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21. 发明公开

EP4095033A1 STRUCTURAL MODULE FOR FIXED OR ROTARY WING 审中-公开
公开(公告)号：EP4095033A1
公开(公告)日：2022-11-30
申请号：EP21425028.4
申请日：2021-05-28
申请人： C.I.R.A. (Centro Italiano Ricerche Aerospaziali) - S.C.P.A.
发明人： Ameduri, Salvatore , Ciminello, Monica , Concilio, Antonio , Dimino, Ignazio , Galasso, Bernardino , Guida, Mariano
IPC分类号： B64C11/20 , B64C3/52 , B64C27/473 , B64C3/18
摘要： A fixed or rotary wing structural module (1) comprises a leading edge structure (2), a torsional actuator (23) mounted on the leading edge structure (2) and comprising a torsion bar (24) and actuating devices (25) operatively coupled to the torsion bar (24). The torsion bar (24) is mounted or mountable on the leading edge structure (2) with a preload torsion, so as to give the structural module (1) a respective predefined twist. The actuation devices (25) are configured to vary a torsional stiffness and/or an angular geometry of the torsion bar (24) so as to vary the twist of the structural module (1) with respect to the predefined twist.

22. 发明授权

EP2727825B1 Device for modifying the airfoil geometry 有权
标题翻译：用于修改所述几何水翼
公开(公告)号：EP2727825B1
公开(公告)日：2014-12-17
申请号：EP12425175.2
申请日：2012-10-30
申请人： C.I.R.A. (Centro Italiano Ricerche Aerospaziali) - S.C.P.A.
发明人： Ameduri, Salvatore
IPC分类号： B64C3/50 , B64C3/48
CPC分类号： B64C3/48 , B64C3/50 , Y02T50/14
摘要： A device (1) for varying a geometry of a wing profile for leading edges of wings (2) of aircraft (100) comprising an exposed surface (8) extending parallel to the longitudinal development direction of the wing (2); the exposed surface (8) defines a front portion of the wing profile (9) of the wing (2), exhibits a first and a second engaging portion (6, 7) constrained stably to the wing (2) and a deformable portion (5) interposed between the first and the second engaging portions (6, 7) and mobile in relation to the wing (2) such as to enable variations in shape of the portion of wing profile (9) of the wing (2), The device (1) comprises a mechanism (10), arranged internally of a housing compartment (9a) of the wing profile, configured such as to move relatively to the wing along at least a plane that is transversal to the main development direction thereof and such as to generate a deformation of the deformable portion (5). The device (1) comprises an activating element (13) configured such as to move the mechanism (10) and provided with an actuator (14) configured such as to generate a push (S) and a kinematic mechanism (28) receiving the push (S) generated by the actuator (14) and configured such as to move the mechanism (10). The actuator (14) is positioned and configured such as to generate a push (S) in a transversal direction to the movement plane of the mechanism (10) and the kinematic mechanism (28) generates a corresponding action on the mechanism (10) such as to move the mechanism (10) in the movement plane thereof transversal to the main development direction (A).

23. 发明公开

EP4175880A1 TACTICAL HYBRID STRATOSPHERIC AIRSHIP 审中-公开
公开(公告)号：EP4175880A1
公开(公告)日：2023-05-10
申请号：EP21740198.3
申请日：2021-06-16
申请人： C.I.R.A. (Centro Italiano Ricerche Aerospaziali) - S.C.P.A.
发明人： PERSECHINO, Giuseppe , BARANIELLO, Vincenzo Rosario , BORSA, Roberto
IPC分类号： B64B1/08 , B64B1/20

25. 发明公开

EP3766691A1 A METHOD FOR MAKING A PREFORM OF FIBER-REINFORCED COMPOSITE MATERIAL 审中-公开
公开(公告)号：EP3766691A1
公开(公告)日：2021-01-20
申请号：EP20185078.1
申请日：2020-07-09
申请人： Petroceramics S.p.A. , C.I.R.A. (Centro Italiano Ricerche Aerospaziali) - S.C.P.A.
发明人： CAVALLI, Lorenzo , VALLE, Massimiliano , DE STEFANO FUMO, Mario , RUFOLO, Giuseppe Carmine , GARDI, Roberto , CANTONI, Stefania
IPC分类号： B32B18/00 , C04B35/528 , C04B35/573 , C04B35/80 , C04B35/83 , C04B37/00 , B29C65/00 , B29C70/06
摘要： The invention relates to a method for making a preform in a fiber-reinforced composite material with continuous fibers, said preform having a predefined complex geometry. The method comprises the following steps: a) forming by compression molding technique one or more sheets in reinforced-fiber composite material; b) shaping from said one or more sheets in a fiber-reinforced composite material a plurality of pieces, the specific shape and size of each of said piece being chosen so that together such plurality of pieces can define, at least partially, the predefined complex geometry of said preform; c) assembling said pieces together to form a structure having a geometry corresponding, at least in part, to the predefined complex geometry of the preform to be made; d) consolidating said structure by means of vacuum bagging, vacuum infusion or resin transfer molding technique by applying fibrous substrates, in laminar form, to said structure at least in predefined portions thereof, to complete the geometry thereof, according to said predefined complex geometry and/or to reinforce said structure, thus obtaining a consolidated structure, which constitutes said preform with said predefined complex geometry.

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