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21. 发明申请

US20020195524A1 Method of fabricating a wing of composite material 失效
标题翻译：制作复合材料翼的方法
公开(公告)号：US20020195524A1
公开(公告)日：2002-12-26
申请号：US10227032
申请日：2002-08-22
申请人： Fuji Jukogyo Kabushiki Kaisha
发明人： Kazuaki Amaoka , Takayuki Nagao , Atsushi Harada , Naoya Takizawa , Hideyuki Sano , Yasuhiro Toi , Megumi Hiraki
IPC分类号： B64C001/00 , B64C003/00 , B64C005/00
CPC分类号： B64C3/00 , B64F5/10 , Y10T428/24174 , Y10T428/24273 , Y10T428/24289
摘要： A wing of composite material has an upper skin, a lower skin and a plurality of intermediate spars arranged between the upper and the lower skin. The intermediate spars extend from roots to tips of the upper and the lower skins. The intermediate spars are integrally formed with the upper and the lower skins or are adhesively bonded to the upper and the lower skins. The wing has a small number of parts, needs greatly reduced time for fabrication and can be fabricated at a low cost.
摘要翻译：复合材料的翼片具有上皮肤，下皮肤和布置在上皮肤和下皮肤之间的多个中间翼片。中间翼梁从根部延伸到上部和下部皮肤的尖端。中间翼梁与上下皮一体地形成，或者粘合到上下皮上。机翼具有少量零件，需要大大缩短制造时间，并可以低成本制造。

22. 发明申请

US20020134888A1 Variable airfoil wing 审中-公开
标题翻译：可变翼型翼
公开(公告)号：US20020134888A1
公开(公告)日：2002-09-26
申请号：US09816185
申请日：2001-03-26
发明人： Allison Earl Hall
IPC分类号： B64C001/00 , B64C003/00 , B64C005/00
CPC分类号： B64C3/50 , Y02T50/14
摘要： The invention lies in the field of fluid dynamics. In particular, the invention pertains to aircraft airfoils and wing designs. The variable airfoil wing is a simple concept which divides an aircraft wing into a forward segment and a rearward segment. The wing forward segment is fixed and the wing rearward segment is movable. Using a symmetrical airfoil design as the base wing shape, the rearward segment is rotated downward to increase the wing camber. When utilized in accordance with specific limitations, the wing design offers a broad range of aerodynamic capabilities.
摘要翻译：本发明在于流体动力学领域。特别地，本发明涉及飞机翼型和机翼设计。可变翼型翼是一种将飞机机翼分成前段和后段的简单概念。机翼前段固定，后翼段可移动。使用对称的翼型设计作为基座翼形，向后的部分向下旋转以增加机翼弧度。当根据具体限制使用时，机翼设计提供了广泛的空气动力学能力。

23. 发明申请

US20020005458A1 Airfoil suitable for forward and reverse flow 审中-公开
标题翻译：翼型适用于正向和反向流动
公开(公告)号：US20020005458A1
公开(公告)日：2002-01-17
申请号：US09877268
申请日：2001-06-08
发明人： Jay W. Carter JR. , John G. Roncz
IPC分类号： B64C003/00
CPC分类号： B64C3/14 , B64C27/023 , B64C27/467 , B64C2003/147 , Y02T50/12
摘要： An airfoil has a concave rear top surface, a concave rear bottom surface, and a rounded trailing edge to increase the lift-to-drag ratio of the airfoil at small angles of attack when air is flowing from the trailing edge to the leading edge (reverse flow), while maintaining a high lift-to-drag ratio when air is flowing from the leading edge to the trailing edge (forward flow). The airfoil design results from a performance compromise between forward and reverse airflow. For structural reasons, the thickness of the airfoil in proportion to its chord length may change along the blade radius. Thus, a family of airfoils has been designed that promote low-drag laminar flow with both forward and reverse flow, permit operation of the airfoil with reverse flow over a reasonable range of angles of attack, and achieve high lift with forward flow.
摘要翻译：机翼具有凹的后顶表面，凹后的后底表面和圆形的后缘，以当空气从后缘流到前缘时在较小的迎角下增加翼型的升降比（反向流动），同时当空气从前缘流向后缘（向前流动）时保持较高的提升阻力比。机翼设计是由于正向和反向气流之间的性能折衷。由于结构原因，与翼弦长度成比例的翼型件的厚度可能沿叶片半径而变化。因此，已经设计了一系列翼型，其促进具有正向和反向流动的低阻力层流，允许在合适的迎角范围内以相反的流动操作翼型件，并且具有向前流动的高升程。

24. 发明申请

US20040124310A1 Blade member for airplane 有权
标题翻译：飞机的叶片成员
公开(公告)号：US20040124310A1
公开(公告)日：2004-07-01
申请号：US10619623
申请日：2003-07-16
发明人： Daiya Yamashita , Fumihiko Shikano , Hiroshi Kato , Akira Kaneko , Takumi Shibata
IPC分类号： B64C001/00 , B64C003/00 , B64C005/00
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。

