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公开(公告)号：US10196124B2
公开(公告)日：2019-02-05
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 Muñoz
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.
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公开(公告)号：US20170106969A1
公开(公告)日：2017-04-20
申请号：US15295099
申请日：2016-10-17
Applicant: Airbus Operations S.L.
CPC classification number: B64C3/30 , B64C3/26 , B64C3/28 , B64C2003/146 , Y02T50/12
Abstract: A leading edge for an airfoil comprising a torsion box, the leading edge comprising a leading plate and a first inflatable element suitable for being filled with air. The leading plate comprises a convex side and a concave side. The first inflatable element is in contact with at least part of the concave side, thus reinforcing the leading plate. An airfoil comprising such a leading edge is also provided.
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公开(公告)号：US10322793B2
公开(公告)日：2019-06-18
申请号：US15295099
申请日：2016-10-17
Applicant: Airbus Operations S.L.
Abstract: A leading edge for an airfoil comprising a torsion box, the leading edge comprising a leading plate and a first inflatable element suitable for being filled with air. The leading plate comprises a convex side and a concave side. The first inflatable element is in contact with at least part of the concave side, thus reinforcing the leading plate. An airfoil comprising such a leading edge is also provided.
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公开(公告)号：US09381992B2
公开(公告)日：2016-07-05
申请号：US14579717
申请日：2014-12-22
Applicant: Airbus Operations S.L.
Inventor： Fernando Pereira Mosqueira , Enrique Guinaldo Fernandez , Carlos Garcia Nieto , Francisco Javier Honorato Ruiz , Andrea Ivan Marasco
Abstract: An optimized leading edge for an aircraft lifting or supporting surfaces, such as wings and stabilizers, wherein the leading edge includes inboard and outboard leading edge sections that are span-wise arranged so as to form together an aerodynamic surface of the leading edge. Each of the leading edge sections includes a skin panel and a support structure formed by spars that are internally arranged in the skin panel. These two support structures are designed taking into account the different load requirements of those two different sections, so that the number of spars in each leading edge section is progressively reduced from root to tip of the leading edge, in such a way that the support structure of the outboard leading edge section, has less spars than the inboard leading edge section. Hence the weight of the leading edge is reduced while still maintaining the required structural behavior.
Abstract translation: 用于飞行器提升或支撑表面（例如翼和稳定器）的优化前缘，其中前缘包括横跨方向布置以一起形成前缘的空气动力学表面的内侧和外侧前缘部分。 每个前缘部分包括皮肤面板和由内部布置在皮肤面板中的翼梁形成的支撑结构。 这两个支撑结构被设计成考虑到这两个不同部分的不同负载要求，使得每个前缘部分中的翼梁的数量从前端的根部到尖端逐渐减小，使得支撑结构 的外侧前缘部分，具有比内侧前缘部分更少的翼梁。 因此，前沿的重量减小，同时仍然保持所需的结构行为。
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公开(公告)号：US20150175253A1
公开(公告)日：2015-06-25
申请号：US14579717
申请日：2014-12-22
Applicant: Airbus Operations S.L.
Inventor： Fernando Pereira Mosqueira , Enrique Guinaldo Fernandez , Carlos Garcia Nieto , Francisco Javier Honorato Ruiz , Andrea Ivan Marasco
Abstract: An optimized leading edge for an aircraft lifting or supporting surfaces, such as wings and stabilizers, wherein the leading edge includes inboard and outboard leading edge sections that are span-wise arranged so as to form together an aerodynamic surface of the leading edge. Each of the leading edge sections includes a skin panel and a support structure formed by spars that are internally arranged in the skin panel. These two support structures are designed taking into account the different load requirements of those two different sections, so that the number of spars in each leading edge section is progressively reduced from root to tip of the leading edge, in such a way that the support structure of the outboard leading edge section, has less spars than the inboard leading edge section. Hence the weight of the leading edge is reduced while still maintaining the required structural behavior.
