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公开(公告)号：US20100297390A1
公开(公告)日：2010-11-25
申请号：US12438252
申请日：2007-08-30
申请人： Mathieu Forzan , Philippe Bernadet
发明人： Mathieu Forzan , Philippe Bernadet
IPC分类号： B32B1/00
CPC分类号： B64C1/064 , B64C1/12 , Y10T428/24174
摘要： A stiffener for a structure submitted to tensile and/or compression and/or shear stresses, that includes a shaped section including: a contact area with an element to be stiffened having a closed cross-section and providing stability, the aforementioned area including first and second legs; and a core normal to the element to be stiffened that provides a support surface capable of element recovery, the aforementioned core being formed by one of the two legs. Application in aircraft structures.
摘要翻译： 一种用于承受拉伸和/或压缩和/或剪切应力的结构的加强件，其包括成形部分，该成形部分包括：与要加固的元件的接触区域，其具有封闭的横截面并提供稳定性，上述区域包括第一和 第二条腿 以及提供能够恢复元件的支撑表面的要加强的元件垂直的芯，所述芯由两条腿之一形成。 飞机结构应用。
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公开(公告)号：US08524352B2
公开(公告)日：2013-09-03
申请号：US12438252
申请日：2007-08-30
申请人： Mathieu Forzan , Philippe Bernadet
发明人： Mathieu Forzan , Philippe Bernadet
IPC分类号： B64C1/06
CPC分类号： B64C1/064 , B64C1/12 , Y10T428/24174
摘要： A stiffener for a structure submitted to tensile and/or compression and/or shear stresses, that includes a shaped section including: a contact area with an element to be stiffened having a closed cross-section and providing stability, the aforementioned area including first and second legs; and a core normal to the element to be stiffened that provides a support surface capable of element recovery, the aforementioned core being formed by one of the two legs. Application in aircraft structures.
摘要翻译： 一种用于承受拉伸和/或压缩和/或剪切应力的结构的加强件，其包括成形部分，该成形部分包括：与要加固的元件的接触区域，其具有封闭的横截面并提供稳定性，上述区域包括第一和 第二条腿 以及提供能够恢复元件的支撑表面的要加强的元件垂直的芯，所述芯由两条腿之一形成。 飞机结构应用。
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3.发明授权Aircraft including stiffener edge junctions and method for producing one such aircraft 有权飞机包括加强筋边缘接头和生产这种飞机的方法公开(公告)号：US08480031B2
公开(公告)日：2013-07-09
申请号：US12738612
申请日：2008-09-12
申请人： Laurent Gauthie , Philippe Bernadet
发明人： Laurent Gauthie , Philippe Bernadet
IPC分类号： B64C1/06
CPC分类号： B64C1/064 , B64C1/069 , B64C2001/0072 , Y02T50/43 , Y10T29/49826
摘要： 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 interrupted by reinforcing frames. At aforementioned interruptions, the stresses experienced by the stiffeners must be transmitted despite the presence of the reinforcing frames. 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 disclosed embodiments include the creation of battens that cover the ends of consecutive sections of a stiffener and the skin of the fuselage, extending under the reinforcing frame in order to join aforementioned two consecutive sections.
摘要翻译： 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中断的扶强材。 在上述中断过程中，尽管存在加强框架，但是加强件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，所公开的实施例包括创建覆盖加强件的连续部分的端部和机身的皮肤的延伸部分，以加强上述两个连续的部分。
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公开(公告)号：US08371531B2
公开(公告)日：2013-02-12
申请号：US12521819
申请日：2008-01-03
IPC分类号： B64C1/14
CPC分类号： B64C1/1492 , Y10T29/49826
摘要： A method for assembling a cabin window to a bay in a side wall of an aircraft fuselage, where the cabin window including an outer transparent element and at least one inner transparent element, includes making a non-through hole in a portion of the side wall. The outer transparent element includes a first part having a diameter greater than that of the bay and which is shaped to co-operate with the portion of the side wall to block the outer transparent element in the bay both laterally and longitudinally. A second part of the outer transparent element has a groove that projects into the fuselage. The outer transparent element and the at least one inner transparent element are welded to the fuselage using a strap which presses a seal against at least the fuselage and the inner wall of the groove.
摘要翻译： 一种用于将舱窗组装到飞行器机身的侧壁中的舱的方法，其中所述舱窗包括外部透明元件和至少一个内透明元件，包括在侧壁的一部分中形成非通孔 。 外部透明元件包括具有大于间隔部分的直径的第一部分，该第一部分被成形为与侧壁的一部分配合以在横向和纵向阻挡隔离物中的外部透明元件。 外部透明元件的第二部分具有突出到机身中的凹槽。 外部透明元件和至少一个内部透明元件使用将至少机身和凹槽的内壁压紧密封件的带焊接到机身上。
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公开(公告)号：US09180625B2
公开(公告)日：2015-11-10
申请号：US13546441
申请日：2012-07-11
CPC分类号： B29C70/207 , B29B11/16 , B29C70/222 , B29C70/342 , B29C70/345 , B29L2031/3082 , Y02T50/43
摘要： A process for the production of an aircraft panel made of double-curved composite material, with the panel being obtained from a three-dimensional preform that includes fibers that are distributed in a defined arrangement, includes manufacturing a flat fiber preform (22), and deforming the flat preform (22) in such a way as to produce the three-dimensional preform, with the fibers following suitable trajectories at the flat preform in such a way as to obtain the defined arrangement of the fibers after deformation.
