公开(公告)号：US20100072325A1

公开(公告)日：2010-03-25

申请号：US12356585

申请日：2009-01-21

申请人： Kenneth William Sambell

发明人： Kenneth William Sambell

IPC分类号： B64C27/22 ,  B64C29/00

CPC分类号： B64C29/0033 ,  B64C11/28 ,  B64C27/50

摘要： This is an improvement of the 1968 Trailing Rotor V/STOL aircraft (Ref. 1). Rotors are mounted on wing-tip pods which can be tilted from the vertical to the horizontal aft position. Rotors are then stopped in the axial-flow condition and indexed to an azimuth position, aft of the wing trailing-edge. Rotor blades are then folded forward (blade-tips upstream of rotor-hubs) and locked into grooves in the tip-pods.The main improvements over Ref. 1 are: a smaller shift of center-of-gravity during transition to cruise mode, and an easier task of locking blades into the tip-pods.The main feature of the autorotative aft rotor tilt is that a soft-inplane rotor can be used, which reduces rotor weight. The blade-folding axis is also the blade-flapping axis.The autorotative mode is used frequently by helicopters during descent. It has been found to be a good, stable mode with rpm-stability. During aft tilt on the UFR, the rotors provide pitching stability to the airframe. During stopping of the rotor, the stability of the autorotating rotor eases the task of passing thru rotor resonance.Also, the wing can be swept back, which is desirable for 400 kt. cruise speeds and can be used for external stores such as fuel and weapons.

摘要翻译： 这是1968年后退转子V / STOL飞机的改进（参考文献1）。 转子安装在翼尖荚上，可从垂直方向倾斜到水平后方。 然后转子在轴向流动状态下停止并且被转位到方位角位置，后翼的后缘。 然后将转子叶片向前折叠（转子轮毂上游的叶片尖端）并锁定在尖端荚中的凹槽中。 参考文献的主要改进。 1是：在过渡到巡航模式期间重心的移动较小，并且更容易将叶片锁定到尖端荚中。 自转式后转子倾斜的主要特征是可以使用软平面转子，这降低了转子的重量。 叶片折叠轴线也是叶片拍动轴。 直升机在下降期间经常使用自动模式。 已经发现这是一个良好的稳定的转速稳定模式。 在UFR的后倾倾斜时，转子为机身提供俯仰稳定性。 在转子停转期间，自转转子的稳定性减轻了通过转子共振的任务。 此外，机翼可以扫过，这对于400 kt是理想的。 巡航速度，可用于外部商店，如燃料和武器。

公开(公告)号：US07207519B2

公开(公告)日：2007-04-24

申请号：US11071504

申请日：2005-03-03

申请人： Peter Hoynash

发明人： Peter Hoynash

IPC分类号： B64C27/00 ,  F16M13/00 ,  E04G3/00 ,  A47F5/00

CPC分类号： B64C27/50 ,  B64C3/56

摘要： A blade restraint system for restraining a blade of a helicopter comprising a blade clamp releasably mounted to the blade and a pole pair releasably mountable to the blade clamp at a clamp end. The pole pair is releasably mountable to the helicopter fuselage at an aircraft. The pole pair includes a first pole and second pole. The first and second poles are moveable relative to each other between a storage position and an extended position. The first pole is positioned generally within the second pole in the storage position.

摘要翻译： 一种用于限制直升机的叶片的叶片约束系统，包括可拆卸地安装到叶片上的叶片夹，以及在夹具端可释放地安装到叶片夹的杆对。 杆对可拆卸地安装在飞机上的直升机机身上。 极对包括第一极和第二极。 第一和第二极可以在存储位置和延伸位置之间相对于彼此移动。 第一极通常位于存储位置的第二极内。

公开(公告)号：US06860450B2

公开(公告)日：2005-03-01

申请号：US10329250

申请日：2002-12-23

申请人： Neal W. Muylaert ,  Angelo A. Scardullo ,  Conan A. Hansen ,  Aidan T. Foley

发明人： Neal W. Muylaert ,  Angelo A. Scardullo ,  Conan A. Hansen ,  Aidan T. Foley

IPC分类号： B64C27/50

CPC分类号： B64C27/50

摘要： A method comprises providing six helicopters. Each helicopter has a fuselage, a main rotor assembly extending out from the fuselage and rotatable about a main rotor axis, and four main rotor blades coupled to the main rotor assembly. The main rotor blades of each helicopter are moveable relative to the main rotor assembly between a deployed position and a stowed position. The deployed position is a position in which the four main rotor blades extend radially from the main rotor. The main rotor blades have a blade rotor diameter of at least forty seven feet when in the deployed position. The four main rotor blades are coupled to the main rotor assembly when in the stowed position. The method further comprises positioning the six helicopters relative to each other such that all six of the helicopters are simultaneously contained within a parallelepiped region having a height of less than fifteen feet, a width of less than twenty feet, and a length of less than one hundred forty five feet. The four main rotor blades of each of the six helicopters are in their stowed positions when the six helicopters are simultaneously contained within the parallelepiped region.

