公开(公告)号：US06786452B2

公开(公告)日：2004-09-07

申请号：US10601650

申请日：2003-06-24

申请人： Daiya Yamashita ,  Hiroshi Kato ,  Jun Nakazawa

发明人： Daiya Yamashita ,  Hiroshi Kato ,  Jun Nakazawa

IPC分类号： B64C318

CPC分类号： B64C3/00 ,  B64C3/18

摘要： In a wing of an airplane, a front spar having a C-shape in section includes a web, flanges, and a reinforcing partition wall. An intermediate spar having an I-shape in section includes a web, flanges, and a reinforcing partition wall. Ribs can be positioned in a span direction by coupling front and rear portions of the ribs to the reinforcing partition wall of the front spar and the reinforcing partition wall of the intermediate spar, without the provision of an assembling jig having a positioning function and without the use of a special positioning member. In addition, the ribs can be positioned in a cord direction by bringing rear ends of the ribs into abutment against a front surface of the web of the intermediate spar. Thus, it is possible to assemble the wing of the airplane using an inexpensive assembling jig having no rib-positioning function.

摘要翻译： 在飞机的翼中，具有C形截面的前翼梁包括腹板，凸缘和加强分隔壁。 具有I形截面的中间翼梁包括腹板，凸缘和加强分隔壁。 通过将肋的前部和后部连接到前翼梁的加强分隔壁和中间翼梁的加强分隔壁，肋可以在跨度方向上定位，而不需要设置具有定位功能的组装夹具 使用特殊的定位构件。 此外，肋可以通过使肋的后端抵靠中间梁的腹板的前表面而沿绳索方向定位。 因此，可以使用没有肋定位功能的廉价的组装夹具来组装飞机的机翼。

公开(公告)号：US07104501B2

公开(公告)日：2006-09-12

申请号：US10619623

申请日：2003-07-16

申请人： Daiya Yamashita ,  Fumihiko Shikano ,  Hiroshi Kato ,  Akira Kaneko ,  Takumi Shibata

发明人： Daiya Yamashita ,  Fumihiko Shikano ,  Hiroshi Kato ,  Akira Kaneko ,  Takumi Shibata

IPC分类号： B64C3/20

CPC分类号： B23H9/00 ,  B23H7/02 ,  B23H9/10 ,  B64C27/473

摘要： It is an object to provide a blade member for an airplane which is simple in structure, and moreover is excellent with respects to weight, aerodynamic performance, cost, strength and durability. A vane of a double-slotted flap includes: an outer skin area surrounded by a first outer skin, a second outer skin, a leading edge and a trailing edge each having a predetermined wall thickness. Front and rear reinforcing areas are provided that extend in a span direction within the outer skin area and are connected to the first outer skin and the second outer skin. The outer skin area and the reinforcing areas are integrally formed by wire electrical discharge-machining. The first outer skin and the second outer skin respectively have thickened portions thicker than the other portions, and the trailing edge is formed to have a thickness which is approximately zero. This blade member can be simplified in structure, leading to reductions in the number of parts, number of assembling steps and weight. Moreover, no step nor seam is generated on a surface of the blade member, and hence it is possible to prevent an increase in drag and the generation of corrosion.

摘要翻译： 本发明的目的是提供一种结构简单的用于飞机的叶片构件，并且在重量，空气动力学性能，成本，强度和耐久性方面都是优异的。 双开口翼片的叶片包括：由第一外皮，第二外皮，前缘和后缘围绕的外皮区域，每个具有预定的壁厚。 提供前后加强区域，其在外皮肤区域内沿跨度方向延伸并连接到第一外皮和第二外皮。 外皮区域和加强区域通过电线放电加工一体形成。 第一外皮和第二外皮分别具有比其他部分更厚的加厚部分，并且后缘形成为具有近似为零的厚度。 该叶片构件可以简化结构，从而减少零件数量，组装步骤数量和重量。 此外，在叶片构件的表面上不产生台阶或接缝，因此可以防止阻力的增加和腐蚀的产生。

公开(公告)号：US06478254B2

公开(公告)日：2002-11-12

申请号：US09842159

申请日：2001-04-26

申请人： Nobuo Matsui ,  Daiya Yamashita

发明人： Nobuo Matsui ,  Daiya Yamashita

IPC分类号： B64C110

CPC分类号： B64C1/10

摘要： A skin/bulkhead structure comprising a barrel-shaped skin and a pressure bulkhead composed of a stiffening member and a bulkhead skin, wherein an end of the stiffening member is mechanically connected to an opening of the barrel-shaped skin through a first connecting member and marginal portion of the bulkhead skin is adhesive-connected to the opening through a second connecting member, the barrel-shaped skin, the stiffening member, the bulkhead skin, the first connecting member and the second connecting member being each made of a fiber-reinforced composite.

摘要翻译： 一种皮肤/隔板结构，包括桶形皮肤和由加强构件和隔板皮肤组成的压力隔板，其中加强构件的端部通过第一连接构件机械地连接到桶形皮肤的开口， 隔板皮肤的边缘部分通过第二连接构件与开口粘合连接，桶状表皮，加强构件，隔板表皮，第一连接构件和第二连接构件各自由纤维增强 综合。

公开(公告)号：US5807454A

公开(公告)日：1998-09-15

申请号：US711678

申请日：1996-09-04

申请人： Shun Kawabe ,  Keiichi Sato ,  Daiya Yamashita ,  Haruo Nakayama ,  Koji Shiraishi ,  Keizo Matsumoto

发明人： Shun Kawabe ,  Keiichi Sato ,  Daiya Yamashita ,  Haruo Nakayama ,  Koji Shiraishi ,  Keizo Matsumoto

IPC分类号： B29C70/44 ,  B29D99/00 ,  B64C3/28 ,  B64D15/04 ,  B32B31/00

CPC分类号： B29D99/0028 ,  B29C70/443 ,  B64C3/28 ,  B64D15/04 ,  B29C2791/001 ,  Y02T50/433 ,  Y10T156/1031

摘要： A leading edge structure for an aircraft has an outer wall, an inner wall disposed within the outer wall and including a partition with, the outer wall, the inner wall and the partition jointly defining a hot-air chamber, and a plurality of flow-rectifying fins or disposed in the hot-air chamber and compartmentalizing the hot-air chamber into a plurality of hot-air passages. The outer wall and the flow-rectifying fins are made of a fiber-reinforced synthetic resin and joined to each other by curing. The inner wall and the partition comprise a single component which is made of a fiber-reinforced synthetic resin, and being bonded to the outer wall. Alternatively, the inner wall and the partition are separate from each other and are joined to each other.

摘要翻译： 用于飞行器的前缘结构具有外壁，内壁，其设置在所述外壁内，并且包括与所述外壁，所述内壁和所述隔板共同限定热空气室的隔板， 整流翅片或设置在热空气室中并将热空气室分隔成多个热空气通道。 外壁和整流翅片由纤维增强合成树脂制成，并通过固化彼此接合。 内壁和隔板包括由纤维增强合成树脂制成并且被结合到外壁的单一部件。 或者，内壁和隔板彼此分离并且彼此接合。