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1.发明授权Method for the orbital assembly of aircraft sections made of composite material 有权用复合材料制成的飞机部件的轨道组装方法公开(公告)号：US08484848B2
公开(公告)日：2013-07-16
申请号：US12995535
申请日：2009-05-26
IPC分类号： B21D53/88
CPC分类号： B64C1/069 , B29C65/56 , B29C66/5229 , B29C66/71 , B29C66/721 , B29C2793/0036 , B29K2023/06 , B29K2067/00 , B29K2105/06 , B29L2031/3082 , B64C2001/0072 , Y02T50/43 , Y10T29/4932 , Y10T29/49622 , Y10T29/49826 , B29K2023/04
摘要： A method for assembling two structural elements, at least one of the two structural elements being tube-shaped and including a skin made of a fiber-reinforced composite material. The ability of the element to adapt to the shape and perimeter of a junction interface is improved by providing longitudinal grooves distributed on the circumference of the junction interface. The grooves are of a sufficient length to provide the junction interface with the flexibility to accommodate, through relative radial movement of each portion located between two grooves, differences in shape and perimeter among the junction interfaces of the two structural elements.
摘要翻译： 一种用于组装两个结构元件的方法，所述两个结构元件中的至少一个是管状的并且包括由纤维增强复合材料制成的表皮。 通过提供分布在接合界面的圆周上的纵向槽来改善元件适应接合界面的形状和周长的能力。 凹槽具有足够的长度以提供具有柔性的接合界面，通过位于两个凹槽之间的每个部分的相对径向移动，以容纳两个结构元件的连接界面之间的形状和周长的差异。
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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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3.发明授权公开(公告)号：US07814729B2
公开(公告)日：2010-10-19
申请号：US11766177
申请日：2007-06-21
IPC分类号： E04C2/38
CPC分类号： B64C1/12 , B29C70/865 , B29C70/887 , B29D99/0014 , B29L2007/002 , B64C3/26 , F16F7/00 , Y02T50/43
摘要： A stiff panel (1) comprises a skin (2) and at least one stiffener (3) of composite material on said skin. Free surface (311) of web (31) of stiffener (3) on the stiff panel according to the invention comprises a deformable core (33) and a covering (34) which covers core (33) and joins said core with structural part (35) of web (31). The width of core (33) is equal to or greater than the width of structural part (35) of web (31) of stiffener (3), depending on the shock energy against which panel (1) must be protected.
摘要翻译： 坚硬的面板（1）包括皮肤（2）和至少一个在所述皮肤上的复合材料的加强件（3）。 根据本发明的刚性面板上的加强筋（3）的腹板（31）的自由表面（311）包括可变形芯（33）和覆盖芯（33）的覆盖物（34），并将所述芯部与结构部分 35）（31）。 根据必须保护面板（1）的冲击能，芯（33）的宽度等于或大于加强件（3）的腹板（31）的结构部件（35）的宽度。
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4.发明申请公开(公告)号：US20100136309A1
公开(公告)日：2010-06-03
申请号：US12595313
申请日：2008-04-09
CPC分类号： B29C70/545 , B29C70/30 , Y10T156/108 , Y10T428/2495
摘要： The disclosed embodiments offer a solution for controlling the thickness of a finished structural composite part when precise tolerances must be complied with for the quality of the assembly and in order to ease the assembly operations of this part. In order to implement the method according to the disclosed embodiments, an additional layer of plies made out of a non-structural composite material, called calibrating plies, is applied onto the structural plies of the structural part, at least in an area where the thickness must be maintained within close tolerances and, after the composite material has been cured, the calibrating plies are machined in order to obtain the thickness required for the finished part. The thickness of the calibrating plies applied is determined according to the possible thicknesses of structural plies, taking into account the manufacturing spreads so that the machining operation for the calibrating plies does not affect the structural plies.
