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1. 发明申请

WO2008043940A3 AIRCRAFT FUSELAGE MADE FROM LONGITUDINAL PANELS AND METHOD OF PRODUCING SUCH A FUSELAGE 审中-公开
标题翻译：远程面板制造的飞机熔接及其制造方法
公开(公告)号：WO2008043940A3
公开(公告)日：2008-06-12
申请号：PCT/FR2007052081
申请日：2007-10-04
申请人： AIRBUS FRANCE , GALLANT GUILLAUME , BERNADET PHILIPPE
发明人： GALLANT GUILLAUME , BERNADET PHILIPPE
IPC分类号： B64C1/00
CPC分类号： B64C1/068 , B64C2211/00
摘要： The invention relates to an aircraft fuselage comprising a nose cone (2), a tail section (2) and a central section (3), the central section comprising longitudinal panels (31 - 39) assembled directly with one another, at least one of these longitudinal panels having a length corresponding to the distance between the nose cone and the tail section in order to connect said nose cone with said tail section.
摘要翻译：本发明涉及一种包括鼻锥体（2），尾部部分（2）和中心部分（3）的飞行器机身，所述中心部分包括彼此直接组装的纵向面板（31-39），至少一个这些纵向面板的长度对应于鼻锥和尾部之间的距离，以将鼻锥与所述尾部部分连接。

2. 发明申请

WO2008096088A2 AIRCRAFT CABIN WINDOW ASSEMBLY METHOD 审中-公开
标题翻译：飞机舱窗户组装方法
公开(公告)号：WO2008096088A2
公开(公告)日：2008-08-14
申请号：PCT/FR2008050008
申请日：2008-01-03
申请人： AIRBUS FRANCE , GALLANT GUILLAUME , AGUERA DAMIEN , BERNADET PHILIPPE
发明人： GALLANT GUILLAUME , AGUERA DAMIEN , BERNADET PHILIPPE
CPC分类号： B64C1/1492 , Y10T29/49826
摘要： The invention relates to a method for assembling a cabin window to a bay in a side wall (12) of an aircraft fuselage, said cabin window comprising an outer transparent element (10) and at least one inner transparent element (11). According to the invention, a non-through hole is made in a portion of the side wall (12) along the edge of the bay. Subsequently, the outer transparent element (10) is positioned in the bay from the exterior of the fuselage, said element including a first part (13) which has a diameter greater than that of the bay and which is shaped to co-operate with the above-mentioned portion such as to block the outer transparent element (10) in the bay both laterally and longitudinally. The outer transparent element (10) also includes a second part (16) having a groove (17) that projects into the fuselage. The outer transparent element (10) and the at least one inner transparent element (11) are welded to the fuselage using a strap (22) which presses a seal (21) against at least the fuselage and the inner wall of the groove (17).
摘要翻译：本发明涉及一种用于将舱窗组装到飞行器机身的侧壁（12）中的舱的方法，所述舱窗包括外部透明元件（10）和至少一个内部透明元件（11）。根据本发明，沿侧壁的边缘在侧壁（12）的一部分中形成非通孔。随后，外部透明元件（10）从机身的外部定位在隔间中，所述元件包括第一部分（13），该第一部分的直径大于海湾的直径，并且其形状与上述部分，例如横向和纵向地阻挡隔间中的外部透明元件（10）。外部透明元件（10）还包括具有突出到机身中的凹槽（17）的第二部分（16）。外部透明元件（10）和至少一个内部透明元件（11）使用将密封件（21）压在至少机身和凹槽（17）的内壁上的带子（22）而焊接到机身上）。

3. 发明申请

WO2008096087A3 SECTION OF AIRCRAFT FUSELAGE AND AIRCRAFT INCLUDING ONE SUCH SECTION 审中-公开
标题翻译：飞机熔接和飞机部分，包括一个这样的部分
公开(公告)号：WO2008096087A3
公开(公告)日：2008-10-23
申请号：PCT/FR2008050006
申请日：2008-01-03
申请人： AIRBUS FRANCE , GALLANT GUILLAUME , AGUERA DAMIEN , BERNADET PHILIPPE
发明人： GALLANT GUILLAUME , AGUERA DAMIEN , BERNADET PHILIPPE
IPC分类号： B64C1/06 , B64C1/14
CPC分类号： B64C1/061 , B64C1/068 , B64C1/14
摘要： The invention relates to a section of fuselage for an aircraft, comprising frames and bays for receiving cabin windows (11). According to the invention, at least some of the frames include at least one frame segment that surrounds at least one bay, said frame segment comprising two branches (15, 16) that are disposed to the side of the bay. The ends of the branches are attached to each of the ends (17, 18) of the frame segment such as to form a Y.
摘要翻译：本发明涉及一种用于飞机的机身的一部分，包括用于接收舱窗（11）的框架和舱。根据本发明，至少一些框架包括围绕至少一个隔间的至少一个框架段，所述框架段包括设置在隔间侧面的两个分支（15,16）。分支的端部附接到框架段的每个端部（17,18），以形成Y.