Abstract translation: 用于飞行器提升或支撑表面（例如翼和稳定器）的优化前缘，其中前缘包括横跨方向布置以一起形成前缘的空气动力学表面的内侧和外侧前缘部分。 每个前缘部分包括皮肤面板和由内部布置在皮肤面板中的翼梁形成的支撑结构。 这两个支撑结构被设计成考虑到这两个不同部分的不同负载要求，使得每个前缘部分中的翼梁的数量从前端的根部到尖端逐渐减小，使得支撑结构 的外侧前缘部分，具有比内侧前缘部分更少的翼梁。 因此，前沿的重量减小，同时仍然保持所需的结构行为。
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Patent Agency Ranking
公开(公告)号：US09868510B2
公开(公告)日：2018-01-16
申请号：US14580456
申请日：2014-12-23
Applicant: Airbus Operations S.L.
Inventor： Fernando Pereira Mosqueira , Enrique Guinaldo Fernandez , Carlos Garcia Nieto , Francisco Javier Honorato Ruiz , Andrea Ivan Marasco , Francisco José Cruz Dominguez
CPC classification number: B64C9/02 , B64C3/185 , B64C3/187 , B64C5/02 , B64C9/00 , B64C2009/005 , Y02T50/44
Abstract: A structure of a control surface for aircrafts, such as elevators, rudders, landing flaps, ailerons, and other similar lifting surfaces. The control surface includes a front spar, a rear spar, a plurality of ribs, at least one hinge fitting, and at least one actuator fitting, the hinge and actuator fittings joined with the front spar. A first rib is joined with a hinge fitting to form a first oblique angle with the front spar; a second rib is joined with an actuator fitting to form a second oblique angle with the front spar. The rear spar, located between the front spar and trailing edge of the control surface, extends only between the second rib and an outboard end of the control surface. The ribs are located in correspondence with the main torsion and bending load paths created in the control surface during flight, landing or takeoff.
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公开(公告)号：US20170253004A1
公开(公告)日：2017-09-07
申请号：US15448800
申请日：2017-03-03
Applicant: Airbus Operations, S.L.
CPC classification number: B32B3/12 , B29D99/0089 , B32B3/02 , B32B5/26 , B32B5/28 , B32B7/02 , B32B15/01 , B32B15/016 , B32B15/20 , B32B27/20 , B32B2250/03 , B32B2250/05 , B32B2250/40 , B32B2307/50 , B32B2307/558 , B32B2571/00 , B32B2605/18 , B33Y80/00 , B64C1/062 , B64C1/12 , B64C7/00 , B64D45/00 , B64D2045/0095
Abstract: A sandwich structure architecture for high speed impact resistant structure includes sandwich skins which enclose a sandwich core formed by a plurality of spacing layers and a plurality of trigger layers, wherein these layers are stacked alternatively in the core. The walls of the trigger layers are thicker than the walls of the spacing layers and/or the walls of the trigger layers include at least one part inclined with respect to the walls of the spacing layers. The spacing and the trigger layers are made of the same type of material, preferably composite materials or metallic materials. The structure is capable of absorbing high-speed impacts, and at the same time can be used as load carrying structure in aircraft fuselages, wings, vertical or horizontal stabilizers.
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公开(公告)号：US10369762B2
公开(公告)日：2019-08-06
申请号：US15448800
申请日：2017-03-03
Applicant: Airbus Operations, S.L.
IPC: B32B5/18 , B32B3/12 , B32B15/01 , B32B27/20 , B32B5/26 , B32B5/28 , B32B7/02 , B32B15/20 , B29D99/00 , B32B3/02 , B64C1/06 , B33Y80/00
Abstract: A sandwich structure architecture for high speed impact resistant structure includes sandwich skins which enclose a sandwich core formed by a plurality of spacing layers and a plurality of trigger layers, wherein these layers are stacked alternatively in the core. The walls of the trigger layers are thicker than the walls of the spacing layers and/or the walls of the trigger layers include at least one part inclined with respect to the walls of the spacing layers. The spacing and the trigger layers are made of the same type of material, preferably composite materials or metallic materials. The structure is capable of absorbing high-speed impacts, and at the same time can be used as load carrying structure in aircraft fuselages, wings, vertical or horizontal stabilizers.
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公开(公告)号：US10286993B2
公开(公告)日：2019-05-14
申请号：US15366126
申请日：2016-12-01
Applicant: AIRBUS OPERATIONS S.L.
Abstract: A pressure bulkhead for an aircraft comprising a fuselage. The pressure bulkhead comprises an inflatable element, suitable for being filled with air, which in turn comprises a cover which delimits an inner zone. The pressure bulkhead further comprises a seal suitable for providing an airtight seal between the cover and the fuselage of the aircraft.
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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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