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公开(公告)号：US20170088249A1
公开(公告)日：2017-03-30
申请号：US15279586
申请日：2016-09-29
Applicant: AIRBUS OPERATIONS, S.L.
Inventor： Carlos GARCÍA NIETO , Iker VELEZ DE MENDIZABAL ALONSO , Enrique GUINALDO FERNANDEZ , Soledad CRESPO PEÑA
CPC classification number: B64C3/187 , B29C70/48 , B29K2105/0872 , B29L2031/3085 , B64C3/20 , B64F5/45 , Y02T50/43
Abstract: The present disclosure refers to the configuration and manufacturing process of a rib for the construction of an aircraft torsion box. In the method, a flat stack of plies of composite material is layered up, which is then cut to form a flat pre-form having an outer contour having flanges, and an internal contour having two or more diagonal trusses with flanges at opposite sides. The flat pre-form is press-formed to fold the flanges of the outer and internal contour to form a rib pre-form, which is finally cured. The present disclosure also refers to a composite rib having a unitary body by forming a single pre-form of stacked plies. The present disclosure allows the manufacture of the rib in one-shot process, integrating all the ribs components such that the assembly time and cost of the rib are minimized.
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公开(公告)号：US20170001703A1
公开(公告)日：2017-01-05
申请号：US15201762
申请日：2016-07-05
Applicant: Airbus Operations S.L. , Airbus Operations Ltd.
Inventor： Jesús Javier VAZQUEZ CASTRO , Fernando PEREIRA MOSQUEIRA , Juan José GUTIERREZ SANTIAGO , Anthony LANGLEY , Guy TOTHILL , Davood SARCHAMY , Miguel MARÍN MUÑOS
CPC classification number: B64C1/12 , B64C1/061 , B64C1/064 , B64C1/34 , B64C3/26 , B64C7/00 , B64C7/02
Abstract: An external part of an aircraft (such as a fairing) comprising a skin made with flexible materials attached to rigid supporting elements (such as longerons and frames) arranged in, at least, two directions. The skin comprises inner inflatable panels in all bays delimited by the rigid supporting elements and/or an external inflatable panel. The skin is joined to the supporting elements so that its external surface complies with aerodynamic requirements.
Abstract translation: 飞机（例如整流罩）的外部部件包括以柔性材料制成的皮肤，所述柔性材料连接到至少两个方向上布置的刚性支撑元件（例如龙骨和框架）。 皮肤包括由刚性支撑元件和/或外部可充气面板界定的所有托架中的内部充气面板。 皮肤被接合到支撑元件，使得其外表面符合空气动力学要求。
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公开(公告)号：US20160341128A1
公开(公告)日：2016-11-24
申请号：US15156619
申请日：2016-05-17
Applicant: AIRBUS OPERATIONS, S.L.
Inventor： Alberto Juarez Becerril , Mario Marcos Garcia
CPC classification number: F02C7/26 , B64D41/00 , F01D19/00 , F02C7/268 , F02N11/0803 , F02N11/087 , F02N2011/0874 , F05D2220/50 , F05D2220/76 , Y02T50/671
Abstract: An auxiliary power unit (APU) starting system for an aircraft comprises an APU comprising a starter motor and a generator, a DC power network, an AC power network, an electric connection line, and a control unit for controlling the APU starting and generating phase. The APU starting system additionally comprises switches for alternatively connecting through the electric connection line the DC power network with the APU starter motor, and the AC power network with the APU generator, wherein the control unit is further configured to operate the switches to connect the DC power network with the APU starter motor during the APU starting phase, and the AC power network with the APU generator during the APU starting phase.
Abstract translation: 用于飞行器的辅助动力单元（APU）起动系统包括一个包括起动马达和发电机的APU，直流电力网络，交流电力网络，电连接线路和用于控制APU启动和生成阶段的控制单元 。 APU启动系统还包括用于通过电连接线与APU启动电动机的直流电网以及与APU发电机的交流电网交替连接的开关，其中控制单元还被配置为操作开关以连接DC 在APU启动阶段使用APU起动电机的电力网络，以及在APU启动阶段与APU发电机的交流电网。
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公开(公告)号：US20160325822A1
公开(公告)日：2016-11-10
申请号：US15147202
申请日：2016-05-05
Applicant: AIRBUS OPERATIONS, S.L.
Inventor： Fernando Pereira Mosqueira , Andrea-Ivan Marasco
Abstract: The present disclosure generally refers to an aircraft horizontal tail plane (HTP) having a multi-rib torsion box formed by first and second lateral torsion boxes symmetrically arranged with respect to a plane of symmetry of the horizontal tail plane. A group of ribs are substantially parallel to the plane of symmetry of the horizontal tail plane, and the stringers are arranged as to define an angle within the range 80°-100° with respect to the plane of symmetry of the horizontal tail plane. Due to this relative arrangement of the ribs and stringers, the stringers are not continuous through ribs, thus the ribs can be manufactured without mouse holes. The HTP of the invention can be manufactured easier and faster than traditional HTP designs.
