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51. 发明授权

US09469399B2 Separable blade attachment for a bearingless rotor of a helicopter 有权
标题翻译：用于直升机无轴承转子的可分离刀片附件
公开(公告)号：US09469399B2
公开(公告)日：2016-10-18
申请号：US14053841
申请日：2013-10-15
申请人： AIRBUS HELICOPTERS DEUTSCHLAND GMBH
发明人： Gerald Kuntze-Fechner , Markus Bauer
IPC分类号： B64C27/33 , B64C27/51
CPC分类号： B64C27/33 , B64C27/51
摘要： The invention relates to a separable blade attachment (1) for a bearingless main rotor of a helicopter with an airfoil blade (2), a flexbeam (3) and a control cuff (4) enclosing at least a predominant portion of said flexbeam (3). A separable junction arrangement between said flexbeam head (13), said control cuff (4, 22) and said root end of said airfoil blade (2) is mechanical with removable fasteners. A stiffened link (17) is provided between respective trailing edges (9) of the control cuff (4) and said airfoil blade (2).
摘要翻译：本发明涉及一种用于直升机的无轴承主转子的可分离叶片附件（1），其具有翼型叶片（2），柔性梁（3）和控制箍（4），所述柔性梁（3）和控制箍（4）至少包围所述柔性梁）。所述挠性头（13），所述控制箍（4,22）和所述翼型叶片（2）的所述根端之间的可分离的连接装置是机械的，具有可移除的紧固件。加强连杆（17）设置在控制套筒（4）的相应后缘（9）和所述翼型叶片（2）之间。

52. 发明申请

US20160272296A1 ROTARY WING AIRCRAFT WITH A MULTIPLE BEAM TAIL 有权
标题翻译：具有多根梁尾的旋转式飞机
公开(公告)号：US20160272296A1
公开(公告)日：2016-09-22
申请号：US14679072
申请日：2015-04-06
申请人： AIRBUS HELICOPTERS DEUTSCHLAND GMBH
发明人： Axel FINK
IPC分类号： B64C1/06 , B64C1/26 , B64C27/82
CPC分类号： B64C1/063 , B64C1/26 , B64C27/82 , B64C2027/8209 , B64C2027/8254 , B64C2027/8263
摘要： A rotary wing aircraft comprising a fuselage, a cabin volume enclosed by the fuselage, a main rotor arranged above the fuselage, a tail rotor mounted on a tail, the tail being attached to a rear part of the fuselage supporting the tail at its rear end, whereas the tail includes two beam boom elements, one element extending at the port side and the other element extending at the starboard side of the rotary wing aircraft, the front root end of each element being hinged to the corresponding lateral side of the fuselage, and both elements being canted with respect to the longitudinal axis of the rotary wing aircraft so as to be interconnected to each other at the rear portion of the tail.
摘要翻译：一种旋翼飞机，其包括机身，由机身包围的舱室体积，设置在机身上方的主转子，安装在尾部上的尾部转子，尾部附接到机身的后部，在后端支撑尾部而尾部包括两个梁起重臂元件，一个在端口侧延伸的元件，另一个元件在旋转翼飞行器的右舷侧延伸，每个元件的前根端铰接到机身的相应外侧，并且两个元件相对于旋转翼飞行器的纵向轴线倾斜，以便在尾部的后部处彼此互连。

53. 发明授权

US09359071B2 Aerodynamic blade attachment for a bearingless rotor of a helicopter 有权
标题翻译：直升机无轴承转子的气动叶片附件
公开(公告)号：US09359071B2
公开(公告)日：2016-06-07
申请号：US13785696
申请日：2013-03-05
申请人： AIRBUS HELICOPTERS DEUTSCHLAND GMBH
发明人： Gerald Kuntze-Fechner , Markus Bauer , Martin Ortner
IPC分类号： B64C27/00 , B64C27/33 , B64C27/48 , B64C27/50
CPC分类号： B64C27/33 , B64C27/48 , B64C27/50
摘要： An aerodynamic blade attachment (1) for a bearingless rotor, particularly a main rotor, of a helicopter, comprising: an airfoil blade (2) having a tip end and a root end and having a pitch axis from said tip end to said root end; a flexbeam (3); a control cuff (4, 22) enclosing and extending along said flexbeam (3) and a separable junction arrangement between said flexbeam (3), said control cuff (4) and said root end of said airfoil blade (2). Said junction arrangement is mechanical between said flexbeam (3), said control cuff (4) and said root end of said airfoil blade (2). Removable fasteners (5, 6) connect said root end of said airfoil blade (2) and said control cuff (4) with said flexbeam (3). Said junction arrangement comprises fairing means (10, 27, 28, 31, 32 and 39) encompass the removable fasteners (5, 6) and said flexbeam (3).
摘要翻译：一种用于直升机的无轴承转子，特别是主转子的空气动力学叶片附件（1），包括：具有尖端和根端并具有从所述尖端到所述根端的俯仰轴的翼型叶片（2） ; 柔性梁（3）; 沿着所述挠性束（3）包围并延伸的控制箍（4,22）和所述柔性梁（3），所述控制箍（4）和所述翼型叶片（2）的所述根端之间的可分离的连接装置。所述接合装置在所述挠性梁（3），所述控制箍（4）和所述翼型叶片（2）的所述根端之间是机械的。可拆卸紧固件（5,6）将所述翼型叶片（2）的所述根端和所述控制箍（4）与所述挠性梁（3）连接。所述接合装置包括包围可拆卸紧固件（5,6）和所述柔性梁（3）的整流装置（10,27,28,31,32和39）。

