公开(公告)号：EP1134070B1

公开(公告)日：2004-03-24

申请号：EP00500167.2

申请日：2000-07-26

申请人： Airbus Espana, S.L.

发明人： Cerezo Pancorbo, Carlos ,  Dominguez Casado, Rafael ,  De Castro Nodal, Manuel ,  Perez Pastor, Augusto ,  Garcia Garcia, Aquilino ,  Huertas Garcia, Manuel

IPC分类号： B29C70/44 ,  B64C3/18 ,  B64C3/24

CPC分类号： B64C3/182 ,  B29C70/44 ,  B29K2105/24 ,  B29K2105/246 ,  B29L2031/003 ,  B64C3/24 ,  Y02T50/43 ,  Y10S264/42

摘要： A process for manufacturing pre-cured parts of composite material with green-applied stiffeners, comprising the lamination of superimposed pre-impregnated composite material sheets to obtain a base part (1) and a second part (2) intended to be bonded with it; curing the base part (1); hot forming the laminate destined to form the second part (2); removing the second part (2) from the forming tool thereof and introducing it in angle pieces, tightening the angle pieces by sections and deposit it over the base part (1), intercalating a structural adhesive sheet between both of them; closing the assembly of both parts inside a vacuum bag and loading said bag in an autoclave, carrying out a curing cycle of the second part (2) under pressure and temperature, so that it is strongly adhered to the base part (1). The invention is applicable to the field of aeronautics.

公开(公告)号：EP1010615B1

公开(公告)日：2005-10-26

申请号：EP99500147.6

申请日：1999-08-17

申请人： Airbus Espana, S.L.

发明人： Dominguez Casado, Rafael ,  Perez Perez, Antonio ,  Huertas Garcia, Manuel ,  De Castro Nodal, Manuel ,  Cerezo Pancorbo, Carlos ,  Robledo Sacristan, Bonifacio ,  Grueso Diez, César ,  Redondo Vara, Enrique

IPC分类号： B64C1/00 ,  F16B1/00

CPC分类号： B64C1/06 ,  B64C2001/0072 ,  Y02T50/43 ,  Y10S29/003 ,  Y10T29/49904 ,  Y10T29/49906 ,  Y10T29/49947 ,  Y10T29/49948

摘要： A process for making a dismountable and/or fixed traction-compression coupling to be applied to composite materials, in which a basic laminate (1) of composite material is folded at least once to obtain at least one skirt (2) forming an angle close to 90 DEG with the rest of the laminate; by using a transition radius between the skirt and the rest of the laminate, a set of distribution plates (5, 6) is applied over the basic laminate to stabilize the skirt and produce a uniform load distribution, making holes in each set of distribution skirt-plates and introducing traction bolts (4) with an initial pretension in said holes, hence obtaining the connection between the components to be joined. The invention is applicable to the aerodynamic structures of aircraft.