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121. 发明授权

US5511944A Pitch link for rotary wing aircraft and automatic adjuster thereof 失效
标题翻译：旋翼飞机的间距连接及其自动调节器
公开(公告)号：US5511944A
公开(公告)日：1996-04-30
申请号：US256723
申请日：1994-07-22
申请人： Hideaki Ide , Shunichi Bandoh , Hiroshi Yasuhara
发明人： Hideaki Ide , Shunichi Bandoh , Hiroshi Yasuhara
IPC分类号： B64C27/605 , B64C27/59 , B64C27/72
CPC分类号： B64C27/72 , Y02T50/34 , Y10T74/18576 , Y10T74/2142 , Y10T74/2151
摘要： A pitch link having an adjustable length is constructed as a diamond-shaped frame by coupling and fixing four flexible beams same in length and rigidity each at end portions thereof. Spherical bearings are provided on opposite ends with the longer diagonal line as an axis of the pitch link. A turnbuckle shaft is screwed into vertex portions on the shorter diagonal line, which is turned so as to adjust a length of the shorter diagonal line, thereby adjusting a length of the pitch link. The turnbuckle shaft is rotated by a detachable motor. Vibrations of a body and the rotational position of a rotor are detected by a vibrosensor and a phase detector respectively while an aircraft equipped with the pitch link is flying, an amount for adjusting the pitch link is calculated by a vibration analyzer from the electrical signals, and the motor is driven through a FM data transmitter/receiver to adjust the pitch link.
摘要翻译： PCT No.PCT / JP93 / 01720 Sec。 371日期1994年7月22日 102（e）日期1994年7月22日PCT 1993年11月24日提交。具有可调节长度的节距链被构造为菱形框架，通过在其端部处连接并固定长度和刚度相同的四根柔性梁。球面轴承设置在两端，较长的对角线作为俯仰杆的轴线。螺丝扣轴被拧入较短对角线上的顶点部分，该斜面线被转动以便调整较短对角线的长度，由此调节节距连杆的长度。螺丝扣轴由可拆卸的电机旋转。当配备有俯仰杆的飞行器飞行时，通过振动传感器和相位检测器分别检测主体的振动和转子的旋转位置，通过振动分析器从电信号计算用于调节俯仰线的量，并且电机通过FM数据发射器/接收器驱动以调节音调链接。

122. 发明授权

US5472386A Stacked compound planetary gear train for an upgraded powertrain system for a helicopter 失效
标题翻译：用于直升机的升级动力系统的堆叠复合行星齿轮系
公开(公告)号：US5472386A
公开(公告)日：1995-12-05
申请号：US250212
申请日：1994-05-26
申请人： Jules G. Kish
发明人： Jules G. Kish
IPC分类号： F16H57/08 , B64C27/14 , F16H1/28 , F16H1/46 , B64C27/59 , F16H1/32 , F16H13/08
CPC分类号： B64C27/14 , F16H1/28 , F16H1/46 , Y10S475/903
摘要： A stacked compound planetary gear train for an upgraded powertrain system for a helicopter that provides an increased reduction ratio to accommodate the increased horsepower output of the augmented powerplant system while concomitantly providing a baseline RPM output to the main rotor shaft. The stacked compound planetary gear train includes a driving sun gear, a set N of primary planetary pinions, a plurality of secondary planetary pinions, a compound drive shaft supporting each respective primary and secondary planetary pinion combination, a fixed ring gear interacting with the secondary planetary pinions, and a planetary carrier assembly disposed in rotatable combination with the compound drive shafts and operative to provide the output of the stacked compound planetary gear train to the main rotor shaft of the helicopter. The set N of primary planetary pinions includes a plurality N/2 of upper primary planetary pinions and a plurality N/2 of lower primary planetary pinions. The upper and lower primary planetary pinions are disposed in a staggered, biplanar relationship wherein each upper primary planetary pinion overlaps the immediately adjacent lower primary planetary pinions. The stacked compound planetary gear train functions as the third stage reduction gearing in the upgraded powertrain system which includes input modules for receiving the increased horsepower output of an augmented powerplant system. The input modules include first stage reduction gearing for coupling power from the input modules to a main transmission assembly gearing. Second stage reduction gearing of the main transmission assembly couples power to the stacked compound planetary gear train to drive the sun gear thereof.
摘要翻译：一种用于直升机的升级动力系统的堆叠式复合行星齿轮系，其提供增加的减速比以适应增加的动力装置系统的增加的马力输出，同时向主转子轴提供基线RPM输出。堆叠的复合行星齿轮系包括驱动太阳齿轮，一组主要行星小齿轮，多个次级行星小齿轮，支撑每个相应的初级和次级行星齿轮组合的复合驱动轴，与次级行星齿轮相互作用的固定齿圈小齿轮和与复合驱动轴可旋转组合设置的行星架构组件，并且可操作以将堆叠的复合行星齿轮系的输出提供给直升机的主转子轴。主要行星小齿轮的组N包括多个N / 2的上部主行星小齿轮和多个N / 2个较小的主行星小齿轮。上部和下部主行星小齿轮以交错的双平面关系设置，其中每个上部主行星齿轮与紧邻的下部主行星齿轮重叠。堆叠的复合行星齿轮系作为升级动力系统中的第三级减速装置，其包括用于接收增加的动力装置系统的增加的马力输出的输入模块。输入模块包括用于将来自输入模块的功率耦合到主传动组件传动装置的第一级减速装置。主变速器组件的第二级减速装置将动力耦合到堆叠的复合行星齿轮系以驱动其太阳齿轮。

