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1.发明授权Energy-absorbing structural element made of a composite material and aircraft fuselage having said absorber 有权由复合材料制成的能量吸收结构元件和具有所述吸收体的飞行器机身公开(公告)号：US08814092B2
公开(公告)日：2014-08-26
申请号：US12866935
申请日：2009-02-13
摘要： An aircraft fuselage has at least one reinforcement frame (13), at least one crossbar (14) and at least one energy-absorbing structural element (2) that includes a compression beam (21) having a longitudinal axis Z and oriented substantially in the direction of compression forces to be absorbed upon an impact, the compression beam being attached at a first end (213) thereof to the crossbar (14) and at a second end (214) thereof to the reinforcement frame (13). The compression beam (21) is attached at least one of its ends (213, 214) via a shoulder bracket (22), wherein the shoulder bracket further has the function of cutting the compression beam (21) in case of an impact.
摘要翻译： 飞机机身具有至少一个加强框架（13），至少一个横梁（14）和至少一个能量吸收结构元件（2），该能量吸收结构元件（2）包括具有纵向轴线Z的压缩梁（21） 在冲击时被吸收的压缩力的方向，压缩梁在其第一端（213）处附接到横杆（14），并且在其第二端（214）附接到加强框架（13）。 压缩梁（21）经由肩托（22）安装在其端部（213,214）中的至少一个上，其中肩部托架还具有在受到冲击的情况下切割压缩梁（21）的功能。
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公开(公告)号：US20100264272A1
公开(公告)日：2010-10-21
申请号：US12738600
申请日：2008-09-12
IPC分类号： B64C1/06
CPC分类号： B64C1/064 , B64C1/069 , B64C2001/0072 , Y02T50/43
摘要： An aircraft structure including stiffened panels assembled at the junction, without continuity of the stiffeners. Multiple panels are used to form the fuselage, tail units and wings of an aircraft. These panels include stiffeners which are interrupted at each panel junction. However, the stresses experienced by the stiffeners must be transmitted despite these interruptions. Known solutions require the use of at least one additional part per stiffener and per interruption. In order to solve this problem, the disclosed embodiments include a doubler necessitating at most one additional part per panel junction area for all of the interrupted stiffeners in this area.
摘要翻译： 一种飞机结构，包括在接合处组装的加强板，不加强筋的连续性。 多个面板用于形成飞机的机身，尾翼和机翼。 这些面板包括在每个面板连接处中断的加强件。 然而，尽管有这些中断，加强件经受的应力必须被传送。 已知的解决方案需要使用每个加强筋至少一个附加部件和每个中断。 为了解决这个问题，所公开的实施例包括对于该区域中的所有被中断的加强件，每个面板接合面积最多需要一个附加部件的倍增器。
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公开(公告)号：US08215584B2
公开(公告)日：2012-07-10
申请号：US12738600
申请日：2008-09-12
IPC分类号： B64C1/06
CPC分类号： B64C1/064 , B64C1/069 , B64C2001/0072 , Y02T50/43
摘要： An aircraft structure including stiffened panels assembled at the junction, without continuity of the stiffeners. Multiple panels are used to form the fuselage, tail units and wings of an aircraft. These panels include stiffeners which are interrupted at each panel junction. However, the stresses experienced by the stiffeners must be transmitted despite these interruptions. Known solutions require the use of at least one additional part per stiffener and per interruption. In order to solve this problem, the disclosed embodiments include a doubler necessitating at most one additional part per panel junction area for all of the interrupted stiffeners in this area.
摘要翻译： 一种飞机结构，包括在接合处组装的加强板，不加强筋的连续性。 多个面板用于形成飞机的机身，尾翼和机翼。 这些面板包括在每个面板连接处中断的加强件。 然而，尽管有这些中断，加强件经受的应力必须被传送。 已知的解决方案需要使用每个加强筋至少一个附加部件和每个中断。 为了解决这个问题，所公开的实施例包括对于该区域中的所有被中断的加强件，每个面板接合面积最多需要一个附加部件的倍增器。
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4.发明申请ENERGY-ABSORBING STRUCTURAL ELEMENT MADE OF A COMPOSITE MATERIAL AND AIRCRAFT FUSELAGE HAVING SAID ABSORBER 有权复合材料的能量吸收结构元件和具有吸收体的飞机熔接公开(公告)号：US20110042513A1
公开(公告)日：2011-02-24
申请号：US12866935
申请日：2009-02-13
摘要： An aircraft fuselage has at least one reinforcement frame (13), at least one crossbar (14) and at least one energy-absorbing structural element (2) that includes a compression beam (21) having a longitudinal axis Z and oriented substantially in the direction of compression forces to be absorbed upon an impact, the compression beam being attached at a first end (213) thereof to the crossbar (14) and at a second end (214) thereof to the reinforcement frame (13). The compression beam (21) is attached at least one of its ends (213, 214) via a shoulder bracket (22), wherein the shoulder bracket further has the function of cutting the compression beam (21) in case of an impact.
摘要翻译： 飞机机身具有至少一个加强框架（13），至少一个横梁（14）和至少一个能量吸收结构元件（2），该能量吸收结构元件（2）包括具有纵向轴线Z的压缩梁（21） 在冲击时被吸收的压缩力的方向，压缩梁在其第一端（213）处附接到横杆（14），并且在其第二端（214）附接到加强框架（13）。 压缩梁（21）经由肩托（22）安装在其端部（213,214）中的至少一个上，其中肩部托架还具有在受到冲击的情况下切割压缩梁（21）的功能。
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