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1. 发明公开

EP0783959A3 Method of fabricating hybrid composite structures 失效
标题翻译：生产杂交复合结构的方法
公开(公告)号：EP0783959A3
公开(公告)日：1998-02-04
申请号：EP97200021.0
申请日：1997-01-06
申请人： THE BOEING COMPANY
发明人： Turner, C. Warren , Lum, Matthew K.S. , Evans, Richard B.
IPC分类号： B32B1/10 , B32B3/12 , B29C70/30 , B29D9/00
CPC分类号： B29C70/088 , B29C70/32 , B29K2705/00 , Y02T50/43
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.

2. 发明授权

EP0783959B2 Method of fabricating hybrid composite structures 失效
标题翻译：生产杂交复合结构的方法
公开(公告)号：EP0783959B2
公开(公告)日：2011-10-12
申请号：EP97200021.0
申请日：1997-01-06
申请人： The Boeing Company
发明人： Turner, C. Warren , Lum, Matthew K.S. , Evans, Richard B.
IPC分类号： B32B1/00 , B32B3/12 , B29C70/30
CPC分类号： B29C70/088 , B29C70/32 , B29K2705/00 , Y02T50/43
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.

3. 发明授权

EP0783959B1 Method of fabricating hybrid composite structures 失效
标题翻译：生产杂交复合结构的方法
公开(公告)号：EP0783959B1
公开(公告)日：2004-01-02
申请号：EP97200021.0
申请日：1997-01-06
申请人： THE BOEING COMPANY
发明人： Turner, C. Warren , Lum, Matthew K.S. , Evans, Richard B.
IPC分类号： B32B1/10 , B32B3/12 , B29C70/30 , B29D9/00
CPC分类号： B29C70/088 , B29C70/32 , B29K2705/00 , Y02T50/43
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.

4. 发明公开

EP0783959A2 Method of fabricating hybrid composite structures 失效
标题翻译： Verfahren zum Herstellen von hybriden Verbundstrukturen
公开(公告)号：EP0783959A2
公开(公告)日：1997-07-16
申请号：EP97200021.0
申请日：1997-01-06
申请人： THE BOEING COMPANY
发明人： Turner, C. Warren , Lum, Matthew K.S. , Evans, Richard B.
IPC分类号： B32B1/10 , B32B3/12 , B29C70/30 , B29D9/00
CPC分类号： B29C70/088 , B29C70/32 , B29K2705/00 , Y02T50/43
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.
摘要翻译：混合复合结构由多层条带（12），包含树脂浸渍的切割带或丝束的聚合物基质复合材料（71）和由多个矩形部分（72）形成的中心蜂窝层形成。前两个步骤包括形成多个高温条并提供模具或叠层心轴（10）。此后，将第一组脉带施加到层叠心轴上以形成第一高岭条带层。随后，将以树脂浸渍的切割带或丝束形式的复合材料施加到第一粗轧带层以形成第一复合材料层。接下来，将第二组高温条带施加到第一层聚合物基质复合材料，与第一高岭条带层相对，以形成至少一个其它的带状层。这创建了具有作为结构的第一层和最后层的高尔夫条带的第一夹层结构。此后，将蜂窝状材料层施加到第一夹层结构的最后层。最后，在与第一夹层结构相对的蜂窝层的一侧上形成与第一夹层结构基本相同的第二夹层结构。因此，形成具有由中央蜂窝层隔开的第一和第二夹层结构的混合复合结构。

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