54. 发明授权

US09283696B2 Molding device 有权
标题翻译：成型装置
公开(公告)号：US09283696B2
公开(公告)日：2016-03-15
申请号：US14513640
申请日：2014-10-14
申请人： AIRBUS HELICOPTERS DEUTSCHLAND GMBH
发明人： Thomas Hertle , Jan-Christoph Arent , Christoph Loy
IPC分类号： B29C59/02 , B29C35/00 , B29C70/44 , B29C33/02
CPC分类号： B29C35/007 , B29C33/02 , B29C70/44
摘要： A molding device for curing of composite components comprising: a molding die, composite material in the molding die, heat application means, sheathing means for the composite material and the molding die and vacuum means for the application of vacuum to the composite material in the molding die. The heat application means comprise at least one heat pipe with a heat exchanger attached to the molding die for thermal conduction to the composite material.
摘要翻译：一种用于复合组件固化的成型装置，包括：成型模具，成型模具中的复合材料，加热装置，复合材料的护套装置和成型模具以及用于在模制中对复合材料施加真空的真空装置死。热施加装置包括至少一个具有附接到模具的热交换器的热管，用于热传导到复合材料。

55. 发明授权

US09254921B2 Air inlet combining a filter and a bypass device for use with a turbine engine 有权
标题翻译：进气口组合一个过滤器和一个与涡轮发动机一起使用的旁路装置
公开(公告)号：US09254921B2
公开(公告)日：2016-02-09
申请号：US14101405
申请日：2013-12-10
申请人： AIRBUS HELICOPTERS DEUTSCHLAND GMBH
发明人： Ralf Braeutigam
IPC分类号： B64D33/02 , B64C27/04
CPC分类号： B64D33/02 , B64C27/04 , B64D2033/0246 , B64D2033/0293
摘要： An air inlet (10) for an engine (20) of an aircraft (50), the air inlet (10) having a duct (2) feeding outside air to said engine (20) together with a filter system combining at least one filter (3) and at least one bypass device (4). Said filter (3) and said bypass device (4) are fastened on a common support (1) situated at one end of said duct (2) and on a flank of a fuselage (51) of said aircraft (50). Said bypass device (4) comprises a cover (5) and an actuator (6) controlling opening of said cover (5). Thus, when said filter (3) no longer allows outside air to pass therethrough, said cover (5) is opened, and outside air passes via the bypass device (4) in order to feed said engine (20) with outside air.
摘要翻译：一种用于飞行器（50）的发动机（20）的空气入口（10），所述进气口（10）具有向与所述发动机（20）供给外部空气的管道（2）以及与至少一个过滤器（3）和至少一个旁路装置（4）。所述过滤器（3）和所述旁路装置（4）被紧固在位于所述管道（2）的一端和所述飞机（50）的机身（51）的侧翼上的公共支撑件（1）上。所述旁路装置（4）包括盖（5）和控制所述盖（5）的开口的致动器（6）。因此，当所述过滤器（3）不再允许外部空气通过时，所述盖（5）打开，并且外部空气经由旁路装置（4）通过，以便向外部空气供给所述发动机（20）。

