Manufacturing procedure of a part made out of a composite material introducing a geometric change in one of its faces
A manufacturing procedure of a composite material part ( 11 ), with an edge region ( 13 ) destined to be joined to another part by rivets, making a change in the geometry of said edge region ( 13 ) with respect to an initial surface ( 41 ) on the part's external face, comprising the following steps: a) providing a laying-up tool incorporating a modified surface ( 43 ) according to said change in the edge region ( 13 ) geometry; b) providing the composite material plies needed for the laying-up of the part, with the plies ( 51, 51′, . . . , 51 n ) destined for the edge region ( 13 ) of the part affected by the geometric modification being already cut so that they finish as they reach said modified surface ( 43 ); c) laying-up said plies over said tool and curing the resultant laminate. The invention also refers to a lower skin of an aircraft wing ( 11 ) manufactured according to said procedure.
1. A manufacturing procedure of a first composite material part with an edge region destined to be joined to a second part by rivets, the first part defining a curved external face, the procedure comprising steps of:
a) providing a laying-up tool incorporating a surface according to a predetermined geometry of the edge region, wherein a middle line extending substantially along a vertical center of the surface is aligned along a chord of the first part;
b) providing composite material plies with a respective length according to a cutting trajectory, wherein the definition of the cutting trajectory of the plies destined to the area of the first part is done by calculating the intersection of said surface with hypothetical surfaces, each hypothetical surface being substantially parallel to the curved external face; and
c) laying up the composite material plies over said tool and curing the resultant laminate.
2. A manufacturing procedure according to claim 1 , wherein said hypothetical surfaces save the first are extending offset from the external face at a distance which corresponds to the thickness of the plies laid-up previously to each of them.
3. A manufacturing procedure according to claim 2 , wherein said first part is the lower skin of an aircraft wing, wherein the second part includes a union plate and a counter plate, and wherein the second part is also joined to a lower panel of a wing central box at a position away from the first part.
4. A manufacturing procedure according to claim 1 , wherein said first part is the lower skin of an aircraft wing, wherein the second part includes a union plate and a counter plate, and wherein the second part is also joined to a lower panel of a wing central box at a position away from the first part.
5. A manufacturing procedure according to claim 1 , wherein said first part is the lower skin of an aircraft wing, wherein the second part includes a union plate and a counter plate, and wherein the second part is also joined to a lower panel of a wing central box at a position away from the first part.
6. A manufacturing procedure according to claim 5 , wherein the predetermined geometry in said edge region is a beveled surface.
7. A manufacturing procedure according to claim 6 , wherein in step a) said surface is defined so that the following conditions are satisfied:
to facilitate the alignment of an intersection of middle lines of the lower wing skin and the lower panel of the central box along a chord of the lower wing skin, wherein the middle lines extend substantially along a vertical center of the lower wing skin and lower panel of the central box, respectively; and
to be smooth enough to avoid producing cutting angles of the plies smaller than 8° with respect to the orientation of their fibers.
8. A lower skin of an aircraft wing characterized by the fact that it is manufactured according to the procedure of claim 5 .
9. A lower skin of an aircraft wing characterized by the fact that it is manufactured according to the procedure of claim 6 .
10. A lower skin of an aircraft wing characterized by the fact that it is manufactured according to the procedure of claim 7 .