发明名称 Composite sandwich panel with differential resin layers
摘要 A composite panel includes a honeycomb core sandwiched by a pair of skins that are attached directly to the core with no separate adhesive layer. The skins are impregnated with a resin material that is unevenly distributed between first and second surfaces, and direct contact is established between the surfaces with the greater resin distribution and the core, reducing weight and eliminating the manufacturing step of incorporating an adhesive layer therebetween.
申请公布号 US9573338(B2) 申请公布日期 2017.02.21
申请号 US201514631770 申请日期 2015.02.25
申请人 B/E AEROSPACE, INC. 发明人 Bartolome Alvin S.
分类号 B32B3/00;B32B3/12;B32B5/02;B32B27/28;B32B7/02;B32B5/12;B32B5/14;B32B5/28;B32B7/04;B32B27/04;B32B27/42;B32B37/14;B32B37/00 主分类号 B32B3/00
代理机构 Oblon, McClelland, Maier & Neustadt, L.L.P. 代理人 Oblon, McClelland, Maier & Neustadt, L.L.P.
主权项 1. A composite panel, comprising: a core having a repeating geometric shape, wherein an upper surface of the core comprises an open lattice of the repeating geometric shape, and a lower surface of the core comprises an open lattice of the repeating geometric shape; a first skin attached directly to the upper surface of the core with no separate adhesive film, and a second skin attached directly to the lower surface of the core with no separate adhesive film, each of the first and second skins having a thermal setting resin on an inner and an outer surface; and wherein a thickness of the thermal setting resin on the inner surface of the first and second skins is greater than a thickness of the thermal setting resin on the outer surface of the first and second skins.
地址 Wellington FL US