摘要翻译： 一种方法包括提供六架直升机。 每个直升机具有机身，主机转子组件，其从机身延伸并可围绕主转子轴线旋转，并且四个主转子叶片联接到主转子组件。 每个直升机的主转子叶片可相对于主转子组件在展开位置和收起位置之间移动。 展开位置是四个主转子叶片从主转子径向延伸的位置。 当处于展开位置时，主转子叶片具有至少四十七英尺的叶片转子直径。 当处于收起位置时，四个主转子叶片联接到主转子组件。 该方法还包括相对于彼此定位六架直升机，使得所有六架直升机同时容纳在具有小于十五英尺的高度，小于二十英尺的宽度和小于一个的长度的平行六面体区域中 一百四十五英尺。 当六架直升机同时包含在平行六面体区域内时，六架直升机中的每一架的四个主要转子叶片处于收起位置。

公开(公告)号：US20040118970A1

公开(公告)日：2004-06-24

申请号：US10329250

申请日：2002-12-23

发明人： Neal W. Muylaert ,  Angelo A. Scardullo ,  Conan A. Hansen ,  Aidan T. Foley

IPC分类号： B64C027/00

CPC分类号： B64C27/50

摘要： A method comprises providing six helicopters. Each helicopter has a fuselage, a main rotor assembly extending out from the fuselage and rotatable about a main rotor axis, and four main rotor blades coupled to the main rotor assembly. The main rotor blades of each helicopter are moveable relative to the main rotor assembly between a deployed position and a stowed position. The deployed position is a position in which the four main rotor blades extend radially from the main rotor. The main rotor blades have a blade rotor diameter of at least forty seven feet when in the deployed position. The four main rotor blades are coupled to the main rotor assembly when in the stowed position. The method further comprises positioning the six helicopters relative to each other such that all six of the helicopters are simultaneously contained within a parallelepiped region having a height of less than fifteen feet, a width of less than twenty feet, and a length of less than one hundred forty five feet. The four main rotor blades of each of the six helicopters are in their stowed positions when the six helicopters are simultaneously contained within the parallelepiped region.

摘要翻译： 一种方法包括提供六架直升机。 每个直升机具有机身，主机转子组件，其从机身延伸并可围绕主转子轴线旋转，并且四个主转子叶片联接到主转子组件。 每个直升机的主转子叶片可相对于主转子组件在展开位置和收起位置之间移动。 展开位置是四个主转子叶片从主转子径向延伸的位置。 当处于展开位置时，主转子叶片具有至少四十七英尺的叶片转子直径。 当处于收起位置时，四个主转子叶片联接到主转子组件。 该方法还包括相对于彼此定位六架直升机，使得所有六架直升机同时容纳在具有小于十五英尺的高度，小于二十英尺的宽度和小于一个的长度的平行六面体区域中 一百四十五英尺。 当六架直升机同时包含在平行六面体区域内时，六架直升机中的每一架的四个主要转子叶片处于收起位置。

公开(公告)号：US6050521A

公开(公告)日：2000-04-18

申请号：US124188

申请日：1998-07-28

申请人： Roberto Regonini

发明人： Roberto Regonini

IPC分类号： B64C1/30 ,  B64C27/04 ,  B64C27/12 ,  B64C27/82 ,  F16D3/18 ,  B64C27/00

CPC分类号： B64C27/50 ,  B64C1/063 ,  B64C1/30 ,  B64C27/12 ,  B64C27/04 ,  Y10S464/901

摘要： A releasable coupling for a power transmission line to a tail rotor of a foldable-tail-section helicopter, the coupling having a first and a second coupling assembly fitted respectively to the body and the tail of the helicopter, and which cooperate with each other when the tail is in the work position; the two coupling assemblies having respective transmission members in turn having respective radial toothings cooperating telescopically with each other, and respective conical male and female lead-in members which are brought into contact with each other prior to the respective toothings to guide connection of the transmission members; at least one of the transmission members being supported orientably.

摘要翻译： 用于到可折叠尾部直升机的尾部转子的输电线的可释放联接器，所述联接器具有分别安装在直升机的主体和尾部上的第一和第二联接组件，并且彼此协作 尾巴处于工作位置; 具有相应的传动部件的两个连接组件依次具有彼此可伸缩地配合的相应的径向齿，以及相应的锥形凸形和阴型引入部件，它们在相应的齿之间彼此接触以引导传动部件的连接 ; 所述传动构件中的至少一个被可取向地支撑。

公开(公告)号：US6047924A

公开(公告)日：2000-04-11

申请号：US953985

申请日：1997-10-20

申请人： Rene Thomassin ,  Jean Jacques Polveda ,  Albert Henri Bernard Gemmati

发明人： Rene Thomassin ,  Jean Jacques Polveda ,  Albert Henri Bernard Gemmati

IPC分类号： B64C27/50 ,  B64C3/56

CPC分类号： B64C27/50

摘要： Once the rotor of a rotary-wing aircraft is held stationary in an indicated position, the method comprises steps consisting in placing the collective pitch control stick in a first predefined position corresponding to a first inclination of the blades about their longitudinal axes, in placing the cyclic pitch control stick in a second predefined position corresponding to a nose-up position of the rotary-wing aircraft, in modifying the length of the control system to cause the inclination of the blades about their longitudinal axes to go to a second value that is different from said first inclination value, in holding a rotary swashplate stationary by placing at least three locking connection rods between the rotary swashplate and a member integral in terms of rotation with a rotor mast, and in folding the blades by rotating each of them about a corresponding coupling pin for coupling it to a coupling member for coupling the blade to a rotor hub.

