利索-全球专利检索

  1. 登录
  2. 注册

搜索结果

13 条记录 (耗时 0.011 秒)

    Leading edge structure of aircraft airfoil and method of fabricating the same
    2.
    发明授权
    Leading edge structure of aircraft airfoil and method of fabricating the same 失效
    飞机机翼的前沿结构及其制造方法

    公开(公告)号：US6119978A

    公开(公告)日：2000-09-19

    申请号：US118870

    申请日：1998-07-20

    申请人： Takashi Kobayashi ,  Michihiko Banno ,  Kazuaki Amaoka

    发明人： Takashi Kobayashi ,  Michihiko Banno ,  Kazuaki Amaoka

    IPC分类号： B21D26/021 ,  B21D26/055 ,  B21D26/059 ,  B23K20/00 ,  B64C3/28 ,  B64D15/04 ,  B64F5/00 ,  B64C3/00

    CPC分类号： B64F5/0009 ,  B21D26/055 ,  B21D26/059 ,  B21D53/92 ,  B64C3/28 ,  B64D15/04 ,  Y10T29/49336 ,  Y10T29/49339 ,  Y10T29/49622

    摘要： A leading edge structure of an aircraft airfoil including an outer skin, a front wall extended in the spanwise direction of the leading edge structure in a front section of the space defined by the outer skin so as to form an anti-icing duct together with a front part of the outer skin, and a plurality of ribs disposed in the space defined by the outer skin so as to form hot air passages. A laminar structure is formed by superposing upper and lower sheets of a superplastic titanium alloy, inserting a pair of core sheets of a superplastic titanium alloy between the upper and the lower sheet, and forming release agent layers in predetermined regions between the sheets. A structure having at least the outer skin, the front wall and ribs is formed by joining together parts of the super-posed sheets corresponding to regions not coated with the release agent layers by diffusion bonding or welding, heating the laminar structure in a forming mold, supplying a superplastic forming gas into spaces between parts of the superposed sheets corresponding to regions coated with the release agent layers to subject the same parts of the superposed sheets to superplastic deformation and to press the upper sheet and the lower sheet against the forming surface of the forming mold.

    摘要翻译： 一种飞机机翼的前缘结构，其包括外皮，前外墙在由外皮限定的空间的前部中沿前缘结构的翼展方向延伸的前壁，以形成防冰导管 外皮的前部，以及设置在由外皮限定的空间中的多个肋，以便形成热空气通道。 层叠结构通过将超塑性钛合金的上下板叠合，在上下板之间插入一对超塑性钛合金芯片，并在片材之间的预定区域中形成剥离剂层而形成。 至少具有外皮，前壁和肋的结构通过通过扩散粘合或焊接将对应于未涂覆有脱模剂层的区域的超级片材的部分接合在一起而形成，在成型模具中加热层状结构 将超塑性成形气体供应到对应于涂覆有脱模剂层的区域的重叠片材的部分之间的空间中，以使叠加片材的相同部分受到超塑性变形，并将上片材和下片材压在成形表面上 成型模具。

    Composite material wing structure
    3.
    发明授权
    Composite material wing structure 失效
    复合材料翼结构

    公开(公告)号：US06237873B1

    公开(公告)日：2001-05-29

    申请号：US09338551

    申请日：1999-06-23

    申请人： Kazuaki Amaoka ,  Hideyuki Sano ,  Naoya Takizawa

    发明人： Kazuaki Amaoka ,  Hideyuki Sano ,  Naoya Takizawa

    IPC分类号： B64C100

    CPC分类号： B64C3/00

    摘要： A composite material wing structure is disclosed, comprising a plurality of composite material multi-spar structures, each including a plurality of spar extending in a span direction, placed in the span direction. A wing structure of an airplane is also disclosed, comprising wing structures divided into plural parts in a span direction, a rib connected to an end of the wing structure to assemble adjacent wing structures, and a coupling material for coupling spars of the adjacent wing structures.

    摘要翻译： 公开了一种复合材料翼结构，其包括多个复合材料多翼梁结构，每个复合材料多翼梁结构包括沿跨度方向延伸的多个翼梁。 还公开了一种飞机的翼结构，其包括在跨度方向上分成多个部分的翼结构，连接到翼结构的端部以组装相邻翼结构的肋，以及用于联接相邻机翼结构的翼梁的联接材料 。

    Rib of composite material and method of forming the same
    4.
    发明授权
    Rib of composite material and method of forming the same 失效
    复合材料的肋骨及其形成方法

    公开(公告)号：US6114012A

    公开(公告)日：2000-09-05

    申请号：US036018

    申请日：1998-03-06

    申请人： Kazuaki Amaoka ,  Yasuo Isano

    发明人： Kazuaki Amaoka ,  Yasuo Isano

    IPC分类号： B29C70/06 ,  B29C70/30 ,  B29C70/34 ,  B29K105/06 ,  B29L31/30 ,  B32B3/28 ,  B32B3/30

    CPC分类号： B29C70/342 ,  B29C70/30 ,  B29D99/0007 ,  Y10T428/24198 ,  Y10T428/24628 ,  Y10T428/24694

    摘要： A rib of a composite material for a box structure such as an airfoil has, in an integral structure, a web and flanges formed so as to extend along opposite longitudinal side edges of the web. The web is provided with a plurality of parallel first ridges or beads formed so as to extend across the web and to protrude outward from the outer surface of the web, and each of the flanges is provided with a plurality of parallel second ridges formed so as to extend across the flange, to protrude inward from the outer surface thereof and to merge into the corresponding first ridges. The structure eliminates causes of wrinkles and provides an increased strength.