Abstract translation: 本发明总体上涉及一种具有由相对于水平尾翼平面的对称平面对称布置的第一和第二横向扭转箱形成的多肋扭转箱的飞机水平尾翼平面（HTP）。 一组肋基本上平行于水平尾翼平面的对称平面，并且桁条被布置成相对于水平尾翼平面的对称平面限定在80°-100°的范围内的角度。 由于肋和桁条的这种相对布置，桁条不通过肋连续，因此肋可以被制造成没有鼠标孔。 本发明的HTP可以比传统的HTP设计更容易和更快地制造。
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公开(公告)号：US20160318214A1
公开(公告)日：2016-11-03
申请号：US15130284
申请日：2016-04-15
Applicant: Airbus Operations S.L.
Inventor： Ricardo PINILLOS MARTÍNEZ , Victor GARCÍA SOLARES , Pilar MUÑOZ LÓPEZ , Melania PÉREZ SÁNCHEZ
CPC classification number: B29C35/02 , B29B11/00 , B29C33/04 , B29C33/08 , B29C35/16 , B29C65/02 , B29C65/48 , B29C66/112 , B29C66/1122 , B29C66/131 , B29C66/301 , B29C66/524 , B29C66/532 , B29C66/71 , B29C66/721 , B29C66/7212 , B29C66/72141 , B29C66/73117 , B29C66/73753 , B29C66/73755 , B29C66/73941 , B29C70/48 , B29C2035/0211 , B29C2035/1616 , B29K2063/00 , B29K2105/089 , B29K2707/04 , B29L2009/00 , B29L2031/3076 , B29L2031/3082 , B29L2031/3085 , B29K2307/04
Abstract: Method for manufacturing composite parts, wherein at least a first composite part is joined to a second composite part, including providing the first composite part preform into a resin transfer mold, heating the first part into the resing transfer mold for performing a curing cycle of the first part, cooling the first part before the curing cycle is completed so that a semi-cured first part is obtained, and joining the semi-cured first part to a cured prepreg second part for obtaining the final composite part.
Abstract translation: 制造复合部件的方法，其中至少第一复合部件连接到第二复合部件，包括将第一复合部件预成型件提供到树脂转移模具中，将第一部件加热到转印模具中以进行固化循环 第一部分，在固化循环完成之前冷却第一部分，从而获得半固化的第一部分，并将半固化的第一部分接合到固化的预浸料坯第二部分以获得最终的复合部件。
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Patent Agency Ranking
公开(公告)号：US09387922B2
公开(公告)日：2016-07-12
申请号：US14083531
申请日：2013-11-19
Applicant: Airbus Operations S.L.
Inventor： Enrique Guinaldo Fernandez , Francisco Cruz Dominguez , Francisco Javier Honorato Ruiz , Paula Mas Mas , Iker Velez de Mendizabal Alonso , Carlos Garcia Nieto
CPC classification number: B64C3/187 , B64C3/185 , B64C5/02 , Y10T29/49622
Abstract: An aircraft lifting surface with a main supporting structure comprising upper and lower faces defining its aerodynamic profile, front and rear faces oriented towards, respectively, the leading and trailing edges, a first set of transverse ribs extended from the front face to the rear face and a second set of transverse ribs crossing the front face and/or the rear face. The integration of leading and trailing edge ribs in the main supporting structure allows a weight and cost reduction of aircraft lifting surfaces. A manufacturing method of said main supporting structure is also disclosed.
Abstract translation: 具有主支撑结构的飞行器提升表面包括限定其空气动力学轮廓的上表面和下表面，前表面和后表面分别面向前缘和后缘，第一组横向肋从前表面延伸到后表面，并且 横过前表面和/或后表面的第二组横向肋。 主支撑结构中的前缘和后缘肋骨的集成允许飞机提升表面的重量和成本降低。 还公开了所述主支撑结构的制造方法。
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147.发明授权Highly integrated structure including leading and trailing edge ribs for an aircraft lifting surface 有权高度一体化的结构，包括用于飞机提升表面的前缘和后缘肋骨公开(公告)号：US09381991B2
公开(公告)日：2016-07-05
申请号：US14086424
申请日：2013-11-21
Applicant: AIRBUS OPERATIONS S.L.
Inventor： Enrique Guinaldo Fernandez , Francisco Cruz Dominguez , Francisco Javier Honorato Ruiz , Paula Más Más , Iker Vélez De Mendizábal Alonso , Carlos Garcia Nieto
IPC: B64C1/00 , B64C3/00 , B64C5/00 , B64C3/18 , B29C70/30 , B64C3/20 , B64C5/02 , B29C35/02 , B29D99/00 , B29L31/30
CPC classification number: B64C3/182 , B29C35/0238 , B29C70/30 , B29D99/0014 , B29L2031/3085 , B64C3/185 , B64C3/187 , B64C3/20 , B64C5/02 , Y02T50/43
Abstract: An aircraft lifting surface with a monolithic main supporting structure of a composite material including an upper skin having at least a part of the upper aerodynamic profile of the leading edge and/or of the trailing edge, a lower skin, a front spar, a rear spar, and leading edge ribs and/or a trailing edge ribs. The main supporting structure allows a weight and cost reduction of aircraft lifting surfaces.
