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61. 发明授权

US07985048B2 Folding rotor for an autogyro device 有权
标题翻译：用于自动装置的折叠转子
公开(公告)号：US07985048B2
公开(公告)日：2011-07-26
申请号：US11860991
申请日：2007-09-25
申请人： Richard D. Jones
发明人： Richard D. Jones
IPC分类号： B64C11/28
CPC分类号： B64C27/022
摘要： In one embodiment, a folding rotor blade for an autogyro device comprises a plurality of connected rotor members. When the folding rotor blade is in a compressed state the folding rotor blade has a compressed length, and some of the connected rotor members are disposed in a non-parallel arrangement. When the folding rotor blade is in an extended state the folding rotor blade has an extended length, which is greater than the compressed length, and the connected rotor members are disposed in a parallel arrangement.
摘要翻译：在一个实施例中，用于自动装置装置的折叠转子叶片包括多个连接的转子构件。当折叠转子叶片处于压缩状态时，折叠转子叶片具有压缩长度，并且一些连接的转子部件以非平行布置的方式设置。当折叠转子叶片处于伸展状态时，折叠转子叶片具有大于压缩长度的延伸长度，并且所连接的转子部件以平行布置的方式设置。

62. 发明申请

US20100163668A1 Helicopter Rotor 有权
标题翻译：直升机转子
公开(公告)号：US20100163668A1
公开(公告)日：2010-07-01
申请号：US12610930
申请日：2009-11-02
申请人： Fabio Nannoni , Pierre Abdel Nour , Dante Ballerio
发明人： Fabio Nannoni , Pierre Abdel Nour , Dante Ballerio
IPC分类号： B64C27/82 , B64C11/28 , B64C27/50
CPC分类号： B64C27/82 , B64C27/35 , B64C27/51
摘要： A rotor for a helicopter, having a drive shaft rotating about a first axis; a hub angularly integral with the drive shaft about the first axis; and at least two blades projecting from the hub, on the opposite side to the first axis, and extending along respective second axes crosswise to the first axis; each blade is movable with respect to the hub and the other blades about a respective fourth axis parallel to the first axis, about the respective second axis, and about a respective third axis crosswise to the first and respective second axis; the rotor also has a number of first dampers for damping vibration associated with at least oscillation of the relative blades about the respective fourth axes; the first dampers are connected to one another and each to a relative blade; and, in a radial direction with respect to the first axis, at least one first damper is located between the first axis and the fourth axis of the relative blade.
摘要翻译：一种用于直升机的转子，具有围绕第一轴旋转的驱动轴; 与所述驱动轴围绕所述第一轴线成一体的毂; 以及至少两个叶片，所述至少两个叶片从所述轮毂在与所述第一轴线相反的一侧上突出，并且沿着相对于所述第一轴线交叉的相应第二轴线延伸; 每个叶片可相对于轮毂和其它叶片围绕平行于第一轴线的相应第四轴线，围绕相应的第二轴线以及围绕与第一和相应的第二轴线交叉的相应的第三轴线移动; 所述转子还具有多个用于阻尼振动的第一阻尼器，所述阻尼振动至少与相应的第四轴线相对的所述相对刀片的振荡相关联; 第一阻尼器彼此连接并且各自连接到相对叶片; 并且在相对于第一轴线的径向方向上，至少一个第一阻尼器位于相对刀片的第一轴线和第四轴线之间。

63. 发明申请

US20080232966A1 Detachable blade assembly for horizontal-axis wind turbine 审中-公开
标题翻译：用于横轴风力发电机的可拆卸刀片组件
公开(公告)号：US20080232966A1
公开(公告)日：2008-09-25
申请号：US11726042
申请日：2007-03-20
申请人： Wen-Chang Wang , Yu-Ching Wang
发明人： Wen-Chang Wang , Yu-Ching Wang
IPC分类号： B64C11/28
CPC分类号： F03D1/0658 , F03D13/40 , F05B2260/02 , F05B2260/301 , Y02E10/721
摘要： A blade assembly for a horizontal-axis wind turbine includes a hub, and a plurality of detachable blade units each mounted on a periphery of the hub and each including a plurality of blades detachably connected with each other by a plurality of connecting devices. Thus, the blade assembly comprises a hub and a plurality of detachable blade units so that all parts of the blade assembly are detachable to reduce the whole volume of the blade assembly before assembly, thereby facilitating packaging, storage and transportation of the blade assembly.
摘要翻译：用于水平轴风力涡轮机的叶片组件包括轮毂和多个可拆卸的叶片单元，每个叶片单元安装在轮毂的周边上，并且每个叶片单元包括通过多个连接装置彼此可拆卸地连接的多个叶片。因此，叶片组件包括轮毂和多个可拆卸刀片单元，使得叶片组件的所有部分都可拆卸，以在组装之前减小叶片组件的整个体积，从而便于叶片组件的包装，储存和运输。

