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公开(公告)号：US3921940A
公开(公告)日：1975-11-25
申请号：US47434074
申请日：1974-05-29
Applicant: AEROSPATIALE
Inventor： MOUILLE RENE LOUIS
IPC: B64C27/00
CPC classification number: B64C27/001 , B64C2027/002 , B64C2027/005
Abstract: As assembly for connecting the lift rotor to a helicopter body filters out vibrations. In the assembly the rotor mast and associated elements form a self-supporting but resiliently deformable system.
Abstract translation: 由于用于将升降机转子连接到直升机机体的组件滤除振动。 在组件中，转子桅杆和相关元件形成自支撑但可弹性变形的系统。
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公开(公告)号：US3920202A
公开(公告)日：1975-11-18
申请号：US46403274
申请日：1974-04-25
Applicant: AEROSPATIALE
Inventor： MOUILLE RENE LOUIS
CPC classification number: B64C27/001 , B64C2027/002 , B64C2027/005 , Y10S416/50
Abstract: The vibration created by torque of a rotor of a helicopter and the like is dampened by fastening a baseplate having a pair of diametrically opposed shoulders to the housing of the transmission box whereto the rotor mast is mounted. Relatively to the fuselage of the helicopter, projections are fixed which are independent of the baseplate and extend in opposition to the shoulders to cooperate therewith for limiting the rotary movement of the baseplate. Between the shoulders and the projections, resilient members are interposed to absorb the compressive force of the rotary movement.
Abstract translation: 通过将具有一对径向相对的肩部的基板紧固到传动箱的安装有转子桅杆的壳体来减轻由直升机的转子的扭矩产生的振动。 相对于直升机的机身，突起被固定，独立于基板并且与肩部相对延伸以与其配合以限制基板的旋转运动。 在肩部和突起之间插入弹性构件以吸收旋转运动的压缩力。
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公开(公告)号：US3679322A
公开(公告)日：1972-07-25
申请号：US3679322D
申请日：1970-05-27
Applicant: AEROSPATIALE
Inventor： MOUILLE RENE LOUIS
CPC classification number: B64C27/32 , B64C27/322 , B64C27/327 , B64C27/39
Abstract: The invention relates to a rotor hub for rotary-wing aircraft, in which a hollow one-piece rotor hub-mast is provided at its upper end with lobes lying in planes parallel to the rotation axis of the rotor hub-mast, pairs of such lobes forming yokes for respectively receiving a flapping hinge-pin for the associated blade.
Abstract translation: 本发明涉及一种用于旋转翼飞机的转子轮毂，其中中空的一体式转子轮毂桅杆在其上端设置有位于平行于转子轮毂桅杆的旋转轴线的平面中的叶片， 叶片形成轭，用于分别接收用于相关叶片的扑动铰链销。
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公开(公告)号：JPH0542896A
公开(公告)日：1993-02-23
申请号：JP35835591
申请日：1991-12-27
Applicant: AEROSPATIALE
Inventor： MOUILLE RENE LOUIS
Abstract: PURPOSE: To provide a light-weight, highly reliable gyrocraft rotor hub body wherein only centrifugal force of a blade operates as a load, and in addition, to provide the rotor hub body suitable for manufacturing with composite materials. CONSTITUTION: This gyrocraft rotor hub body 1 has a form wherein each blade is connected with the rotor hub body 1 by joint-connecting members. The gyrocraft rotor hub body 1 consists of two rings 7, 8 located in the plane, which cross at right angles with an axle line extending from a column to a rotor in parallel with each other. These two rings 7, 8 are provided across a thin wall having an opening part 10 which is larger enough to insert the joint in. Supporting points for fixing the joint are fixed by a fixing member supported by holes 12, 14 of the rings 7, 8. As a result, a hard brace is formed, which enables power transmission.
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公开(公告)号：FR2689483A1
公开(公告)日：1993-10-08
申请号：FR9302822
申请日：1993-03-11
Applicant: AEROSPATIALE
Inventor： MOUILLE RENE LOUIS
Abstract: The gyroplane rotor hub, to which the blades are attached by pivots and couplings, has two flanges (7, 8) connected by a thin wall (9) and set at a distance from one another which is sufficient to contain the pivots. The wall (9) is cylindrical in shape with apertures (10) of sufficient size for the couplings to pass through. The two flanges have holes (12, 14) through them lying parallel to the axis of the hub and in line with the middle of the apertures (10) to receive the pivot pins. The connection between the hub and the rotor shaft is made via a thin base (4), truncated conical in shape, with its large end fixed to the inside of the lower flange (8), and its smaller end fixed to the top of the rotor shaft (3).
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Patent Agency Ranking6.发明专利
公开(公告)号：IN163642B
公开(公告)日：1988-10-22
申请号：IN223DE1984
申请日：1984-03-12
Applicant: AEROSPATIALE
Inventor： MOUILLE RENE LOUIS , DECLERCQ MARC , JALAGUIER JEAN-PIERRE , JAUGEY BERNARD
IPC: B64C11/22 , B29C43/02 , B29C43/18 , B29C43/20 , B29C43/32 , B29C43/34 , B29C57/00 , B29C67/00 , B29C70/06 , B29D99/00 , B29K105/10 , B32B3/12 , B64C11/26 , B64C27/46 , B64C27/473 , B64C27/82 , F01D5/28 , B64C11/06
Abstract: A variable pitch multi-blade propeller suitable for use on a helicopter is constructed of a foam preform joined with a fibrous spar enclosed in resin-impregnated foils and fitted with a metal leading edge. Various components are assembled in a mold and the resins, then cured. The structure may further include a reinforcing yoke of carbon fiber fabrics preimpregnated with a polymerizable synthetic resin. The process may further include a heat treating step to effect polymerization.
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公开(公告)号：FR2584995A1
公开(公告)日：1987-01-23
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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8.发明专利
公开(公告)号：FR2427251A1
公开(公告)日：1979-12-28
申请号：FR7816521
申请日：1978-06-02
Applicant: AEROSPATIALE
Inventor： MOUILLE RENE LOUIS
Abstract: The strut(7) which connects the blade to the hub is built up from alternate layers of metal strips(7a-7c) and strips(7d-7e) which are made from a tough elastic material with large remanence under deformation and form a frequency adaptor. The ends of the struts are connected via ball joints at one end to the end of the rotor blade(5) and the other end to a point on the hub(1). The strut is always inclined at a small angle to its rotor-blade. The centre of one ball joint(12) is near the axis(d) about which the rotor blade can move up and down.
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公开(公告)号：FR2416839A1
公开(公告)日：1979-09-07
申请号：FR7803810
申请日：1978-02-10
Applicant: AEROSPATIALE
Inventor： MOUILLE RENE LOUIS , GENOUX GERARD CHARLES LOUIS , DECLERCQ MARC AUGUSTE , LEMAN JEAN-LUC MICHEL , SUZZI ROBERT JEAN
Abstract: The invention relates to a device for damping the vibrations of a rotary-wing aircraft rotor. An annular weight is disposed concentrically of the rotor axis. This weight is supported by at least three resiliently deformable elements such as helical springs, radially biased in directions distributed regularly around the rotor axis. The inner ends of the springs directly bear on a part extending the rotor shaft axially. Their outer ends directly bear on the annular weight so that the spring apply statically balanced centrifugal thrusts to the annular weight. The springs are so still that they support the annular weight without substantially bending.
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公开(公告)号：DE2903856A1
公开(公告)日：1979-08-16
申请号：DE2903856
申请日：1979-02-01
Applicant: AEROSPATIALE
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