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41. 发明申请

US20080253891A1 Swash Plate Anti-Torque Mechanism 有权
标题翻译：斜盘反扭矩机构
公开(公告)号：US20080253891A1
公开(公告)日：2008-10-16
申请号：US12088894
申请日：2006-10-03
申请人： Pedro L. Cabrera , Stephen V. Poulin , Francis D. Federici
发明人： Pedro L. Cabrera , Stephen V. Poulin , Francis D. Federici
IPC分类号： B64C27/54
CPC分类号： B64C27/10 , B64C27/605
摘要： An anti-torque mechanism which permits a full range of swashplate assembly motion. The anti-torque mechanism generally includes an anti-torque shaft and a compound bearing mounted thereto to provide five-degrees-of-freedom (spherical-linear-elastomeric) so as to permit a swashplate attachment point to move axially in response to pitch input; pivot in response to swashplate tilt; and move in/out in the radial direction.
摘要翻译：允许全范围的斜盘组装运动的抗扭矩机构。抗扭矩机构通常包括防扭矩轴和安装在其上的复合轴承以提供五自由度（球形 - 线性弹性体），以便允许斜盘附接点响应于俯仰输入而轴向移动 ; 回应斜盘倾斜; 并沿径向方向进/出。

42. 发明授权

US07425167B2 Toy helicopter 有权
标题翻译：玩具直升机
公开(公告)号：US07425167B2
公开(公告)日：2008-09-16
申请号：US11953826
申请日：2007-12-10
申请人： Alexander Jozef Magdalena Van de Rostyne
发明人： Alexander Jozef Magdalena Van de Rostyne
IPC分类号： A63H27/127 , B64C11/00 , B64C27/54
CPC分类号： A63H27/12
摘要： A helicopter has a main rotor with propeller blades which is driven by a rotor shaft and which is hinge-mounted to this rotor shaft. The angle between the surface of rotation of the main rotor and the rotor shaft may vary. A swinging manner on an oscillatory shaft is essentially transverse to the rotor shaft of the main rotor and is directed transversally to the longitudinal axis of the vanes. The main rotor and the auxiliary rotor are connected to each other by a mechanical link. The swinging motions of the auxiliary rotor controls the angle of incidence (A) of at least one of the propeller blades of the main rotor. There are wings from the body and a stabilizer at the tail.
摘要翻译：直升机具有主转子，其具有由转子轴驱动的螺旋桨叶片，并且铰链安装在该转子轴上。主转子和转子轴的旋转表面之间的角度可以变化。振荡轴上的摆动方式基本上横向于主转子的转子轴，横向于叶片的纵向轴线。主转子和辅助转子通过机械连接相互连接。辅助转子的摆动运动控制主转子至少一个螺旋桨叶片的入射角（A）。身上有翅膀和尾巴的稳定器。

43. 发明申请

US20070284475A1 Programmable trim control system for marine applications 有权
标题翻译：适用于海洋应用的可编程微调控制系统
公开(公告)号：US20070284475A1
公开(公告)日：2007-12-13
申请号：US11436072
申请日：2006-05-17
申请人： Michael B. Gee , Dana L. Birkland , Robert B. Bertolasi , Darryl S. Babu , Klaus Meyersieck , Dean J. Bratel , David D. N. Vann , Steven B. Hall , Mark B. Wilson , Russel E. Gates , Frederic E. Nystrom , Robert N. Schenk
发明人： Michael B. Gee , Dana L. Birkland , Robert B. Bertolasi , Darryl S. Babu , Klaus Meyersieck , Dean J. Bratel , David D. N. Vann , Steven B. Hall , Mark B. Wilson , Russel E. Gates , Frederic E. Nystrom , Robert N. Schenk
IPC分类号： B64C27/54
CPC分类号： B63B39/06
摘要： A programmable trim control system for marine applications preferably includes a controller, a control panel, a display device and a plurality of sensors. The controller receives input from the control panel and the plurality of sensors. The display device acts as a monitor for the controller. Each sensor monitors a single drive device, trim device or operational parameter. The controller further includes output ports connected to the drive devices and trim devices for controlling thereof. The trim control system preferably includes a manual mode, a diagnostic mode, a program mode and a preset mode. The positions or settings of the trim and drive devices are set in the program mode and recorded in the controller. Data stored in the controller will be accessed by the trim control system when in the preset mode.
摘要翻译：用于海洋应用的可编程装饰控制系统优选地包括控制器，控制面板，显示装置和多个传感器。控制器接收来自控制面板和多个传感器的输入。显示设备用作控制器的监视器。每个传感器监控单个驱动装置，装饰装置或操作参数。控制器还包括连接到驱动装置的输出端口和用于控制的装置装置。修剪控制系统优选地包括手动模式，诊断模式，程序模式和预设模式。修剪和驱动装置的位置或设置被设置在程序模式中并记录在控制器中。在预设模式下，调节控制系统将存储在控制器中的数据。

