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公开(公告)号：US08434716B2
公开(公告)日：2013-05-07
申请号：US12965451
申请日：2010-12-10
IPC分类号： B64C1/14
CPC分类号： B64C1/10 , B64C1/36 , Y10T156/10
摘要： An aircraft forward pressure bulkhead and an aircraft crown panel are described herein. The forward pressure bulkhead includes a malleable and deformable dome that is configured to “catch” foreign objects, such as birds. The dome is intentionally designed to deform in response to a foreign object strike that imparts at least a threshold amount of impact energy to the bulkhead. The dome is free of rigid stiffeners and non-deformable reinforcement members that would otherwise hinder the flexible characteristic of the dome. Practical embodiments of the bulkhead utilize fewer parts, are less heavy, and are less expensive than traditional bulkheads that utilize rigid stiffeners. The crown panel has similar compliant characteristics. The crown panel is designed to simultaneously deform and deflect in response to foreign object impacts such as birds and hail. The crown panel is formed from a monolithic one-piece material, such as aluminum, and various reinforcing features are integrally formed in the material.
摘要翻译： 这里描述了飞机前进压舱壁和飞机冠面板。 前向压力舱壁包括可塑性和可变形的穹顶，其配置成“捕获”诸如鸟类的异物。 圆顶被有意地设计成响应于向舱壁施加至少一个阈值量的冲击能量的异物撞击而变形。 圆顶没有刚性加强件和不可变形的加强件，否则会妨碍圆顶的柔性特性。 隔板的实际实施例使用更少的部件，更不重，并且比使用刚性加强件的传统舱壁便宜。 冠面板具有类似的柔顺特性。 冠面板设计成可以响应诸如鸟和冰雹等异物影响而同时变形和偏转。 冠面板由诸如铝的单片整体材料形成，并且在该材料中一体地形成各种增强特征。
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公开(公告)号：US08398021B2
公开(公告)日：2013-03-19
申请号：US11682818
申请日：2007-03-06
IPC分类号： B64C1/12
CPC分类号： B64C1/10 , B64C1/36 , Y10T156/10
摘要： An aircraft forward pressure bulkhead and an aircraft crown panel are described herein. The forward pressure bulkhead includes a malleable and deformable dome that is configured to “catch” foreign objects, such as birds. The dome is intentionally designed to deform in response to a foreign object strike that imparts at least a threshold amount of impact energy to the bulkhead. The dome is free of rigid stiffeners and non-deformable reinforcement members that would otherwise hinder the flexible characteristic of the dome. Practical embodiments of the bulkhead utilize fewer parts, are less heavy, and are less expensive than traditional bulkheads that utilize rigid stiffeners. The crown panel has similar compliant characteristics. The crown panel is designed to simultaneously deform and deflect in response to foreign object impacts such as birds and hail. The crown panel is formed from a monolithic one-piece material, such as aluminum, and various reinforcing features are integrally formed in the material.
摘要翻译： 这里描述了飞机前进压舱壁和飞机冠面板。 前向压力舱壁包括可塑性和可变形的穹顶，其构造成捕获诸如鸟类的异物。 圆顶被有意地设计成响应于向舱壁施加至少一个阈值量的冲击能量的异物撞击而变形。 圆顶没有刚性加强件和不可变形的加强件，否则会妨碍圆顶的柔性特性。 隔板的实际实施例使用更少的部件，更不重，并且比使用刚性加强件的传统舱壁便宜。 冠面板具有类似的柔顺特性。 冠面板设计成可以响应诸如鸟和冰雹等异物影响而同时变形和偏转。 冠面板由诸如铝的单片整体材料形成，并且在该材料中一体地形成各种增强特征。
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3.发明申请AIRCRAFT HAVING A FORWARD-FACING SECTION THAT DEFLECTS ELASTICALLY UNDER IMPACT LOADS 审中-公开具有在冲击负载下弹性偏移的前进部分的飞机公开(公告)号：US20100282904A1
公开(公告)日：2010-11-11
申请号：US12839286
申请日：2010-07-19
申请人： Max U. Kismarton , William J. Koch
发明人： Max U. Kismarton , William J. Koch
IPC分类号： B64C1/06
CPC分类号： B64C1/00 , B29C70/342 , B29K2105/246 , B29K2995/0089 , B29L2031/3082 , B64C1/068 , B64C1/12 , B64C2001/0072 , Y02T50/43
摘要： An aircraft comprises a forward-facing aircraft section including composite aircraft skin and a substructure for the skin. The substructure includes a plurality of hoop-shaped composite frames. The frames are designed to deflect elastically under bird impact loads.
