Wing cover panel assembly and wing cover panel for an aircraft wing and a method of forming thereof

1. A wing cover panel assembly for an aircraft wing comprising:

a wing cover panel having an aerofoil surface on one side for providing an aerofoil surface for a wing and a continuous attachment surface on the other side for providing one or more attachment points for one or more wing structural elements;

a pair of opposing lugs formed in said continuous attachment surface so as to provide a locating channel in said attachment surface; and

a wing structural element having a first flange and a second flange each arranged to be captured within said locating channel by respective said pair of opposing lugs so as to fix said wing structural element to said wing cover panel to form said wing cover panel assembly, and

wherein said wing structural element is freeze fitted within said locating channel.

2. A wing cover panel assembly according to claim 1 in which said first flange and said second flange each is fitted to respective one of said pair of opposing lugs.

3. A wing cover panel assembly according to claim 1 in which said attachment surface further comprises a seat disposed generally opposite said lug within said channel, said seat being arranged as a bearing surface for a first portion of said flange captured within said channel and to hold a remaining second portion of said flange away from said attachment surface.

4. A wing cover panel assembly according to claim 1 in which a bonding layer is provided between said wing structural element and said attachment surface.

5. A wing cover panel assembly according to claim 1 in which the pair of opposing lugs form said locating channel by providing opposing grooves, said opposing grooves each having a tapered depth so as to provide clamping effect on the respective one of said first and second flanges.

6. A wing cover panel assembly according to claim 1 in which said wing structural element is a stringer.

7. A wing cover panel assembly according to claim 1 in which said wing structural element is a spar.

8. A wing cover panel assembly according to claim 1 in which said wing cover panel is integrally formed with said locating channel.

9. A wing cover panel assembly according to claim 1 in which said wing cover panel is formed from one or more sub-panels.

10. A wing cover panel for an aircraft wing comprising:

a wing cover panel having an aerofoil surface on one side for providing an aerofoil surface for a wing and a continuous attachment surface on the other side for providing one or more attachment points for one or more wing structural elements; and

a pair of opposing lugs formed in said continuous attachment surface so as to provide a locating channel in said attachment surface, said locating channel being arranged to capture a first flange and a second flange of a wing structural element so as to fit said wing structural element to said wing cover panel, and

wherein said wing structural element is freeze fitted within said channel.

11. A method of forming a wing cover panel assembly for an aircraft wing, said method comprising the steps of:

a) forming a wing cover panel having an aerofoil surface on one side for providing an aerofoil surface for a wing and an attachment surface on the other side for providing one or more attachment points for one or more wing structural elements;

b) forming a pair of opposing lugs in said attachment surface so as to provide a locating channel in said attachment surface;

c) locating a first flange and a second flange of a wing structural element within said locating channel by capturing said flanges within respective said opposing lugs; and

d) freeze fitting said wing structural element within said channel so as to fit said wing structural element to said wing cover panel to form said wing cover panel assembly.

12. A method according to claim 11 in which said first flange and said second flange each is fastened to respective one of said opposing lugs.

13. A method according to claim 11 in which said attachment surface further comprises a seat disposed generally opposite said lug within said channel, said seat being arranged as a bearing surface for a first portion of said flange captured within said channel and to hold a remaining second portion of said flange away from said attachment surface.

14. A method according to claim 11 in which a bonding layer is provided between said wing structural element and said attachment surface.

15. A method according to claim 11 in which the pair of opposing lugs form said locating channel by providing opposing grooves, said opposing grooves having a tapered depth so as to provide clamping effect on the respective one of said first and second flanges.

16. A method according to claim 11 in which said wing structural element is a stringer.

17. A method according to claim 11 in which said wing structural element is a spar.

18. A method according to claim 11 in which said wing cover panel is integrally formed with said locating channel.

19. A method according to claim 11 in which said wing cover panel is formed from one or more sub-panels.