbox comprising an upper cover, a lower cover and a pair of spars;
a plurality of ribs in the wingbox,
wherein the plurality of ribs divide the wingbox into bays;
a fuel tank in the wingbox, wherein all or part of the fuel tank is located in a first one of the bays between a first one of the ribs and a second one of the ribs,
the fuel tank comprising a tank wall and first and second tank lugs extending from the fuel tank wall,
wherein the first tank lug is located in the first one of the bays between the first one of the ribs and the second one of the ribs;
a first fastener attaching the first tank lug to the first one of the ribs;
a second fastener attaching the second tank lug to the second one of the ribs; and
wherein the first or second one of the ribs comprises a rib hole, and the rib hole and the fuel tank are configured to enable one or both of the first and second tank lugs to pass through the rib hole.
2. An aircraft wingbox assembly according to claim 1 , wherein the rib hole and the fuel tank are configured to enable both of the first and second tank lugs to pass through the rib hole.
3. An aircraft wingbox assembly according to claim 1 , wherein the fuel tank extends through the first one of the ribs and the second one of the ribs; a first part of the fuel tank is located in the first one of the bays; a second part of the fuel tank is located in a second one of the bays; and a third part of the fuel tank is located in a third one of the bays.
4. An aircraft wingbox assembly according to claim 3 , wherein the tank wall extends continuously through the first, second and third ones of the bays.
5. An aircraft wingbox assembly according to claim 1 , wherein each of the ribs comprises a rib web, and rib feet attaching the rib to the upper and lower covers; the first tank lug is attached to the rib web of the first one of the ribs or to a rib foot of the first one of the ribs; and the second tank lug is attached to the rib web of the second one of the ribs or to a rib foot of the second one of the ribs.
6. An aircraft wingbox assembly according to claim 1 , wherein the first one of the ribs comprises a first rib lug; the second one of the ribs comprises a second rib lug; the first fastener attaches the first tank lug to the first rib lug; and the second fastener attaches the second tank lug to the second rib lug.
7. An aircraft wingbox assembly according to claim 1 , wherein the first and second tank lugs are spaced apart along a length of the fuel tank, or the first and second tank lugs are spaced apart across a width of the fuel tank.
8. An aircraft wingbox assembly according to claim 1 , wherein the fuel tank is a hydrogen fuel tank.
9. An aircraft wingbox assembly according to claim 1 , wherein the fuel tank contains a fuel which is a pressurised gas or a cryogenically cooled liquid.
10. An aircraft wingbox assembly according to claim 1 , wherein the first and second tank lugs are retractable.
11. An aircraft wingbox assembly according to claim 1 , wherein the pair of spars extend in a spanwise direction; and the bays are spaced apart in the spanwise direction.
12. An aircraft wingbox assembly according to claim 1 , wherein the fuel tank wall is rigid.
13. A method of assembling an aircraft wingbox assembly according to claim 1 , the method comprising: installing the fuel tank so that at least part of the fuel tank is located in the first one of the bays; attaching the first one of the tank lugs to the first one of the ribs with the first fastener; and attaching the second one of the tank lugs to the second one of the ribs with the second fastener.
14. A method according to claim 13 wherein during the installing, the tank lugs are carried by the fuel tank wall.
15. A method according to claim 13 , wherein during the installing, one or both of the tank lugs passes through the first one of the ribs and/or through the second one of the ribs.
16. A method according to claim 13 , wherein during the installing, the fuel tank passes through the first one of the ribs and/or through the second one of the ribs.
17. A method according to claim 13 , wherein the fuel tank has a length, and during the installing, the fuel tank is moved along its length, and then rotated or moved laterally to bring the tank lugs to fastening positions.
18. An aircraft wingbox assembly according to claim 1 , wherein the first fastener is directly attaching the first tank lug to the first one of the ribs; and the second fastener is directly attaching the second tank lug to the second one of the ribs.
19. An aircraft wingbox assembly, comprising:
a wingbox comprising an upper cover, a lower cover and a pair of spars;
a plurality of ribs in the wingbox, wherein the plurality of ribs divide the wingbox into bays;
a fuel tank in the wingbox, wherein all or part of the fuel tank is located in a first one of the bays between a first one of the ribs and a second one of the ribs, the fuel tank comprising a tank wall and first and second tank lugs extending from the fuel tank wall; a first fastener attaching the first tank lug to the first one of the ribs;
a second fastener attaching the second tank lug to the second one of the ribs, and
wherein a lower half of the fuel tank carries the tank lugs and an upper half of the fuel tank is free of tank lugs and free of other attachment features.