Composite material structure
View Patent ↗A laminated composite material structure, in the form of a load-bearing rib of a wing of an aircraft, comprises an upper laminated portion, which is angled with respect to a middle laminated portion, and a curved corner portion being continuous with and interposed between the upper and middle portions. (The rib has a curve that connects the upper and middle portions, which are perpendicular or transverse to each other). The corner portion is in the form of a kinked portion or joggled, that is, the portion includes two regions of positive curvature (concave regions) and a region of negative curvature (convex region) interposed therebetween, whereby the formation or propagation of delaminations or cracks at the bend between the middle and upper portions, due to fuel pressure loading and low through-thickness strength, may be reduced.
1. A laminated composite material structure for forming a part of an aircraft, the structure comprising first and second laminated portions angled with respect to each other and a third laminated portion being continuous with and interposed between the first and second laminated portions, wherein the third laminated portion includes at least one unsupported region of positive curvature and at least one unsupported region of negative curvature for increasing flexibility of said third laminated portion.
2. A structure according to claim 1 , wherein at least one of the regions of curvature has a cross-section in the form of an arc having a substantially constant radius of curvature.
3. A structure according to claim 1 , wherein the third portion includes a first region of curvature positioned between second and third regions of curvature of the opposite sign to that of the first region of curvature.
4. A structure according to claim 1 , wherein the first and second laminated portions are transverse to each other.
5. A structure according to claim 1 , wherein the direction at any point along the notional route described by the third portion moving from the first portion to the second portion includes a positive component in the direction from the boundary between the first and third portions to the boundary between the third and second portions.
6. A structure according to claim 1 , wherein the structure is a load bearing structure.
7. A structure according to claim 1 , wherein the first portion of the structure forms at least a part of the portion of a rib for a wing of an aircraft, the portion of the rib being attachable to a wing skin of an aircraft.
8. An aircraft wing structure including a structure as claimed in claim 1 .
9. An aircraft including an aircraft wing structure as claimed in claim 8 .