64. 发明申请

US20070098554A1 Rotorcraft blade provided with a tiltable flap and a fastener tongue 有权
标题翻译：旋翼刀刀片设有可倾斜的挡板和紧固舌
公开(公告)号：US20070098554A1
公开(公告)日：2007-05-03
申请号：US11585209
申请日：2006-10-24
申请人： Francois Lorin De La Grandmaison , Michel Morant , Jacques Gaffiero
发明人： Francois Lorin De La Grandmaison , Michel Morant , Jacques Gaffiero
IPC分类号： B64C11/28
CPC分类号： B64C27/615 , B64C27/72 , B64C2027/7272 , Y02T50/34
摘要： The present invention relates to a rotorcraft rotor blade (1) that comprises at least one tiltable trailing-edge flap (5), said flap (5) being suitable for pivoting about a virtual hinge axis (Y′) extending substantially in the span direction of said blade (1) and of said flap (5). The blade (1) is remarkable in that the flap (5) is provided with at least two fastener ball joints (30), each provided with an inner cage (32) together with an outer cage (33) and a first pin (31) that is also secured to said flap (5), the first pins (31) of the fastener ball joints (30) being perpendicular to the virtual pivot axis (Y′) of the flap (5). In addition, the blade (1) is provided at its trailing edge (BF) with a fastener tongue (20) provided with ball-receiving sockets (21), the outer cages (33) of the fastener ball joints (30) being secured to the ball-receiving sockets (21).
摘要翻译：本发明涉及一种旋翼航空器转子叶片（1），其包括至少一个可倾斜的后缘翼片（5），所述翼片（5）适于围绕基本在翼展方向上延伸的虚拟铰链轴线（Y'）枢转的所述叶片（1）和所述翼片（5）。叶片（1）的特征在于，翼片（5）设置有至少两个紧固件球窝接头（30），每个紧固件球窝接头（30）与外笼（33）和第一销（31）一起设置有内笼），其也固定到所述翼片（5），所述紧固件球窝接头（30）的第一销（31）垂直于所述翼片（5）的虚拟枢转轴线（Y'）。此外，叶片（1）在其后缘（BF）处设置有具有球接收插座（21）的紧固舌（20），紧固件球窝接头（30）的外笼（33）被固定到球接收插座（21）。

65. 发明申请

US20070031254A1 Fluid flow energy conversion apparatus 失效
标题翻译：流体流动能量转换装置
公开(公告)号：US20070031254A1
公开(公告)日：2007-02-08
申请号：US11199537
申请日：2005-08-08
申请人： Cecil Albert Rains
发明人： Cecil Albert Rains
IPC分类号： B64C11/28
CPC分类号： F03B13/183 , F03B13/264 , F03D3/067 , Y02E10/28 , Y02E10/38 , Y02E10/74
摘要： Tidal forces used for generation of electrical power has long been a solution to a recognized need. A really practical device to convert the energy of the fluid flow through tidal inlets into electrical power is the subject of this invention.
摘要翻译：用于发电的潮汐力一直是公认需求的解决方案。将通过潮汐入口的流体流的能量转换成电力的真正实用的装置是本发明的主题。

66. 发明申请

US20060062672A1 Expandable impeller pump 有权
标题翻译：可扩展叶轮泵
公开(公告)号：US20060062672A1
公开(公告)日：2006-03-23
申请号：US11227277
申请日：2005-09-15
申请人： Mark McBride , Thomas Mallison , Gregory Dillon , Robert Campbell , David Boger
发明人： Mark McBride , Thomas Mallison , Gregory Dillon , Robert Campbell , David Boger
IPC分类号： B64C11/28
CPC分类号： F04D29/181 , A61M1/101 , A61M1/1012 , A61M1/1024 , A61M1/1034 , A61M1/122 , A61M1/125 , B63B2231/42 , B63H1/26 , B63H11/08 , F04D3/00 , F04D3/02 , F04D19/02 , F04D29/026 , F04D29/247 , F04D29/382 , F04D29/526 , F04D29/528 , F05D2210/11 , F05D2250/51 , F05D2250/52 , F05D2300/43 , Y10S415/90 , Y10T29/49229
摘要： An impeller according to an example of the present invention comprises a hub, and at least one blade supported by the hub. The impeller has a deployed configuration in which the blade extends away from the hub, and a stored configuration in which the impeller is radially compressed, for example by folding the blade towards the hub. The impeller may comprise a plurality of blades, arranged in blade rows, to facilitate radial compression of the blades. The outer edge of a blade may have a winglet, and the base of the blade may have an associated indentation to facilitate folding of the blade.
摘要翻译：根据本发明的示例的叶轮包括轮毂和由轮毂支撑的至少一个叶片。叶轮具有展开构造，其中叶片远离轮毂延伸，并且存储构造，其中叶轮被径向压缩，例如通过将叶片朝向轮毂折叠。叶轮可以包括多个叶片，其布置成叶片排，以便于叶片的径向压缩。叶片的外边缘可以具有小翼，并且叶片的基部可以具有相关联的凹口以便于叶片的折叠。