摘要翻译： 所公开的实施例提供了一种用于控制成品结构复合材料部件的厚度的解决方案，因为对于组件的质量必须遵守精确的公差，并且为了简化该部件的组装操作。 为了实现根据所公开的实施例的方法，将由称为校准层的非结构复合材料制成的层的附加层施加到结构部件的结构层上，至少在厚度 必须保持在非常公差范围内，并且在复合材料固化之后，校准层被加工以获得成品部件所需的厚度。 考虑到制造涂层，根据结构层的可能厚度确定校准层的厚度，使得校准层的加工操作不影响结构层。
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5.发明申请公开(公告)号：US20080010942A1
公开(公告)日：2008-01-17
申请号：US11766177
申请日：2007-06-21
IPC分类号： E04C2/38
CPC分类号： B64C1/12 , B29C70/865 , B29C70/887 , B29D99/0014 , B29L2007/002 , B64C3/26 , F16F7/00 , Y02T50/43
摘要： A stiff panel (1) comprises a skin (2) and at least one stiffener (3) of composite material on said skin. Free surface (311) of web (31) of stiffener (3) on the stiff panel according to the invention comprises a deformable core (33) and a covering (34) which covers core (33) and joins said core with structural part (35) of web (31). The width of core (33) is equal to or greater than the width of structural part (35) of web (31) of stiffener (3), depending on the shock energy against which panel (1) must be protected.
摘要翻译： 坚硬的面板（1）包括皮肤（2）和至少一个在所述皮肤上的复合材料的加强件（3）。 根据本发明的刚性面板上的加强筋（3）的腹板（31）的自由表面（311）包括可变形芯（33）和覆盖芯（33）的覆盖物（34），并将所述芯部与结构部分 35）（31）。 根据必须保护面板（1）的冲击能，芯（33）的宽度等于或大于加强件（3）的腹板（31）的结构部件（35）的宽度。
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6.发明申请WINDOW PANEL AND METHOD OF MANUFACTURING SUCH A WINDOW, AIRCRAFT COMPRISING A WINDOW PANEL 有权窗户面板和制造这样一个窗户的方法，包括窗户的飞机公开(公告)号：US20090230246A1
公开(公告)日：2009-09-17
申请号：US12400359
申请日：2009-03-09
申请人： Alain Depeige , Jean-Claude Lacombe
发明人： Alain Depeige , Jean-Claude Lacombe
CPC分类号： B64C1/1492
摘要： This invention relates to the design of aircraft (100) having a fuselage (104, 106, 110) of composite type and more particularly to that of aircraft fuselage panels (110) bearing cabin windows (206, 306).The invention thus concerns a fuselage panel (110) bearing a window (206) comprising a composite structure cast in one piece (200, 212), the said structure comprising a main portion (200) and at least one opening (204) to accommodate a window (206), the said structure having, on a zone (213, 214, 216)) surrounding the said opening (204), a thickness more or less constant and greater than the thickness of the main portion (200) of the said structure.The invention also concerns an aircraft (100) comprising a composite fuselage (104, 106, 110), the latter comprising such a panel or a similar panel made of metal material (110).
摘要翻译： 本发明涉及具有复合类型的机身（104,106,110）的飞机（100）的设计，更具体地涉及承载舱窗（206,306）的飞机机身面板（110）的设计。 因此，本发明涉及一种机身板（110），其具有包括铸造成一体（200,212）的复合结构的窗口（206），所述结构包括主要部分（200）和至少一个开口（204），以容纳 窗口（206），所述结构在围绕所述开口（204）的区域（213,214,216）上具有或多或少恒定并且大于所述主体部分（200）的厚度的厚度 说结构。 本发明还涉及一种包括复合机身（104,106,110）的飞行器（100），后者包括由金属材料（110）制成的面板或类似面板。
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公开(公告)号：US07503524B2
公开(公告)日：2009-03-17
申请号：US10974537
申请日：2004-10-27
IPC分类号： B64C1/14
CPC分类号： B29C73/10 , B64C1/1446 , B64F5/10
摘要： A removable plate and a flange that occupies a hole in a panel. The flange has the particular feature of taking up compressive force to which the panel is subjected in its plane, perpendicularly to the hole. The weight of the device used to equip the hole is reduced, and the mechanical behavior of the panel at the position of the hole is improved.
摘要翻译： 一个可移动板和一个占用面板孔洞的法兰。 该凸缘具有吸收面板垂直于孔的平面所承受的压缩力的特征。 用于装备孔的装置的重量减小，并且在孔的位置处的面板的机械性能得到改善。
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8.发明申请公开(公告)号：US20120056740A1
公开(公告)日：2012-03-08
申请号：US13040928
申请日：2011-03-04
IPC分类号： G08B1/08
CPC分类号： H04B1/0483 , H01P1/26 , H04B1/0466 , H04B7/18515
摘要： A radiofrequency circuit embedded onboard a satellite, data being transmitted on several channels by radiofrequency signals, includes a channel corresponding to a frequency band, and a succession of gains being able to be associated with a channel so as to generate the radiofrequency signal to be transmitted on the latter. The succession includes at least one variable-gain amplifier, the radiofrequency signals thus generated being multiplexed by a multiplexer composed of bandpass filters. The successions of gains comprise a power load arranged so as to dissipate the power of signals which is reflected by the filters of the multiplexer, said load including means for generating an alarm signal representative of the power level of the reflected signals, the alarm signal being used to control the gain of the variable-gain amplifier. The subject of the invention is also a power load.