44. 发明申请

US20060049303A1 Mechanical density altitude compensation device for helicopter tail rotors 审中-公开
标题翻译：直升机尾转子机械密度高度补偿装置
公开(公告)号：US20060049303A1
公开(公告)日：2006-03-09
申请号：US11209540
申请日：2005-08-23
申请人： Darrell Wilkerson
发明人： Darrell Wilkerson
IPC分类号： B64C27/54
CPC分类号： B64C13/16 , B64C27/82
摘要： A helicopter tail rotor pitch-range altering device is disclosed. The device is incorporated into the existing helicopter tail rotor pitch-change control system of a helicopter and automatically alters the amount of tail rotor pitch available from the helicopter's tail rotor pitch-change control system based on changes in density altitude. The device comprises an ambient air density sensing device and a movable member located within or located in proximity to the helicopter tail rotor pitch-change flight control system. In one embodiment, a sealed bellows is connected directly to a movable member within the helicopter tail rotor pitch-change control system. As density altitude changes, the length of the bellows changes accordingly and moves the movable member within the helicopter's tail rotor pitch-change control system providing a varying tail rotor pitch-range based on density altitude.
摘要翻译：公开了一种直升机尾桨桨距变距装置。该装置并入现有的直升机直升机尾翼桨距变桨控制系统中，并根据密度高度的变化自动改变直升机尾桨桨距变桨控制系统的尾桨桨距。该装置包括环境空气密度感测装置和位于直升机尾部转子变桨飞行控制系统内或位于其附近的可动构件。在一个实施例中，密封的波纹管直接连接在直升机尾部转子桨距变桨控制系统内的可动构件上。当密度高度变化时，波纹管的长度相应地改变，并且使可移动构件在直升机的尾部转子变桨控制系统内移动，基于密度高度提供变化的尾部转子桨距范围。

45. 发明申请

US20050133314A1 Brake device for the rotor of a helicopter or the like, associating a main brake mechanism having a disk and a secondary brake mechanism for use in strong wind 有权
标题翻译：用于直升机等的转子的制动装置，将具有盘的主制动机构和用于强风的二次制动机构相关联
公开(公告)号：US20050133314A1
公开(公告)日：2005-06-23
申请号：US11010277
申请日：2004-12-14
申请人： Michel Bonfils
发明人： Michel Bonfils
IPC分类号： B64C27/54 , B64C27/12 , B64C27/48 , F16D65/14 , F16D66/00 , F16C1/16
CPC分类号： B64C27/12 , F16D66/00 , F16D2121/14 , F16D2123/00 , F16D2125/26 , F16D2125/64
摘要： A brake device for the rotor of a helicopter, the device associating a mechanism having a disk and a manual control for main braking of the rotor, and a mechanism for secondary braking of the rotor under strong wind. The secondary braking device includes a secondary lever hinged to the body and capable of being actuated against secondary return elements to drive a bearing finger against a main lever of the main brake mechanism and cause the jaws of the mechanism to move correspondingly towards each other so that the secondary lever actuates the main lever in order to amplify the clamping forces applied to the disk by the jaws in comparison with the forces they exert when driven by the main lever alone.
摘要翻译：一种用于直升机的转子的制动装置，该装置将具有盘的机构和用于转子的主制动的手动控制相关联，以及用于在强风下转子的二次制动的机构。二次制动装置包括铰链到主体并且能够被驱动抵靠第二返回元件的辅助杆，以将轴承手指驱动抵靠主制动机构的主杆，并且使得机构的夹爪相对于彼此移动，使得副杠杆致动主杆，以便与由主杆单独驱动时相比施加的力相比，通过钳口放大施加到盘的夹紧力。