67. 发明申请

US20050093507A1 Methods and systems for starting propeller-driven devices 有权
标题翻译：启动螺旋桨驱动装置的方法和系统
公开(公告)号：US20050093507A1
公开(公告)日：2005-05-05
申请号：US10976566
申请日：2004-10-29
申请人： Steven Sliwa , Andreas von Flotow , Brian Dennis
发明人： Steven Sliwa , Andreas von Flotow , Brian Dennis
IPC分类号： B63H20060101 , B64C11/00 , B64C11/04 , B64C11/14 , B64C11/28 , B64C39/02 , B64D41/00 , F02K5/02 , H02J7/00
CPC分类号： B64C11/003 , A63H27/02 , B64C11/04 , B64C11/14 , B64C11/28 , B64C39/024 , B64C2201/044 , B64C2201/082 , B64C2201/102 , B64C2201/165 , B64C2201/182 , B64C2201/201 , B64C2201/206 , B64D41/007 , F02K5/023 , F05D2260/85 , Y02T50/44 , Y02T50/672
摘要： Methods and systems for starting propeller driven aircraft and other devices are disclosed. A system in accordance with one embodiment of the invention includes a removable fixture that is coupled to the propeller and has at least one portion exposed to a flowstream to rotate the propeller during engine start-up. The fixture is configured to separate from the propeller after the engine begins to turn over (e.g., after the engine starts and/or rotates above a threshold rate). Accordingly, the system can include a releasable link between the fixture and the propeller.
摘要翻译：公开了用于启动螺旋桨驱动的飞机和其他装置的方法和系统。根据本发明的一个实施例的系统包括可拆卸的固定装置，其连接到螺旋桨并且具有暴露于流动流中的至少一个部分以在发动机起动期间旋转螺旋桨。发动机开始翻转（例如在发动机起动和/或旋转高于阈值速率之后），该固定装置构造成与螺旋桨分离。因此，系统可以包括夹具和螺旋桨之间的可释放的连接。

68. 发明授权

US6109870A Rotor blade flap driving apparatus 有权
标题翻译：转子叶片挡板驱动装置
公开(公告)号：US6109870A
公开(公告)日：2000-08-29
申请号：US239799
申请日：1999-01-29
申请人： Eiichi Yamakawa , Tatsuro Hongu , Mitsumasa Sato , Shun-ichi Bandoh
发明人： Eiichi Yamakawa , Tatsuro Hongu , Mitsumasa Sato , Shun-ichi Bandoh
IPC分类号： B64C27/00 , B64C27/615 , B64C27/64 , F15B15/00 , B64C11/28
CPC分类号： B64C27/615 , B64C27/001 , B64C2027/7266 , Y02T50/34
摘要： A flap is attached to a rear end of a blade so as to be angularly displaceable. Displacement magnifying means magnifies the amount of displacement from an actuator to drive the flap. An input portion to which the displacement is applied from the actuator is expandably and contractibly supported by bellows. Likewise, an output portion to which the input amount of displacement is magnified is expandably and contractibly supported by a bellows. Consequently, displacement magnifying means is realized in which, compared with a existing piston with O ring which slides on the cylinder inner wall, no deterioration in response characteristic due to high friction occurs when the actuator is displaced at high speed, and no fluid leakage due to deterioration or wear of the O ring occurs. According to this structure, a rotor blade flap driving apparatus is obtained which has displacement magnifying means with fast response and no fluid leakage.
摘要翻译：翼片附接到叶片的后端以便成角度地移位。位移放大装置放大来自致动器的位移量以驱动翼片。从致动器施加位移的输入部分由波纹管可膨胀和收缩地支撑。类似地，输入量的位移的放大的输出部分由波纹管可膨胀和收缩地支撑。因此，实现了一种位移放大装置，其中与现有的具有在气缸内壁上滑动的O形环的活塞相比，当致动器高速位移时，由于高摩擦而导致的响应特性不会降低，并且没有流体泄漏发生O环的劣化或磨损。根据该结构，获得了具有快速响应且无流体泄漏的位移放大装置的转子叶片挡板驱动装置。