摘要翻译： 嵌入在卫星上的射频电路，通过射频信号在几个信道上发送的数据包括与频带相对应的信道，以及能够与信道相关联的一系列增益，以便生成要发送的射频信号 后者。 该序列包括至少一个可变增益放大器，由如此产生的射频信号被由带通滤波器组成的多路复用器复用。 增益的连续性包括布置成消散由多路复用器的滤波器反射的信号的功率的功率负载，所述负载包括用于产生表示反射信号的功率电平的报警信号的装置，报警信号为 用于控制可变增益放大器的增益。 本发明的主题也是电力负载。
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公开(公告)号：US5796370A
公开(公告)日：1998-08-18
申请号：US683779
申请日：1996-07-16
申请人： Veronique Courtonne , Dominique Morin , Jean-Claude Lacombe , Jean-Pierre Carbonell , Didier Rene
发明人： Veronique Courtonne , Dominique Morin , Jean-Claude Lacombe , Jean-Pierre Carbonell , Didier Rene
CPC分类号： H01Q3/16 , H01Q19/191 , H01Q19/192
摘要： An antenna is orientable, directional and capable of use as a transmit and/or receive antenna. It includes at least one reflector, at least one source of electromagnetic radiation including means for exciting the source with two orthogonal linear polarizations and a mechanical system for positioning and holding the source and the reflector. The orientation of the antenna is made up of depointing and rotation about a preferred direction of propagation of the radiation and the mechanical system enables such rotation while keeping the source fixed, so conserving the orientation of the orthogonal linear polarization. A preferred embodiment of the antenna includes a parabolic main reflector and a hyperbolic auxiliary reflector in a Cassegrain geometry, and the mechanical system enables rotation of both reflectors about the preferred direction of radiation and holds the source fixed to conserve the orthogonal linear polarization axes of the beam. Applications include radar, direct broadcast satellites and telecommunications employing frequency re-use by polarization diversity, especially advantageous in space and airborne applications.
摘要翻译： 天线是可定向的，定向的并且能够用作发射和/或接收天线。 它包括至少一个反射器，至少一个电磁辐射源，包括用两个正交线性偏振激发光源的装置和用于定位和保持光源和反射器的机械系统。 天线的方向由围绕放射线的优选传播方向的去耦和旋转组成，并且机械系统能够在保持源固定的同时进行这种旋转，从而节省正交线偏振的取向。 天线的优选实施例包括抛物线主反射器和卡塞格林几何中的双曲面辅助反射器，并且机械系统能够绕两个辐射的优选方向旋转两个反射器，并且保持源固定以节省正交线偏振轴 光束。 应用包括雷达，直播广播卫星和通过极化分集频率重用的电信，在空间和机载应用中特别有利。
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公开(公告)号：US09126671B2
公开(公告)日：2015-09-08
申请号：US13557390
申请日：2012-07-25
申请人： Jéôme Dubost , Jean Claude Lacombe
发明人： Jéôme Dubost , Jean Claude Lacombe
CPC分类号： B64C1/12 , B64C1/064 , B64C3/182 , B64C2001/0072 , E04C2/324 , Y02T50/43 , Y10T428/24174 , Y10T428/24182
摘要： A stiffened panel includes a panel at least one of whose surfaces is equipped with stiffeners each of which includes a base that is pressed against the surface of panel, as well as a core that is oriented orthogonally relative to the base and whose first longitudinal edge is integral to the latter. At least one of the stiffeners includes a multitude of notches that cross over a second longitudinal edge of the core opposite the first edge, so that they extend towards the outside of the stiffener.
摘要翻译： 加强板包括面板，其表面中的至少一个配备有加强件，每个加强件包括压靠在面板表面上的基座以及相对于基座正交定向的芯部，并且其第一纵向边缘为 与后者不可分割。 加强件中的至少一个包括跨越与第一边缘相对的芯的第二纵向边缘的多个凹口，使得它们朝向加强件的外部延伸。
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