    摘要翻译： 用于诸如翼型的盒结构的复合材料的肋具有整体结构，所述腹板和凸缘形成为沿着腹板的相对的纵向侧边缘延伸。 腹板设置有多个平行的第一脊或珠，其形成为跨越腹板延伸并且从腹板的外表面向外突出，并且每个凸缘设置有多个平行的第二脊，其形成为 延伸穿过凸缘，从其外表面向内突出并且合并到相应的第一脊中。 该结构消除了皱纹的原因并提供了增加的强度。

    Method of fabricating aircraft fuselage structure
    5.
    发明授权
    Method of fabricating aircraft fuselage structure 失效
    制造飞机机身结构的方法

    公开(公告)号：US5223067A

    公开(公告)日：1993-06-29

    申请号：US913904

    申请日：1992-07-16

    申请人： Kenji Hamamoto ,  Kazuaki Amaoka ,  Naoya Takizawa ,  Masanori Hosoi

    发明人： Kenji Hamamoto ,  Kazuaki Amaoka ,  Naoya Takizawa ,  Masanori Hosoi

    IPC分类号： B29C53/80 ,  B29D23/00 ,  B64C1/00 ,  B64C1/06 ,  B64C1/12

    CPC分类号： B64C1/12 ,  B29C53/805 ,  B29C70/32 ,  B29D23/001 ,  B29D99/0014 ,  B64C1/061 ,  B64C1/064 ,  B29C33/505 ,  B29L2031/3082 ,  Y02T50/433

    摘要： An aircraft fuselage structure is fabricated by the following steps. A plurality of ring-shaped members are first prepared, each member being provided around the outer peripheral surface thereof at positions spaced apart in the circumferential direction thereof with a plurality of recesses. Elongated plate members are provided which have respective convex parts corresponding to the recesses, to form stringers. The ring-shaped members are then arranged at a coaxially spaced-apart paralleled disposition, and thereafter a laminating jig is inserted into the coaxially arranged ring-shaped members with a silicone bag interposed therebetween, the silicone bag having an open opposite end. The ring-shaped members are placed in annular recesses provided in the laminating jig and in correspondingly formed annular recesses provided in the bag. Then stringers are placed on the ring-shaped members with the convexed parts fitted in the recesses of the ring-shaped members, so that a framework of the ring-shaped members and the stringers are formed. The framework is thereafter fitted on a winding jig, and a fiber-reinforced prepreg of tape form is wound around the framework. The entire assembly is subjected to curing and bagging processes. The jigs and bag are removed finally.

    摘要翻译： 通过以下步骤制造飞机机身结构。 首先准备多个环状构件，每个构件围绕其外周表面设置在其周向上与多个凹部间隔开的位置处。 设置有与凹部对应的各凸部的细长板构件，以形成桁条。 然后将环状构件以同轴间隔开的并排布置布置，然后将层压夹具插入到同轴布置的环形构件中，硅树脂袋插入其间，硅树脂袋具有敞开的相对端。 环形构件被放置在设置在层压夹具中的环形凹部中以及设置在袋中的相应形成的环形凹部中。 然后将桁条放置在环形构件上，其中凸起部分装配在环形构件的凹部中，从而形成环形构件和桁条的框架。 然后将框架安装在卷绕夹具上，并且将带状的纤维增强预浸料卷绕在框架周围。 整个组件经受固化和装袋过程。 最后卸下夹具和袋子。

    Method of making a leading edge structure of aircraft airfoil
    7.
    发明授权
    Method of making a leading edge structure of aircraft airfoil 有权
    制造飞机机翼前缘结构的方法

    公开(公告)号：US06279228B1

    公开(公告)日：2001-08-28

    申请号：US09634986

    申请日：2000-08-08

    申请人： Takashi Kobayashi ,  Michihiko Banno ,  Kazuaki Amaoka

    发明人： Takashi Kobayashi ,  Michihiko Banno ,  Kazuaki Amaoka

    IPC分类号： B21D5378

    CPC分类号： B64D15/04 ,  B21D26/055 ,  B21D26/059 ,  B21D53/92 ,  B64C3/28 ,  B64F5/10 ,  Y10T29/49336 ,  Y10T29/49339 ,  Y10T29/49622

    摘要： A leading edge structure of an aircraft airfoil comprises an outer skin, a front wall extended in the spanwise direction of the leading edge structure in a front section of the space defined by the outer skin so as to form an anti-icing duct together with a front part of the outer skin, and a plurality of ribs disposed in the space defined by the outer skin so as to form hot air passages. A laminar structure is formed by superposing upper and lower sheets of a superplastic titanium alloy, inserting a pair of core sheets of a superplastic titanium alloy between the upper and the lower sheet, and forming release agent layers in predetermined regions between the sheets. A structure having at least the outer skin, the front wall and ribs is formed by joining together parts of the superposed sheets corresponding to regions not coated with the release agent layers by diffusion bonding or welding, heating the laminar structure in a forming mold, supplying a superplastic forming gas into spaces between parts of the superposed sheets corresponding to regions coated with the release agent layers to subject the same parts of the superposed sheets to superplastic deformation and to press the upper sheet and the lower sheet against the forming surface of the forming mold.

