发明名称 STRUCTURAL ARRANGEMENT AND METHOD OF FABRICATING A COMPOSITE TRAILING EDGE CONTROL SURFACE
摘要 The present disclosure is generally directed to a composite trailing edge control surface including a contiguous one-piece composite control surface skin wrapped around a plurality of stiffening cores, a plurality of hinge fittings, and a plurality of substantially parallel ribs. The contiguous one-piece composite control surface skin provides a control surface on opposing sides of the trailing edge control surface and substantially distributes bending, shear and torsion loads of the trailing edge control surface to the plurality of hinge fittings and the plurality of substantially parallel ribs. A method of manufacturing the trailing edge control surface includes positioning a contiguous one-piece composite control surface skin on a substantially flat tool. A plurality of stiffener cores having a plurality of thin covering skins are positioned on the contiguous one-piece composite control surface skin and are cured to create a laminate sandwich composite structure skin that is trimmed and has fastener apertures and hinge fitting access apertures provided there-through.
申请公布号 EP3126125(A2) 申请公布日期 2017.02.08
申请号 EP20150744717 申请日期 2015.01.12
申请人 The Boeing Company 发明人 REUSCH, David C.
分类号 B29C70/30;B64C1/00;B64C3/20;B64C9/02;B64C9/16;B64F5/00 主分类号 B29C70/30
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