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公开(公告)号：CA2055953A1
公开(公告)日：1992-06-28
申请号：CA2055953
申请日：1991-11-21
Applicant: AEROSPATIALE
Inventor： MOUILLE RENE LOUIS
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公开(公告)号：DE68901521D1
公开(公告)日：1992-06-17
申请号：DE68901521
申请日：1989-09-19
Applicant: AEROSPATIALE
Inventor： MOUILLE RENE LOUIS , SUZZI ROBERT JEAN
Abstract: The invention relates to a flapping restrainer device for the blades of a rotorcraft main rotor, and a rotor head comprising the same. The lower restrainers comprise a reciprocal star-shaped plate (32), having as many radial branches (33) as blades, and each one of the branches being engaged into a radial opening (6) of the hub (3). Outside the latter, the star-shaped plate (32) cooperates with supporting runners (47) integral with the blades. The upper restrainers comprise, for each blade, a stop which is retractable by the effect of the centrifugal force and which is composed of a lever (52), pivoting on a pivot (53) carried by the hub (3), and a first arm (55) of which constitutes a stop finger directed towards an upper supporting component (60) integral with the blade, while a second arm (56) carries a governor weight (57) and a nose (58) for support against a shoulder (59) integral with the hub (3).
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公开(公告)号：IN170751B
公开(公告)日：1992-05-16
申请号：IN485DE1987
申请日：1987-06-05
Applicant: AEROSPATIALE
Inventor： MOUILLE RENE LOUIS , ROLLET PHILIPPE ALAIN
Abstract: A directional and stabilizing device is provided including a faired antitorque rotor, driven in rotation in a transverse aperture formed in a fairing slanted with respect to the vertical by an angle between 0 DEG and 45 DEG . It also includes a "V" empennage fixed to the top of the fairing and the two aerodynamic surfaces of which extend disymmetrically with respect to the vertical plane passing through the top of this fairing, the aerodynamic surfaces being slanted in angular planes between 0 DEG and 45 DEG .
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公开(公告)号：IN170169B
公开(公告)日：1992-02-22
申请号：IN235DE1989
申请日：1989-03-13
Applicant: AEROSPATIALE
Inventor： MOUILLE RENE LOUIS , LEMAN JEAN-LUC
IPC: B64C27/00
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公开(公告)号：IN167852B
公开(公告)日：1990-12-29
申请号：IN636DE1986
申请日：1986-07-16
Applicant: AEROSPATIALE
Inventor： MOUILLE RENE LOUIS , LEMAN JEAN-JUC
Abstract: The invention provides an integrated hub-mast with a single piece tubular body which supports, by its hub body part (3), a reinforcing girdle (6) on each side of which openings (10, 11) are formed. For each blade of the rotor a retaining and pivoting member (13), formed preferably by a spherical stratified stop, is fixed to the girdle (6) and is retained in the hub body (3), and this member (13) is also fixed between the ends inside the hub body (3), of the lower (20) and upper (21) branches of a forked fastening part (19) connecting the blade to this member (13), these branches passing through the openings (10, 11) of a corresponding pair of openings. A heel (23) fixed under the lower branch (20) bears against a reciprocal ring (24) mounted on a support (29) in the hub-mast (1), which has external fastenings for coupling to resilient return and drag damping members of the blades.
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Patent Agency Ranking
公开(公告)号：DE3560771D1
公开(公告)日：1987-11-19
申请号：DE3560771
申请日：1985-08-05
Applicant: AEROSPATIALE
Inventor： MOUILLE RENE LOUIS
Abstract: In a main transmission gearbox for a helicopter having two engines, a lifting rotor and an anti-torque rotor, each of the two engines drives a main kinematic chain comprising from upstream down, an input shaft, a twistable shaft, a gear train forming a first reduction stage having a first bevel pinion meshing with a second bevel pinion which drives in rotation a vertical shaft bearing having a third pinion in mesh with a gearwheel which is common to the two main chains and forms with the third pinions a second reduction stage. The torque received at the gearwheel is transmitted to the driving shaft of the main rotor by way of a supplementary reduction stage of epicyclic type. A third chain comprising two input pinions each of which is mounted upon one of the input shafts and an intermediate pinion which drives the driving shaft of the anti-torque rotor, ensures the distribution of power over the two main chains in the event of breakdown of one engine.
