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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：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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公开(公告)号：US07721995B2
公开(公告)日：2010-05-25
申请号：US11610444
申请日：2006-12-13
申请人： Richard B. Tanner , Ian C. Burford , Thomas V. Gendzwill , Gregory B. Doty , James R. Huck , Dean E. Wilson , Brian H. Korenaga
发明人： Richard B. Tanner , Ian C. Burford , Thomas V. Gendzwill , Gregory B. Doty , James R. Huck , Dean E. Wilson , Brian H. Korenaga
IPC分类号： B64C1/12
摘要： An innovative wing structure provides fibs to support skin panels without an attachment between the rib and the stringer free flange or the web. The support is provided by rib shear ties installed directly to the stringer skin flange. The rib incorporates a cut away to allow the stringer to pass through the rib. The composite stringer is an ‘I’ section and is stable under compression, not requiring mechanical methods to prevent rolling over.
摘要翻译： 创新的机翼结构提供纤维，以支撑皮肤面板，而不需要在肋和无筋边缘法兰或网之间的连接。 支撑由直接安装在纵梁皮肤法兰上的肋剪力提供。 肋骨包含切口以允许桁条穿过肋条。 复合纵梁是“I”截面，在压缩下是稳定的，不需要机械方法来防止翻滚。
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公开(公告)号：US20080173757A1
公开(公告)日：2008-07-24
申请号：US11867158
申请日：2007-10-04
申请人： Richard B. Tanner , Ian C. Burford , Thomas V. Gendzwill , Gregory B. Doty , James R. Huck , Dean E. Wilson , Brian H. Korenaga
发明人： Richard B. Tanner , Ian C. Burford , Thomas V. Gendzwill , Gregory B. Doty , James R. Huck , Dean E. Wilson , Brian H. Korenaga
IPC分类号： B64C1/12
摘要： A method and apparatus for an aircraft structure. In one advantageous embodiment, the aircraft structure may have a rib, a plurality of stringers, and a set of shear ties. The plurality of stringers may have skin flanges at ends of the plurality of stringers capable of being fastened to skin for the aircraft structure. The set of shear ties may extend from the rib and have a set of elongate members in which the set of elongate members are attached to the plurality of stringers.
摘要翻译： 一种飞机结构的方法和装置。 在一个有利的实施例中，飞行器结构可以具有肋，多个桁条和一组剪切连接。 多个桁条可以在多个桁条的端部具有能够紧固到飞行器结构的皮肤的皮肤凸缘。 剪切带的一组可以从肋延伸并且具有一组细长构件，其中该组细长构件附接到多个桁条。
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公开(公告)号：US07686251B2
公开(公告)日：2010-03-30
申请号：US11867158
申请日：2007-10-04
申请人： Richard B. Tanner , Ian C. Burford , Thomas V. Gendzwill , Gregory B. Doty , James R. Huck , Dean E. Wilson , Brian H. Korenaga
发明人： Richard B. Tanner , Ian C. Burford , Thomas V. Gendzwill , Gregory B. Doty , James R. Huck , Dean E. Wilson , Brian H. Korenaga
IPC分类号： B64C1/12
摘要： A method and apparatus for an aircraft structure. In one advantageous embodiment, the aircraft structure may have a rib, a plurality of stringers, and a set of shear ties. The plurality of stringers may have skin flanges at ends of the plurality of stringers capable of being fastened to skin for the aircraft structure. The set of shear ties may extend from the rib and have a set of elongate members in which the set of elongate members are attached to the plurality of stringers.
摘要翻译： 一种飞机结构的方法和装置。 在一个有利的实施例中，飞行器结构可以具有肋，多个桁条和一组剪切连接。 多个桁条可以在多个桁条的端部具有能够紧固到飞行器结构的皮肤的皮肤凸缘。 剪切带的一组可以从肋延伸并且具有一组细长构件，其中该组细长构件附接到多个桁条。
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公开(公告)号：US20080210821A1
公开(公告)日：2008-09-04
申请号：US11610444
申请日：2006-12-13
申请人： Richard B. Tanner , Ian C. Burford , Thomas V. Gendzwill , Gregory B. Doty , James R. Huck , Dean E. Wilson , Brian H. Korenaga
发明人： Richard B. Tanner , Ian C. Burford , Thomas V. Gendzwill , Gregory B. Doty , James R. Huck , Dean E. Wilson , Brian H. Korenaga
摘要： An innovative wing structure provides ribs to support skin panels without an attachment between the rib and the stringer free flange or the web. The support is provided by rib shear ties installed directly to the stringer skin flange. The rib incorporates a cut away to allow the stringer to pass through the rib. The composite stringer is an ‘I’ section and is stable under compression, not requiring mechanical methods to prevent rolling over.