25. 发明申请

US20040118978A1 Helicopter rotor and method of repairing same 审中-公开
标题翻译：直升机转子及其修理方法
公开(公告)号：US20040118978A1
公开(公告)日：2004-06-24
申请号：US10326995
申请日：2002-12-24
发明人： Bruce D. Anning
IPC分类号： B64C001/00 , B64C003/00 , B64C005/00
CPC分类号： B64C11/205 , B64C27/473
摘要： An aerofoil, particularly a helicopter main rotor blade has a leading edge protector comprising a strip of resilient polymer, preferably polyurethane, adhered to the leading edge of the blade.
摘要翻译：机翼，特别是直升机主转子叶片具有前缘保护器，其包括粘附到叶片的前缘上的弹性聚合物条，优选聚氨酯。

26. 发明申请

US20030230669A1 Trailing edge shape of laminar-flow airfoil 有权
标题翻译：层流翼型的后缘形状
公开(公告)号：US20030230669A1
公开(公告)日：2003-12-18
申请号：US10373694
申请日：2003-02-27
发明人： Michimasa Fujino , Yoshinori Wariishi
IPC分类号： B64C003/00
CPC分类号： B64C3/14 , B64C2003/149 , Y02T50/12
摘要： An upper wing surface of a laminar-flow airfoil includes: a front profile portion which has a positive curvature radius, and which is provided to extend from a leading edge to a largest-thickness point located at a position corresponding to 38% of a wing chord length. The front profile portion forms a laminar-flow boundary layer. A central profile portion has a positive curvature radius and is provided to extend from the largest-thickness point to the vicinity of a position corresponding to 90% of the wing chord length at which a value obtained by dividing a thicknesswise difference between the position and the largest-thickness point by a distance in a direction of the wing chord from the largest-thickness point is equal to or smaller than 0.12. The central profile portion forms a gentle pressure gradient to suppress separation of the boundary layer and a rear profile portion has a negative curvature radius which is provided to extend from the vicinity of a position corresponding to 95% of the wing chord length to the trailing edge. The rear profile portion forming a pressure gradient is steeper than that formed by the central profile portion to induce slight separation of the boundary layer, whereby a head-lowering pitching moment about an aerodynamic center is decreased. Thus, it is possible to decrease an undesirable head-lowering pitching moment, while maintaining an effect of decreasing a drag on a laminar-flow airfoil.
摘要翻译：层流翼型件的上翼面包括：前轮廓部分，其具有正曲率半径，并且设置成从位于对应于翼的38％的位置的前缘到最大厚度点延伸弦长。前轮廓部分形成层流边界层。中心轮廓部分具有正曲率半径，并且被设置成从最大厚度点延伸到对应于翼弦长度的90％的位置附近，在该位置处，通过将位置和位置之间的厚度差除以最大厚度点距离最大厚度点的翼弦方向的距离等于或小于0.12。中央轮廓部分形成温和的压力梯度以抑制边界层的分离，并且后轮廓部分具有负曲率半径，该曲率半径设置为从对应于翼弦长度的95％的位置附近延伸到后缘。形成压力梯度的后轮廓部分比由中央轮廓部分形成的后轮廓部分更陡，以引起边界层的轻微分离，从而降低了围绕空气动力学中心的头部降低俯仰力矩。因此，可以在保持降低层流翼型上的阻力的作用的同时降低不期望的头降低俯仰力矩。

27. 发明申请

US20030226935A1 Structural members having improved resistance to fatigue crack growth 审中-公开
标题翻译：具有改善的抗疲劳裂纹扩展的结构构件
公开(公告)号：US20030226935A1
公开(公告)日：2003-12-11
申请号：US10286937
申请日：2002-11-02
发明人： Matthew D. Garratt , Gary H. Bray , Diana K. Denzer , Patrick Ulysse
IPC分类号： B64C001/00 , B64C003/00 , B64C005/00
CPC分类号： B64C3/24 , B21B1/026 , B21B1/08 , B21B2001/022 , B21B2003/001 , B21C23/001 , B21C23/14 , C22C21/16 , C22F1/053 , C22F1/057 , Y10S148/902 , Y10T428/12375 , Y10T428/12389 , Y10T428/1241
摘要： An extruded structural member having improved damage tolerance. The structural member comprising: a base section; a rib stiffening section having at least one pair of structural ribs, the structural ribs integral with the base section and projecting outwardly thereof; and at least one intra-rib area positioned between the pair of structural ribs, the intra-rib area having a microstructure with intentionally increased amounts of fiber texture to reduce the rate of fatigue crack growth in the extruded structural member.
摘要翻译：具有改善的损伤容限的挤压结构件。所述结构构件包括：基部; 肋加强部分，其具有至少一对结构肋，所述结构肋与所述基部一体并向外突出; 以及位于所述一对结构肋之间的至少一个肋内区域，所述肋内区域具有有意增加的纤维织构数量的微结构，以降低所述挤压结构构件中的疲劳裂纹扩展速率。

