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公开(公告)号：US08926786B1
公开(公告)日：2015-01-06
申请号：US13364995
申请日：2012-02-02
IPC分类号： B32B37/00
CPC分类号： B29C70/086 , B29D24/007 , B29L2031/608 , B32B3/04 , B32B3/12 , B32B3/30 , B32B5/26 , B32B7/12 , B32B15/14 , B32B29/02 , B32B2262/101 , B32B2262/106 , B32B2307/54 , B32B2307/546 , B32B2307/718 , B32B2605/18 , E04C2/365 , Y10T428/24149
摘要： A method of manufacturing a composite panel is described. The method includes pre-stabilizing a honeycomb core with at least one layer of a pre-stabilizing material, surrounding the honeycomb core with at least one composite laminate skin layer, and curing the at least one composite laminate skin layer.
摘要翻译： 对复合板的制造方法进行说明。 该方法包括用至少一层预稳定材料预先稳定蜂窝芯，用至少一层复合层压板表层围绕蜂窝芯，并固化至少一层复合层压板表皮层。
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公开(公告)号：US07975965B2
公开(公告)日：2011-07-12
申请号：US12119898
申请日：2008-05-13
IPC分类号： B64C5/00
CPC分类号： B64C3/18 , B64C23/069 , Y02T50/164
摘要： An aircraft joint comprises a wing structure and a wing tip. The wing structure has a first part of a clevis and lug fastening system located around an outer end of the wing structure. The wing tip has a second part of the clevis and lug fastening system located around an end of the wing tip. The wing tip is capable of being joined to the outer end of the wing structure. An upper aerodynamic surface and a lower aerodynamic surface are formed by joining the wing structure and the wing tip. The first part and the second part are located about a center between the upper aerodynamic surface and the lower aerodynamic surface. The first part and the second part engage each other such that a moment reaction occurs around the upper aerodynamic surface and the lower aerodynamic surface.
摘要翻译： 飞机接头包括机翼结构和翼尖。 机翼结构具有位于翼结构的外端周围的U形夹和凸耳紧固系统的第一部分。 翼尖具有位于翼尖端部周围的U形夹和凸耳紧固系统的第二部分。 翼尖能够连接到机翼结构的外端。 通过连接翼结构和翼尖形成上空气动力学表面和下空气动力学表面。 第一部分和第二部分围绕上部空气动力学表面和下部空气动力学表面之间的中心定位。 第一部分和第二部分彼此接合，使得在上部空气动力学表面和下部空气动力学表面周围发生力矩反作用力。
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公开(公告)号：US07628358B2
公开(公告)日：2009-12-08
申请号：US11553017
申请日：2006-10-26
IPC分类号： B64C3/20
CPC分类号： B64C3/26
摘要： A wing panel structure for an aerospace vehicle or the like may include an outer layer of material having a predetermined thickness. A core structure may be placed on at least a portion of the outer layer of material. An inner layer of material may be placed at least on the core structure. The inner layer of material may have a selected thickness less than the predetermined thickness of the outer layer of material.
摘要翻译： 用于航空航天车辆等的翼板结构可以包括具有预定厚度的外层材料。 核心结构可以放置在外层材料的至少一部分上。 材料的内层可以至少放置在芯结构上。 材料的内层可以具有小于外层材料的预定厚度的选定厚度。
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公开(公告)号：US20090283639A1
公开(公告)日：2009-11-19
申请号：US12119898
申请日：2008-05-13
IPC分类号： B64C3/18
CPC分类号： B64C3/18 , B64C23/069 , Y02T50/164
摘要： An aircraft joint comprises a wing structure and a wing tip. The wing structure has a first part of a clevis and lug fastening system located around an outer end of the wing structure. The wing tip has a second part of the clevis and lug fastening system located around an end of the wing tip. The wing tip is capable of being joined to the outer end of the wing structure. An upper aerodynamic surface and a lower aerodynamic surface are formed by joining the wing structure and the wing tip. The first part and the second part are located about a center between the upper aerodynamic surface and the lower aerodynamic surface. The first part and the second part engage each other such that a moment reaction occurs around the upper aerodynamic surface and the lower aerodynamic surface.