摘要翻译： 一种用于生产由双曲面复合材料制成的飞行器面板的方法，其特征在于，由三维预成型件获得，所述三维预成型件包括以限定的布置分布的纤维，包括制造扁平纤维预制件（22），以及 使扁平预成型件（22）变形，以便制造三维预成型件，其中纤维在平坦预制件上按照合适的轨迹，以便获得变形后的纤维的限定布置。
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公开(公告)号：US08567720B2
公开(公告)日：2013-10-29
申请号：US12521367
申请日：2008-01-03
IPC分类号： B64C1/14
摘要： The invention relates to a section of fuselage for an aircraft, including frames and bays for receiving cabin windows. According the disclosed embodiments, at least some of the frames include at least one frame segment that surrounds at least one bay, the frame segment having two branches that are disposed to the side of the bay. The ends of the branches are attached to each of the ends of the frame segment such as to form a Y.
摘要翻译： 本发明涉及飞机机身的一部分，包括用于接收舱窗的框架和舱。 根据所公开的实施例，至少一些框架包括围绕至少一个隔间的至少一个框架段，框架段具有设置在隔间侧面的两个分支。 分支的端部附接到框架段的每个端部，以形成Y.
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7.发明申请AIRCRAFT FUSELAGE MADE FROM LONGITUDINAL PANELS AND METHOD OF PRODUCING SUCH A FUSELAGE 审中-公开远程面板制造的飞机熔接及其制造方法公开(公告)号：US20100032523A1
公开(公告)日：2010-02-11
申请号：US12444972
申请日：2007-10-04
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, a tail section and a central section, the central section comprising longitudinal panels 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，尾部部分和中心部分的飞行器机身，中心部分包括彼此直接组装的纵向面板，这些纵向面板中的至少一个具有对应于鼻锥体之间的距离的长度 和尾部，以便将所述鼻锥与所述尾部部分连接。
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8.发明申请AIRCRAFT INCLUDING STIFFENER EDGE JUNCTIONS AND METHOD FOR PRODUCING ONE SUCH AIRCRAFT 有权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：US20100258676A1
公开(公告)日：2010-10-14
申请号：US12738612
申请日：2008-09-12
申请人： Laurent Gauthie , Philippe Bernadet
发明人： Laurent Gauthie , Philippe Bernadet
CPC分类号： B64C1/064 , B64C1/069 , B64C2001/0072 , Y02T50/43 , Y10T29/49826
摘要： 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 interrupted by reinforcing frames. At aforementioned interruptions, the stresses experienced by the stiffeners must be transmitted despite the presence of the reinforcing frames. 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 disclosed embodiments include the creation of battens that cover the ends of consecutive sections of a stiffener and the skin of the fuselage, extending under the reinforcing frame in order to join aforementioned two consecutive sections.
摘要翻译： 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中断的扶强材。 在上述中断过程中，尽管存在加强框架，但是加强件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，所公开的实施例包括创建覆盖加强件的连续部分的端部和机身的皮肤的延伸部分，以加强上述两个连续的部分。
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公开(公告)号：US07810756B2
公开(公告)日：2010-10-12
申请号：US11798374
申请日：2007-05-14
CPC分类号： B64C1/065 , B64C1/26 , B64C2001/0072 , B64C2001/0081 , Y02T50/43
摘要： A beam for reinforcing the structure of an aircraft is located inside the fuselage of the aircraft. The fuselage includes at least one pressurized zone (P) that is separated by at least one airtight wall (18) of at least one other non-pressurized zone (16), the beam and the at least one airtight wall being intersecting. The beam traverses the at least one airtight wall (18) that includes a cutaway that is adapted to the section of the beam, whereby sealing elements (30) are provided to ensure the sealing between the beam and the airtight wall (18) that is traversed.
摘要翻译： 用于加强飞机结构的梁位于飞机的机身内。 机身包括由至少一个其它非加压区域（16）的至少一个气密壁（18）分开的至少一个加压区域（P），所述梁和所述至少一个气密壁相交。 梁横穿至少一个密封壁（18），其包括适于梁的截面的切口，由此设置密封元件（30）以确保梁和气密壁（18）之间的密封，即密封壁 穿过
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公开(公告)号：US20100044513A1
公开(公告)日：2010-02-25
申请号：US12521819
申请日：2008-01-03
CPC分类号： B64C1/1492 , Y10T29/49826
摘要： A method for assembling a cabin window to a bay in a side wall of an aircraft fuselage, the cabin window including an outer transparent element and at least one inner transparent element. A non-through hole is made in a portion of the side wall along the edge of the bay. Subsequently, the outer transparent element is positioned in the bay from the exterior of the fuselage. The element includes a first part 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 in the bay both laterally and longitudinally. A second part of the outer transparent element has a groover that projects into the fuselage. The outer transparent element and the at least one inner transparent element are welded to the fuselage using a strap which presses a seal against at least the fuselage and the inner wall of the groove.
摘要翻译： 一种用于将舱窗组装到飞行器机身的侧壁中的舱的方法，所述舱窗包括外透明元件和至少一个内透明元件。 一个非贯通孔沿着该边缘的边缘在该侧壁的一部分中形成。 随后，外部透明元件从机身外部定位在隔间中。 该元件包括第一部分，该第一部分的直径大于该间隔部分的直径，并且该第一部分被成形为与上述部分配合，以便在横向和纵向上阻挡该间隔室中的外部透明元件。 外部透明元件的第二部分具有投影到机身中的凹槽。 外部透明元件和至少一个内部透明元件使用将至少机身和凹槽的内壁压紧密封件的带焊接到机身上。
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