-
1.发明公开
公开(公告)号：EP4422972A1
公开(公告)日：2024-09-04
申请号：EP22735037.8
申请日：2022-06-23
申请人： Leonardo S.p.a.
发明人： ANTONI, Andrea , VANNI, Roberto
-
公开(公告)号：EP3598263A1
公开(公告)日：2020-01-22
申请号：EP19194312.5
申请日：2017-10-05
申请人： LEONARDO S.p.A.
摘要： A stability and command augmentation system (20) for controlling an aircraft (1), comprising: a first member (19) moveable by a pilot input device (10, 11, 15) to a first position defining a first input (xi); a second member (22) moveable to a second position associated with a second input (xd); and an adder device (21) configured to add the first and second inputs (xi, xd) and supply an output signal (xv) defining a command for an element to be controlled (9, 14) of the aircraft (1); the stability and command augmentation system (20) comprises: a casing (30), a first and a second piston (31, 32) integrally movable with one another inside the casing (30) and operatively connected to the second member (22); and control means (33) configured to exert a first force on the first piston and a second force on the second piston (31, 32); the second force is independent of the first force.
-
3.发明公开
公开(公告)号：EP4173949A1
公开(公告)日：2023-05-03
申请号：EP21205724.4
申请日：2021-10-29
申请人： Leonardo S.p.a.
发明人： ANTONI, Andrea , VANNI, Roberto
摘要： Control device (50) for controlling the variation of the angle of attack of the blades (8) of the anti-torque rotor (4) of an aircraft capable of hovering (1), comprising: - a control element (16) sliding along a first axis (a) with respect to a shaft (6) of the rotor and rotatable integrally therewith; the control element operatively connected to a plurality of blades articulated on the shaft for varying the angle of attack thereof following a translation of the element itself along the axis; - a control rod (10) axially sliding along the axis with respect to the shaft and angularly fixed with respect to the axis; - a rolling bearing (17) interposed between the control rod and the control element, sliding along the axis integrally with the control rod; - a threaded element (51) screwed onto the control rod and cooperating with the rolling bearing to constrain it axially with respect to the control rod; a bushing (52) coupled in an angularly and axially fixed manner to the threaded element, and in an angularly fixed manner to the control rod.
-
公开(公告)号：EP3467608A1
公开(公告)日：2019-04-10
申请号：EP17194901.9
申请日：2017-10-05
申请人： LEONARDO S.p.A.
摘要： A stability and command augmentation system (20) for controlling an aircraft (1), comprising: a first member (19) moveable by a pilot input device (10, 11, 15) to a first position defining a first input (xi); a second member (22) moveable to a second position associated with a second input (xd); and an adder device (21) configured to add the first and second inputs (xi, xd) and supply an output signal (xv) defining a command for an element to be controlled (9, 14) of the aircraft (1); the stability and command augmentation system (20) comprises: a casing (30), a first and a second piston (31, 32) integrally movable with one another inside the casing (30) and operatively connected to the second member (22); and control means (33) configured to exert a first force on the first piston and a second force on the second piston (31, 32); the second force is independent of the first force.
-
公开(公告)号：EP3670338A1
公开(公告)日：2020-06-24
申请号：EP18214922.9
申请日：2018-12-20
申请人： LEONARDO S.p.A.
发明人： VANNI, Roberto , ANTONI, Andrea
摘要： A vertical take-off and/or landing aircraft (1) comprising: a fuselage (2) having a longitudinal axis (d); a pair of semi-wings (3) protruding from the fuselage (2) in a transversal direction with respect to the longitudinal axis (D); a pair of a predetermined breaking areas (11) of the semi-wings (3) defining respective preferred rupture sections (12) at which the respective semi-wings (3) are designed to break, during operation, in a controlled way moving along a preferred collapse trajectory in the event of impact; and at least one fluidic line (13) configured to convey at least one service fluid from and/or towards at least one said semi-wing (3) and crossing at least one of said preferred rupture sections (12); the aircraft (1) comprises a self-sealing coupling (15) movable between a first configuration in which it enables the flow of said service fluid from and/or towards the semi-wing (3), and a second configuration in which it prevents the above-mentioned flow and the spilling of the service fluid from the fluidic line (13); the self-sealing coupling (15) is movable from the first to the second configuration via the movement of the semi-wing (3) along the preferred collapse trajectory.
-
-
-
-
搜索结果
5 条记录 (耗时 0.008 秒)