摘要翻译： 飞机接头包括机翼结构和翼尖。 机翼结构具有位于翼结构的外端周围的U形夹和凸耳紧固系统的第一部分。 翼尖具有位于翼尖端部周围的U形夹和凸耳紧固系统的第二部分。 翼尖能够连接到机翼结构的外端。 通过连接翼结构和翼尖形成上空气动力学表面和下空气动力学表面。 第一部分和第二部分围绕上部空气动力学表面和下部空气动力学表面之间的中心定位。 第一部分和第二部分彼此接合，使得在上部空气动力学表面和下部空气动力学表面周围发生力矩反作用力。
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公开(公告)号：US20090155524A1
公开(公告)日：2009-06-18
申请号：US11955959
申请日：2007-12-13
CPC分类号： B29C70/086 , B29D24/007 , B29L2031/608 , B32B3/04 , B32B3/12 , B32B3/30 , B32B5/26 , B32B7/12 , B32B15/14 , B32B29/02 , B32B2262/101 , B32B2262/106 , B32B2307/54 , B32B2307/546 , B32B2307/718 , B32B2605/18 , E04C2/365 , Y10T428/24149
摘要： A method of manufacturing a composite panel is described. The method includes pre-stabilizing a honeycomb core with at least one layer of a pre-stabilizing material, surrounding the honeycomb core with at least one composite laminate skin layer, and curing the at least one composite laminate skin layer.
摘要翻译： 对复合板的制造方法进行说明。 该方法包括用至少一层预稳定材料预先稳定蜂窝芯，用至少一层复合层压板表层围绕蜂窝芯，并固化至少一层复合层压板表皮层。
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公开(公告)号：US20080277531A1
公开(公告)日：2008-11-13
申请号：US11747760
申请日：2007-05-11
CPC分类号： B29C70/088 , B29C70/20 , B29C70/22 , B29C70/30 , B29C70/386 , B29L2031/3076 , Y02T50/43 , Y10T428/24
摘要： Hybrid composite panel systems and methods are disclosed. In one embodiment, an assembly includes a primary section, a matrix member engaged with the primary section, and a secondary section engaged with the matrix member opposite the primary section. The primary section includes a plurality of first composite layers reinforced with a first reinforcing material, and the secondary section includes a plurality of second composite layers reinforced with a second reinforcing material. The primary and secondary sections are configured to bear an operating load at least partially transversely to the first and second composite layers, and are asymetrically configured such that the primary section bears a majority of the applied operating load.
摘要翻译： 公开了混合复合面板系统和方法。 在一个实施例中，组件包括主要部分，与主要部分接合的矩形部件以及与基部部件相对的主要部分接合的次级部分。 主要部分包括用第一增强材料增强的多个第一复合层，并且次级部分包括用第二增强材料增强的多个第二复合层。 主要部分和次要部分被构造成承受至少部分地横向于第一和第二复合层的操作载荷，并且被非对称地构造成使得主要部分承受所施加的操作载荷的大部分。
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公开(公告)号：US20080099613A1
公开(公告)日：2008-05-01
申请号：US11553017
申请日：2006-10-26
IPC分类号： B64C3/20
CPC分类号： B64C3/26
摘要： A wing panel structure for an aerospace vehicle or the like may include an outer layer of material having a predetermined thickness. A core structure may be placed on at least a portion of the outer layer of material. An inner layer of material may be placed at least on the core structure. The inner layer of material may have a selected thickness less than the predetermined thickness of the outer layer of material.
摘要翻译： 用于航空航天车辆等的翼板结构可以包括具有预定厚度的外层材料。 核心结构可以放置在外层材料的至少一部分上。 材料的内层可以至少放置在芯结构上。 材料的内层可以具有小于外层材料的预定厚度的选定厚度。
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