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公开(公告)号：EP2714512B1
公开(公告)日：2018-02-21
申请号：EP12723862.4
申请日：2012-05-23
IPC分类号： B64C39/02 , B64C27/605 , B64C27/32 , B64C27/58
CPC分类号： B64C27/605 , B64C27/00 , B64C27/08 , B64C27/32 , B64C27/50 , B64C27/58 , B64C27/59 , B64C39/024 , B64C2201/027 , B64C2201/042 , B64C2201/102 , B64C2201/108 , B64D27/02 , B64D27/24 , B64F1/04
摘要： Embodiments of the present invention relate to a rocket or ballistic launch rotary wing air vehicle.
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2.发明公开SYSTEME DE COMMANDE D'UN ROTOR DE GIRAVION, GIRAVION EQUIPE D'UN TEL SYSTEME ET METHODE DE COMMANDE ASSOCIEE 有权旋翼机的转子的控制系统，这样的系统上搭载的挥杆平面和相关的控制方法
公开(公告)号：EP3081484A1
公开(公告)日：2016-10-19
申请号：EP16162517.3
申请日：2016-03-29
申请人： Airbus Helicopters
摘要： La présente invention concerne un système de commande (1) d'un rotor (2) d'un giravion, un giravion ainsi équipé et une méthode de commande correspondante.
L'invention se caractérise en ce que ledit système de commande (1) comporte :
- des moyens de sélection (4) pour définir, entre deux butées physiques correspondant aux limites de déplacement d'un organe de commande (3), au moins deux plages disjointes de positions dudit organe de commande (3), une première plage de positions étant définie entre au moins deux premières valeurs limites autour d'une position d'effort nul de l'organe de commande (3) et au moins une seconde plage de positions étant définie entre au moins une desdites au moins deux premières valeurs limites et au moins une seconde valeur limite,
- des moyens de commande (5) pour affecter une première loi de commande à ladite première plage de positions dudit organe de commande (3) et une seconde loi de commande à ladite seconde plage de positions dudit organe de commande (3), lesdites première et seconde lois de commande étant choisies distinctes l'une de l'autre.摘要翻译： 用于控制旋翼飞行器的旋翼，装配有一个有旋翼飞行器，和一种控制方法相对应的控制系统。 该系统包括选择装置用于定义至少两个不相交的位置的范围内对两个物理支座对应于控制部件的移动极限之间的控制部件，所述至少两个第一极限值之间限定约的零力位置的第一位置范围 控制部件和至少一个第二位置范围被所述至少两个第一限制值中的至少一个和至少一个第二极限值之间限定; 装置和用于分配第一控制律到控制构件和第二控制法向控制件的第二位置范围的第一位置范围控制中，第一和第二控制法被选择为彼此不同的。
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3.发明授权COMPOSITE-STEEL HYBRID MAST FOR ROTORCRAFT AND METHOD OF MAKING A MAST 有权HYBRID转子轴复合钢的旋翼飞机和HESTELLUNGSVERFAHREN转子轴
公开(公告)号：EP2054192B1
公开(公告)日：2015-04-01
申请号：EP07840974.5
申请日：2007-08-15
发明人： LIN, Sherman, S.
CPC分类号： B64C27/12 , B64C27/58 , Y02T50/43 , Y10S416/50 , Y10T428/1355 , Y10T428/1359
摘要： A composite-steel hybrid mast for a rotorcraft includes a tubular, steel portion having an internal surface defining a space therein and a composite portion disposed within the space defined by the internal surface of the steel portion and held in a fixed spatial relationship with respect to the internal surface of the steel portion.
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公开(公告)号：EP2099676A2
公开(公告)日：2009-09-16
申请号：EP07875043.7
申请日：2007-11-12
IPC分类号： B64C27/48
摘要： A bearingles.s rotor system (20) includes a flexbeam assembly having a first, beam (30A) and a second beam '(30B) arranged in a back-to-back orientation with a pitch shaft (32) channeled therebetween. The beams morph into a rotor blade spar (66) at an outboard rotor blade station. The outboard section of the flexbeam assembly receives the full pitch input from the pitch shaft (32) while the most inboard section of the flexbeam assembly is essentially fixed in pitch by a blade attachment (26) to a rotor hub assembly. The flexbeam assembly twist versus span is essentially linear from the most inboard to the most outboard rotor blade stations. The outboard rotor blade station, being attached to the outboard section of the flexbeam assembly, thereby also defines the pitch input equivalent from the outboard rotor blade station to the rotor blade tip.