摘要翻译： 创新的机翼结构提供了肋骨来支撑皮肤面板，而不需要在肋骨和无筋边缘法兰或腹板之间进行连接。 支撑由直接安装在纵梁皮肤法兰上的肋剪力提供。 肋骨包含切口以允许桁条穿过肋条。 复合纵梁是“I”截面，在压缩下是稳定的，不需要机械方法来防止翻滚。
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公开(公告)号：US20080023585A1
公开(公告)日：2008-01-31
申请号：US11027570
申请日：2004-12-29
申请人： Jan A. Kordel , Richard B. Tanner , Ian C. Burford , Victor A. Munsen , Daniel E. McGinty , Scott N. Rampton , Bruce R. Fox , James M. Kelly , Miles O. Johnson
发明人： Jan A. Kordel , Richard B. Tanner , Ian C. Burford , Victor A. Munsen , Daniel E. McGinty , Scott N. Rampton , Bruce R. Fox , James M. Kelly , Miles O. Johnson
IPC分类号： B64C3/00
CPC分类号： B64C3/00
摘要： Aircraft wing assemblies having both composite and metal panels are disclosed. In one embodiment, a wing assembly includes a support structure, an upper panel assembly formed from a metal material and coupled to the support structure, and a lower panel assembly formed from a composite material and coupled to the support structure. The metal material may be aluminum, titanium, or any other suitable metal, and the composite material may be a carbon fiber reinforced plastic (CFRP) material or other suitable composite material. In another embodiment, the upper panel assembly includes a downwardly depending first web portion, and the lower panel assembly includes an upwardly depending second web portion, the second web portion being proximate the first web portion, and an interface member of an isolating material is disposed between the first and second web portions.
摘要翻译： 公开了具有复合材料和金属板的飞机机翼组件。 在一个实施例中，翼组件包括支撑结构，由金属材料形成并联接到支撑结构的上面板组件，以及由复合材料形成并联接到支撑结构的下部面板组件。 金属材料可以是铝，钛或任何其它合适的金属，并且复合材料可以是碳纤维增强塑料（CFRP）材料或其它合适的复合材料。 在另一个实施例中，上面板组件包括向下悬垂的第一腹板部分，并且下面板组件包括向上悬垂的第二腹板部分，第二腹板部分靠近第一腹板部分，并且设置隔离材料的接口构件 在第一和第二纤维网部分之间。
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公开(公告)号：US07387277B2
公开(公告)日：2008-06-17
申请号：US11027570
申请日：2004-12-29
申请人： Jan A. Kordel , Richard B. Tanner , Ian C. Burford , Victor A. Munsen , Daniel E. McGinty , Scott N. Rampton , Bruce R. Fox , James M. Kelly , Miles O. Johnson
发明人： Jan A. Kordel , Richard B. Tanner , Ian C. Burford , Victor A. Munsen , Daniel E. McGinty , Scott N. Rampton , Bruce R. Fox , James M. Kelly , Miles O. Johnson
IPC分类号： B64C3/20
CPC分类号： B64C3/00
摘要： Aircraft wing assemblies having both composite and metal panels are disclosed. In one embodiment, a wing assembly includes a support structure, an upper panel assembly formed from a metal material and coupled to the support structure, and a lower panel assembly formed from a composite material and coupled to the support structure. The metal material may be aluminum, titanium, or any other suitable metal, and the composite material may be a carbon fiber reinforced plastic (CFRP) material or other suitable composite material. In another embodiment, the upper panel assembly includes a downwardly depending first web portion, and the lower panel assembly includes an upwardly depending second web portion, the second web portion being proximate the first web portion, and an interface member of an isolating material is disposed between the first and second web portions.
摘要翻译： 公开了具有复合材料和金属板的飞机机翼组件。 在一个实施例中，翼组件包括支撑结构，由金属材料形成并联接到支撑结构的上面板组件，以及由复合材料形成并联接到支撑结构的下部面板组件。 金属材料可以是铝，钛或任何其它合适的金属，并且复合材料可以是碳纤维增强塑料（CFRP）材料或其它合适的复合材料。 在另一个实施例中，上面板组件包括向下悬垂的第一腹板部分，并且下面板组件包括向上悬垂的第二腹板部分，第二腹板部分靠近第一腹板部分，并且设置隔离材料的接口构件 在第一和第二纤维网部分之间。
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