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公开(公告)号：US4668169A
公开(公告)日：1987-05-26
申请号：US622275
申请日：1984-06-19
申请人： Frederick J. Perry
发明人： Frederick J. Perry
IPC分类号： B64C27/46
CPC分类号： B64C27/46
摘要： An outboard region of a helicopter rotor blade of aerofoil cross section has a thickness to chord ratio not greater than twelve percent and an inboard region has a thickness to chord ratio greater than twelve percent. Preferably, the thickness to chord ratio of the inboard region is greater than eighteen percent and may increase towards the root end to about twenty four percent. The inboard region may extend outwardly to a position not exceeding sixty percent of an operating radius of the rotor blade.
摘要翻译： 机翼横截面的直升机转子叶片的外侧区域具有不大于12％的厚度和弦比，并且内侧区域的厚度与弦比大于12％。 优选地，内侧区域的厚度与弦比大于十八％，并且可以朝向根端增加到大约百分之二十四。 内侧区域可以向外延伸到不超过转子叶片的操作半径的百分之六十的位置。
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公开(公告)号：US4615413A
公开(公告)日：1986-10-07
申请号：US603412
申请日：1984-04-24
CPC分类号： F16H57/0456 , F01M11/10 , F16N29/00 , F16H57/0404
摘要： A recirculating lubricating system includes a monitor filter unit (16) between a pump (13) and a main filter element (17). The monitor filter unit (16) includes diverting means (23, 31) to ensure that a proportion of the oil flowing between the pump and the main filter element is diverted through a removable monitor filter element (28).
摘要翻译： 循环润滑系统包括在泵（13）和主过滤元件（17）之间的监测过滤器单元（16）。 监视器过滤器单元（16）包括转向装置（23,31），以确保在泵和主过滤器元件之间流动的一部分油被转移通过可移除的监视器过滤元件（28）。
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公开(公告)号：US4466775A
公开(公告)日：1984-08-21
申请号：US440285
申请日：1982-11-09
申请人： Alfred C. Martin
发明人： Alfred C. Martin
CPC分类号： B64C27/50
摘要： A helicopter rotor having a rotor hub and a plurality of rotor blades includes for each blade a blade fold mechanism comprising a reversible rotary power source and a rack and pinion mechanism adapted to operate one or more lock pins and to fold the blades between an operational spread position and a folded position. Two embodiments of the invention are described and illustrated.
摘要翻译： 具有转子轮毂和多个转子叶片的直升机转子包括用于每个叶片的叶片折叠机构，其包括可逆旋转动力源和齿条和小齿轮机构，其适于操作一个或多个锁定销并且在操作扩展 位置和折叠位置。 描述和说明本发明的两个实施例。
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公开(公告)号：US4447023A
公开(公告)日：1984-05-08
申请号：US367960
申请日：1982-04-13
申请人： Peter Reid
发明人： Peter Reid
CPC分类号： B64C27/00
摘要： A helicopter (10) incorporates apparatus (15) for mounting a device such as an aerial or a sight (14) above a main sustaining rotor (13). The apparatus comprises first and second ring gears (16, 20) located respectively below and above the rotor, the first gear (16) being supported from helicopter structure (17) concentrically of an axis of rotation (11) of the sustaining rotor, support means (37) supporting the second gear and the device above the rotor in a manner permitting relative rotation of the rotor hub, and synchronizing means (25) rotationally fixed to the rotor hub and meshing with the first and second gears to retain the device stationary during rotation of the rotor system. In a preferred embodiment, positioning means are provided to rotate the first gear in either direction of rotation whereby the device can be rotated and selectively positioned independently of the rotation of the rotor.
摘要翻译： 直升机（10）包括用于在主维持转子（13）上方安装诸如天线或视线（14）的装置的装置（15）。 该装置包括分别位于转子下方和上方的第一和第二环形齿轮（16,20），第一齿轮（16）由维持转子的旋转轴线（11）同心的直升机结构（17）支撑，支撑 以允许所述转子轮毂相对旋转的方式支撑所述第二齿轮和所述转子上方的装置的装置（37），以及旋转地固定到所述转子轮毂并与所述第一和第二齿轮啮合的同步装置（25），以将所述装置固定 在转子系统旋转期间。 在优选实施例中，提供定位装置以在任一旋转方向上旋转第一齿轮，由此可以独立于转子的旋转而旋转和选择性地定位装置。
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公开(公告)号：US5050477A
公开(公告)日：1991-09-24
申请号：US742079
申请日：1985-03-19
申请人： Roy L. Cowdery , James W. Schofield
发明人： Roy L. Cowdery , James W. Schofield
IPC分类号： B64D7/08
CPC分类号： B64D7/08
摘要： A helicopter includes missile storage means (29) adapted to store a plurality of missiles (26) laterally within a fuselage (28) and missile launcher means (40) located at the end of a lateral outrigger (27) for pivotal movement about a generally vertical axis (42) between a loading position generally laterally of the fuselage and a launch position generally parallel with a longitudinal centreline of the fuselage. In the illustrated embodiment, the launcher means comprises an elongated support beam (45) for selective engagement by a longitudinally extending tubular member (32) attached to each missile and includes transfer means (51, 52, 60, 61) for transferring a missile between the storage means and the launcher means when the latter is in said loading position.
