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    STIFFENING ELEMENT AND REINFORCED STRUCTURE
    2.
    发明申请
    STIFFENING ELEMENT AND REINFORCED STRUCTURE 有权
    强化元素和强化结构

    公开(公告)号：US20160375632A1

    公开(公告)日：2016-12-29

    申请号：US15105705

    申请日：2013-12-20

    Applicant: SAAB AB

    Inventor： Per Hallander ,  Anders Lundberg ,  Tonny Nyman ,  Mikael Petersson

    IPC: B29C65/48 ,  B64C1/06 ,  B29C65/00 ,  B29C65/02 ,  B29C70/38

    CPC classification number: B29C65/48 ,  B29C65/02 ,  B29C66/00145 ,  B29C70/382 ,  B29C70/386 ,  B29D99/0014 ,  B29K2105/06 ,  B29L2031/3076 ,  B64C1/061 ,  B64C1/064 ,  B64C1/12 ,  Y02T50/43

    Abstract: A stiffening element including at least a first stiffening profile and at least a second stiffening profile. The first stiffening profile includes a profile member. At least one structural flange is connected to the profile member. A through-passage extends through the profile member. At least one support flange is connected to the profile member. The second stiffening profile includes a bottom portion and at least one support side portion connected to the bottom portion. A method for manufacturing a stiffening element. A method for manufacturing a reinforced structure, where the reinforced structure includes at least one structural element and at least one stiffening element.

    Abstract translation: 一种加强元件，包括至少第一加强型材和至少第二加强型材。 第一加强型材包括型材构件。 至少一个结构法兰连接到轮廓构件。 通道延伸穿过轮廓构件。 至少一个支撑凸缘连接到轮廓构件。 第二加强型材包括底部和连接到底部的至少一个支撑侧部分。 一种加强元件的制造方法。 一种用于制造加强结构的方法，其中所述加强结构包括至少一个结构元件和至少一个加强元件。

    Smooth surface forming tool and manufacture thereof
    3.
    发明授权
    Smooth surface forming tool and manufacture thereof 有权

    公开(公告)号：US10766232B2

    公开(公告)日：2020-09-08

    申请号：US14688074

    申请日：2015-04-16

    Applicant: SAAB AB

    Inventor： Per Hallander ,  Mikael Petersson ,  Björn Weidmann ,  Tommy Grankäll ,  Göte Strindberg ,  Pontus Nordin

    IPC: B29C70/88 ,  B32B27/08 ,  B29C70/44 ,  B29C35/02 ,  B29K105/08 ,  B29L31/30 ,  B29K105/16

    Abstract: A method of manufacture of a composite aircraft article aerodynamic surface by forming the composite aircraft article aerodynamic surface on an aircraft article composite forming tool. The aircraft article composite forming tool includes a matrix laminate including an upper ply including a forming surface for forming the composite aircraft article aerodynamic surface. The upper ply of the aircraft article composite forming tool includes a nano filament structure embedded therein. A blank is conformed onto the aircraft article composite forming tool. The aircraft article is formed on the upper ply of the forming surface. The forming surface of the aircraft article composite forming tool is adapted to form an aerodynamic surface of the aircraft article. The blank is cured into the aircraft article. The composite aircraft article is finished.

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