-
公开(公告)号：US4797064A
公开(公告)日：1989-01-10
申请号：US80370
申请日：1987-07-30
CPC分类号： B64C27/32
摘要： A fiber reinforced braided composite main helicopter rotor hub retention plate whose fiber orientation withstands forces both in the plane of the retention plate and normal to the plane. The retention plate comprises a fiber reinforced resin braided tubular ring having substantially circumferential fibers interwoven with angled fibers disposed about a central core. Arms extend inward from the braided ring for attachment to a driveshaft.
-
2.发明授权Tension/compression rod arrangement for damping helicopter rotor blade oscillations 失效用于阻尼直升机转子叶片振动的张力/压缩杆布置
公开(公告)号：US4645423A
公开(公告)日：1987-02-24
申请号：US760232
申请日：1985-07-29
申请人： Donald L. Ferris , David G. Matuska
发明人： Donald L. Ferris , David G. Matuska
CPC分类号： B64C27/51
摘要： Apparatus for damping blade lead/lag motion on a hingeless helicopter rotor assembly, including a hub, blades and flexbeam(s) interposed between the root end of the blades and the hub. Rigid, radial links extend the length of the flexbeams for attachment to the outboard ends thereof. Lead/lag motion at the outboard end of the flexbeam causes flexbeam bending, which is converted to radial translation of the links. This radial translation of the links and likewise the blade lead/lag motion is damped by damper means connected between the inboard ends of the links and the hub.
摘要翻译： 用于在无铰链直升机转子组件上阻尼叶片引导/滞后运动的装置，包括插入在叶片的根端和轮毂之间的轮毂，叶片和挠性束。 刚性的径向连接件延伸柔性梁的长度以附接到其外侧端部。 在柔性梁的外侧的引导/延迟运动导致弯曲弯曲，其被转换成链节的径向平移。 连杆的径向平移以及叶片的前进/后退运动被连接在连杆的内侧端和轮毂之间的阻尼装置阻尼。
-
公开(公告)号：US4569629A
公开(公告)日：1986-02-11
申请号：US655384
申请日：1984-09-27
摘要： Hub moment and driving torque is provided for a helicopter gimbal rotor by two-part flat springs that are in-plane with the rotor tilt point (P). The inboard end of an outward part of each spring is connected to the rotorshaft and the inboard end of an inward part of the spring is connected to the tiltable hub member. The outboard ends of the two spring parts are journaled together by an eccentric elastomeric joint that allows for spring foreshortening that accompanies rotor tilt.
摘要翻译： 通过与转子倾斜点（P）处于平面的两部分平面弹簧为直升机万向转子提供轮毂力矩和驱动扭矩。 每个弹簧的向外部分的内侧端部连接到转轴，并且弹簧的向内部分的内侧端部连接到可倾斜的毂部件上。 两个弹簧部件的外侧端部通过一个偏心的弹性接头连在一起，该弹性接头允许伴随转子倾斜的弹簧缩短。
-
公开(公告)号：US4368006A
公开(公告)日：1983-01-11
申请号：US176151
申请日：1980-08-07
CPC分类号： B64C27/322
摘要： An improved droop stop for a fully articulated helicopter rotor is providedherein curved mating surfaces are employed between the spindle pad and the centrifugal droop stop static support arm to provide surface rather than line contact therebetween during centrifugal operation. The centers of the curved surfaces are coincident at the pivot point of the droop stop centrifugal arm to force the downward load of the blade to pass through this pivot point.
摘要翻译： 提供了一种用于完全铰接的直升机转子的改进的下垂停止件，其中在主轴垫和离心下垂停止静力支撑臂之间采用弯曲配合表面，以在离心操作期间提供表面而不是线间接触。 弯曲表面的中心在下垂停止离心臂的枢转点处重合，以迫使叶片的向下的载荷通过该枢转点。
-
公开(公告)号：USRE30713E
公开(公告)日：1981-08-18
申请号：US62851
申请日：1979-08-01
IPC分类号： B64C27/33
CPC分类号： B64C27/33
摘要： A helicopter rotor having opposed blades interconnected by a common flexible spar which passes across the rotor axis is connected to the drive shaft by clamped hub plates. A spanwise extending torque tube having a pitch horn at its inner end forms a rigid connection with the spar and blade at its outboard end. A centering bearing assembly is positioned at the inner end of the torque tube and spar to react control loads, centralize the torque tube about the spar, and provide pitch, flap, and lead-lag decoupling.