摘要翻译： 直升机包括适于在机身（28）内横向存储多个导弹（26）的导弹存储装置（29）和位于外部支腿（27）的端部处的导弹发射装置（40），用于围绕一般的 在机身的大致横向的加载位置与大致平行于机身的纵向中心线的发射位置之间的垂直轴线（42）。 在所示实施例中，发射器装置包括细长的支撑梁（45），用于通过附接到每个导弹的纵向延伸的管状构件（32）进行选择性接合，并且包括用于在两个导弹之间传送导弹的传送装置（51,52,60,61） 当后者处于所述装载位置时，存储装置和发射器装置。
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公开(公告)号：US4819182A
公开(公告)日：1989-04-04
申请号：US10699
申请日：1987-02-04
CPC分类号： B64C27/001 , F16F7/10 , B64C2027/002
摘要： This invention relates to a method and apparatus for reducing vibration of a helicopter fuselage. The apparatus comprises a plurality of actuators interconnecting parts of the helicopter structure capable of relative motion at an exciting frequency, means to continuously oscillate the actuators at a frequency corresponding to the exciting frequency, a plurality of accelerometers attached to the fuselage for generating signals representative of fuselage dynamic accelerations, and processing means for processing said signals and providing output signals for controlling the phase and magnitude of operation of the actuators. In a described embodiment, one of the relatively movable parts comprises a raft structure carrying the gearbox and engines and attached to the fuselage by a resilient attachment adjacent each of its four corners.
摘要翻译： 本发明涉及减轻直升机机身振动的方法和装置。 该装置包括使能够以激励频率相对运动的直升机结构的部分相互连接的多个致动器，用于以对应于激励频率的频率连续振荡致动器的装置，附接到机身的多个加速度计，用于产生代表 机身动态加速和用于处理所述信号并提供用于控制致动器的操作的相位和幅度的输出信号的处理装置。 在所描述的实施例中，相对可动部件中的一个包括承载齿轮箱和发动机的筏结构，并且通过邻近其四个角中的每一个的弹性附件而附接到机身。
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公开(公告)号：US4785710A
公开(公告)日：1988-11-22
申请号：US887532
申请日：1986-07-21
申请人： James W. Schofield
发明人： James W. Schofield
摘要： A helicopter (10) has a fuselage (11) provided with storage means (19, 20, 24) for storing a plurality of missiles (16) longitudinally of the fuselage, reloadable turret means (17) beneath the fuselage for movement in azimuth and elevation and transfer means (20b, 21) for transferring a missile from the storage means to the turret means. In the illustrated embodiment the missiles are stored externally of generally vertical side walls (13) and a lower generally horizontal wall (14) of the fuselage and fairings (39) are provided to protect the externally mounted missiles.
摘要翻译： 直升机（10）具有机身（11），其具有存储装置（19,20,24），用于在机身的纵向上存储多个导弹（16），机身下方的可重新加载的转塔装置（17）用于在方位角上移动， 用于将导弹从存储装置传送到转台装置的高度和转移装置（20b，21）。 在所示实施例中，导弹存储在大体上垂直的侧壁（13）的外部，机身和整流罩（39）的下部大致水平的壁（14）被设置以保护外部安装的导弹。
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公开(公告)号：US4549850A
公开(公告)日：1985-10-29
申请号：US633420
申请日：1984-07-23
申请人： Alan H. Vincent
发明人： Alan H. Vincent
CPC分类号： B64C27/51
摘要： A bearingless helicopter rotor includes an integral damper and pitch change assembly (16) adapted to damp lead/lag movements of a rotor blade and to change the pitch of the rotor blade. In described embodiments, the assembly includes a generally tubular body portion (17, 27) closed at one end and attached by torque transmitting means (18, 28) to a flexure member blade attachment and a rod (20, 29) protruding axially from the other end of the body portion and attached adjacent the rotor hub. Pitch change movements are effected by rotation of the body portion about its longitudinal axis and damping of lead/lag movements either by metering of an incompressible medium across a piston (23) in a chamber (24) formed internally of the body portion or by an annular body of elastomer material (34) bonded to the outside diameter of the rod and the inside diameter of the body portion.
