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    A POROUS COATING APPLIED ONTO AN AERIAL ARTICLE
    2.
    发明申请
    A POROUS COATING APPLIED ONTO AN AERIAL ARTICLE 审中-公开
    适用于某一专利文献的多孔涂料

    公开(公告)号：US20150292074A1

    公开(公告)日：2015-10-15

    申请号：US14439929

    申请日：2012-10-31

    Applicant: SAAB AB

    Inventor： Pontus Nordin ,  Per Hallander ,  Jonas Bohlin ,  Thomas Hellstrom

    IPC: C23C4/06 ,  B64C21/10 ,  C23C4/18 ,  C23C14/34 ,  C23C4/12

    CPC classification number: C23C4/06 ,  B64C11/205 ,  B64C21/10 ,  B64C23/005 ,  B64C2230/12 ,  B64D15/12 ,  B64D45/00 ,  B64D45/02 ,  B64D2045/009 ,  C23C4/08 ,  C23C4/12 ,  C23C4/18 ,  C23C14/34 ,  C23C14/5886 ,  C23C24/04 ,  F01D5/288 ,  F05D2300/514 ,  F05D2300/6032 ,  Y02T50/166 ,  Y02T50/43 ,  Y02T50/672 ,  Y02T50/673 ,  Y02T50/6765

    Abstract: An aerial article including a composite skin, a leading edge facing an airflow during use of the aerial article, an erosion resistant coating including a metallic material, and an aerodynamic surface. The coating at least partly covers the composite skin of the aerial article. The coating has a porosity sufficiently high to provide an open area, diffusion passage way, so as to permit moisture transportation from the composite skin to the aerodynamic surface of the coating. A method of applying an erosion resistant coating including a metallic material to a composite skin of an aerial article. An erosion resistant coating material is provided onto the composite skin over a selected area of the article. The coating is porous. The outer surface of the coating is polished to achieve a smooth aerodynamic surface.

    Abstract translation: 包括复合皮肤的空中物品，在使用空中物品期间面向气流的前缘，包括金属材料的抗侵蚀涂层和空气动力学表面。 该涂层至少部分地覆盖空中物品的复合皮肤。 涂层具有足够高的孔隙以提供开放区域，扩散通道的方式，以便允许水分从复合表皮输送到涂层的空气动力学表面。 将包含金属材料的耐侵蚀涂层施加到空中物品的复合表皮的方法。 在制品的选定区域上的复合皮肤上提供抗侵蚀涂层材料。 涂层是多孔的。 抛光涂层的外表面以实现平滑的空气动力学表面。

    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.

    Composite article having multifunctional properties and method for its manufacture
    4.
    发明授权
    Composite article having multifunctional properties and method for its manufacture 有权

    公开(公告)号：US10343372B2

    公开(公告)日：2019-07-09

    申请号：US15322972

    申请日：2014-07-03

    Applicant: SAAB AB

    Inventor： Per Hallander ,  Pontus Nordin ,  Goete Strindberg

    IPC: B32B5/26 ,  B29C70/48 ,  B32B5/12 ,  B29C70/08 ,  B82Y30/00 ,  B29C70/88 ,  B29K105/08 ,  B29L31/30

    Abstract: The present invention regards an article (5) comprising at least one composite material, comprising matrix material (19) and at least one micro-sized reinforcement element distributions (23), arranged in plies (13) positioned on top of each other. The nano-sized reinforcement elements (17, 17′, 17″, 17′″) are arranged in between and/or inside the micro-sized reinforcement element distributions (23), the nano-sized reinforcement elements (17, 17′, 17″, 17′″) having matrix material accumulation properties so as to provide a tailored increased reinforcement volume of said one or more distributions (23). The present invention regards a method for manufacture of a composite article (5) and use of the article (5).

    STIFFENING ELEMENT AND REINFORCED STRUCTURE
    6.
    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。

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