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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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Patent Agency Ranking
公开(公告)号：US20150197328A1
公开(公告)日：2015-07-16
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: An optimized 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 and at least one hinge fitting, as well as and an actuator fitting joined with the front spar. At least one rib is connected with the actuator fitting and it is arranged so as to define an oblique angle with the front spar. One or more ribs are located in correspondence with the main torsion and bending load paths created in the control surface during flight, landing or takeoff, so the same structural behavior of the control surface is achieved, but, with a reduced number of ribs, so that the weight of the control surface is reduced.
Abstract translation: 用于飞机的控制面的优化结构，例如电梯，方向舵，落地襟翼，副翼和其他类似的提升表面。 控制表面包括前翼梁，后翼梁，多个肋和至少一个铰接配件，以及与前翼梁连接的致动器配件。 至少一个肋与致动器配件连接，并且其布置成与前翼梁形成倾斜的角度。 一个或多个肋对应于在飞行，着陆或起飞期间在控制表面中产生的主扭转和弯曲载荷路径，因此实现了控制表面的相同结构特性，但是随着肋的数量减少， 控制面的重量减小。
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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：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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