摘要翻译： 一旦旋转翼飞行器的转子在指示位置保持静止，则该方法包括以下步骤：将集体俯仰控制杆放置在对应于叶片围绕其纵向轴线的第一倾斜度的第一预定位置， 循环桨距控制杆处于对应于旋转翼飞行器的上升位置的第二预定位置中，在改变控制系统的长度以使得叶片围绕其纵向轴线的倾斜度转到第二值，即， 与所述第一倾斜度值不同的是，通过将至少三个锁定连接杆放置在旋转斜盘和旋转角度与转子桅杆成一体的构件之间，将旋转斜盘固定在一起，并且通过使叶片围绕 相应的联接销，用于将其联接到用于将叶片联接到转子毂的联接构件。

公开(公告)号：US4786236A

公开(公告)日：1988-11-22

申请号：US107241

申请日：1987-10-09

申请人： Michael Hahn ,  Gerald Kuntze-Fechner

发明人： Michael Hahn ,  Gerald Kuntze-Fechner

IPC分类号： B64C27/50

CPC分类号： B64C27/50

摘要： A helicopter rotor with foldable blades has, in the hub and blade roots, holes for mounting the blade roots to the rotor hub with connecting bolts passing through these holes in the operating position of the blades. Additionally, at least one blade of two blades and the hub have aligned holes for holding the respective foldable blade in a folded position, whereby one of the regular connecting bolts passes through the aligned holes, which are located as close as possible to the pivoting point connecting a pitch angle control rod to a pitch angle control sleeve.

摘要翻译： 具有可折叠刀片的直升机转子在轮毂和叶片根部具有用于将叶片根部安装到转子毂上的孔，其中连接螺栓在叶片的操作位置通过这些孔。 另外，两个叶片的至少一个叶片和轮毂具有对准的孔，用于将相应的可折叠刀片保持在折叠位置，由此一个规则连接螺栓穿过对准的孔，其尽可能靠近枢转点 将俯仰角控制杆连接到俯仰角控制套筒。

公开(公告)号：US4623300A

公开(公告)日：1986-11-18

申请号：US777799

申请日：1985-09-19

申请人： Harry L. Ruzicka

发明人： Harry L. Ruzicka

IPC分类号： B64C27/50

CPC分类号： B64C27/50

摘要： Folded helicopter blades are secured against undesirable motion by a device that attaches to a receptacle in the underside of each blade. The device comprises a pin for engaging the receptacle, a spherical bearing disposed about the pin, an annular housing disposed about the bearing and including two diametrically opposed recesses therein, a primary strut attached at one end to the fuselage and at the other end to a clevis-type yoke, wherein the yoke ends are pivotally attached to the housing within the recesses, a secondary strut attached at one end to the fuselage and attached at the other end to the primary strut near the yoke. This arrangement forms a three bar linkage.

摘要翻译： 折叠的直升机叶片通过附接到每个叶片的下侧的容器的装置抵抗不期望的运动。 该装置包括用于接合容器的销，围绕销设置的球形轴承，围绕轴承设置的环形壳体，并且在其中包括两个直径相对的凹部，主支柱一端连接到机身，另一端附接到 U形夹式轭，其中轭架端部在凹槽内枢转地附接到壳体，辅助支柱在一端附接到机身并且在另一端附接到靠近轭架的主支柱。 这种布置形成三杆连杆。

公开(公告)号：US4354234A

公开(公告)日：1982-10-12

申请号：US195808

申请日：1980-10-10

申请人： Roderick A. MacLennan ,  William J. Mulvey

发明人： Roderick A. MacLennan ,  William J. Mulvey

IPC分类号： B64C27/50 ,  B64C27/54 ,  G06F15/20

CPC分类号： B64C27/54 ,  B64C27/50

摘要： The foldable rotor blades (12) of a helicopter are automatically adjusted to pitch angles where they can be locked as a prerequisite to folding by commands generated (98, 112) to cause trim actuators (39-41) to drive swash plate servos (17-19) to the correct positions, initially (98) in response to stored trim references (120) and eventually (112) in response to the difference (109) between stored swash plate servo positions (120) and current servo positions (20-22).

摘要翻译： 直升机的可折叠转子叶片（12）被自动调节到俯仰角，在此角度可以将其锁定，作为通过产生（98,112）所产生的命令来折叠的先决条件，以使修剪致动器（39-41）驱动斜盘舵机（17 -19）到响应于所存储的微调参考（120）和最后（112）响应于存储的斜盘伺服位置（120）和当前伺服位置（20-）之间的差（109）的起始（98） 22）。

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

IPC分类号： B64C27/50 ,  B64C11/28 ,  B64C27/38

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。