发明名称 FUSELAGE MANDREL INSERT AND METHOD
摘要 The present invention relates to an apparatus used for forming a composite structure around a mandrel. A generally flexible pneumatic tool and a generally rigid insert are inserted end to end in a cavity of the mandrel. A first end of the insert is positioned in the cavity to be adjacent to the pneumatic tool, and defines an interface therebetween. The retainer is connected to the insert proximate the first end of the insert. The retainer has an end that extends outwardly from the first end of the insert across the interface and over a portion of the end of the pneumatic tool. The uppermost surfaces of the insert, retainer, and pneumatic tool are generally flush with one another and facilitate a smooth surface being formed over such uppermost surfaces as the composite material is wound about the mandrel in the formation of the composite structure.
申请公布号 KR20150001617(A) 申请公布日期 2015.01.06
申请号 KR20140066334 申请日期 2014.05.30
申请人 THE BOEING COMPANY 发明人 LOI K. NGUYEN;JESSE M. HAVENS;JEAN MARC MORASSUTTI
分类号 B29C70/32;B29C35/00 主分类号 B29C70/32
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