公开(公告)号：US20150004347A1

公开(公告)日：2015-01-01

申请号：US14489115

申请日：2014-09-17

Applicant: The Boeing Company

Inventor： William T. Kline ,  Charles J. Nelson ,  Thang D. Phung ,  Curtis M. Groth ,  Robert G. Meyer ,  Peter J. VanVoast ,  Charles Y. Hu ,  Geoffrey A. Butler ,  Dan D. Day ,  Thomas J. Kennedy ,  Luis J. Perla ,  Richard A. Ransom ,  Justin L. Holland ,  Erik Lund ,  Joseph F. Warren

IPC: B32B37/02 ,  B29C65/02

CPC classification number: B29C65/02 ,  B29C33/02 ,  B29C33/30 ,  B29C35/02 ,  B29C43/10 ,  B29C43/3642 ,  B29C43/52 ,  B29C43/58 ,  B29C65/18 ,  B29C65/26 ,  B29C65/4835 ,  B29C65/5042 ,  B29C65/505 ,  B29C65/5071 ,  B29C65/5085 ,  B29C66/1122 ,  B29C66/1142 ,  B29C66/1162 ,  B29C66/128 ,  B29C66/14 ,  B29C66/5241 ,  B29C66/5243 ,  B29C66/63 ,  B29C66/71 ,  B29C66/721 ,  B29C66/7212 ,  B29C66/723 ,  B29C66/73941 ,  B29C66/81261 ,  B29C66/81455 ,  B29C66/81811 ,  B29C66/81831 ,  B29C66/91212 ,  B29C66/91231 ,  B29C66/91421 ,  B29C66/91443 ,  B29C66/91631 ,  B29C66/9221 ,  B29C66/9241 ,  B29C66/961 ,  B29C70/44 ,  B29C2043/3615 ,  B29C2043/3649 ,  B29C2043/5816 ,  B29K2105/06 ,  B29L2031/003 ,  B29L2031/3085 ,  B64F5/10 ,  Y10T428/19 ,  Y10T428/192 ,  B29K2307/04 ,  B29K2063/00 ,  B29C65/00

Abstract: A method for forming a structural member and a structural member produced thereby includes positioning a first composite section and a second composite section within a tool. The tool has an inner surface and a wall intersection and is supported by a tool platform. The tool platform and a pressure platform are relatively movable between an open position and a closed position. The tool has a non-planar outer surface against which the member may be pressed. A composite splice member is positioned at least partially overlapping both the first composite section and the second composite section to form a joint in the composite structural member. The composite structural member is pressed against the non-planar outer surface of the tool by applying pressure to the joint from a pressure bladder. Heat is applied to the composite structural member at the joint to cure the composite splice member to the first composite section and the second composite section.

Abstract translation: 由此制成的结构件和结构件的形成方法包括将第一复合部分和第二复合部分定位在工具内。 工具具有内表面和墙壁交叉点，并由工具平台支撑。 工具平台和压力平台可在打开位置和关闭位置之间相对移动。 该工具具有非平面的外表面，该构件可与该外表面按压。 复合接头构件被定位成至少部分地与第一复合部分和第二复合部分重叠，以在复合结构部件中形成接头。 通过从压力囊对接头施加压力，将复合结构构件压靠在工具的非平面外表面上。 在接头处对复合结构构件施加热量，以将复合接合构件固化到第一复合段和第二复合段。

公开(公告)号：US10710327B2

公开(公告)日：2020-07-14

申请号：US15829780

申请日：2017-12-01

Applicant: The Boeing Company

Inventor： Geoffrey A. Butler

IPC: B29C65/00 ,  B32B3/26 ,  B32B7/12 ,  B32B37/06 ,  B32B37/12 ,  B32B38/18 ,  B32B37/18 ,  B29C70/44 ,  B29C70/54 ,  B29C70/00 ,  B32B37/10 ,  B32B38/00 ,  B29C65/48 ,  B29C65/70 ,  B29C67/00

Abstract: A method of forming a composite article. One step involves applying adhesive on surfaces of a plurality of sublaminate units, each ply of each sublaminate unit comprising fibers impregnated with resin which has been initially cured to 30% to 50% of full cure. The initially cured sublaminate units are then arranged in a stack, which stack is pressed against a surface of a forming tool. While pressure is being applied, the stack is heated to an intermediate temperature above a glass transition temperature of the resin for a time interval sufficient to intermediately cure the resin to 50% to 70% of full cure to form a composite laminate having a contour defined by the surface of the forming tool. Then the resin is finally cured at a final temperature higher than the intermediate temperature.

