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272 条记录 (耗时 0.019 秒)

    Fiber/metal laminate splice
    68.
    发明授权
    Fiber/metal laminate splice 失效

    公开(公告)号：US5567535A

    公开(公告)日：1996-10-22

    申请号：US238143

    申请日：1994-05-04

    申请人： Richard G. Pettit

    发明人： Richard G. Pettit

    IPC分类号： B29C70/08 ,  B32B15/14 ,  B64C1/00 ,  B64C1/12 ,  B23B7/10

    CPC分类号： B64C1/12 ,  B29C70/088 ,  B32B15/14 ,  B29K2105/256 ,  B29K2705/00 ,  B64C2001/0072 ,  B64C2001/0081 ,  Y02T50/433 ,  Y10S428/902 ,  Y10T428/12444 ,  Y10T428/12632 ,  Y10T428/12639 ,  Y10T428/12764 ,  Y10T428/187 ,  Y10T428/31681

    摘要： Currently, fiber/metal laminate sheets are limited in width due to restrictions in the width of thin metal sheets available. This invention solves that problem by providing an integral splice concept and a method for manufacturing a laminate employing the inventive concept. Specifically, a fiber/metal laminate sheet is provided having at least two metal plies and at least one fiber layer. Each of the metal plies comprises at least two metal sheets which are arranged side-by-side and have sheet metal breaks therebetween. All of the sheet metal breaks lie within the integral splice. An important feature of the invention is that the sheet metal breaks in each metal ply are staggered widthwise across the laminate with respect to the sheet metal breaks in the remaining metal plies, in accordance with a predetermined metal break staggering pattern, thereby maximizing the bond engagement of the discontinuous metal plies with the adjacent fiber layers. Another important inventive feature is that the fiber layers are continuous through the integral splice region. The resultant spliced laminate may have any desired width, and is strong, fatigue-resistant, durable, and easy to manufacture.

    Composite structures and methods of manufacturing such structures
    70.
    发明授权
    Composite structures and methods of manufacturing such structures 失效
    复合结构及其制造方法

    公开(公告)号：US5451377A

    公开(公告)日：1995-09-19

    申请号：US128169

    申请日：1993-09-29

    申请人： Don L. Asher ,  George O. Sherrick

    发明人： Don L. Asher ,  George O. Sherrick

    IPC分类号： F16S1/00 ,  B29C70/44 ,  B29D99/00 ,  B64C1/00 ,  B32B3/28 ,  D01D5/20

    CPC分类号： B29D99/0014 ,  B29C70/44 ,  B29C70/446 ,  B29L2031/3076 ,  Y02T50/433 ,  Y10T428/24182 ,  Y10T428/2457 ,  Y10T428/24612 ,  Y10T428/24661

    摘要： A process for manufacturing stiffened composite skin panel structures possessing novel hollow crown-shaped stiffener elements, and further including any combination of forward spars, aft spars, and transversely extending shear ties. The novel process embraces fabrication and curing of these structures without the use of mandrels. In practicing the method, the crown-shaped stiffeners, spars and shear ties are integrally bonded to a planar or curved skin structure to provide axial stiffness in semimonocoque components such as aircraft wings, stabilizers, fuselages, etc. The method of fabrication yields highly producible, structurally efficient composite aircraft components.

    摘要翻译： 制造具有新颖的中空冠状​​加强件元件的加强复合蒙皮板结构的方法，并且还包括前翼梁，后翼梁和横向延伸的剪切连杆的任何组合。 该新颖的方法包括这些结构的制造和固化，而不使用心轴。 在实施该方法时，冠状加强件，翼梁和剪切连接件整体地结合到平面或弯曲的皮肤结构，以在诸如飞行器机翼，稳定器，机身等的半月板部件中提供轴向刚度。制造方法产生高度可生产性 ，结构高效的复合飞机部件。