公开(公告)号：US20090277994A1

公开(公告)日：2009-11-12

申请号：US12119210

申请日：2008-05-12

申请人： Fabiano LOBATO ,  Clovis Augusto Ferreira ,  Jose Donizette Aguiar ,  Lucio Camargo Fortes ,  Sadao Takanashi

发明人： Fabiano LOBATO ,  Clovis Augusto Ferreira ,  Jose Donizette Aguiar ,  Lucio Camargo Fortes ,  Sadao Takanashi

IPC分类号： B64C1/12 ,  B21D53/92

CPC分类号： B64C1/061 ,  B64C1/064 ,  B64C1/069 ,  B64C1/12 ,  B64C2001/0072 ,  B64C2001/0081 ,  Y02T50/43 ,  Y10T29/49622 ,  Y10T29/49826

摘要： An aircraft fuselage assembly of basic construction in composite materials employs metallic frames with reduced quantity of metallic shear ties attached to the composite stiffened skin, formed by two or more longitudinal panels, spliced with longitudinal metallic splice members. Typically, the latitudinal metallic frame members are fastened to the inward outstanding flange portion of the composite stringers which are in turn integrated to the skin. As such, the frame members are spaced from (floating over) the fuselage skin. An electrical path may thus be established so as to protect the fuselage structure against the impact of electrical discharges commonly encountered in the atmosphere by providing metallic shear ties interconnecting the frame and splice members so as to span the space therebetween.

摘要翻译： 复合材料基础结构的飞机机身组件使用金属框架，金属框架与金属剪切带的数量相连，附着在复合加强皮肤上，由两个或多个纵向面板形成，与纵向金属接合构件接合。 通常，纬向金属框架构件紧固到复合纵梁的向内突出的凸缘部分，这些凸缘部分又与皮肤集成。 因此，框架构件与机身皮肤间隔开（浮动）。 因此，可以建立电气路径，以便通过提供互连框架和接合构件以跨越它们之间的空间的金属剪切带来保护机身结构抵抗通常在大气中遇到的放电的冲击。

公开(公告)号：US07967250B2

公开(公告)日：2011-06-28

申请号：US12119210

申请日：2008-05-12

申请人： Fabiano Lobato ,  Clóvis Augusto Eça Ferreira ,  José Donizette Aguiar ,  Lucio Camargo Fortes ,  Sadao Takanashi

发明人： Fabiano Lobato ,  Clóvis Augusto Eça Ferreira ,  José Donizette Aguiar ,  Lucio Camargo Fortes ,  Sadao Takanashi

IPC分类号： B64C1/00

CPC分类号： B64C1/061 ,  B64C1/064 ,  B64C1/069 ,  B64C1/12 ,  B64C2001/0072 ,  B64C2001/0081 ,  Y02T50/43 ,  Y10T29/49622 ,  Y10T29/49826

摘要： An aircraft fuselage assembly of basic construction in composite materials employs metallic frames with reduced quantity of metallic shear ties attached to the composite stiffened skin, formed by two or more longitudinal panels, spliced with longitudinal metallic splice members. Typically, the latitudinal metallic frame members are fastened to the inward outstanding flange portion of the composite stringers which are in turn integrated to the skin. As such, the frame members are spaced from (floating over) the fuselage skin. An electrical path may thus be established so as to protect the fuselage structure against the impact of electrical discharges commonly encountered in the atmosphere by providing metallic shear ties interconnecting the frame and splice members so as to span the space therebetween.

摘要翻译： 复合材料基础结构的飞机机身组件使用金属框架，金属框架与金属剪切带的数量相连，附着在复合加强皮肤上，由两个或多个纵向面板形成，与纵向金属接合构件接合。 通常，纬向金属框架构件紧固到复合纵梁的向内突出的凸缘部分，这些凸缘部分又与皮肤集成。 因此，框架构件与机身皮肤间隔开（浮动）。 因此，可以建立电气路径，以便通过提供互连框架和接合构件以跨越它们之间的空间的金属剪切带来保护机身结构抵抗通常在大气中遇到的放电的冲击。