    摘要翻译： 飞机机翼的前缘结构包括外皮，在外皮的空间前部的前缘结构的翼展方向上延伸的前壁，以便与外皮形成防冰导管， 外皮的前部，以及设置在由外皮限定的空间中的多个肋，以便形成热空气通道。 层叠结构通过将超塑性钛合金的上下板叠合，在上下板之间插入一对超塑性钛合金芯片，并在片材之间的预定区域中形成剥离剂层而形成。 至少具有外皮，前壁和肋骨的结构通过扩散粘合或焊接将对应于未涂覆有脱模剂层的区域的重叠片材的部分接合在一起而形成，在成型模具中加热层状结构， 将超塑性成形气体输送到叠加片的部分之间的空间中，所述空间对应于涂覆有脱模剂层的区域，以使叠加的片材的相同部分经受超塑性变形，并将上部片材和下部片材压靠在成形 模子。

    Composite airfoil structures and their forming methods
    8.
    发明授权
    Composite airfoil structures and their forming methods 失效

    公开(公告)号：US06234423B1

    公开(公告)日：2001-05-22

    申请号：US09363396

    申请日：1999-07-29

    申请人： Makoto Hirahara ,  Yasuo Isano ,  Ryuhei Shimizu ,  Kazuaki Amaoka

    发明人： Makoto Hirahara ,  Yasuo Isano ,  Ryuhei Shimizu ,  Kazuaki Amaoka

    IPC分类号： B64C320

    CPC分类号： B64C3/18 ,  B64C3/20 ,  B64C3/26

    摘要： A box-structure airfoil is constructed of a composite material upper skin, a composite material lower skin 12 and a spar. Ribs and an elongate projection are formed integrally on the inner surface of each of the two skins. The upper and lower skins and the spar are simultaneously bonded by an adhesive to form a single structure. Since the ribs and the elongate projection are one-piece formed with each skin, it is possible to reduce the number of principal constituent components. Furthermore, since assembly operation is made by using the adhesive, there is no need for fasteners or the like for assembling. Moreover, the spar is bonded not only to Moreover, because not only a web but also flanges on both sides of the spar are bonded to the respective skins, it is possible to obtain a large strength. According to the invention, it is possible to reduce the number of principal constituent components and that of assembling components of an airfoil, thereby achieving its cost reduction.

    Method of making composite airfoil structures
    10.
    发明授权
    Method of making composite airfoil structures 失效
    制造复合翼型结构的方法

    公开(公告)号：US06689246B2

    公开(公告)日：2004-02-10

    申请号：US09824678

    申请日：2001-04-04

    申请人： Makoto Hirahara ,  Yasuo Isano ,  Ryuhei Shimizu ,  Kazuaki Amaoka

    发明人： Makoto Hirahara ,  Yasuo Isano ,  Ryuhei Shimizu ,  Kazuaki Amaoka

    IPC分类号： B64C320

    CPC分类号： B64C3/18 ,  B64C3/20 ,  B64C3/26

    摘要： A box-structure airfoil is constructed of a composite material uppers skin, a composite material lower a skin 12 and a spar. Ribs and an elongate projection are formed integrally on the inner surface of each of the two skins. The upper and lower skins and the spar are simultaneously bonded by an adhesive to form a single structure. Since the ribs and the elongate projection are one-piece formed with each skin, it is possible to reduce the number of principal constituent components. Furthermore, since assembly operation is made by using the adhesive, there is no need for fasteners or the like for assembling. Moreover, the flanges on both sides of the spar can also be bonded to the respective skins. According to the invention, it is possible to reduce the number of principal constituent components and that of assembling components of an airfoil, thereby achieving its cost reduction.

    摘要翻译： 箱形结构的翼型由复合材料上皮构成，复合材料降低皮肤12和翼梁。 肋和细长突起一体地形成在两个皮肤中的每一个的内表面上。 上下表皮和翼梁通过粘合剂同时粘合以形成单一结构。 由于肋和细长突起与每个皮肤成形为一体，因此可以减少主要构成部件的数量。 此外，由于通过使用粘合剂进行组装操作，因此不需要用于组装的紧固件等。 此外，翼梁两侧的凸缘也可以粘合到相应的表皮上。 根据本发明，可以减少主要构成部件的数量和组装翼型部件的数量，从而实现成本降低。