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1. 发明授权

EP3760535B1 PROPELLER BLADE ANGLE CONTROL SYSTEM 有权
公开(公告)号：EP3760535B1
公开(公告)日：2023-01-25
申请号：EP20185788.5
申请日：2017-06-16
发明人： WADDLETON, David
IPC分类号： B64C11/38 , B64C27/64 , B64C27/59 , B64C27/605 , B64C27/615 , F15B21/04

2. 发明授权

EP3786060B1 BOITE DE TRANSMISSION DE PUISSANCE, GIRAVION EQUIPÉ D'UNE TELLE BOITE DE TRANSMISSION ET MÉTHODE DE VARIATION DE PAS DES PALES D'UN ROTOR ASSOCIÉE 有权
公开(公告)号：EP3786060B1
公开(公告)日：2023-01-04
申请号：EP20181577.6
申请日：2020-06-23
发明人： GOUJET, Damien
IPC分类号： B64C27/12 , B64C27/58 , B64C27/59 , B64C27/605 , B64C27/78 , F16C33/66 , F16H57/04 , B64C11/30

3. 发明公开

EP4086171A1 A CYCLIC PITCH ANGLE ADJUSTMENT APPARATUS 有权
公开(公告)号：EP4086171A1
公开(公告)日：2022-11-09
申请号：EP21400009.3
申请日：2021-05-05
申请人： AIRBUS HELICOPTERS DEUTSCHLAND GmbH
发明人： Czech, Ian-Luca
IPC分类号： B64C27/54 , B64C27/59 , B64C27/72
摘要： The present embodiments relate to a cyclic pitch angle adjustment apparatus 200 for a rotor 110 or propeller, to a rotor 110 with such a cyclic pitch angle adjustment apparatus 200, and to a rotorcraft 100 with such a rotor 110. The cyclic pitch angle adjustment apparatus 200 includes levers 230a, 230b that rotate rotor blades 212a, 212b around associated pitch axes 235a, 235b, rods 240a, 240b that mechanically link the levers 230a, 230b with a bearing 220 such that the rods 240a, 240b are movable relative to a central point 223, the bearing 220 being attached to a central rod 250 that is movable and adapted for adjusting the cyclic pitch angle of the rotor blades 112 from one pitch angle in one position to another pitch angle in another position 265.

4. 发明授权

EP3533710B1 A PASSIVE PITCH ANGLE ADJUSTMENT APPARATUS 有权
公开(公告)号：EP3533710B1
公开(公告)日：2021-01-27
申请号：EP18400006.5
申请日：2018-02-28
发明人： Schmiedel, Patrik , Leitner, Harald , Kraus, Julian , Dannemann, Ludwig , Kiesewetter, Uwe
IPC分类号： B64C27/54 , B64C27/58 , B64C27/59

5. 发明公开

EP3587845A1 REDUNDANT HELICOPTER PITCH CHANGE BEARING 有权
公开(公告)号：EP3587845A1
公开(公告)日：2020-01-01
申请号：EP19182757.5
申请日：2019-06-27
申请人： Sikorsky Aircraft Corporation
发明人： WITTKE, Kevin M. , HOWARD, Bertrand J.
IPC分类号： F16C19/52 , B64C11/32 , B64C27/59 , B64C27/605 , B64C27/78 , B64C27/82 , F16C19/54 , F16C39/02
摘要： An aircraft rotor system includes a rotating pitch change shaft which rotates about an axis, a translating element disposed within the rotating pitch change shaft and movable along the axis and a pitch change bearing assembly which transfers movement of the translating element to the pitch change shaft. The pitch change bearing assembly includes a primary bearing and a secondary bearing coupled to the rotating pitch change shaft via the translating element when the primary bearing is in a first mode. A thrust shoulder is coupled to the translating element. The thrust shoulder is movable into engagement with the secondary bearing in response to failure of the primary bearing such that in a second mode, movement of the translating element is primarily transferred to the pitch change shaft via the secondary bearing.

