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    COMPOSITE SHEAR TIE
    2.
    发明申请
    COMPOSITE SHEAR TIE 审中-公开
    复合剪刀

    公开(公告)号：WO2008067460A2

    公开(公告)日：2008-06-05

    申请号：PCT/US2007/085928

    申请日：2007-11-29

    Applicant: THE BOEING COMPANY ,  PHAM, Doan D. ,  TOLLAN, Mark W.

    Inventor： PHAM, Doan D. ,  TOLLAN, Mark W.

    IPC: B64C3/18

    CPC classification number: B64C3/182 ,  B64C3/26

    Abstract: A composite shear tie for connecting a rib in a wing of an aircraft to a skin panel. The shear tie includes a web section having a first edge, a second edge, and a third edge. The web section is formed from a composite material. The first edge is parallel to the second edge, and the web section is configured to be connected to the rib in the wing of the aircraft. The shear tie also has a first free flange extending from the first edge, wherein the first free flange is around perpendicular to the web section and wherein the first free flange is formed from the composite material. A second free flange is present in the shear tie in which the second free flange extends from the second edge, wherein the second free flange is around perpendicular to the web section and wherein the second free flange is formed from the composite material. The shear tie has a base flange section extending from the third edge, wherein the first base flange is configured for attachment to the skin panel and wherein the first base flange is formed from the composite material.

    Abstract translation: 用于将飞机机翼中的肋连接到皮肤面板的复合剪切带。 剪切带包括具有第一边缘，第二边缘和第三边缘的腹板部分。 腹板部分由复合材料形成。 第一边缘平行于第二边缘，并且腹板部分构造成连接到飞机机翼中的肋条。 剪切带还具有从第一边缘延伸的第一自由凸缘，其中第一自由凸缘围绕垂直于腹板部分并且其中第一自由凸缘由复合材料形成。 在第二自由凸缘从第二边缘延伸的剪切连接件中存在第二自由凸缘，其中第二自由凸缘围绕垂直于腹板部分并且其中第二自由凸缘由复合材料形成。 剪切带具有从第三边缘延伸的基部凸缘部分，其中第一基底凸缘被构造成附接到皮肤面板，并且其中第一基底凸缘由复合材料形成。

    COMPOSITE PLY STABILIZING MECHANISM AND METHOD
    4.
    发明申请
    COMPOSITE PLY STABILIZING MECHANISM AND METHOD 审中-公开
    复合材料稳定机理及方法

    公开(公告)号：WO2011081726A1

    公开(公告)日：2011-07-07

    申请号：PCT/US2010/056470

    申请日：2010-11-12

    Applicant: THE BOEING COMPANY ,  PHAM, Doan D. ,  TOLLAN, Mark W. ,  OUTZEN, Richard M. ,  LOCKLEER, John C. ,  HARRIS, Christopher G.

    Inventor： PHAM, Doan D. ,  TOLLAN, Mark W. ,  OUTZEN, Richard M. ,  LOCKLEER, John C. ,  HARRIS, Christopher G.

    IPC: B29C70/44 ,  B29C70/54 ,  B29D99/00 ,  B29D24/00

    CPC classification number: B32B37/10 ,  B29C70/44 ,  B29C70/541 ,  B29C70/543 ,  B29D99/0021 ,  Y02T50/43 ,  Y10T156/10 ,  Y10T156/1092 ,  Y10T428/31504

    Abstract: A stabilizing mechanism (72) for resisting relative movement of upper and lower laminates (30) of a composite structure having a core (20) comprises a lower grip strip (78) and at least one upper grip strip (76). The lower grip strip (78) may be mounted to a tool (50) upon which the composite structure may be processed. The lower grip strip may include an outer surface having at least one engagement feature for engaging at least one of the upper and lower laminates which make up the composite structure. The upper grip strip may have opposing outer surfaces which may include at least one engagement feature (76d) such as a protusion (76e) for engaging the lower strip and at least one of the upper and lower laminates (30).

    Abstract translation: 用于抵抗具有芯部（20）的复合结构的上部和下部层压体（30）的相对运动的稳定机构（72）包括下部抓握条（78）和至少一个上部抓握条（76）。 下把手条（78）可以安装到工具（50）上，复合结构可以在该工具上加工。 下夹带可以包括具有至少一个接合特征的外表面，用于接合构成复合结构的上层和下层板中的至少一个。 上部抓握条可以具有相对的外表面，其可以包括至少一个接合特征（76d），例如用于接合下部条带和上部和下部层压板（30）中的至少一个的突起（76e）。

    COMPOSITE SHEAR TIE
    6.
    发明申请
    COMPOSITE SHEAR TIE 审中-公开
    复合剪刀

    公开(公告)号：WO2008067460A3

    公开(公告)日：2008-07-10

    申请号：PCT/US2007085928

    申请日：2007-11-29

    Applicant: BOEING CO ,  PHAM DOAN D ,  TOLLAN MARK W

    Inventor： PHAM DOAN D ,  TOLLAN MARK W

    IPC: B64C3/18

    CPC classification number: B64C3/182 ,  B64C3/26

    Abstract: A composite shear tie (500) for connecting a rib (504) in a wing of an aircraft to a skin panel (514). The shear tie includes a web (520) section having a first edge, a second edge, and a third edge. The web section is formed from a composite material. The first edge is parallel to the second edge, and the web section (520) is configured to be connected to the rib (504) in the wing of the aircraft. The shear tie also has a first free flange (522) extending from the first edge, wherein the first free (522) flange is around perpendicular to the web section and wherein the first free flange is formed from the composite material. A second free flange (524) is present in the shear tie in which the second free flange (524) extends from the second edge, wherein the second free flange is around perpendicular to the web section and wherein the second free flange is formed from the composite material. The shear tie has a base flange section (534) extending from the third edge, wherein the first base flange (534) is configured for attachment to the skin panel (514) and wherein the first base flange is formed from the composite material.

