Composite laminate with self-healing layer
a self-healing layer and composite laminate technology, applied in the direction of synthetic resin layered products, transportation and packaging, chemistry apparatus and processes, etc., can solve the problems of global failure of secondary structure, and crack propagation and follow a path which cannot be previously determined
Inactive Publication Date: 2013-08-15
AIRBUS OPERATIONS LTD
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Benefits of technology
The self-healing laminate effectively arrests crack propagation, enhancing safety, simplifying certification, and maintaining structural integrity by resisting crack propagation without degrading the mechanical performance of the composite structure.
Problems solved by technology
Due to fatigue loading, cracks will propagate and follow a path which cannot be previously determined.
This will cause a global failure of the secondary structure 41, which will stop its collaboration with the primary structure 40.
This scenario can either cause global failure of secondary structure 41 or partially reduce its capability.
This scenario is not acceptable since it leads to catastrophic failure of the primary structure 40 and therefore must be avoided.
According to Trask et al, the incorporation of HGF as discrete plies was deemed unsuitable for CFRP laminates as it would effectively produce a hybrid glass-carbon laminate and result in a significant reduction to their outstanding mechanical properties.
Method used
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[0037]The composite laminate structure shown in FIG. 2 comprises a primary structure 1 and a secondary structure 2 joined at a bond line 14. Each structure 1, 2 is formed by assembling a stack of plies of composite material. Each ply of composite material comprises a plurality of reinforcement fibres embedded within a matrix. An exemplary ply 3 is shown in FIG. 3. In this case the ply 3 is a so-called “prepreg” with a single layer of unidirectional carbon fibres 4 impregnated with a partially cured epoxy resin matrix 5. For ease of illustration the fibres 4 in the figures are all shown directed in an out of the page. However in practice the direction of the fibres can vary through the stack to give desired mechanical properties to the stack.
[0038]FIG. 4 shows how the primary structure 1 is formed. A stack of N plies of composite material is laid onto a table 50 in a stacking sequence including a first ply (i=1) at the bottom of the stacking sequence and an Nth ply (i=N) at the top....
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A composite structure comprising: a first stack comprising a plurality of plies of composite material and at least one ply of self-healing material, the ply of self-healing material comprising a plurality of containers each containing a curable healing liquid; and a second stack comprising a plurality of plies of composite material, the stacks being joined together at a bond line. By placing a ply of self-healing material in one of the stacks (preferably relatively close to the bond line) the ply of self-healing material can resist the propagation of cracks between the first stack and the second stack. Preferably the global strength of the first stack is greater than the global strength of the second stack.
Description
FIELD OF THE INVENTION[0001]The present invention relates to a composite laminate structure, and a method of forming a joint between a pair of composite structures.BACKGROUND OF THE INVENTION[0002]FIG. 1a shows a bonded joint between a primary structure 40 and a secondary structure 41. Due to fatigue loading, cracks will propagate and follow a path which cannot be previously determined. Three different scenarios may be identified.[0003]The crack 43b propagates through the secondary structure 41, parallel to the bond line 42 (FIG. 1b). This will cause a global failure of the secondary structure 41, which will stop its collaboration with the primary structure 40. Generally this scenario is not catastrophic. If a fail-safe design philosophy is employed, failure of the secondary structure 41 will not generate global failure of the structure, which remains capable of withstanding the external loads.[0004]The crack 43c propagates toward the external surface of secondary structure 41 and e...
Claims
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IPC IPC(8): B32B5/14B32B27/04
CPCB32B5/28B32B5/14Y10T156/10Y10T428/2495B32B27/04B32B5/12B32B5/22B32B5/26B32B7/12B32B2260/021B32B2260/046B32B2262/101B32B2262/106B32B2307/50B32B2307/762B32B2250/20Y10T428/249953Y10T428/24994Y10T428/249945Y10T428/249997Y10T428/24995Y10T428/24996Y10T428/249946
InventorCOSENTINO, ENZO
OwnerAIRBUS OPERATIONS LTD