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公开(公告)号：US20180072423A1
公开(公告)日：2018-03-15
申请号：US15704114
申请日：2017-09-14
发明人： Iker VÉLEZ DE MENDIZÁBAL ALONSO , Esteban MARTINO GONZÁLEZ , Carlos GARCÍA NIETO , Edouard MENARD , Enrique GUINALDO FERNÁNDEZ , Soledad CRESPO PEÑA , Jesús Javier VÁZQUEZ CASTRO
CPC分类号： B64D7/00 , B32B5/02 , B32B15/14 , B32B2307/558 , B32B2571/02 , B32B2605/18 , B64C1/062 , B64C1/066 , B64C1/12 , F01D21/045 , F41H5/0457 , F41H5/0471
摘要： A lightweight shield for aircraft protection against threat of high energy impacts, which comprises, a structural layer that has a first side and a second side, the first side being intended for receiving the impact, and a ballistic material layer for absorbing high energy impacts, having a first side and a second side. The first side of the ballistic material layer is faced to the second side of structural layer and joined to the structural layer via a progressively detachable interface and, the second side of the ballistic material layer is a free surface.
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公开(公告)号：US20180362142A1
公开(公告)日：2018-12-20
申请号：US16009344
申请日：2018-06-15
发明人： Jesús Javier VÁZQUEZ CASTRO , Carlos GARCÍA NIETO , Enrique GUINALDO FERNÁNDEZ , José CARRASCO-FERNÁNDEZ , Darío CALVO-SÁNCHEZ , Carlos MARTÍN-CUBILLO
摘要： An inflatable panel comprising two flexible face sheets and a core located between the two flexible face sheets, and lateral joining members configured to be joined to an aircraft structure and coupled to the inflatable panel. The lateral joining members cover at least part of the linear contour of the two flexible face sheets and have a first part covering an edge portion adjacent to the contour of one of the face sheets and a second part covering an edge portion adjacent to the contour of the other face sheet.
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3.发明申请公开(公告)号：US20200010218A1
公开(公告)日：2020-01-09
申请号：US16502436
申请日：2019-07-03
发明人： Francisco Javier HONORATO RUIZ , Jesús Javier VÁZQUEZ CASTRO , Enrique GUINALDO FERNÁNDEZ , Carlos GARCÍA NIETO , Iker VÉLEZ DE MENDIZÁBAL ALONSO
摘要： A method for manufacturing the trailing edge ribs and the bearing ribs of trailing edges of aircraft lifting surfaces, in which the trailing edge ribs and the bearing ribs are made by joining simple C-shaped parts and/or simple L-shaped parts so as to obtain the final trailing edge ribs and bearing ribs. The manufacturing of the simple C-shaped parts uses the same tooling both for the trailing edge ribs and the bearing ribs, and the manufacturing of the simple L-shaped parts uses the same tooling both for the trailing edge ribs and the bearing ribs.
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公开(公告)号：US20180201360A1
公开(公告)日：2018-07-19
申请号：US15872619
申请日：2018-01-16
发明人： Carlos GARCÍA NIETO , Iker VÉLEZ DE MENDIZÁBAL ALONSO , Soledad CRESPO PEÑA , Enrique GUINALDO FERNÁNDEZ , Jesús Javier VÁZQUEZ CASTRO , Álvaro TORRES SALAS
CPC分类号： B64C9/18 , B64C5/02 , B64C5/10 , B64C23/06 , Y02T50/162
摘要： A lifting surface comprising a movable discontinuity located in the surface of the lifting surface. The movable discontinuity is movable between an active position in which the movable discontinuity acts as vortex generator, and a passive position in which the movable discontinuity is integrated into the surface of the lifting surface without acting as vortex generator. The lifting surface may be in an elevator, the elevator being rotatable around a hinge line with respect to the rest of the lifting surface. A bar is rigidly joined to the elevator. The bar, the elevator and the movable discontinuity are configured such that when the elevator rotates with respect to the rest of the lifting surface, the bar moves the movable discontinuity that departs from the surface of the lifting surface, acting as a vortex generator.
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公开(公告)号：US20170158304A1
公开(公告)日：2017-06-08
申请号：US15366126
申请日：2016-12-01
CPC分类号： B64C1/10 , B64C1/34 , B64C2001/0072
摘要： 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：US20180201361A1
公开(公告)日：2018-07-19
申请号：US15872460
申请日：2018-01-16
发明人： Carlos GARCÍA NIETO , Iker VÉLEZ DE MENDIZÁBAL ALONSO , Soledad CRESPO PEÑA , Enrique GUINALDO FERNÁNDEZ , Jesús Javier VÁZQUEZ CASTRO , Álvaro TORRES SALAS
CPC分类号： B64C21/08 , B64C21/10 , B64C23/06 , B64C2230/08 , B64C2230/26 , Y02T50/162
摘要： A lifting device including: a movable discontinuity (1) located in a surface of the lifting device, the movable discontinuity (1) being movable between: an active position in which the movable discontinuity (1) acts as vortex generator, and a passive position in which the movable discontinuity (1) is integrated into the surface of the lifting surface, a conduit (2) located in the spanwise direction of the lifting surface and in communication with the movable discontinuity (1), the lifting surface including openings (3) in its surface spanwise distant from each other in communication with the conduit (2), the movable discontinuity (1) and the conduit (2) being configured such that when an airflow goes through the conduit (2), this airflow activates the movable discontinuity (1) to act as a vortex generator of the lifting surface.
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公开(公告)号：US20180155006A1
公开(公告)日：2018-06-07
申请号：US15801669
申请日：2017-11-02
发明人： Alberto ARANA HIDALGO , Esteban MARTINO GONZÁLEZ , Jesús Javier VÁZQUEZ CASTRO , Pablo CEBOLLA GARROFE
摘要： An aircraft stabilizer (15, 17) with an enlarged area of laminar flow. The lateral skins (45a, 45b; 65a, 65b) of its torsion box (43; 63) include joggled areas (53a, 53b; 73a, 73b) as attachment areas of its leading edge (41; 61) which are arranged in a rearward position with respect to the forward most spar of the stabilizer (15, 17).
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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
CPC分类号： B64C3/30 , B64C3/26 , B64C3/28 , B64C2003/146 , Y02T50/12
摘要： 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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