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1. 发明申请

WO99047417A1 ROTOR BLADE, IN PARTICULAR FOR HELICOPTER ANTITORQUE TAIL ROTOR 审中-公开
标题翻译：转子叶片，特别适用于直升机反导尾轮转子
公开(公告)号：WO99047417A1
公开(公告)日：1999-09-23
申请号：PCT/FR1999/000581
申请日：1999-03-16
IPC分类号： B64C27/82 , B64C27/35 , B64C27/45 , B64C27/48
CPC分类号： B64C27/48 , B64C27/35 , B64C27/45
摘要： The invention concerns a rotor blade, in particular for helicopter antitorque tail rotor, comprising: a blade shank (3) mounted rotating in said rotor hub (4E), to enable said blade to rotate about its step axis (P-P); and means for fixing said rotor shank (3) to said rotor hub, including a member capable of elastic twist deformation about said step axis. The invention is characterised in that: said blade shank (3) is hollow and open at its inner end so as to comprise an internal recess (12); said member capable of elastic twist deformation consists of an elastic stop (15) housed inside said blade shank internal recess (12) and capable of functioning like a spherical mounting with limited action, centred on said step axis; and a rigid tie rod (6) connects said elastic stop to said rotor hub (4C).
摘要翻译：本发明涉及一种转子叶片，特别是用于直升机反尾翼尾转子，包括：叶片柄（3），其安装在所述转子轮毂（4E）中旋转，以使所述叶片绕其台阶轴线（P-P）旋转; 以及用于将所述转子柄（3）固定到所述转子轮毂的装置，包括能够围绕所述台阶轴线弹性扭转变形的构件。本发明的特征在于：所述叶片柄（3）在其内端是中空的并且是开口的，以便包括一个内凹槽（12）; 所述能够弹性扭曲变形的构件由容纳在所述叶片柄内部凹部（12）内部的弹性止挡（15）组成，并且能够以有限的作用以与所述台阶轴为中心的球面安装起作用; 并且刚性连杆（6）将所述弹性止挡件连接到所述转子毂（4C）。

2. 发明申请

WO1993002916A1 DUCTED FAN AND PITCH CONTROLS FOR TAIL ROTOR OF ROTARY WING AIRCRAFT 审中-公开
标题翻译：旋转式飞机尾部转子的风扇和调节控制
公开(公告)号：WO1993002916A1
公开(公告)日：1993-02-18
申请号：PCT/US1992006441
申请日：1992-07-31
申请人： THE BOEING COMPANY
发明人： THE BOEING COMPANY , DESJARDINS, Rene, A. , McCARDLE, Francis, H.
IPC分类号： B64C27/45
CPC分类号： B64C27/82 , B64C27/45 , B64C2027/8254
摘要： A tail rotor (8) for a rotary wing aircraft is located in a laterally directed duct (9) located at the end of a tail cone (7) extending rearward from the aircraft cabin and at the base of an empennage (5) extending upward from the duct. The rotor includes a rotor shaft (50) driveably connected to a power source, a rotor hub (10) connected to the rotor shaft (50), a rotating control shaft (64), a stationary control shaft (124), and an actuator (132) connected to the stationary control shaft (124) for moving the rotating control shaft (64) axially. The rotor hub (10) includes rotor arms (12) each supporting a pitch shaft-blade spar (18, 16) assembly for pivotable movement about a pitch axis. A pitch beam (96) supports flexures (94), each connected to a pitch arm (80) offset laterally from the associated pitch axis. The flexures (94) driveably connect the pitch arms (80) to the pitch beam (96) and transmit pitch control motion to the blades (14) as the pitch beam (96) moves along the rotor axis. Pitch bearings (20, 22), on which the pitch shafts (18) turn about the pitch axes, are supported on a rotor hub shell (46) fixed to the rotor hub (10).
摘要翻译：用于旋转翼飞行器的尾部转子（8）位于位于从飞机机舱向后延伸并在向上延伸的尾翼（5）的底部的尾锥体（7）的端部处的横向定向的管道（9）从管道。转子包括可驱动地连接到电源的转子轴（50），连接到转子轴（50）的转子轮毂（10），旋转控制轴（64），静止控制轴（124）和致动器（132），其连接到用于使旋转控制轴（64）轴向移动的固定控制轴（124）。转子轮毂（10）包括转子臂（12），每个转子臂支撑俯仰轴叶片翼梁（18,16）组件，用于围绕俯仰轴线的可枢转运动。俯仰梁（96）支撑弯曲部（94），每个弯曲部（94）均连接到从关联的俯仰轴线侧向偏移的俯仰臂（80）。当俯仰梁（96）沿着转子轴线移动时，挠曲件94可驱动地将俯仰臂（80）连接到俯仰梁（96）并将桨距控制运动传递到叶片（14）。俯仰轴（18）围绕俯仰轴转动的俯仰轴承（20,22）支撑在固定在转子毂（10）上的转子轮毂壳（46）上。

3. 发明申请

WO1996029243A1 HUB FOR ROTARY WING AIRCRAFT 审中-公开
标题翻译： HUB FOR旋转式飞机
公开(公告)号：WO1996029243A1
公开(公告)日：1996-09-26
申请号：PCT/US1996003479
申请日：1996-03-14
申请人： THE BOEING COMPANY
发明人： THE BOEING COMPANY , MCARDLE, Francis, H.
IPC分类号： B64C27/45
CPC分类号： B64C27/45
摘要： A rotor hub for a rotary wing aircraft is described which allows the use of more than three blades on the rotor head while providing all of the required functional features. The rotor head is constructed using a central barrel (2) to which is attached a plurality of blade attachment points on its exterior surface. The pitch arm (14) actuating points (24) are located inside of the hub barrel (2) extending from the outer surface into the hub barrel (2) through arcuate slots (30) in the barrel (2). The hub is particularly adapted for use with tilt rotor rotary wing aircraft and provides a negative Delta 3 blade pitch input in response to wind gusts and abrupt pilot control inputs.
摘要翻译：描述了一种用于旋转飞行器的转子轮毂，其允许在转子头上使用三个以上的叶片，同时提供所有所需的功能特征。转子头部使用中心筒（2）构造，在其外表面上附接有多个叶片附接点。俯仰臂（14）致动点（24）位于通过枪管（2）中的弓形槽（30）从轮毂筒（2）的内表面延伸到轮毂筒（2）内。轮毂特别适用于倾斜转子旋翼飞机，并响应于阵风和突发的先导控制输入提供负三角叶片桨距输入。

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