公开(公告)号：US20230033330A1

公开(公告)日：2023-02-02

申请号：US17789325

申请日：2020-12-24

Applicant: LEONARDO S.P.A.

Inventor： Paolo Pisani ,  Federico Montagna ,  Roberto Regonini ,  Daniele Podda

IPC: B64C27/14 ,  B64C27/22 ,  B64C27/00

Abstract: An aircraft is described comprising a transmission unit with a first module and a lubrication system; the first module comprises a casing and a movable member; the lubrication system comprises a header, a nozzle fed with the lubricating fluid and designed to feed the lubricating fluid inside the casing of the first module, a collection tank for the lubricating fluid injected by the nozzle, and recirculation means designed to cause the recirculation of the lubricating fluid from the collection tank to the feed header; the first module comprises a valve available in a first configuration, in which it enables the outflow of said lubricating fluid from said module to the recirculation means when the pressure of the lubricating fluid inside the header is greater than a threshold value; and in a second configuration, in which it fluidically isolates the module from the recirculation means when the pressure of the lubricating fluid inside the header is less than the threshold value.

公开(公告)号：US20210229199A1

公开(公告)日：2021-07-29

申请号：US17055030

申请日：2019-10-17

Applicant: LEONARDO S.P.A.

Inventor： Dario Colombo ,  Roberto Regonini ,  Sergio Fiorio

IPC: B23G1/16 ,  B23P6/00 ,  B64F5/40 ,  B23B49/02

Abstract: It is described a method for reconditioning a damaged thread of a transmission of a hover-capable aircraft; the damaged thread being arranged inside a first hole of the transmission; wherein the method includes the following steps: i) centering a tool on the first hole; ii) inserting a first tool inside the tool centred on the first hole and removing the damaged thread through the first tool; iii) inserting a second tool inside the tool and creating a new thread inside the first hole having a diameter larger than the one of the damaged thread; iv) screwing an insert having a thread inside the new thread, so that the insert engages the first hole and defines a reconditioned thread; and v) keeping the transmission mounted on the hover-capable aircraft during steps i), ii), iii), iv).

公开(公告)号：US11891187B2

公开(公告)日：2024-02-06

申请号：US17414499

申请日：2019-11-28

Applicant: LEONARDO S.P.A.

Inventor： Daniele Podda ,  Andrea Gabrielli ,  Roberto Regonini ,  Federico Montagna ,  Stefano Poggi

IPC: B64D35/00 ,  B64C29/00 ,  F16C19/18 ,  F16C19/54 ,  F16C25/08

CPC classification number: B64D35/00 ,  B64C29/0033 ,  F16C19/18 ,  F16C19/543 ,  F16C25/083 ,  F16C2326/43

Abstract: An aircraft is described comprising: a support element; a shaft rotating about an axis; a pair of oblique rolling bearings mounted so as to couple the shaft to the support element rotatingly about the axis; the rolling bearings comprising: respective first races cooperating radially in contact with a first component defined by one from the support element and the shaft; respective second races cooperating radially in contact with a second component defined by the other from the support element and the shaft; and respective pluralities of rolling elements adapted to roll on the first and second races; the aircraft further comprises a pair of preloaded elastic members, which couple the first races to the first component respectively, axially and in an elastically yielding manner.

公开(公告)号：US12134468B2

公开(公告)日：2024-11-05

申请号：US17789325

申请日：2020-12-24

Applicant: LEONARDO S.P.A.

Inventor： Paolo Pisani ,  Federico Montagna ,  Roberto Regonini ,  Daniele Podda

IPC: B64C27/14 ,  B64C27/00 ,  B64C27/12 ,  B64C27/22 ,  F16H57/04 ,  F16K11/07 ,  F16K31/122

Abstract: An aircraft is described comprising a transmission unit with a first module and a lubrication system; the first module comprises a casing and a movable member; the lubrication system comprises a header, a nozzle fed with the lubricating fluid and designed to feed the lubricating fluid inside the casing of the first module, a collection tank for the lubricating fluid injected by the nozzle, and recirculation means designed to cause the recirculation of the lubricating fluid from the collection tank to the feed header; the first module comprises a valve available in a first configuration, in which it enables the outflow of said lubricating fluid from said module to the recirculation means when the pressure of the lubricating fluid inside the header is greater than a threshold value; and in a second configuration, in which it fluidically isolates the module from the recirculation means when the pressure of the lubricating fluid inside the header is less than the threshold value.

公开(公告)号：US20220073201A1

公开(公告)日：2022-03-10

申请号：US17414499

申请日：2019-11-28

Applicant: LEONARDO S.P.A.

Inventor： Daniele Podda ,  Andrea Gabrielli ,  Roberto Regonini ,  Federico Montagna ,  Stefano Poggi

IPC: B64C29/00 ,  F16C25/08 ,  F16C19/18 ,  F16C19/54

Abstract: An aircraft is described comprising: a support element; a shaft rotating about an axis; a pair of oblique rolling bearings mounted so as to couple the shaft to the support element (rotatingly about the axis; the rolling bearings comprising: respective first races cooperating radially in contact with a first component (defined by one from the support element and the shaft; respective second races cooperating radially in contact with a second component (defined by the other from the support element and the shaft; and respective pluralities of rolling elements adapted to roll on the first and second races; the aircraft further comprises a pair of preloaded elastic members, which couple the first races to the first component respectively, axially and in an elastically yielding manner.

公开(公告)号：US11319061B2

公开(公告)日：2022-05-03

申请号：US16621178

申请日：2018-06-28

Applicant: LEONARDO S.P.A.

Inventor： Attilio Colombo ,  Luigi Bottasso ,  Paolo Pisani ,  Andrea Favarotto ,  Dario Colombo ,  Federico Montagna ,  Roberto Regonini ,  Francesco Braghin ,  Simone Cinquemani

IPC: B64C27/04 ,  B64C27/00 ,  B64C27/08 ,  F16H1/06 ,  F16H1/16 ,  F16H1/28

Abstract: A rotor for an aircraft is described that comprises: a hub rotatable about an axis and, in turn, comprising a plurality of blades; a mast connectable to a drive member of the aircraft and connected to the hub to drive the hub in rotation about the axis; and damping means to dampen the transmission of vibrations to the mast in a plane orthogonal to the axis; the damping means comprising at least a first mass and a second mass that can eccentrically rotate about the axis with a first and a second speed of rotation, respectively; the first mass and second mass are operatively connected to the mast to generate, respectively, a first and a second damping force on the mast having a main component in a direction radial to the axis; the rotor comprises a transmission unit, which is interposed between the mast and the first and second masses so as to drive the first and second masses in rotation.