6. 发明授权

EP3296198B1 ADJUSTMENT OF TRACK AND BALANCE OF A MULTI-BLADE ROTOR 有权
公开(公告)号：EP3296198B1
公开(公告)日：2018-11-14
申请号：EP16400042.4
申请日：2016-09-15
申请人： AIRBUS HELICOPTERS DEUTSCHLAND GmbH
发明人： Büsing, Moritz
IPC分类号： B64C27/00 , B64C27/605 , B64C11/32 , B64C27/32 , B64C27/59 , B64C27/72
CPC分类号： B64C27/59 , B64C11/32 , B64C27/008 , B64C27/32 , B64C27/605 , B64C2027/7216
摘要： The invention is related to a multi-blade rotor (1) of a rotary wing aircraft, the multi-blade rotor (1) comprising at least one rotor blade (2) that defines a pitch axis (3) and that is provided with an associated pitch-control lever (5) that is operatively coupled to a pitch link rod (4), the pitch link rod (4) defining a longitudinal axis (4a), wherein the associated pitch-control lever (5) comprises an accommodation (5a) that is located on the longitudinal axis (4a) of the pitch link rod (4) at a predetermined distance (4c) from the pitch axis (3) of the at least one rotor blade (2), the pitch link rod (4) being operatively coupled to the associated pitch-control lever (5) at the accommodation (5a) of the associated pitch-control lever (5), wherein the predetermined distance (4c) is adjustable in order to enable adjustment of track and balance of the multi-blade rotor (1).

7. 发明公开

EP3279087A1 MULTI-SHAFT POWER SOURCE UNMANNED FLIGHT EQUIPMENT 无效
标题翻译：多轴电源无人飞行设备
公开(公告)号：EP3279087A1
公开(公告)日：2018-02-07
申请号：EP17182959.1
申请日：2017-07-25
申请人： Ewatt Technology Co., Ltd.
发明人： ZHAO, Guocheng , LUO, Wei , QI, Pengcheng
IPC分类号： B64C27/08 , B64C27/12 , B64C27/59 , B64D35/04
CPC分类号： F02B61/04 , B64C27/08 , B64C27/12 , B64C27/14 , B64C27/59 , B64C39/024 , B64C2201/027 , B64C2201/044 , B64C2201/108 , B64D35/04 , F02B67/06 , F02B73/00 , F02B75/16 , F16H1/222 , F16H7/02 , F16H37/065
摘要： The present invention discloses a multi-shaft power source unmanned flight equipment, and belongs to the technical field of unmanned aerial vehicles. The multi-shaft power source unmanned flight equipment comprises a frame (1), a plurality of rotor sets (2) and a power device (3). The plurality of rotor sets (2) are rotatably fixed on the frame (1), and the power device (3) is correspondingly movably connected with each rotor set (2) respectively. Power is provided for flight of the unmanned flight equipment by the power device (3) with oil drive characteristics, mechanical kinetic energy is generated by burning a combustion material pre-injected in the power device (3), and rotors (21) in each rotor set (2) correspondingly connected with the power device are driven to rotate, thereby replacing the traditional electric multi-rotor unmanned aerial vehicle structure adopting electric modes such as batteries, electronic speed controllers and the like to supply power and provide power for the rotation of the rotors (21); and the unmanned flight equipment has the characteristics of long duration and strong loading capacity.
摘要翻译：本发明公开了一种多轴动力源无人飞行器，属于无人机技术领域。该多轴动力源无人飞行器包括机架（1），多个转子组（2）和动力装置（3）。多个转子组（2）可转动地固定在机架（1）上，动力装置（3）分别与每个转子组（2）对应活动连接。动力装置（3）为具有油驱特性的无人飞行装备提供动力，通过燃烧预先注入动力装置（3）中的燃烧材料产生机械动能，并且每个转子（21）中的转子驱动与动力装置对应连接的转子组（2）旋转，从而代替采用电池，电子调速器等电动模式的传统电动多旋翼无人机结构为旋转动力提供动力并提供动力的转子（21）; 无人飞行器具有持续时间长，载重能力强的特点。