Abstract translation: 一种具有复合材料的整体主支撑结构的飞行器提升表面，其包括具有前缘和/或后缘的上空气动力学轮廓的至少一部分的上皮，下皮，前翼梁，后 翼梁和前缘肋骨和/或后缘肋骨。 主要的支撑结构允许飞机提升表面的重量和成本降低。
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公开(公告)号：US20160167318A1
公开(公告)日：2016-06-16
申请号：US14970130
申请日：2015-12-15
Applicant: AIRBUS OPERATIONS S.L.
Inventor： Pablo CEBOLLA GARROFE
CPC classification number: B29C70/545 , B25J11/006 , B29C37/02 , B29C70/06 , B29C70/30 , B29C2793/009 , B29K2307/04 , B29L2031/3076
Abstract: A Method for manufacturing of a CFRP part includes laying out one or more pre-preg or composite plies, on a mould comprising a marking tool, forming an uncured laminate with a guiding mark on the uncured laminate using curing the laminate giving the part the final shape with the guiding mark and trimming and/or drilling the CFRP part taking as reference the guiding mark. There are also provided a mould for moulding and curing a CFRP part comprising a marking tool adapted to perform a guiding mark on a fresh CFRP part, and a system for manufacturing of a moulded CFRP part.
Abstract translation: 一种用于制造CFRP部件的方法包括在包括标记工具的模具上布置一个或多个预浸料或复合层，在未固化的层压板上形成具有引导标记的未固化层压板，其中使用该层压板，使部件成为最终 形状具有引导标记，并修剪和/或钻孔CFRP部件作为参考标记。 还提供了一种用于模制和固化CFRP部件的模具，其包括适于在新鲜CFRP部件上执行引导标记的标记工具，以及用于制造模制CFRP部件的系统。
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公开(公告)号：US09359085B2
公开(公告)日：2016-06-07
申请号：US13724360
申请日：2012-12-21
Applicant: AIRBUS OPERATIONS S.L.
Inventor： Diego Folch Cortés , Eduardo Vinué Santolalla , Esteban Martino González , Julien Guillemaut , Pablo Goya Abaurrea
CPC classification number: B64D45/00 , B64C1/06 , B64C1/10 , B64D27/02 , B64D27/14 , B64D27/20 , B64D2027/005 , Y02T50/66
Abstract: Internal shield in the rear fuselage of an aircraft having a propulsion system formed by two engines mounted on each side of it; the rear fuselage having at least a vertical symmetry plane; the rear fuselage being made of a composite material; the internal shield being located in said vertical symmetry plane and extended in an area that covers the possible trajectories of a set of pre-defined fragments detached from one of said engines in a failure event that would impact on critical elements of the opposite engine; the internal shield having a flat shape and an energy absorption capability that allows stopping said fragments. The invention also refers to a method for determining the area of an internal shield and to an aircraft having said internal shield.
Abstract translation: 具有由安装在其每侧的两个发动机形成的推进系统的飞行器的后机身中的内部盾构; 后机身至少具有垂直对称平面; 后机身由复合材料制成; 所述内部屏蔽件位于所述垂直对称平面中，并且延伸在覆盖一组预定义片段的可能轨迹的区域中，所述一组预先定义的片段在将影响相对发动机的关键元件的故障事件中与所述发动机中的一个分离; 内部屏蔽具有平坦的形状和能量吸收能力，其允许停止所述碎片。 本发明还涉及一种用于确定内部屏蔽件和具有所述内部屏蔽件的飞行器的面积的方法。
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公开(公告)号：US20160076444A1
公开(公告)日：2016-03-17
申请号：US14857103
申请日：2015-09-17
Applicant: Airbus Operations S.L.
Inventor： Nicolas BAILEY NOVAL , Raul LLAMAS SANDIN
CPC classification number: F02C3/107 , F02C7/36 , F02K3/06 , F02K3/077 , F05D2220/32 , F05D2260/4031 , F16H1/20
Abstract: A multi-fan engine including a gas turbine engine, a casing and fans encased by geared rings, which connect with the geared rings of an adjacent fan(s) such that the rotation of one fan rotates the other fans. Intermediate gears may prove the connection between adjacent geared rings, wherein the intermediate gears are retracted by linear actuators to disengage the intermediate gears from the geared rings and thereby disengage the fans from each other. The multi-fan engine may be mounted flush to the fuselage of an aircraft invention to capture into the fans boundary layer airflow moving over the skin of the fuselage.
Abstract translation: 一种多风扇发动机，其包括燃气涡轮发动机，壳体和由齿轮环包围的风扇，其与相邻风扇的齿轮环连接，使得一个风扇的旋转使另一个风扇旋转。 中间齿轮可以证明相邻的齿轮环之间的连接，其中中间齿轮通过线性致动器缩回以使中间齿轮与齿轮传动环分离，从而使风扇彼此脱离。 多风扇发动机可以平行地安装在飞机发明的机身上，以捕获到风扇边界层气流在机身的皮肤上移动。
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