46. 发明授权

US5026254A Calibrated pitch change link 失效
标题翻译：校准音高改变链接
公开(公告)号：US5026254A
公开(公告)日：1991-06-25
申请号：US421020
申请日：1989-10-13
申请人： Russell W. Ford , David S. Shepherd
发明人： Russell W. Ford , David S. Shepherd
IPC分类号： B64C27/59 , B64C27/00 , B64C27/54 , F16C7/06
CPC分类号： F16C7/06 , B64C27/008 , B64C27/54 , Y10T74/2151
摘要： A calibration device for a pitch change link (10) for a helicopter rotor grip where the link (10) includes a bearing (12) and includes a plurality of sequential reference numbers (22) equally spaced apart and concentrically disposed around the link (10). An indexing device (30) is mounted to the bearing (12) and is disposed adjacent to the plurality of sequential reference numbers (22) for locating one of the plurality of reference numbers (22) representing the length of the link (10). The indexing device (30) includes a window (40) which indexes one of the plurality of reference numbers (22) as the link (10) rotates.
摘要翻译：一种用于直升机转子夹持器的变桨连杆（10）的校准装置，其中所述连杆（10）包括轴承（12）并且包括多个等间隔开并同心地设置在所述连杆（10）周围的顺序参考标号（22））。分度装置（30）安装到轴承（12）上并与多个顺序参考编号（22）相邻设置，用于定位代表连杆（10）的长度的多个参考编号（22）中的一个。分度装置（30）包括窗口（40），当窗口（10）旋转时，窗口（40）对多个参考数字（22）中的一个进行索引。

47. 发明授权

US4730795A Heliplane 失效
标题翻译：直升机
公开(公告)号：US4730795A
公开(公告)日：1988-03-15
申请号：US833667
申请日：1986-02-26
申请人： Constant V. David
发明人： Constant V. David
IPC分类号： B64C27/10 , B64C27/22 , B64C27/54
CPC分类号： B64C27/10 , B64C27/22
摘要： The basic characteristics of an airplane and of a helicopter are combined into one flying craft: a HELIPLANE. This aircraft can fly forward like an airplane and hover like a helicopter. In the hovering mode, the craft lifting force is generated by gyrating blades and the craft control forces and moments are provided by a tail end propeller. In the forward flying mode, the craft lifting forces are generated by two wings and the gyrating blades. The propeller alone provides the forward propulsive thrust. The operations of the gyrating blades, of the craft control surfaces and of the power plant are all integrated, monitored and controlled to coordinate such operations during hovering, forward flight and any transition phase between hovering and forward flight. The gyrating blades never generate any forward propulsive thrust. The cyclic pitch motion of the gyrating blades needed to accommodate the craft forward flight velocity is induced by this forward velocity. Opposite gyrating blades are free to rotate around their longitudinal axes of rotation, but are solidly and rigidly connected to each other, so that both blades in any pair are always forced to rotate together by the same amount and in the same direction. The collective pitch of the gyrating blades is adjustable to meet the requirements of altitiude, craft weight and rate of ascent changes which affect the upward lifting force needed. The complex dynamic behavioral response of helicopters to cyclic pitch variations, and the consequences thereof, are eliminated in the present invention. All control and actuating means of the gyrating blades are well protected and shielded from environmental hazards.
摘要翻译：一架飞机和一架直升机的基本特征组合成一个飞行器：一个HELIPLANE。这架飞机能像飞机一样向前飞，像直升机一样翱翔。在悬停模式下，旋转叶片产生工艺提升力，并由尾端螺旋桨提供工艺控制力和力矩。在向前飞行模式中，工艺提升力由两个翼和旋转叶片产生。单独的螺旋桨提供了向前的推进推力。旋转叶片，工艺控制表面和发电厂的操作都被整合，监控和控制，以便在盘旋，向前飞行和盘旋和向前飞行之间的任何过渡阶段协调此类操作。回转叶片从不产生任何向前的推进推力。由前进速度引起的旋转叶片的旋转桨距运动，以适应飞行器的前进飞行速度。相对的旋转叶片可绕其纵向旋转轴线自由旋转，但是彼此牢固且刚性地连接，使得任何一对中的两个叶片总是被迫以相同的量和相同的方向一起旋转。回转叶片的集合间距是可调节的，以满足影响所需向上提升力的上升变化的要求，工艺重量和上升速率。在本发明中，消除了直升机对循环桨距变化的复杂的动态行为响应及其后果。旋转叶片的所有控制和驱动装置都得到很好的保护，防止环境危害。