摘要翻译： 一架飞机包括一个朝前的飞机部分，包括复合飞机皮肤和一个皮肤下层结构。 子结构包括多个环形复合框架。 这些框架设计成在鸟类撞击负载下弹性偏转。
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公开(公告)号：US5899463A
公开(公告)日：1999-05-04
申请号：US738277
申请日：1996-10-25
申请人： William J. Koch
发明人： William J. Koch
CPC分类号： B64D29/00 , F01D11/003 , F02K1/805 , F16J15/52 , F16J3/042 , F05D2220/323 , F05D2250/75 , Y10S277/921
摘要： A kiss seal (42) of C-shaped cross section is provided. The kiss seal (42) includes a first leg (54), a second leg (56), and an arcuate middle portion (46) extending therebetween. The first leg (54) includes a contact surface (24') positioned adjacent a separable flange (28). The second leg (56) is attached to an opposed attachment flange (18) using a face plate (20') and a number of screws (22). The second leg (56) is generally located directly beneath the first leg (54). During sealing use, the arcuate middle portion (46) extends greater-than-180 degrees and is located outboard of one or both flange outboard edges (31). This provides a resultant force vector (58) that acts to enhance sealing. The greater the pressure (P) on the arcuate middle portion (46), the greater the force vector components available to promote sealing.
摘要翻译： 提供C形横截面的吻封（42）。 亲密封（42）包括第一腿（54），第二腿（56）和在它们之间延伸的弓形中间部分（46）。 第一腿部（54）包括邻近可分离凸缘（28）定位的接触表面（24'）。 第二腿（56）使用面板（20'）和多个螺钉（22）附接到相对的附接凸缘（18）。 第二腿（56）通常位于第一腿（54）正下方。 在密封使用期间，弓形中间部分（46）延伸大于180度，并且位于一个或两个凸缘外侧边缘（31）的外侧。 这提供了用于增强密封的合力矢量（58）。 弧形中间部分（46）上的压力（P）越大，可用于促进密封的力矢量分量越大。
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公开(公告)号：US08376275B2
公开(公告)日：2013-02-19
申请号：US11636056
申请日：2006-12-08
申请人： Akif O. Bolukbasi , Thomas R. Baxter , Tuan A. Nguyen , Mostafa Rassaian , Kevin R. Davis , William J. Koch , Lee C. Firth
发明人： Akif O. Bolukbasi , Thomas R. Baxter , Tuan A. Nguyen , Mostafa Rassaian , Kevin R. Davis , William J. Koch , Lee C. Firth
IPC分类号： B64C1/00
CPC分类号： B64C1/062
摘要： Energy absorbing structure disposed beneath the cargo area of an aircraft provides maximum energy absorption and structural strength using carbon fiber reinforced epoxy composites. The energy absorbing structure uses laminated stanchions having ply drop-offs to produce stable, progressive crushing of the stanchions during a wheels-up crash landing. Integrally formed flanges on the stanchions allow direct mounting of the stanchions on the structural members of the aircraft, without the need for specialized fittings.
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公开(公告)号：US07997529B2
公开(公告)日：2011-08-16
申请号：US12042629
申请日：2008-03-05
IPC分类号： B64C7/00
摘要： A pressurized bulkhead or panel for an aircraft includes an energy absorbing skin that deforms in response to an object strike that imparts at least a threshold amount of impact energy to the skin. The skin may be configured as a dome or a lofted panel that is essentially free of rigid stiffeners and non-deformable reinforcement members that would otherwise hinder the flexible characteristics of the skin. The skin may be formed from a monolithic one-piece material, such as metal of composites, and may include various integrally formed reinforcing features.
摘要翻译： 用于飞行器的加压隔板或面板包括能量吸收皮肤，其响应于向皮肤施加至少阈值量的冲击能量的物体撞击而变形。 皮肤可以被配置为基本上没有刚性加强件和不可变形的加强件的圆顶或顶部面板，否则会妨碍皮肤的柔性特性。 皮肤可以由单片整体材料形成，例如复合材料的金属，并且可以包括各种整体形成的增强特征。
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公开(公告)号：US20110101164A1
公开(公告)日：2011-05-05
申请号：US12965451
申请日：2010-12-10
CPC分类号： B64C1/10 , B64C1/36 , Y10T156/10
摘要： An aircraft forward pressure bulkhead and an aircraft crown panel are described herein. The forward pressure bulkhead includes a malleable and deformable dome that is configured to “catch” foreign objects, such as birds. The dome is intentionally designed to deform in response to a foreign object strike that imparts at least a threshold amount of impact energy to the bulkhead. The dome is free of rigid stiffeners and non-deformable reinforcement members that would otherwise hinder the flexible characteristic of the dome. Practical embodiments of the bulkhead utilize fewer parts, are less heavy, and are less expensive than traditional bulkheads that utilize rigid stiffeners. The crown panel has similar compliant characteristics. The crown panel is designed to simultaneously deform and deflect in response to foreign object impacts such as birds and hail. The crown panel is formed from a monolithic one-piece material, such as aluminum, and various reinforcing features are integrally formed in the material.