    Abstract translation: 一种用于将飞机机翼中的肋（504）连接到皮肤面板（514）的复合剪切带（500）。 剪切带包括具有第一边缘，第二边缘和第三边缘的腹板（520）部分。 腹板部分由复合材料形成。 第一边缘平行于第二边缘，并且腹板部分（520）构造成连接到飞机机翼中的肋（504）。 剪切带还具有从第一边缘延伸的第一自由凸缘（522），其中第一自由（522）凸缘围绕垂直于腹板部分并且其中第一自由凸缘由复合材料形成。 第二自由凸缘（524）存在于剪切连接件中，第二自由凸缘（524）从第二边缘延伸，其中第二自由凸缘围绕垂直于腹板部分并且其中第二自由凸缘由 复合材料。 剪切带具有从第三边缘延伸的基部凸缘部分（534），其中第一基底凸缘（534）构造成用于附接到皮肤面板（514），并且其中第一基底凸缘由复合材料形成。

    FLEXIBLE MANDREL FOR HIGHLY CONTOURED COMPOSITE STRINGER
    7.
    发明申请
    FLEXIBLE MANDREL FOR HIGHLY CONTOURED COMPOSITE STRINGER 审中-公开
    灵活的人造革用于高度复合的复合材料

    公开(公告)号：WO2007001447A2

    公开(公告)日：2007-01-04

    申请号：PCT/US2005/039967

    申请日：2005-11-04

    Applicant: THE BOEING COMPANY ,  TOLLAN, Mark, W. ,  PHAM, Doan, D.

    Inventor： TOLLAN, Mark, W. ,  PHAM, Doan, D.

    IPC: B29C70/34 ,  B29C70/44 ,  B29C33/76

    CPC classification number: B29C70/345 ,  B29C70/446 ,  B29L2031/3085 ,  Y02T50/43

    Abstract: An aircraft stringer lay-up assembly is provided comprising a contoured curing block and a first mandrel element positioned thereon. The first mandrel assembly includes a first bar assembly having a plurality of rigidity reducing first slots formed along a first mandrel length. The plurality of rigidity reducing first slots protruding partially through a first mandrel depth of the first mandrel element to allow the first bar assembly to conform to the contoured curing block. A composite ply assembly is laid up onto the first mandrel element and cured while conformed to said contoured curing block such that a contoured composite stringer element is generated

    Abstract translation: 提供了一种飞机纵梁组合组件，其包括轮廓固化块和定位在其上的第一心轴元件。 第一心轴组件包括具有沿着第一心轴长度形成的多个刚度减小的第一槽的第一杆组件。 所述多个刚度减小的第一狭槽部分地突出穿过第一心轴元件的第一心轴深度，以允许第一杆组件符合轮廓的固化块。 将复合层叠组件放置在第一心轴元件上并固化，同时符合所述轮廓的固化块，使得产生成形的复合纵梁元件

    FLEXIBLE MANDREL FOR HIGHLY CONTOURED COMPOSITE STRINGER AND METHOD OF PRODUCING SAID STRINGER
    8.
    发明申请
    FLEXIBLE MANDREL FOR HIGHLY CONTOURED COMPOSITE STRINGER AND METHOD OF PRODUCING SAID STRINGER 审中-公开
    用于高度复合复合材料的灵活人造丝器及其制造方法

    公开(公告)号：WO2007001447A3

    公开(公告)日：2007-03-22

    申请号：PCT/US2005039967

    申请日：2005-11-04

    Applicant: BOEING CO ,  TOLLAN MARK W ,  PHAM DOAN D

    Inventor： TOLLAN MARK W ,  PHAM DOAN D

    IPC: B29C70/34 ,  B29C33/76 ,  B29C70/44

    CPC classification number: B29C70/345 ,  B29C70/446 ,  B29L2031/3085 ,  Y02T50/433

    Abstract: An aircraft stringer lay-up assembly (10) is provided comprising a contoured curing block and a first mandrel element (12) positioned thereon. The first mandrel assembly includes a first bar assembly (16) having a plurality of rigidity reducing first slots (18) formed along a first mandrel length. The plurality of rigidity reducing first slots protruding partially through a first mandrel depth of the first mandrel element to allow the first bar assembly to conform to the contoured curing block. A composite ply assembly is laid up onto the first mandrel element and cured while conformed to said contoured curing block such that a contoured composite stringer element is generated.

    Abstract translation: 提供了一种飞机纵梁组合组件（10），其包括轮廓固化块和位于其上的第一心轴元件（12）。 第一心轴组件包括第一杆组件（16），其具有沿着第一心轴长度形成的多个刚性减小的第一狭槽（18）。 所述多个刚度减小的第一狭槽部分地突出穿过第一心轴元件的第一心轴深度，以允许第一杆组件符合轮廓的固化块。 将复合层叠组件放置在第一心轴元件上并固化，同时符合所述轮廓的固化块，从而产生成形的复合纵梁元件。

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