56. 发明授权

US09214088B2 Obstacle information system of a helicopter 有权
标题翻译：直升机障碍物信息系统
公开(公告)号：US09214088B2
公开(公告)日：2015-12-15
申请号：US13908270
申请日：2013-06-03
申请人： AIRBUS HELICOPTERS DEUTSCHLAND GMBH
发明人： Wolfgang Kreitmair-Steck , Benno Van Noort
IPC分类号： G08G5/04 , G01S17/93 , G01S13/93 , G01S7/06 , G01C23/00
CPC分类号： G08G5/04 , G01C23/00 , G01S7/062 , G01S13/9303 , G01S17/933
摘要： An obstacle information system and method for a helicopter with a warning information processor (3) and a display unit (1) for any obstacle (2) within a predetermined minimum distance d4. Said warning information processor (3) is fed with information related to detected distance d5 and direction of said at least one obstacle (2) detected by an obstacle sensor system (4) to compute and prepare the information for presentation on the display unit (1). Said display unit (1) comprises at least an indication area with a central circular surface (6) and a concentric ring-shaped area (7) around the circular surface (6). Said circular surface (6) is used exclusively for alerts. The ring-shaped area (7) is used for both. Warnings and alerts and the repartition in the indication area of circular surface (6) and ring-shaped area (7) are dependent on the detected distance d5 of said at least one obstacle (2).
摘要翻译：一种用于具有警告信息处理器（3）的直升机和在预定最小距离d4内的任何障碍物（2）的显示单元（1）的障碍物信息系统和方法。所述警告信息处理器（3）被馈送与由障碍物传感器系统（4）检测到的检测距离d5和所述至少一个障碍物（2）的方向有关的信息，以计算和准备用于呈现在显示单元（1）上的信息）。所述显示单元（1）至少包括具有中心圆形表面（6）和围绕圆形表面（6）的同心环形区域（7）的指示区域。所述圆形表面（6）仅用于警报。环形区域（7）用于两者。警告和警报以及圆形表面（6）和环形区域（7）的指示区域中的重新分配取决于所述至少一个障碍物（2）的检测距离d5。

57. 发明申请

US20150307182A1 ADVANCED PITCH STABILIZER 有权
标题翻译：高级搅拌稳定器
公开(公告)号：US20150307182A1
公开(公告)日：2015-10-29
申请号：US14554142
申请日：2014-11-26
申请人： AIRBUS HELICOPTERS DEUTSCHLAND GMBH
发明人： Sebastian MORES , Alessandro D'ALASCIO , Uwe KIESEWETTER , Stefan PROBST , Christian WEHLE , Marius BEBESEL
IPC分类号： B64C5/10 , B64C9/06
CPC分类号： B64C5/10 , B64C9/06 , B64C27/82 , B64C2027/8254 , B64C2027/8272 , B64C2027/8281
摘要： A pitch stabilizer with box configuration suitable for providing stability to a rotorcraft comprising a vertical mid-plane and a fuselage; the pitch stabilizer comprising one or two pitch stabilizing assemblies, with no more than one pitch stabilizing assembly on each side of the vertical mid-plane, wherein each pitch stabilizing assembly comprises upper pitch stabilizing means, lower pitch stabilizing means and a wing tip element.
摘要翻译：一种具有箱形结构的桨距稳定器，其适于为包括垂直中平面和机身的旋翼飞机提供稳定性; 所述桨距稳定器包括一个或两个俯仰稳定组件，在垂直中平面的每一侧上不超过一个桨距稳定组件，其中每个俯仰稳定组件包括上桨距稳定装置，下桨距稳定装置和翼尖元件。

58. 发明申请

US20150197334A1 FLEXBEAM UNIT FOR A BEARINGLESS OR A HINGE AND BEARINGLESS MULTI-BLADE ROTOR OF A ROTARY WING AIRCRAFT 审中-公开
标题翻译：用于无轴承的弹性单元或旋转式飞行器的铰链和无轴承多叶轮转子
公开(公告)号：US20150197334A1
公开(公告)日：2015-07-16
申请号：US14595547
申请日：2015-01-13
申请人： AIRBUS HELICOPTERS DEUTSCHLAND GMBH
发明人： Rupert PFALLER
IPC分类号： B64C27/33 , B64C27/48
CPC分类号： B64C27/33 , B64C27/48
摘要： A flexbeam unit comprising a plurality of flexbeam elements, each defining a load passing member that is attachable to a rotor hub associated with a rotor shaft of said multi-blade rotor, said plurality of flexbeam elements defining a predetermined number of torsion elements that are connectable with associated rotor blades of said multi-blade rotor, wherein at least one of the predetermined number of torsion elements comprises at least one first flexbeam element defining a first longitudinal direction and at least one second flexbeam element defining a second longitudinal direction, wherein said at least one first and second flexbeam elements are interconnected by a beam connector in a direction transverse to said first and/or second longitudinal directions.
摘要翻译：柔性梁单元，其包括多个柔性梁元件，每个柔性梁单元限定可连接到与所述多叶片转子的转子轴相关联的转子毂的载荷通过构件，所述多个挠性梁元件限定可连接的预定数量的扭转元件与所述多叶片转子的相关联的转子叶片，其中所述预定数量的扭转元件中的至少一个包括限定第一纵向方向的至少一个第一柔性梁元件和限定第二纵向方向的至少一个第二弹性梁元件，其中，至少一个第一和第二柔性元件通过横梁与横向于所述第一和/或第二纵向方向的梁连接器相互连接。