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公开(公告)号：FR2584995B1
公开(公告)日：1987-11-13
申请号：FR8511158
申请日：1985-07-22
Applicant: AEROSPATIALE
Inventor： MOUILLE RENE LOUIS , LEMAN JEAN-LUC
Abstract: The invention provides an integrated hub-mast with a single piece tubular body which supports, by its hub body part (3), a reinforcing girdle (6) on each side of which openings (10, 11) are formed. For each blade of the rotor a retaining and pivoting member (13), formed preferably by a spherical stratified stop, is fixed to the girdle (6) and is retained in the hub body (3), and this member (13) is also fixed between the ends inside the hub body (3), of the lower (20) and upper (21) branches of a forked fastening part (19) connecting the blade to this member (13), these branches passing through the openings (10, 11) of a corresponding pair of openings. A heel (23) fixed under the lower branch (20) bears against a reciprocal ring (24) mounted on a support (29) in the hub-mast (1), which has external fastenings for coupling to resilient return and drag damping members of the blades.
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公开(公告)号：IN157742B
公开(公告)日：1986-05-31
申请号：IN64DE1982
申请日：1982-01-28
Applicant: AEROSPATIALE
Inventor： MOUILLE RENE LOUIS
Abstract: The invention concerns a helicopter rotor, the rigid hub (1) of which comprises a central drum (2) which is disposed substantially in line with the rotor mast (3) and which carries an upper plate (4) and a lower plate (6). This rigid hub (1) is connected to the root of each blade (26) by way of a laminated spherical stop (13) and a resilient-return drag brace. Each blade (26) comprises, in the zone of its root, a rigid loop (27) which surrounds the laminated spherical stop (13) in a continuous manner and is engaged in the inner movable fitting (24) of this stop (13) by means of a wedge (30) co-operating with the outer fixed fitting (15) of the stop (13).
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公开(公告)号：FR2568541A1
公开(公告)日：1986-02-07
申请号：FR8412400
申请日：1984-08-06
Applicant: AEROSPATIALE
Inventor： MOUILLE RENE LOUIS
Abstract: In a main transmission gearbox for a helicopter having two engines, a lifting rotor and an anti-torque rotor, each of the two engines drives a main kinematic chain comprising from upstream down, an input shaft, a twistable shaft, a gear train forming a first reduction stage having a first bevel pinion meshing with a second bevel pinion which drives in rotation a vertical shaft bearing having a third pinion in mesh with a gearwheel which is common to the two main chains and forms with the third pinions a second reduction stage. The torque received at the gearwheel is transmitted to the driving shaft of the main rotor by way of a supplementary reduction stage of epicyclic type. A third chain comprising two input pinions each of which is mounted upon one of the input shafts and an intermediate pinion which drives the driving shaft of the anti-torque rotor, ensures the distribution of power over the two main chains in the event of breakdown of one engine.
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公开(公告)号：DE3265103D1
公开(公告)日：1985-09-05
申请号：DE3265103
申请日：1982-11-17
Applicant: AEROSPATIALE
Inventor： MOUILLE RENE LOUIS
Abstract: The invention concerns a helicopter rotor, the rigid hub (1) of which comprises a central drum (2) which is disposed substantially in line with the rotor mast (3) and which carries an upper plate (4) and a lower plate (6). This rigid hub (1) is connected to the root of each blade (26) by way of a laminated spherical stop (13) and a resilient-return drag brace. Each blade (26) comprises, in the zone of its root, a rigid loop (27) which surrounds the laminated spherical stop (13) in a continuous manner and is engaged in the inner movable fitting (24) of this stop (13) by means of a wedge (30) co-operating with the outer fixed fitting (15) of the stop (13).
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