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：WO2020254894A1

公开(公告)日：2020-12-24

申请号：PCT/IB2020/054977

申请日：2020-05-26

Applicant: LEONARDO S.P.A.

Inventor： DELLI PAOLI, Michele ,  NANNONI, Fabio ,  VANNI, Roberto

IPC: B64C27/82 ,  B64C27/59 ,  B64C27/605 ,  B64C27/78 ,  B64C11/32 ,  F16C39/02 ,  F16C21/00 ,  F16C19/52 ,  B64C27/54

Abstract: An anti-torque rotor (4) is described for a helicopter (1), comprising: a mast (6) rotatable about a first axis (A); a plurality of blades (8) hinged on the mast (6), extending along respective second axes (B) transversal to said first axis (A) and rotatable about respective said second axes (B) to alter the respective angles of attack; a control element (16) sliding and rotating with respect to the mast (6), and operatively connected to said blades (8) to cause the rotation of said blades (8) about respective second axes (B) following a translation of said element (16) along the first axis (A); a control rod (10) sliding axially along first axis (A) with respect to the mast (6) and angularly fixed with respect to the first axis (A); and a connection element (17) interposed between the control rod (10) and the control element (16), sliding along the first axis (A) with respect to the mast (6) and integrally with the control rod (10); the anti-torque rotor (4) further comprises an interface (18, 93) made of an antifriction material interposed between said control rod (10) and said connection element (17).

公开(公告)号：WO2020260979A1

公开(公告)日：2020-12-30

申请号：PCT/IB2020/054976

申请日：2020-05-26

Applicant: LEONARDO S.P.A.

Inventor： DELLI PAOLI, Michele ,  NANNONI, Fabio ,  VANNI, Roberto

IPC: B64C27/82 ,  B64C27/59

Abstract: An anti-torque rotor (4) is described comprising: a mast (6) rotatable about a first axis (A); a plurality of blades (8) hinged on the mast (6) and rotatable about respective second axes (B) to vary the respective angles of attack; a control element (16) sliding along the first axis (A) with respect to the mast (6), rotatable with the mast (6) and connected to the blades (8) to cause the rotation about the second axes (B); a control mechanism (10), axially sliding and angularly fixed with respect to the mast (6); and a connection element (17) interposed between the control mechanism (10) and the control element (16), sliding integrally with the control mechanism (10) along the mast (6); the control mechanism (10) comprises a first and a second rod (60, 61); the rotor (4) comprises a coupling (70), which is configured to enable/prevent rotation of the second rod (61) with respect to the first rod (60) when the torque exerted by the first connection element (17) on the second rod (61) about the first axis (A) is greater/less than a threshold value in the event of failure of the connection element (17).

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.

公开(公告)号：WO2020254895A1

公开(公告)日：2020-12-24

申请号：PCT/IB2020/054979

申请日：2020-05-26

Applicant: LEONARDO S.P.A.

Inventor： DELLI PAOLI, Michele ,  NANNONI, Fabio ,  VANNI, Roberto

IPC: B64C27/78 ,  B64C27/82 ,  B64C27/12

Abstract: An anti-torque rotor (4, 4') is described that comprises: a mast (6) rotatable about a first axis (A); a plurality of blades (8) extending along respective second axes (B); a control element (16) sliding along the first axis (A) with respect to the mast (6), integrally rotatable with said mast (6), and connected to said blades (8); a control rod (10) sliding axially along first axis (A) and angularly fixed with respect to said first axis (A); a connection element (17) interposed between the control rod (10) and the control element (16), sliding along the first axis (A) integrally with the control rod (10), and configured to enable the relative rotation of said control element (16) with respect to the control rod (10) about the first axis (A); and a transmission unit (45) available in an active configuration or an inactive configuration; the transmission unit (45), in turn, comprises: an annular ridge (61) axially and angularly integral with the control rod (10) and radially projecting from the control rod (10); and a seat (64) engaged by the ridge (61) and angularly integral with the control element (16).

公开(公告)号：WO2019069287A1

公开(公告)日：2019-04-11

申请号：PCT/IB2018/057759

申请日：2018-10-05

Applicant: LEONARDO S.P.A.

Inventor： VANNI, Roberto ,  GAGLIOSTRO, Davide ,  CASOLA, Davide

IPC: G05D1/08 ,  B64C13/00 ,  F15B18/00 ,  G05B13/00 ,  G05G11/00

Abstract: 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.