公开(公告)号：WO2020079645A1

公开(公告)日：2020-04-23

申请号：PCT/IB2019/058874

申请日：2019-10-17

Applicant: LEONARDO S.P.A.

Inventor： COLOMBO, Dario ,  REGONINI, Roberto ,  FIORIO, Sergio

IPC: B23P6/00 ,  B64C27/12 ,  B64F5/40 ,  F16H57/00 ,  F16H57/02 ,  B64C39/02 ,  B23B47/28 ,  B23B49/02 ,  B25B27/18 ,  B23G1/16

Abstract: It is described a method for reconditioning a damaged thread (8) of a transmission (1) of a hover-capable aircraft; the damaged thread (8) being arranged inside a first hole (23a) of the transmission (1); wherein the method includes the following steps: i) centering a tool (20) on the first hole (23a); ii) inserting a first tool (25) inside the tool (20) centred on the first hole (23a) and removing the damaged thread (8) through the first tool (25); iii) inserting a second tool (26) inside the tool (20) and creating a new thread (16) inside the first hole (23a) having a diameter larger than the one of the damaged thread (8); iv) screwing an insert (61) having a thread inside the new thread (16), so that the insert (61) engages the first hole (23a) and defines a reconditioned thread (8'); and v) keeping the transmission (1) mounted on the hover-capable aircraft during steps i), ii), iii), iv).

公开(公告)号：WO2019002513A1

公开(公告)日：2019-01-03

申请号：PCT/EP2018/067495

申请日：2018-06-28

Applicant: LEONARDO S.P.A.

Inventor： COLOMBO, Attilio ,  BOTTASSO, Luigi ,  PISANI, Paolo ,  FAVAROTTO, Andrea ,  COLOMBO, Dario ,  MONTAGNA, Federico ,  REGONINI, Roberto ,  BRAGHIN, Francesco ,  CINQUEMANI, Simone

IPC: B64C27/00

Abstract: A rotor (3, 3', 3'', 3''') for an aircraft (1) is described that comprises: a hub (5) rotatable about an axis (A) and, in turn, comprising a plurality of blades (9); a mast (6) connectable to a drive member of the aircraft (1) and connected to the hub (5) to drive the hub (5) in rotation about the axis (A); and damping means (15; 20a, 20b; 21a, 21b) to dampen the transmission of vibrations to the mast (6) in a plane orthogonal to the axis (A); the damping means (15; 20a, 20b; 21a, 21b) comprising at least a first mass (20a, 20b) and a second mass (21a, 21b) that can eccentrically rotate about the axis (A) with a first and a second speed of rotation ((N- 1)*Ω; -(N+1)*Ω), respectively; the first mass (20a, 20b) and second mass (21a, 21b) are operatively connected to the mast (6) to generate, respectively, a first and a second damping force on the mast (6) having a main component in a direction radial to the axis (A); the rotor (3, 3', 3'', 3''') comprises a transmission unit (19, 19', 19'', 19'''), which is interposed between the mast (6) and the first and second masses (20a, 20b; 21a, 21b) so as to drive the first and second masses in rotation (20a, 20b; 21a, 21b).

公开(公告)号：WO2021130719A1

公开(公告)日：2021-07-01

申请号：PCT/IB2020/062437

申请日：2020-12-24

Applicant: LEONARDO S.P.A.

Inventor： PISANI, Paolo ,  MONTAGNA, Federico ,  REGONINI, Roberto ,  PODDA, Daniele

IPC: B64C27/14 ,  B64C27/00 ,  B64D35/00 ,  B64D35/04 ,  B64D35/08 ,  B64C27/22 ,  B64C27/006

Abstract: An aircraft (1) is described comprising a transmission unit (9) with a first module (11, 13, 15) and a lubrication system (25, 25'); the first module (11, 13, 15) comprises a casing (20) and a movable member (17, 18, 19); the lubrication system (25, 25') comprises a header (26), a nozzle (27, 28) fed with the lubricating fluid and designed to feed the lubricating fluid inside the casing (20) of the first module (11, 13, 15), a collection tank (30, 100') for the lubricating fluid injected by the nozzle (27, 28), and recirculation means (35) designed to cause the recirculation of the lubricating fluid from the collection tank (30, 100') to the feed header (26); the first module (11, 13, 15) comprises a valve (60, 60') available in a first configuration, in which it enables the outflow of said lubricating fluid from said module (11) to the recirculation means (35) when the pressure of the lubricating fluid inside the header (26) is greater than a threshold value; and in a second configuration, in which it fluidically isolates the module (11) from the recirculation means (35) when the pressure of the lubricating fluid inside the header (26) is less than the threshold value.

公开(公告)号：WO2020128691A1

公开(公告)日：2020-06-25

申请号：PCT/IB2019/060299

申请日：2019-11-28

Applicant: LEONARDO S.P.A.

Inventor： PODDA, Daniele ,  GABRIELLI, Andrea ,  REGONINI, Roberto ,  MONTAGNA, Federico ,  POGGI, Stefano

IPC: B64C27/28 ,  F16C19/54 ,  F16C25/08

Abstract: An aircraft (1) is described comprising: a support element (16; 16'); a shaft (12; 12') rotating about an axis (E, E'); a pair of oblique rolling bearings(17; 17') mounted so as to couple the shaft (12; 12') to the support element (16; 16') rotatingly about the axis (E, E'); the rolling bearings (17; 17') comprising: respective first races (18, 19; 18', 19') cooperating radially in contact with a first component (16, 12; 16', 12') defined by one from the support element (16; 16') and the shaft (12; 12'); respective second races (19, 18; 19', 18') cooperating radially in contact with a second component (12, 16; 12', 16') defined by the other from the support element (16; 16') and the shaft (12; 12'); and respective pluralities of rolling elements (20; 20') adapted to roll on the first and second races (18, 19; 18' 19'; 19, 18; 19', 18'); the aircraft (1) further comprises a pair of preloaded elastic members (21; 21'), which couple the first races 18, 19; 18', 19') to the first component (16, 12; 16', 12') respectively, axially and in an elastically yielding manner.