Methods for manufacturing an i-stringer of an aircraft and devices for use in such methods
First Claim
1. A method for manufacturing a reinforced composite structure for an aircraft, the method comprising the steps of:
- forming a composite material layout by arranging a first composite material ply overlying a second composite material ply and positioning a pre-cured cap insert on the first composite material ply;
advancing the composite material layout through a cap-forming device, wherein the advancing results in a preformed cap section, a first length of the composite material layout and a second length of the composite material layout;
removing the composite material layout from the cap-forming device;
arranging the preformed cap section of the composite material layout within a cavity of a flexible mandrel with a foot portion of the first length and a foot portion of the second length remaining outside the cavity of the flexible mandrel;
contacting the foot portion of the first length and the foot portion of the second length with a skin structure; and
heating and pressurizing the composite material layout using the flexible mandrel to cure the composite material layout and form the reinforced composite structure affixed to the skin structure.
1 Assignment
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Accused Products
Abstract
Methods for manufacturing a reinforced composite structure for an aircraft and devices used in such methods are provided. A method includes advancing a composite material layout through a cap-forming device. The advancing results in a preformed cap section, a first length of the layout and a second length of the layout. The layout is removed from the cap-forming device and the preformed cap section of the layout is arranged within a cavity of a flexible mandrel with a foot portion of the first length and a foot portion of the second length remaining outside the cavity of the flexible mandrel. The foot portion of the first length and the foot portion of the second length contact a skin structure. The layout is heated and pressurized using the flexible mandrel to cure the layout and form the reinforced composite structure affixed to the skin structure.
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Citations
14 Claims
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1. A method for manufacturing a reinforced composite structure for an aircraft, the method comprising the steps of:
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forming a composite material layout by arranging a first composite material ply overlying a second composite material ply and positioning a pre-cured cap insert on the first composite material ply; advancing the composite material layout through a cap-forming device, wherein the advancing results in a preformed cap section, a first length of the composite material layout and a second length of the composite material layout; removing the composite material layout from the cap-forming device; arranging the preformed cap section of the composite material layout within a cavity of a flexible mandrel with a foot portion of the first length and a foot portion of the second length remaining outside the cavity of the flexible mandrel; contacting the foot portion of the first length and the foot portion of the second length with a skin structure; and heating and pressurizing the composite material layout using the flexible mandrel to cure the composite material layout and form the reinforced composite structure affixed to the skin structure. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14)
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Specification