59. 发明申请

US20150158584A1 ROTARY WING AIRCRAFT WITH A TAIL SHROUD 有权
标题翻译：旋转翼飞机与尾巴
公开(公告)号：US20150158584A1
公开(公告)日：2015-06-11
申请号：US14563054
申请日：2014-12-08
申请人： AIRBUS HELICOPTERS DEUTSCHLAND GMBH
发明人： Sebastian MORES , Alessandro D'ALASCIO , Rainer GRODAU , Qinyin ZHANG , Christian WEHLE , Stefan PROBST
IPC分类号： B64C27/82 , B64C27/06
CPC分类号： B64C27/82 , B64C2027/8254 , B64C2027/8272
摘要： A rotary wing aircraft with a tail rotor in a rotor duct of a shroud. A bumper projects from a lower transition region of said shroud, said lower transition region having a left hand and a right hand lower transition edge between respectively the left hand and the right hand annular surface around the rotor duct and the bumper. Upper leading edges of a vertical fin and of said shroud are provided with left hand and right hand trailing edges. A projection of the upper transition edge to an upright longitudinal plane is defined by a spline curve through points Pi (i=1 . . . 5) and a projection of the lower transition edge to the plane is defined by a spline curve through points Pi (i=6 . . . 10) defined by their respective coordinates (xi, zi) relative to a centre of the shrouded tail rotor.
摘要翻译：一种旋翼式飞机，其尾翼具有护罩的转子导管。保险杠从所述护罩的下过渡区域突出，所述下过渡区域分别在转子管道和保险杠周围的左手和右手环形表面之间具有左手和右手下过渡边缘。垂直翅片和所述护罩的上前缘设置有左手和右手后缘。上过渡边缘到垂直纵向平面的投影由通过点Pi（i = 1.5）的样条曲线定义，并且下过渡边缘到平面的投影由通过点Pi的样条曲线定义（i = 6·10）相对于被覆盖的尾部转子的中心各自的坐标（xi，zi）定义。

60. 发明申请

US20150158582A1 BEAM FOR A ROTORCRAFT ROTOR AND ROTORCRAFT ROTOR 审中-公开
标题翻译：转子转子和转子转子的梁
公开(公告)号：US20150158582A1
公开(公告)日：2015-06-11
申请号：US14557995
申请日：2014-12-02
申请人： AIRBUS HELICOPTERS DEUTSCHLAND GMBH
发明人： Moritz BUESING
IPC分类号： B64C27/33
CPC分类号： B64C27/33 , B64C27/35
摘要： A beam for a rotorcraft rotor and particularly to a helicopter rotor. Said beam comprises a hub connection portion, a blade connection portion, a first flexure portion located between the hub connection portion and the blade connection portion and having a bending stiffness about a first axis which is orthogonal to the longitudinal axis of the blade, said bending stiffness being smaller than that of the hub connection portion and that of the blade connection portion and a shear portion located between the hub connection portion and the blade connection portion and having a shear stiffness parallel to a second axis which is orthogonal to the longitudinal axis of the blade and non-parallel to the first axis. Said shear stiffness is smaller than that of the hub connection portion and that of the blade connection portion.
摘要翻译：用于旋翼航空器转子的梁，特别是直升机转子。所述梁包括轮毂连接部分，叶片连接部分，位于轮毂连接部分和叶片连接部分之间的第一弯曲部分，并且具有围绕与叶片的纵向轴线正交的第一轴线的弯曲刚度，所述弯曲刚度小于轮毂连接部分的刚度，以及叶片连接部分的刚度和位于轮毂连接部分和叶片连接部分之间的剪切部分，并且具有平行于第二轴线的剪切刚度，该第二轴线垂直于纵向轴线叶片并且不平行于第一轴。所述剪切刚度小于轮毂连接部分和叶片连接部分的剪切刚度。

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