4. 发明申请

WO2009050357A3 AIRCRAFT INCLUDING STIFFENER EDGE JUNCTIONS AND METHOD FOR PRODUCING ONE SUCH AIRCRAFT 审中-公开
标题翻译：包括用于生产一个这样的飞机的加强器边缘接头和方法的飞机
公开(公告)号：WO2009050357A3
公开(公告)日：2009-06-11
申请号：PCT/FR2008051630
申请日：2008-09-12
申请人： AIRBUS FRANCE , GAUTHIE LAURENT , BERNADET PHILIPPE
发明人： GAUTHIE LAURENT , BERNADET PHILIPPE
IPC分类号： B64C1/06
CPC分类号： B64C1/064 , B64C1/069 , B64C2001/0072 , Y02T50/433 , Y10T29/49826
摘要： The invention relates to a system for transmitting stresses at the intersection between a reinforcing frame and a stiffener in a fuselage and to a method for producing one such system. An aircraft fuselage includes stiffeners (4) interrupted by reinforcing frames (5). At said interruptions, the stresses experienced by the stiffeners (4) must be transmitted despite the presence of the reinforcing frames (5). Known solutions are difficult to manufacture and install and do not provide a simple stress transmission path when produced solely from composite materials. In order to solve this problem, the invention includes the creation of battens (15) that cover the ends (16) of consecutive sections (6) of a stiffener (4) and the skin (7) of the fuselage (1), extending under the reinforcing frame (5) in order to join said two consecutive sections (6).
摘要翻译：本发明涉及一种用于在机身中的加强框架和加强件之间的交叉处传递应力的系统以及用于生产一个这样的系统的方法。飞机机身包括由加强框架（5）中断的加强件（4）。在所述中断过程中，尽管存在加强框架（5），加强件（4）所经受的应力必须被传递。已知的解决方案难以制造和安装，并且当仅由复合材料制造时，不提供简单的应力传递路径。为了解决这个问题，本发明包括产生覆盖加强件（4）的连续部分（6）的端部（16）和机身（1）的皮肤（7）的端部（15），延伸在加强框架（5）下面，以便连接所述两个连续的部分（6）。

5. 发明申请

WO2009050357A9 AIRCRAFT INCLUDING STIFFENER EDGE JUNCTIONS AND METHOD FOR PRODUCING ONE SUCH AIRCRAFT 审中-公开
标题翻译：包括用于生产一个这样的飞机的加强器边缘接头和方法的飞机
公开(公告)号：WO2009050357A9
公开(公告)日：2010-07-29
申请号：PCT/FR2008051630
申请日：2008-09-12
申请人： ALRBUS OPERATIONS S A S , GAUTHIE LAURENT , BERNADET PHILIPPE
发明人： GAUTHIE LAURENT , BERNADET PHILIPPE
IPC分类号： B64C1/06
CPC分类号： B64C1/064 , B64C1/069 , B64C2001/0072 , Y02T50/433 , Y10T29/49826
摘要： The invention relates to a system for transmitting stresses at the intersection between a reinforcing frame and a stiffener in a fuselage and to a method for producing one such system. An aircraft fuselage includes stiffeners (4) interrupted by reinforcing frames (5). At said interruptions, the stresses experienced by the stiffeners (4) must be transmitted despite the presence of the reinforcing frames (5). Known solutions are difficult to manufacture and install and do not provide a simple stress transmission path when produced solely from composite materials. In order to solve this problem, the invention includes the creation of battens (15) that cover the ends (16) of consecutive sections (6) of a stiffener (4) and the skin (7) of the fuselage (1), extending under the reinforcing frame (5) in order to join said two consecutive sections (6).
摘要翻译：本发明涉及一种用于在机身中的加强框架和加强件之间的交叉处传递应力的系统以及用于生产一个这样的系统的方法。飞机机身包括由加强框架（5）中断的加强件（4）。在所述中断过程中，尽管存在加强框架（5），加强件（4）所经受的应力必须被传递。已知的解决方案难以制造和安装，并且当仅由复合材料制造时，不提供简单的应力传递路径。为了解决这个问题，本发明包括产生覆盖加强件（4）的连续部分（6）的端部（16）和机身（1）的皮肤（7）的端部（15），延伸在加强框架（5）下面，以便连接所述两个连续的部分（6）。

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