发明名称 Method of fabricating hybrid composite structures
摘要 A hybrid composite structure is formed from layers of gore strips (12), polymeric matrix composite (71) comprising a resin impregnated slit tape or tow, and a central honeycomb layer formed from a plurality of rectangular sections (72). The first two steps include forming a plurality of the gore strips and providing a mold, or lay-up mandrel (10). Thereafter, a first set of gore strips is applied to the lay-up mandrel to form a first gore strip layer. Subsequently, the composite material in form of resin impregnated slit tape or tow is applied to the first gore strip layer to form a first composite material layer. Next, a second set of gore strips is applied to the first layer of polymeric matrix composite, opposite the first gore strip layer, to form at least one other gore strip layer. This creates a first sandwich structure having gore strips as the first and last layers of the structure. Thereafter, the layer of honeycomb material is applied to the last layer of the first sandwich structure. Finally, a second sandwich structure, substantially identical to the first sandwich structure, is formed on the side of the honeycomb layer opposite the first sandwich structure. Thus, a hybrid composite structure is formed having first and second sandwich structures separated by a central honeycomb layer. <IMAGE>
申请公布号 EP0783959(A3) 申请公布日期 1998.02.04
申请号 EP19970200021 申请日期 1997.01.06
申请人 THE BOEING COMPANY 发明人 TURNER, C. WARREN;LUM, MATTHEW K.S.;EVANS, RICHARD B.
分类号 B32B1/08;B29C70/08;B29C70/16;B29C70/32;B29K105/08;B29L31/30;B32B15/08 主分类号 B32B1/08
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