-
公开(公告)号：US4284387A
公开(公告)日：1981-08-18
申请号：US35364
申请日：1979-05-02
申请人： Donald L. Ferris
发明人： Donald L. Ferris
CPC分类号： B64C27/50
摘要： In a fully articulated helicopter rotor head, utilizing an elastomeric bearing to support each rotor blade and react centrifugal flight loads, a blade restraint, effective in three axes is provided for use during blade folding for aircraft stowage purposes. The restraint allows the blade to be folded through a predetermined fold plane, and held there while preventing or minimizing deflection of the elastomeric bearing.
摘要翻译： 在完全铰接的直升机转子头中，利用弹性轴承来支撑每个转子叶片并且反应离心飞行载荷，提供了有效的三个轴线的叶片约束装置，用于在用于飞行器装载目的的叶片折叠期间使用。 约束允许刀片折叠通过预定的折叠平面，并且在防止或最小化弹性轴承的偏转的同时保持在那里。
-
公开(公告)号：US4244677A
公开(公告)日：1981-01-13
申请号：US924110
申请日：1978-07-12
CPC分类号： B64C27/33
摘要： A cross-beam helicopter rotor in which the torque tube enveloping the flexible spar is supported in relation thereto by an elastomeric primary snubber which is readily replaceable in the field and which utilizes a snubber retainer plate bonded to the spar with an elastomer layer of selected shape factor so that the retainer plate remains adhered to the spar while accommodating all blade and spar pitch and flapping motions and so that the retainer plate elastomer layer is substantially more durable than the elastomer layers of the primary snubber. This primary snubber may be used in combination with an auxiliary snubber.
摘要翻译： 横梁直升机转子，其中包围柔性翼梁的扭矩管通过弹性初级缓冲器相对于其支撑，该弹性主缓冲器可在现场容易地更换，并且利用与所述翼梁结合的缓冲器保持板，其中弹性体层具有选定形状 因此保持板保持粘附到翼梁上，同时容纳所有的叶片和翼梁间距和振动运动，并且使得保持板弹性体层比主缓冲器的弹性体层基本上更耐用。 该主缓冲器可以与辅助缓冲器组合使用。
-
8.发明授权Adjustable bearing centering means for helicopter rotor elastomeric bearings 失效用于直升机转子弹性轴承的可调轴承定心装置
公开(公告)号：US4242047A
公开(公告)日：1980-12-30
申请号：US35365
申请日：1979-05-02
申请人： Donald L. Ferris , Peter C. Ogle
发明人： Donald L. Ferris , Peter C. Ogle
CPC分类号： B64C27/322 , B64C27/35
摘要： Apparatus to center and compressively load a spherical elastomeric bearing about its static apex during helicopter rotor static mode, which centering means is adjustable from a station external of the rotor and is operable to be out of contact during helicopter rotor dynamic mode.
摘要翻译： 在直升机转子静止模式期间将球形弹性轴承围绕其静态顶点中心并压缩加载的装置，其中心装置可从转子外部的台架调节，并可在直升机转子动态模式期间脱离接触。
-
9.发明授权Helicopter rotor having lead-lag damper operable with pitch and flap decoupling 失效直升机转子具有可调节俯仰和翼片解耦功能的前置滞后阻尼器
公开(公告)号：US4178130A
公开(公告)日：1979-12-11
申请号：US849064
申请日：1977-11-07
CPC分类号： B64C27/51
摘要： A helicopter rotor having at least one blade projecting from the central hub and mounted for pitch change, flapping and lead-lag motion and including a lead-lag damper mounted to be pivotally movable in a selected plane and connected to the blade through a pivotal link connection to avoid the adverse effects of pitch and flap coupling.
摘要翻译： 一种直升机转子，其具有至少一个叶片，其从中心轮毂突出并安装成用于俯仰变化，拍打和超前延迟运动，并且包括安装成可在选定平面中枢转运动并且通过枢转连杆 连接以避免俯仰和翼片耦合的不利影响。
-
公开(公告)号：US4174137A
公开(公告)日：1979-11-13
申请号：US927704
申请日：1978-07-24
申请人： Donald L. Ferris
发明人： Donald L. Ferris
CPC分类号： B64C13/30 , F16C11/0614 , F16C7/02 , Y10T29/49696
摘要： A stop device limits rods, such as control rods, used in helicopter flight control systems, from roll-over in selected directions, while allowing substantially unrestricted motion in other directions.
摘要翻译： 停止装置限制在直升机飞行控制系统中使用的杆，例如用于选定方向的翻转的杆，同时允许在其他方向上基本上无限制的运动。
-
-
-
-
-
-
-
-
-
搜索结果
24 条记录 (耗时 0.016 秒)