公开(公告)号：US09862175B2

公开(公告)日：2018-01-09

申请号：US14795209

申请日：2015-07-09

Applicant: The Boeing Company

Inventor： Marc R. Matsen ,  Mark A. Negley ,  Marc J. Piehl ,  Kay Y. Blohowiak ,  Alan E. Landmann ,  Richard H. Bossi ,  Robert L. Carlsen ,  Gregory Alan Foltz ,  Geoffrey A. Butler ,  Liam S. Cavanaugh Pingree ,  Stephen G. Moore ,  John Mark Gardner ,  Robert A. Anderson

IPC: B32B37/00 ,  B32B37/14 ,  B32B7/12 ,  B32B15/00 ,  B32B15/08 ,  B32B19/02 ,  B32B27/00 ,  B32B3/06 ,  B29C73/10

CPC classification number: B32B37/144 ,  B29C73/10 ,  B32B3/06 ,  B32B7/12 ,  B32B15/00 ,  B32B15/08 ,  B32B19/02 ,  B32B27/00 ,  B32B2250/42 ,  B32B2260/021 ,  B32B2305/08 ,  B32B2307/202 ,  B32B2307/204 ,  B32B2307/54 ,  B32B2307/558 ,  B32B2311/00 ,  B32B2398/00 ,  B32B2405/00 ,  B32B2605/18 ,  Y10T29/49208 ,  Y10T29/49885 ,  Y10T156/10 ,  Y10T428/24752 ,  Y10T428/31678

Abstract: A method of forming a molybdenum composite hybrid laminate is disclosed. The method includes treating a surface of each of a plurality of molybdenum foil layers. The method further includes interweaving the surface treated molybdenum foil layers with a plurality of composite material layers. The method further includes bonding with an adhesive layer each of the surface treated molybdenum foil layers to adjacent composite material layers to form a molybdenum composite hybrid laminate having improved yield strength.

公开(公告)号：US09669579B2

公开(公告)日：2017-06-06

申请号：US14489115

申请日：2014-09-17

Applicant: The Boeing Company

Inventor： William T. Kline ,  Charles J. Nelson ,  Thang D. Phung ,  Curtis M. Groth ,  Robert G. Meyer ,  Peter J. VanVoast ,  Charles Y. Hu ,  Geoffrey A. Butler ,  Dan D. Day ,  Thomas J. Kennedy ,  Luis A. Perla ,  Richard A. Ransom ,  Justin L. Holland ,  Erik Lund ,  Joseph F. Warren

IPC: B29C65/00 ,  B29C65/02 ,  B29C70/44 ,  B29C65/26 ,  B29C65/48 ,  B29C65/50 ,  B29C35/02 ,  B29C43/36 ,  B29C65/18 ,  B29C43/10 ,  B64F5/10 ,  B29K105/06 ,  B29L31/00 ,  B29C33/02 ,  B29C33/30 ,  B29C43/52 ,  B29C43/58 ,  B29L31/30

CPC classification number: B29C65/02 ,  B29C33/02 ,  B29C33/30 ,  B29C35/02 ,  B29C43/10 ,  B29C43/3642 ,  B29C43/52 ,  B29C43/58 ,  B29C65/18 ,  B29C65/26 ,  B29C65/4835 ,  B29C65/5042 ,  B29C65/505 ,  B29C65/5071 ,  B29C65/5085 ,  B29C66/1122 ,  B29C66/1142 ,  B29C66/1162 ,  B29C66/128 ,  B29C66/14 ,  B29C66/5241 ,  B29C66/5243 ,  B29C66/63 ,  B29C66/71 ,  B29C66/721 ,  B29C66/7212 ,  B29C66/723 ,  B29C66/73941 ,  B29C66/81261 ,  B29C66/81455 ,  B29C66/81811 ,  B29C66/81831 ,  B29C66/91212 ,  B29C66/91231 ,  B29C66/91421 ,  B29C66/91443 ,  B29C66/91631 ,  B29C66/9221 ,  B29C66/9241 ,  B29C66/961 ,  B29C70/44 ,  B29C2043/3615 ,  B29C2043/3649 ,  B29C2043/5816 ,  B29K2105/06 ,  B29L2031/003 ,  B29L2031/3085 ,  B64F5/10 ,  Y10T428/19 ,  Y10T428/192 ,  B29K2307/04 ,  B29K2063/00 ,  B29C65/00

Abstract: A method for forming a structural member and a structural member produced thereby includes positioning a first composite section and a second composite section within a tool. The tool has an inner surface and a wall intersection and is supported by a tool platform. The tool platform and a pressure platform are relatively movable between an open position and a closed position. The tool has a non-planar outer surface against which the member may be pressed. A composite splice member is positioned at least partially overlapping both the first composite section and the second composite section to form a joint in the composite structural member. The composite structural member is pressed against the non-planar outer surface of the tool by applying pressure to the joint from a pressure bladder. Heat is applied to the composite structural member at the joint to cure the composite splice member to the first composite section and the second composite section.