摘要翻译： 这里描述了飞机前进压舱壁和飞机冠面板。 前向压力舱壁包括可塑性和可变形的穹顶，其配置成“捕获”诸如鸟类的异物。 圆顶被有意地设计成响应于向舱壁施加至少一个阈值量的冲击能量的异物撞击而变形。 圆顶没有刚性加强件和不可变形的加强件，否则会妨碍圆顶的柔性特性。 隔板的实际实施例使用更少的部件，更不重，并且比使用刚性加强件的传统舱壁便宜。 冠面板具有类似的柔顺特性。 冠面板设计成可以响应诸如鸟和冰雹等异物影响而同时变形和偏转。 冠面板由诸如铝的单片整体材料形成，并且在该材料中一体地形成各种增强特征。
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公开(公告)号：US07871040B2
公开(公告)日：2011-01-18
申请号：US11558735
申请日：2006-11-10
申请人： Shin S. Lee , Adrian Viisoreanu , William J. Koch
发明人： Shin S. Lee , Adrian Viisoreanu , William J. Koch
IPC分类号： B64C1/12
CPC分类号： B64C1/068 , B64C1/12 , B64C2001/0072 , Y02T50/43
摘要： A composite panel structure for an aircraft includes a plurality of annular, hat-shaped frames disposed coaxially along a long axis of the aircraft in a spaced, parallel relationship, an inner skin having an inner surface bonded to an outer surface of the hat frames, a plurality of elongated, hat-shaped stringers disposed in a longitudinal direction along an outer surface of the inner skin in a spaced, parallel relationship, a solid or rigid foam offset bonded to an outer surface of each of the stringers, and an outer skin having an inner surface bonded to an upper surface of each of the offsets. The inner skin carries the loads of the structure and the outer skin defines an aerodynamic surface of the aircraft and provides impact and lighting protection. The frames, inner skin and stringers are formed on a single forming tool and cured and bonded with each other simultaneously.
摘要翻译： 用于飞行器的复合面板结构包括多个环形的帽形框架，其以间隔开的平行关系沿着飞行器的长轴同轴设置，内表面具有结合到帽子框架的外表面的内表面， 多个细长的帽形桁条，沿间隔开的平行关系沿着内表皮的外表面在纵向方向上设置，固定或刚性的泡沫粘合到每个桁条的外表面上，外表皮 具有粘合到每个偏移的上表面的内表面。 内表皮承载结构的载荷，外表皮限定飞机的空气动力学表面，并提供冲击和照明保护。 框架，内皮和桁条形成在单个成形工具上并同时固化和粘合。
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公开(公告)号：US07766277B2
公开(公告)日：2010-08-03
申请号：US11335275
申请日：2006-01-19
IPC分类号： H01Q1/42
CPC分类号： B64C1/10 , B64C1/36 , Y10T156/10
摘要： An aircraft forward pressure bulkhead as described herein includes a malleable and deformable dome that is configured to “catch” foreign objects, such as birds. The dome is intentionally designed to deform in response to a foreign object strike that imparts at least a threshold amount of impact energy to the bulkhead. The dome is free of rigid stiffeners and non-deformable reinforcement members that would otherwise hinder the flexible characteristic of the dome. Practical embodiments of the bulkhead utilize fewer parts, are less heavy, and are less expensive than traditional bulkheads that utilize rigid stiffeners.
摘要翻译： 如本文所述的飞行器前进压力舱壁包括可延展且可变形的穹顶，其被配置为“捕获”异物，例如鸟。 圆顶被有意地设计成响应于向舱壁施加至少一个阈值量的冲击能量的异物撞击而变形。 圆顶没有刚性加强件和不可变形的加强件，否则会妨碍圆顶的柔性特性。 隔板的实际实施例使用更少的部件，更不重，并且比使用刚性加强件的传统舱壁便宜。
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公开(公告)号：US20080111024A1
公开(公告)日：2008-05-15
申请号：US11558735
申请日：2006-11-10
申请人： Shin S. Lee , Adrian Viisoreanu , William J. Koch
发明人： Shin S. Lee , Adrian Viisoreanu , William J. Koch
CPC分类号： B64C1/068 , B64C1/12 , B64C2001/0072 , Y02T50/43
摘要： A composite panel structure for an aircraft includes a plurality of annular, hat-shaped frames disposed coaxially along a long axis of the aircraft in a spaced, parallel relationship, an inner skin having an inner surface bonded to an outer surface of the hat frames, a plurality of elongated, hat-shaped stringers disposed in a longitudinal direction along an outer surface of the inner skin in a spaced, parallel relationship, a solid or rigid foam offset bonded to an outer surface of each of the stringers, and an outer skin having an inner surface bonded to an upper surface of each of the offsets. The inner skin carries the loads of the structure and the outer skin defines an aerodynamic surface of the aircraft and provides impact and lighting protection. The frames, inner skin and stringers are formed on a single forming tool and cured and bonded with each other simultaneously.
摘要翻译： 用于飞行器的复合面板结构包括多个环形的帽形框架，其以间隔开的平行关系沿着飞行器的长轴同轴设置，内表面具有结合到帽子框架的外表面的内表面， 多个细长的帽形桁条，沿间隔开的平行关系沿着内表皮的外表面在纵向方向上设置，固定或刚性的泡沫粘合到每个桁条的外表面上，外表皮 具有粘合到每个偏移的上表面的内表面。 内表皮承载结构的载荷，外表皮限定飞机的空气动力学表面，并提供冲击和照明保护。 框架，内皮和桁条形成在单个成形工具上并同时固化和粘合。
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