Composite wing and manufacturing process thereof
First Claim
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1. A forwardly swept composite wing for an aircraft comprising:
- a plurality of discrete elongated hollow one-piece composite spars having hollow interiors, respectively, extending from wing root to wing tip, said spars being arranged in juxtaposed generally parallel relation in an array defining an airfoil, each of said spars having at least one surface defining a portion of the airfoil and a vertical surface, said spars being arranged so as to present said vertical surfaces to one another in close juxtaposed relation, and a composite skin bonded to the one surface of each of said spars, said composite skin being reinforced by fibers wound about said spar assembly at a forwardly swept angle of approximately 12°
to a laterally extending central axis of the wing to minimize aeroelastic divergence of said wing.
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Abstract
A composite wing for an aircraft comprises a plurality of elongated hollow one-piece composite spars arranged in juxtaposed generally parallel relation in an array defining an airfoil with a composite skin disposed about said assembled spars.
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Citations
1 Claim
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1. A forwardly swept composite wing for an aircraft comprising:
a plurality of discrete elongated hollow one-piece composite spars having hollow interiors, respectively, extending from wing root to wing tip, said spars being arranged in juxtaposed generally parallel relation in an array defining an airfoil, each of said spars having at least one surface defining a portion of the airfoil and a vertical surface, said spars being arranged so as to present said vertical surfaces to one another in close juxtaposed relation, and a composite skin bonded to the one surface of each of said spars, said composite skin being reinforced by fibers wound about said spar assembly at a forwardly swept angle of approximately 12°
to a laterally extending central axis of the wing to minimize aeroelastic divergence of said wing.
Specification
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Current AssigneeWilliams International Company LLC
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Original AssigneeWilliams International Company LLC
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InventorsWilliams, Sam B.
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Primary Examiner(s)Huppert, Michael S.
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Assistant Examiner(s)BIDWELL, ANNE
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Application NumberUS07/894,455Time in Patent Office781 DaysField of Search244/123, 244/124, 244/117 R, 416/226, 416/229 R, 416/232, 416/233US Class Current244/123.3CPC Class CodesB29C 70/446 Moulding structures having ...B29D 99/0025 Producing blades or the lik...B29L 2031/3085 WingsB64C 3/20 Integral or sandwich constr...Y02T 50/40 Weight reduction
