AIRCRAFT STRUCTURE WITH STRUCTURAL NON-FIBER REINFORCING BONDING RESIN LAYER
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Abstract
The present invention regards an aircraft structure comprising an aerodynamic composite shell (7), the interior face (9) of which in whole or in part is bonded with at least one two- or three-dimensional structural composite part (11) by means of a bonding material (15). It also regards a method of manufacture of the aircraft structure. The bonding material (15) comprises a non-structural fiber reinforced resin system, wherein at least one portion of the bonding material, which portion spatially corresponds with an interior face filling volume (21), is thicker than other portions of the bonding material (15), due to settlement of resin of the non-structural fiber reinforced resin system in said interior face filling volume (21) during the viscous phase of the curing of the non-structural fiber reinforced resin system.
8 Citations
30 Claims
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1-14. -14. (canceled)
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15. An aircraft structure comprising an aerodynamic composite shell (7), the interior face (9) of which in whole or in part is bonded with at least one two- or three-dimensional structural composite part (11) via a bonding material (15), wherein the bonding material (15) is a wide spread layer having various thickness and within the range of about at least 50 cm2 to 50 m2, comprising a structural resin system not having structural fibers;
- and wherein at least one portion of the bonding material, which portion spatially corresponds with an interior face filling volume (21), is thicker than other portions of the bonding material (15) due to settlement of resin of the structural resin system not having structural fibers in said interior face filling volume (21) during the viscous phase of the curing of the structural resin system not having structural fibers.
- View Dependent Claims (16, 17, 18, 19, 20, 21)
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22. A method of manufacturing an aircraft structure (2) comprising an aerodynamic composite shell (7), the interior face (9) of which in whole or in part is bonded with at least one two- or three-dimensional structural composite part (11) via a bonding material (15) that is a wide spread layer having various thickness and within the range of about at least 50 cm2 to 50 m2 in the form of a structural resin system not having structural fibers, a first resin substrate of the aerodynamic composite shell (7) and a second resin substrate of the structural composite part (11) cure at a temperature higher than the temperature at which a third resin substrate of the bonding material (15) cures, the method comprising the steps of:
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forming the first and second resin substrate into an uncured aerodynamic composite shell (7) and an uncured structural composite part (11); applying an uncured bonding material (15) onto at least one of the interior face (9) or the surface (10) of the uncured structural composite part (11) facing the interior face (9); applying the uncured structural composite part (11) to the interior face (9) of the uncured aerodynamic shell (7); and integrally co-curing the first resin substrate, the second resin substrate, the third resin substrate in one cure cycle, in such way that the third resin during the viscous phase freely flows into an interior face filling volume (21) defined between the interior face (9) and part surface (10), and following temperature increase provides curing of the third resin before curing of the first and second resin substrates. - View Dependent Claims (23, 24, 25, 26, 27, 28, 29, 30)
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Specification