48. 发明授权

US4379678A Individual blade control 失效
标题翻译：单独刀片控制
公开(公告)号：US4379678A
公开(公告)日：1983-04-12
申请号：US194804
申请日：1980-10-07
申请人： Gaylord W. Carlock , Jimmy G. Garner , Charles M. Gatlin , Kenneth F. Guinn , Peter A. Reyes
发明人： Gaylord W. Carlock , Jimmy G. Garner , Charles M. Gatlin , Kenneth F. Guinn , Peter A. Reyes
IPC分类号： B64C27/54 , B64C27/72 , B64C27/74
CPC分类号： B64C27/72 , B64C27/54 , B64C2027/7255 , Y02T50/34
摘要： Individual blade control of a helicopter rotor is accomplished by rotation of a mast (10) about a standpipe (12) where an individual blade (16) is coupled to the mast through a hub (18). Pilot input signals are transmitted by fly-by-optic transmission lines (14) through a fiber optic slip ring (40,42) to signal generators (134, 136, 138) for each of three sections of triplex actuators (76-79) coupled to individual rotor blades. Hydraulic fluid for positioning each of the actuators (76-79) is provided by electrohydraulic power packages (88, 90 and 92) where each package includes a pump and alternator. As each blade rotates about the mast (76) the pitch angle changes by individualizing the output of the signal generators (134-138) for each actuator.
摘要翻译：直升机转子的单独叶片控制通过围绕立管（12）的桅杆（10）的旋转来实现，其中单个叶片（16）通过轮毂（18）联接到桅杆。导频输入信号通过光纤传输线（14）通过光纤滑环（40,42）传输到三重致动器（76-79）的三个部分中的每一个的信号发生器（134,136,138）耦合到单个转子叶片。用于定位每个致动器（76-79）的液压流体由电动液压动力包（88,90和92）提供，其中每个包装包括泵和交流发电机。当每个叶片围绕桅杆（76）旋转时，俯仰角通过对每个致动器的信号发生器（134-138）的输出进行个性化而改变。

49. 发明授权

US3771924A Combination gyroplane 失效
标题翻译：组合GYROPLANE
公开(公告)号：US3771924A
公开(公告)日：1973-11-13
申请号：US3771924D
申请日：1970-10-06
申请人： DORNIER AG
发明人： BUCHSTALLER A
IPC分类号： B64C27/54 , B64C27/48
CPC分类号： B64C27/54
摘要： This invention relats to a combination gyroplane having a lockable rotor and rotor blades adapted to be retracted in the locked condition, comprising an equal number of rotor blades positioned in at least two planes offset with respect to each other with reference to the rotor axis, and means for maintaining the blade groups in operative position in a staggered arrangement and for causing the rotor blades of the groups to overlap for the retracting operation.
摘要翻译：本发明相对于具有可锁定转子和适于在锁定状态中缩回的转子叶片的组合陀螺仪，包括相对于转子轴线相对于彼此偏移的至少两个平面中的相等数量的转子叶片，以及用于将叶片组以交错布置保持在操作位置并且用于使组的转子叶片重叠以用于缩回操作的装置。

50. 发明授权

US3756743A Rotors for rotary winged aircraft 失效
标题翻译：旋转飞机的转子
公开(公告)号：US3756743A
公开(公告)日：1973-09-04
申请号：US3756743D
申请日：1971-04-15
申请人： ROBERTSON F
发明人： ROBERTSON F
IPC分类号： B64C27/54 , B64C27/58
CPC分类号： B64C27/54
摘要： This invention relates to a hub for a rigid rotor of a rotary winged aircraft and includes means for varying the blade angle of attack of each blade of a rotor as each blade rotates around the path traced out by the rotor to bring about a non-sinusoidal cyclic pitch change whilst independently allowing a sinusoidal cyclic pitch control to be superimposed thereon through the medium of a spider, the means being associated with each of the blade roots and includes a spindle for each blade, the spindles being equidistantly mounted for rotational movement in a rotatable component of the hub, and at their inner ends are each in spiral-splined engagement with a plunger whose inner end bears on a fixed cam and whose outer periphery has a predetermined peripheral profile to enable, for each blade, the blade angle of attack in relation to its azimuth position to be varied to suit the speed of the rotary winged aircraft.
摘要翻译：本发明涉及一种用于旋转翼飞机的刚性转子的轮毂，并且包括用于当每个叶片围绕由转子追踪出的路径旋转以改变非正弦曲线的路径时，改变转子的每个叶片的叶片迎角的装置循环间距变化，同时独立地允许通过蜘蛛的介质将正弦曲线循环桨距控制叠加在其上，该装置与叶片根部中的每一个相关联并且包括用于每个叶片的心轴，该心轴被等距地安装成用于在轮毂的可旋转部件，并且在它们的内端各自与柱塞螺旋花键接合，其内端承载在固定凸轮上，并且其外周具有预定的周边轮廓，以使得对于每个叶片，能够使叶片的迎角相对于其方位位置要变化以适应旋转飞机的速度。

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