28. 发明申请

US20030192986A1 Variable size blended wing body aircraft 失效
标题翻译：可变尺寸混合翼体飞机
公开(公告)号：US20030192986A1
公开(公告)日：2003-10-16
申请号：US10437763
申请日：2003-05-14
发明人： Mark A. Page , Jennifer P. Whitlock , Matthew W. Wilks
IPC分类号： B64C001/00 , B64C003/00
CPC分类号： B64C1/0009 , B64C39/10 , B64C2039/105 , B64C2211/00
摘要： A blended wing body aircraft having a modular body having a body that includes a plurality of laterally-extending body structures. Changes to the cargo capacity of the aircraft is accomplished through the employment of body structures that are wider or narrower. Configuration in this manner provides the aircraft with a structure that is relatively strong and efficient. While the body structures of this embodiment are not shared across a family of variously sized aircraft, the base design of the body structures is readily modifiable to adjust for an increase or decrease in width associated with a desired change to the aircraft's cargo capacity.
摘要翻译：具有模块主体的混合翼体飞机具有包括多个横向延伸的主体结构的主体。通过使用更宽或更窄的身体结构，可以改变飞机的货物能力。以这种方式进行的配置为飞机提供了相对较强和高效的结构。虽然该实施例的车身结构不是在不同尺寸的飞机系列之间共享，但是主体结构的基本设计是容易地可修改的，以适应与飞机货物容量的期望变化相关联的宽度的增加或减少。

29. 发明申请

US20030173460A1 Tubular members integrated to form a structure 失效
标题翻译：管状构件整合形成结构
公开(公告)号：US20030173460A1
公开(公告)日：2003-09-18
申请号：US10366606
申请日：2003-02-13
发明人： W. Cullen Chapman JR.
IPC分类号： B64C001/00 , B64C003/00 , B64C005/00
CPC分类号： B29D24/004 , B29C53/60 , B29C53/821 , B29C53/822 , B29C70/32 , B29L2031/3076 , B64C1/06 , B64C2001/0072 , Y02T50/43
摘要： Integrally stiffened and formed, load carrying structures comprising a plurality of elongated thin-walled tubes placed co-extensively in a complementary side-by-side fashion which together form a hollow structure having a desired external contour. Integral skins forming the external and internal surfaces of the structure cooperatively therewith. The structure can be formed with an underlying internal support member spanning the interior of the load carrying structure, thereby connecting opposite sides of the structure together. Also, each of the tubes are wound with fibers in controlled orientations generally paralleling the direction of the loads applied to the tubes to optimize the strength to weight ratio of the tubes.
摘要翻译：整体加强和形成的承载结构包括多个细长的薄壁管，其以互补的并排方式共同放置，共同形成具有期望的外部轮廓的中空结构。与该结构的外表面和内表面协同地形成的整体表皮。该结构可以形成有横跨负载承载结构的内部的底部内部支撑构件，从而将结构的相对侧连接在一起。而且，每个管子以受控取向通常与施加在管上的负载方向平行的纤维缠绕，以优化管的强度与重量比。

30. 发明申请

US20030141409A1 Aircraft control system 有权
标题翻译：飞机控制系统
公开(公告)号：US20030141409A1
公开(公告)日：2003-07-31
申请号：US10310415
申请日：2002-12-05
发明人： Derek L. Lisoski , Greg T. Kendall
IPC分类号： B64C001/00 , B64C003/00 , B64C005/00
CPC分类号： B64C3/42 , B64C3/52 , B64C15/02 , B64C39/024 , B64C39/10 , B64C2201/028 , B64C2201/042 , B64C2201/102 , B64C2201/122 , B64C2201/126 , B64C2201/127 , B64C2201/146 , B64C2201/165 , B64D27/24 , B64D31/06 , B64D2211/00 , G05D1/0022 , G05D1/0077 , H04B7/18504 , Y02T50/12 , Y02T50/14 , Y02T50/44 , Y02T50/55 , Y02T50/62
摘要： A solar rechargeable, long-duration, span-loaded flying wing, having no fuselage or rudder. Having a two-hundred foot wingspan that mounts photovoltaic cells on most all of the wing's top surface, the aircraft uses only differential thrust of its eight propellers to turn, pitch and yaw. The wing is configured to deform under flight loads to position the propellers such that the control can be achieved. Each of five segments of the wing has one or more motors and photovoltaic arrays, and produces its own lift independent of the other segments, to avoid loading them. Five two-sided photovoltaic arrays, in all, are mounted on the wing, and receive photovoltaic energy both incident on top of the wing, and which is incident also from below, through a bottom, transparent surface.
摘要翻译：太阳能可再充电，长时间，跨度的飞翼，没有机身或方向舵。拥有两百英尺的翼展，将光伏电池安装在大部分机翼的顶部表面上，飞机只使用其八个螺旋桨的差速推力来转弯，俯仰和偏航。机翼构造成在飞行载荷下变形以定位螺旋桨，使得可以实现控制。翼的五个部分中的每一个具有一个或多个电动机和光伏阵列，并且独立于其它部分产生其自身的升降机，以避免加载它们。五个双面光伏阵列总体上安装在机翼上，并且接收能量入射到机翼的顶部并且从下方入射的光能通过底部的透明表面。

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