69. 发明授权

US5636969A Torque tube/spar assembly for variable diameter helicopter rotors 失效
公开(公告)号：US5636969A
公开(公告)日：1997-06-10
申请号：US412175
申请日：1995-03-28
申请人： David G. Matuska , Edward W. Gronenthal , W. Donald Jepson
发明人： David G. Matuska , Edward W. Gronenthal , W. Donald Jepson
IPC分类号： B64C11/00 , B64C27/473 , B64C29/00 , B64C11/28
CPC分类号： B64C11/003 , B64C29/0033
摘要： A torque tube/spar assembly (100) for transferring operational loads of a Variable Diameter Rotor blade assembly (16) to a rotor hub assembly (18) and includes a torque tube member (24), a spar member (30) and a bearing assembly (40a, 40b) for telescopically mounting the spar member (30) to the torque tube member (24) and furthermore defines an internal channel (62) for housing a retraction/extension mechanism (64) which mounts to an internally formed restraint surface (86) of the spar member (30) and is operative to vary the length of the rotor blade assembly (18). The torque tube member (30) has a substantially constant external geometry along the length of bearing assembly engagement and defines a root end region (102), a tip end region (106) and an intermediate transition region (104) disposed therebetween. The spar member (30) has a substantially constant internal geometry and defines a root end region (110), a first transition (112), an intermediate region (114), a second transition region (116), a restraint region (118) and a tip end region (120). Each of the various regions of the torque tube and spar members (24, 30) have a characteristic stiffness value wherein the characteristic values (104m, 106m) of the intermediate transition and tip end regions (104,106) of the torque tube member (24) are less than the characteristic stiffness value (102m) of the root end region (102) thereof, and wherein the characteristic stiffness value (118m) of the restraint region (118) of the spar member (30) is greater than said characteristic stiffness values (114m, 120m) of the intermediate and tip end regions (114, 120) thereof, and wherein the characteristic stiffness value (114m) of the intermediate region (114) is less than the characteristic stiffness values (110m, 112m, 116m, 118m) of the root end, first transition, second transition and restraint regions (110, 112, 116, 118).

70. 发明授权

US4688743A Aircraft with a retractable variable pitch propeller or a fluid motor driven multi propeller aircraft 失效
标题翻译：具有可伸缩变桨螺旋桨或液压马达驱动多螺旋桨飞机的飞机
公开(公告)号：US4688743A
公开(公告)日：1987-08-25
申请号：US709872
申请日：1985-03-08
申请人： Karl Eickmann
发明人： Karl Eickmann
IPC分类号： B64C11/28 , B64C27/04 , B64C27/12 , B64C29/00 , B64D31/14 , B64D35/00 , F02B75/02
CPC分类号： B64D35/00 , B64C11/28 , B64C27/04 , B64C27/12 , B64C29/00 , B64D31/14 , B64C2700/6281 , F02B2075/025
摘要： An aircraft has a pair of wing portions with propellers of a propeller pair which are driven and synchronized by a fluid transmission between the power plant and the propellers. A fluid line structure keeps most components of the craft together and consists preferredly of three pipes which are also utilized to carry the driving fluid to and from the motors, to hold the motors and to hold the wings. The take over of a plurality of functions by the interior pipe structure reduces weight and secures safe and economic operation of the craft. In the type of the aircraft where this application deals with, a variable pitch propeller may be applied which operates with variable pitch at flight to obtain its best efficiency at the respective speed of flight while the propeller is set with its chord parallel to the chord of the wing or tail when it is retracted into a slot in the wing or tail when another propeller drives the craft forward in leveled flight. This arrangement makes it suitable to apply a plurality of propellers for short way or vertical take off and landing while those propellers which are not needed or would reduce the efficiency at forward flight can be retracted to reduce drag at high speed forward flight.
摘要翻译：飞机具有一对具有螺旋桨对的螺旋桨的机翼部分，其通过在发电厂和螺旋桨之间的流体传动驱动并同步。流体管线结构将工艺的大多数部件保持在一起，并且优选地由三个管道组成，这三个管道也用于将驱动流体运送到电动机和从电动机运送驱动流体，以保持电动机并保持机翼。通过内部管道结构接管多个功能减轻了重量并确保了工艺的安全和经济的操作。在本申请所涉及的飞机的类型中，可以应用可变桨距螺旋桨，其在飞行时以可变桨距运行，以在各自的飞行速度下获得最佳效率，同时螺旋桨的弦平行于弦当翼或尾翼缩回到翼或尾部的槽中时，当另一个螺旋桨在平层飞行中向前推动飞行器时。这种布置使得适合于在短时间或垂直起飞和着陆时应用多个螺旋桨，而不需要或将降低前进飞行的效率的螺旋桨可以缩回以在高速向前飞行中减小阻力。

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