公开(公告)号：US20160346995A1

公开(公告)日：2016-12-01

申请号：US14723355

申请日：2015-05-27

Applicant: The Boeing Company

Inventor： Geoffrey A. Butler ,  Robert Courdji

IPC: B29C65/00 ,  B29C35/02 ,  B29C65/48

CPC classification number: B29C66/43441 ,  B29C65/483 ,  B29C65/5057 ,  B29C66/112 ,  B29C66/131 ,  B29C66/1312 ,  B29C66/342 ,  B29C66/343 ,  B29C66/496 ,  B29C66/524 ,  B29C66/532 ,  B29C66/61 ,  B29C66/71 ,  B29C66/721 ,  B29C66/7212 ,  B29C66/72141 ,  B29C66/73751 ,  B29C66/73752 ,  B29C66/73755 ,  B29C66/73941 ,  B29C66/81455 ,  B29C70/342 ,  B29K2063/00 ,  B29K2105/0872 ,  B29L2031/3082 ,  B29L2031/3085 ,  B29K2307/04 ,  B29K2309/08

Abstract: A method of reducing residual stress in a composite assembly may include assembling a first composite part to a second composite part to form a detail assembly. The first and second composite part may each have a flange and a web connected by a bend radius. The webs may be arranged back-to-back. The detail assembly may be cured on a compensated cure tool compensated for cure shrinkage spring-in predicted to occur in the first and second composite part. The method may include allowing the first and second composite part to spring in from cure shrinkage, and assembling the detail assembly to an uncured third composite. The method may also include co-bonding the detail assembly to the third composite part on an assembly cure tool to form a composite assembly having reduced cure shrinkage residual stress in the bend radii of the first and second composite part.

Abstract translation: 减少复合组件中的残余应力的方法可包括将第一复合部件组装到第二复合部件以形成细节组件。 第一和第二复合部件可以各自具有通过弯曲半径连接的凸缘和腹板。 腹板可以背对背地布置。 细节组件可以在补偿的固化收缩弹簧补偿的固化工具上固化，预测将发生在第一和第二复合部件中。 该方法可以包括允许第一和第二复合部件从固化收缩弹出，以及将细节组件组装到未固化的第三复合材料。 该方法还可以包括在组装固化工具上将细节组件共同粘合到第三复合部件，以形成具有减小的第一和第二复合部件的弯曲半径中的固化收缩残余应力的复合组件。

公开(公告)号：US20150306859A1

公开(公告)日：2015-10-29

申请号：US14795209

申请日：2015-07-09

Applicant: The Boeing Company

Inventor： Marc R. Matsen ,  Mark A. Negley ,  Marc J. Piehl ,  Kay Y. Blohowiak ,  Alan E. Landmann ,  Richard H. Bossi ,  Robert L. Carlsen ,  Gregory Alan Foltz ,  Geoffrey A. Butler ,  Liam S. Cavanaugh Pingree ,  Stephen G. Moore ,  John Mark Gardner ,  Robert A. Anderson

IPC: B32B37/14 ,  B32B15/08 ,  B32B7/12

CPC classification number: B32B37/144 ,  B29C73/10 ,  B32B3/06 ,  B32B7/12 ,  B32B15/00 ,  B32B15/08 ,  B32B19/02 ,  B32B27/00 ,  B32B2250/42 ,  B32B2260/021 ,  B32B2305/08 ,  B32B2307/202 ,  B32B2307/204 ,  B32B2307/54 ,  B32B2307/558 ,  B32B2311/00 ,  B32B2398/00 ,  B32B2405/00 ,  B32B2605/18 ,  Y10T29/49208 ,  Y10T29/49885 ,  Y10T156/10 ,  Y10T428/24752 ,  Y10T428/31678

Abstract: A method of forming a molybdenum composite hybrid laminate is disclosed. The method includes treating a surface of each of a plurality of molybdenum foil layers. The method further includes interweaving the surface treated molybdenum foil layers with a plurality of composite material layers. The method further includes bonding with an adhesive layer each of the surface treated molybdenum foil layers to adjacent composite material layers to form a molybdenum composite hybrid laminate having improved yield strength.

Abstract translation: 公开了一种形成钼复合混合层压板的方法。 该方法包括处理多个钼箔层中的每一个的表面。 该方法还包括用多个复合材料层交织经表面处理的钼箔层。 该方法还包括将每个表面处理的钼箔层的粘合剂层粘合到相邻的复合材料层，以形成具有改进的屈服强度的钼复合混合层合物。