公开(公告)号：US20050039843A1

公开(公告)日：2005-02-24

申请号：US10646509

申请日：2003-08-22

Applicant: Brice Johnson ,  Stephen Spoon ,  Randal Darras

Inventor： Brice Johnson ,  Stephen Spoon ,  Randal Darras

IPC: B29C53/60 ,  B29C53/62 ,  B29C53/66 ,  B29C53/68 ,  B29C53/70 ,  B29C53/80 ,  B29C70/32 ,  B29C70/38 ,  B65H81/00

CPC classification number: B29C70/386 ,  B29C53/62 ,  B29C53/70 ,  B29C53/8016 ,  B29C70/32 ,  B29C70/545 ,  B29L2031/3076 ,  Y10T156/17

Abstract: An aircraft part manufacturing device for automated composite lamination on a mandrel surface of a tool having a rotational axis includes a mechanical supporting structure that supports multiple material delivery heads. The tool is moveable and rotatable relative to the mechanical supporting structure. The mechanical supporting structure provides for axial translation of the material delivery heads relative to the mandrel surface while the mandrel surface is rotated for laying down courses of composite material over the entire mandrel surface of the tool. The position and movement of each of the plurality of material delivery heads is individually adjustable. Arm mechanisms provide motion of each material delivery head in a direction normal to the mandrel surface; rotation about an axis normal to the mandrel surface; circumferential position adjustment in a hoop direction relative to the mandrel surface; and axial position adjustment relative to the other material delivery heads.

Abstract translation: 用于在具有旋转轴线的工具的心轴表面上的用于自动复合层压的飞行器部件制造装置包括支撑多个材料输送头的机械支撑结构。 该工具相对于机械支撑结构是可移动的和可旋转的。 机械支撑结构提供了材料输送头相对于心轴表面的轴向平移，同时心轴表面旋转以在复合材料的整个心轴表面上放置层叠的过程。 多个材料输送头中的每一个的位置和运动是单独调节的。 臂机构提供每个材料输送头沿与心轴表面垂直的方向的运动; 围绕与心轴表面垂直的轴旋转; 相对于心轴表面在环向方向上的周向位置调整; 和相对于其他材料输送头的轴向位置调节。

公开(公告)号：US20050102814A1

公开(公告)日：2005-05-19

申请号：US10717030

申请日：2003-11-18

Applicant: Donald Anderson ,  Brice Johnson ,  Stephen Spoon

Inventor： Donald Anderson ,  Brice Johnson ,  Stephen Spoon

IPC: B29C33/68 ,  B29C37/00 ,  B29C53/60 ,  B29C53/68 ,  B29C69/00 ,  B29C70/30 ,  B29C70/44 ,  B29C70/54 ,  B23P11/02 ,  B23P19/04

CPC classification number: B29C70/543 ,  B29C33/68 ,  B29C37/0003 ,  B29C53/60 ,  B29C53/68 ,  B29C70/30 ,  B29C70/446 ,  Y02T50/43 ,  Y10T29/49867 ,  Y10T29/49879 ,  Y10T29/49895 ,  Y10T29/49998

Abstract: A method of transferring an uncured composite laminate skin from a lay-up surface of a male mandrel tool to a female cure tool includes defining multiple vacuum zones on the lay-up surface, each zone corresponding to one of a multiple of portions into which the skin is to be separated. For example, to separate the skin into two portions, a low profile seal of a first membrane to the lay-up surface is formed at a first vacuum zone and a second low profile seal for a second membrane is formed at a second vacuum zone. The method further includes laying up a composite laminate skin over all the vacuum zones; separating the composite laminate skin into portions, for example, a first portion over the first vacuum zone and a second portion over the second vacuum zone; and releasing the portions individually into cure tools having an outside mold line surface.

Abstract translation: 将未固化的复合层合物表皮从阳性心轴工具的铺叠表面转移到阴性固化工具的方法包括在铺设表面上限定多个真空区，每个区对应于多个部分中的一个， 皮肤是分开的。 例如，为了将皮肤分成两部分，在第一真空区域形成第一膜至叠层表面的低轮廓密封，并且在第二真空区域形成用于第二膜的第二低轮廓密封。 该方法还包括在所有真空区域上铺设复合层压体皮肤; 将复合层压板表皮分离成例如第一真空区上的第一部分和第二真空区上的第二部分; 并且将这些部分单独地释放到具有外部模具线表面的固化工具中。

公开(公告)号：US20070273067A1

公开(公告)日：2007-11-29

申请号：US11695561

申请日：2007-04-02

Applicant: Donald Anderson ,  Brice Johnson ,  Stephen Spoon

Inventor： Donald Anderson ,  Brice Johnson ,  Stephen Spoon

IPC: B32B37/00

CPC classification number: B29C70/543 ,  B29C33/68 ,  B29C37/0003 ,  B29C53/60 ,  B29C53/68 ,  B29C70/30 ,  B29C70/446 ,  Y02T50/43 ,  Y10T29/49867 ,  Y10T29/49879 ,  Y10T29/49895 ,  Y10T29/49998

Abstract: A method is provided for making a composite laminate aircraft skin for a fuselage in multiple composite panels. A resin-impregnated composite tape is placed on a lay-up surface of a mandrel tool to form the composite laminate aircraft skin as a barrel that is substantially the shape of a fuselage section. The barrel is cut into a plurality of panels on the mandrel tool, and at least one panel of the plurality of panels is transferred, individually and independently of all other of the plurality of panels, from the lay-up surface of the mandrel tool to a first cure tool of a plurality of cure tools having an aero surface tooled to an outer mold line. The at least one of the panels is cured on the first cure tool to form a cured composite panel. The first cure tool defines and controls the outer mold line of the at least one panel. The cured composite panel is removed from the first cure tool.

Abstract translation: 提供了一种用于制造用于多个复合板中的机身的复合层压飞机皮肤的方法。 将树脂浸渍的复合带放置在心轴工具的叠置表面上，以形成基本上为机身部分形状的复合层压飞机皮肤。 将筒体切割成心轴工具上的多个面板，并且多个面板中的至少一个面板独立地且独立于多个面板中的所有其他面板从芯棒工具的叠置表面传递到 多个固化工具的第一固化工具，其具有加工到外模线的航空表面。 所述至少一个所述面板在所述第一固化工具上固化以形成固化的复合板。 第一固化工具定义和控制至少一个面板的外模线。 固化的复合板从第一固化工具移除。