摘要翻译： 无轴承的直升机转子包括适于阻止转子叶片的引导/滞后运动并改变转子叶片间距的整体式阻尼器和变桨组件（16）。 在所描述的实施例中，组件包括在一端封闭并通过扭矩传递装置（18,28）附接到挠曲构件刀片附件的大致管状主体部分（17,27）和从所述弹性构件刀片附件轴向突出的杆（20,29） 主体部分的另一端并且邻近转子毂安装。 间距变化运动通过主体部分围绕其纵向轴线的旋转和通过在形成在主体部分内部的腔室（24）内的活塞（23）上计量不可压缩介质来阻止引线/滞后运动来实现， 结合到杆的外径和主体部分的内径的弹性体材料（34）的环形体。
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公开(公告)号：US4507341A
公开(公告)日：1985-03-26
申请号：US581191
申请日：1984-02-17
申请人： Mark J. Heseltine
发明人： Mark J. Heseltine
CPC分类号： H01Q9/38 , H01B1/24 , H01Q1/48 , Y10T428/24074 , Y10T428/24099 , Y10T428/24124 , Y10T428/24826 , Y10T428/249945 , Y10T428/30 , Y10T428/31678
摘要： A portion of the surface area of a resin bonded structure comprises an exposed dimpled electrically conductive metal shim bonded to the structure to provide a low electrical impedance connection for mounting a device such as a radio antenna. Preferably, a ply of unidirectional carbon fibres coated with an electrically conductive material such as a uniform and concentric coating of electroplated nickel is located between the shim and the outer carbon fibre layer of the structure with the fibre orientation of the ply of coated carbon fibres at 90 degrees to the carbon fibre layer. The invention also extends to a method of providing a low electrical impedance connection on to a pre-cured resin bonded carbon fibre structure and to a method of attaching a radio antenna on to such a structure.
摘要翻译： 树脂接合结构的表面积的一部分包括接合到该结构的暴露的凹坑导电金属垫片，以提供用于安装诸如无线电天线的装置的低电阻抗连接。 优选地，涂覆有诸如电镀镍的均匀和同心的涂层的导电材料的单向碳纤维层位于结构的垫片和外碳纤维层之间，其中涂覆的碳纤维的帘布层的纤维取向在 90度到碳纤维层。 本发明还延伸到对预固化树脂粘合碳纤维结构提供低电阻抗连接的方法以及将无线电天线附接到这种结构的方法。
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公开(公告)号：US4484491A
公开(公告)日：1984-11-27
申请号：US388637
申请日：1982-06-15
申请人： Harry Cocking
发明人： Harry Cocking
CPC分类号： F16H57/038 , B64C27/14 , F16H2057/02056 , F16H2057/02091 , Y10T74/19014 , Y10T74/19051 , Y10T74/19628 , Y10T74/19991 , Y10T74/2186
摘要： A helicopter transmission system includes a gearbox comprising a gearcase (11) having a hollow stub axle (12) by which operational loads are transmitted from a main sustaining rotor to a fuselage structure. One or more input speed reducing gear trains (20, 21, 22, 23) are individually supported in hollow lobe portion(s) (14) supported from the axle (12), the or each lobe portion having an individual lubricating oil sump (18) and circulating means (31) adapted to circulate lubricating oil to the respective gear trains. Preferably, interconnecting means (33) are provided to connect the respective individual sumps, and valve means (32, 35) are adapted to maintain a flow of lubricating oil in the event of a loss of oil from one of the sumps.
摘要翻译： 直升机传动系统包括齿轮箱，齿轮箱包括具有中空短轴（12）的齿轮箱（11），通过该齿轮箱将操作负载从主维持转子传递到机身结构。 一个或多个输入减速齿轮系（20,21,22,23）被单独地支撑在从轴（12）支撑的中空凸缘部分（14）中，所述或每个凸起部分具有单独的润滑油槽（ 18）和适于将润滑油循环到相应齿轮系的循环装置（31）。 优选地，提供互连装置（33）以连接相应的单独的水槽，并且阀装置（32,35）适于在从一个水池损失油的情况下维持润滑油的流动。
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