公开(公告)号：WO2023073440A1

公开(公告)日：2023-05-04

申请号：PCT/IB2022/055834

申请日：2022-06-23

Applicant: LEONARDO S.P.A

Inventor： ANTONI, Andrea ,  VANNI, Roberto

IPC: B64C27/78 ,  B64C27/82 ,  F16B37/14 ,  F16B39/08

Abstract: A control device (50) for controlling the variation of the angle of attack of the blades (8) of the anti-torque rotor (4) for an aircraft (1) capable of hovering is described, comprising a control element (16) sliding along a first axis (A) with respect to a shaft (6) of the rotor (4) and rotatable integrally therewith; the control element (16) is operatively connected to a plurality of blades (8) articulated on the shaft (6) in order to vary the angle of attack thereof following a translation of the element (16) itself along the axis (A); a control rod (10) axially sliding along the axis (A) with respect to the shaft (6) and angularly fixed with respect to the axis (A); and a rolling bearing (17) interposed between the control rod (10) and the control element (16), sliding along the axis (A) with respect to the shaft (6) and integrally with the control rod (10); the control device (50) comprises a threaded element (51) screwed onto the control rod (10) and cooperating with the bearing (17) to constrain it axially with respect to the control rod (10) and a bushing (52) coupled in an angularly and axially fixed manner to the threaded element (51), and in an angularly fixed manner to the control rod (10).

公开(公告)号：WO2020128661A1

公开(公告)日：2020-06-25

申请号：PCT/IB2019/059359

申请日：2019-10-31

Applicant: LEONARDO S.P.A.

Inventor： VANNI, Roberto ,  ANTONI, Andrea

IPC: B64C27/00 ,  B64C27/26 ,  B64C29/00 ,  B64C13/40 ,  B64C29/02

Abstract: 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.