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5.发明授权
公开(公告)号：EP1858756B1
公开(公告)日：2008-04-30
申请号：EP06708674.4
申请日：2006-03-07
申请人： THALES
IPC分类号： B64C27/68
摘要： The invention concerns a device for compensating helicopter flight control mechanical clearance. The invention concerns helicopter automatic pilot appliances (1). The helicopter automatic pilot device (2) acts on the helicopter flight controls (25, 26) assigned to mechanical clearances by means of a group of actuators called "series actuators" (6) with rapid response and short stroke and mechanically irreversible, arranged in series on the flight controls (25, 26). The invention is characterized in that the device comprises at least one sensor of variation direction of movement setpoints of the series actuators and a clearance compensator adding to the setpoint, based on the variation direction thereof, a corrective term based on the mechanical clearance (311) affecting the flight control (25, 26) equipped with the "series actuator" concerned.
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公开(公告)号：EP1156963A1
公开(公告)日：2001-11-28
申请号：EP00914109.4
申请日：2000-03-04
IPC分类号： B64C27/14 , B64C27/605
摘要： The invention relates to a helicopter with rotor blades that are mounted on a rotor head. Said rotor head is linked in a non-rotational manner with a rotor mast (1) that is rotatably mounted in a transmission housing. Said rotor head is driven by one or more driving mechanisms via a transmission. The pitch of the rotor blades vis-à-vis the plane of rotation is controlled via a wobble plate and control rods (12) and/or via individual actuators (9) that are allocated to the individual rotor blades. The aim of the invention is to provide a novel helicopter in which the control devices of the rotor blades do not interfere with the air flow. The control devices should not be affected by the air flow and only to a limited extent by the centrifugal forces and additional stresses. They should also be protected from the influences of weather. To this end, the control rods (12) and the actuators (9) are mounted inside the rotor mast (1) and/or the rotor head and act upon a pivoted lever (7) which adjusts the pitch via a mixing lever (11) and a control rod (8) individually for each rotor blade.
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7.发明公开Automatic cancellation device for control force errors for aircraft, particulary helicopters 失效用于飞机，特殊直升机的控制力误差的自动取消装置
公开(公告)号：EP0179209A3
公开(公告)日：1987-07-22
申请号：EP85109650
申请日：1985-07-31
CPC分类号： G05D1/0858 , B64C27/58 , G05D1/0061
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公开(公告)号：EP0157875A4
公开(公告)日：1986-01-28
申请号：EP84904019
申请日：1984-09-17
申请人： SUNDSTRAND CORP
发明人： ALDRICH ALLYN M
IPC分类号： B64C20060101 , B64C11/32 , B64C27/58 , B64C27/59 , B64C27/72
摘要： A helicopter blade position and control mechanism including a hollow rotor shaft (14) for mounting a plurality of rotor blades (22) with provision for pitch adjustment. A control shaft (28) is disposed within the rotor shaft and is rotatable relative thereto and is associated with actuators (20) for the blades such that the pitch of the blades is changed when the control shaft rotates relative to the rotor shaft. A planetary gear assembly (44) interconnects to control shaft and a source of power fixed to the helicopter fuselage (10) and is such that when an input to the planetary gear assembly is quiescent, the control shaft will rotate in the same direction and at the same rate as the rotor shaft to maintain a desired blade pitch. Conversely, when an input is placed on the planetary gear system, relative rotation between the control shaft and the rotor shaft will occur to provide the desired adjustment in blade pitch. The system allows accurate blade position feedback signals to be taken from a feedback device stationarily mounted on the fuselage.
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公开(公告)号：EP3299671A1
公开(公告)日：2018-03-28
申请号：EP17190421.2
申请日：2017-09-11
发明人： POSTER, Scott David
CPC分类号： F16H57/0416 , B64C27/12 , B64C27/58 , F16H57/02 , F16H57/0404 , F16H57/0417 , F16H57/0435 , F16H57/0436 , F16H57/045
摘要： The present invention includes a cooling system for a gearbox (327), the cooling system comprising: a pressurized housing (300) in fluid communication with the gearbox (327) configured to circulate a pressurized lubricant; and one or more cooling fins (308) about the pressurized housing (300), wherein heat from the pressurized lubricant within the pressurized housing (300) is actively convected through the one or more cooling fins (308).
摘要翻译： 本发明包括用于齿轮箱（327）的冷却系统，该冷却系统包括：与齿轮箱（327）流体连通的加压壳体（300），其配置为使加压润滑剂循环; 和围绕加压壳体（300）的一个或多个冷却翅片（308），其中来自加压壳体（300）内的加压润滑剂的热量通过一个或多个冷却翅片（308）主动对流。
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10.发明授权SYSTEME DE COMMANDE D'UN ROTOR DE GIRAVION, GIRAVION EQUIPE D'UN TEL SYSTEME ET METHODE DE COMMANDE ASSOCIEE 有权SYSTEME DE COMMANDE D'UN ROTOR DE GIRAVION，GIRAVION EQUIPE D'UN TELE SYSTEME ET METHODE DE COMMANDE ASSOCIEE
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