8. 发明公开

EP3257744A1 PROPELLER BLADE ANGLE CONTROL SYSTEM 有权
标题翻译：螺旋桨叶片角度控制系统
公开(公告)号：EP3257744A1
公开(公告)日：2017-12-20
申请号：EP17176439.2
申请日：2017-06-16
申请人： Pratt & Whitney Canada Corp.
发明人： WADDLETON, David
IPC分类号： B64C11/38 , B64C27/64 , B64C27/59 , B64C27/605 , B64C27/615 , F15B21/04
摘要： A control circuit (20) for changing the angle of propeller blades (17) includes a propeller control unit (21) controlling a supply of oil to modify an angle of propeller blades (17), and a fixed-displacement pump (22) providing the supply of oil from an engine oil return system (13) to the propeller control unit (21). An oil cooling line (23) extends between an outlet (22B) of the pump (22) and the engine oil return system (13). The oil cooling line (23) defines an oil leakage path (27) leading to the engine oil return system (13) for cooling the oil. A flow regulator (30) between the pump (22) and the propeller control unit (21) is operable between an open position where oil is directed through the oil cooling line (23) to the engine oil return system (13) for cooling the oil, and a closed position blocking the oil cooling line (23) and directing oil toward the propeller control unit (21) to modify the angle of the propeller blades (17).
摘要翻译：一种用于改变螺旋桨叶片（17）的角度的控制电路（20）包括控制供油以改变螺旋桨叶片（17）的角度的螺旋桨控制单元（21），以及提供固定排量泵（22）从发动机回油系统（13）向螺旋桨控制单元（21）供油。油冷却管线（23）在泵（22）的出口（22B）和发动机机油返回系统（13）之间延伸。油冷却管路（23）限定了通向发动机机油返回系统（13）的用于冷却机油的机油泄漏路径（27）。泵（22）和螺旋桨控制单元（21）之间的流量调节器（30）可在将油通过油冷却管路（23）引导至发动机机油返回系统（13）的打开位置之间操作，以及封闭油冷却管路（23）并将油导向螺旋桨控制单元（21）以改变螺旋桨叶片（17）的角度的闭合位置。

9. 发明授权

EP2384969B1 Système de commandes de vol simplifiées comportant un dispositif de friction débrayable 有权转让
标题翻译：与脱开联接器装置的简化的飞行控制系统
公开(公告)号：EP2384969B1
公开(公告)日：2015-11-11
申请号：EP11003320.6
申请日：2011-04-20
申请人： Airbus Helicopters
发明人： Leguay, Pascal , Carlavan, Cédric
IPC分类号： B64C13/10 , B64C27/56 , B64C27/59 , G05D1/08 , G05G5/03 , G05G5/22 , G05G5/08 , B64C13/30
CPC分类号： B64C13/10 , B64C13/30 , B64C27/59 , G05G5/08 , G05G5/22 , Y02T50/44

10. 发明公开

EP2384969A3 Système de commandes de vol simplifiées comportant un dispositif de friction débrayable 有权转让
标题翻译：与脱开联接器装置的简化的飞行控制系统
公开(公告)号：EP2384969A3
公开(公告)日：2014-11-26
申请号：EP11003320.6
申请日：2011-04-20
申请人： Airbus Helicopters
发明人： Leguay, Pascal , Carlavan, Cédric
IPC分类号： B64C13/10 , B64C27/56 , B64C27/59 , G05D1/08 , G05G5/03 , G05G5/22 , G05G5/08 , B64C13/30
CPC分类号： B64C13/10 , B64C13/30 , B64C27/59 , G05G5/08 , G05G5/22 , Y02T50/44
摘要： La présente invention concerne un dispositif de friction (11) pour maintenir dans une position déterminée un organe de commande (2,8) comportant :
- une pièce de contact (16) mobile entre une position stable débrayée et une position stable embrayée et inversement, ladite position stable embrayée correspondant à une position dans laquelle la pièce de contact (16) est en appui sur l'organe de commande (2,8) de manière à établir une force de friction déterminée,
- des moyens d'entraînement pour déplacer la pièce de contact (16) entre les deux positions stables,

caractérisé en ce qu'il comprend un moyen de commande à distance pour activer et désactiver les moyens d'entraînement.

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