123. 发明授权

US4477224A Helicopter rotor 失效
标题翻译：直升机转子
公开(公告)号：US4477224A
公开(公告)日：1984-10-16
申请号：US417338
申请日：1982-09-13
申请人： Kenneth Watson
发明人： Kenneth Watson
IPC分类号： B64C27/72 , B64C27/59 , B64C27/74
CPC分类号： B64C27/59
摘要： A helicopter rotor (10, 29) includes a rotor hub (11, 30) supporting a plurality of rotor blades, and a pitch control means comprising a universal joint (21, 45) adapted to permit both tilting and axial vertical movements of the control means to change the pitch of the rotor blades both cyclically and collectively. The universal joint has three radially extending pins (22) each supporting a radially slidable and rotatable bearing (23) having a spherical external surface (25), the bearings being located in generally axially extending tracks (26) having a circular cross-sectional shape for rolling engagement by the bearings.Axial movements are permitted by rolling of the bearings along the tracks and tilting movements by a combination of rolling and a sliding movement of the bearings along the pins.Several embodiments are described and illustrated.
摘要翻译：直升机转子（10,29）包括支撑多个转子叶片的转子轮毂（11,30），以及包括万向接头（21,45）的俯仰控制装置，其适于允许控制器的倾斜和轴向垂直运动意味着循环地和集体地改变转子叶片的桨距。万向节具有三个径向延伸的销（22），每个销支撑具有球形外表面（25）的可径向滑动和可旋转的轴承（23），所述轴承位于大致轴向延伸的轨道（26）中，该轨道具有圆形横截面形状用于滚动轴承的接合。允许轴承沿着轨道滚动并通过滚动和轴承沿销的滑动运动的组合来进行倾斜运动。描述和示出了几个实施例。

124. 发明授权

US3786695A Redundant pitch link 失效
标题翻译：冗余PITCH链接
公开(公告)号：US3786695A
公开(公告)日：1974-01-22
申请号：US3786695D
申请日：1972-04-28
申请人： BOEING CO
发明人： BARRETT L
IPC分类号： B64C27/59 , B64C27/54 , F16L
CPC分类号： B64C27/54 , F16C7/06 , Y10T74/2151 , Y10T403/29
摘要： A redundant pitch link for providing a connection between a helicopter rotor blade and control assembly. A primary load path is provided for use during normal operation and a secondary load path is provided in the event the primary load path becomes inoperable. The pitch link is constructed by locating a primary turn buckle around a secondary or back-up turn buckle. Teflon fabric is used to prevent fretting while maintaining the secondary turn buckle in a substantially unloaded condition during normal usage as well as when the secondary turn buckle is operative due to failure of the primary turn buckle.
摘要翻译：用于提供直升机转子叶片和控制组件之间的连接的冗余俯仰杆。提供主要负载路径以在正常操作期间使用，并且在主负载路径变得不可操作的情况下提供次级负载路径。俯仰链接是通过将次级或后备转弯扣的初级转弯扣定位而构成的。特氟隆织物用于防止微动，同时在正常使用期间以及当次级转弯扣由于初级转弯失效而可操作时将次级转弯扣保持在基本无负载状态。

125. 发明授权

US3572616A Pitch control mechanism for bladed rotor 失效
公开(公告)号：US3572616A
公开(公告)日：1971-03-30
申请号：US3572616D
申请日：1969-09-18
申请人： UNITED AIRCRAFT CORP
发明人： ULISNIK HAROLD DANFORD
IPC分类号： B64C27/54 , B64C27/59 , B64C27/10 , B64C27/72
CPC分类号： B64C27/59 , B64C27/54
摘要： Two Z-crank mechanisms connect at different stations to a rotor swashplate so that translation of the mechanisms causes collective pitch variation of the blades and so that rotation of the mechanisms either together or separately causes cyclic pitch variations of the blades.

126. 发明授权

US2484099A Aircraft rotor and control thereof 失效
标题翻译：飞机转子及其控制
公开(公告)号：US2484099A
公开(公告)日：1949-10-11
申请号：US70143446
申请日：1946-10-05
申请人： KOEPPE ALVERN E
发明人： KOEPPE ALVERN E
IPC分类号： B64C27/59
CPC分类号： B64C27/59

127. 发明授权

US11623744B2 Rotor for a hover-capable aircraft and related method of control 有权
公开(公告)号：US11623744B2
公开(公告)日：2023-04-11
申请号：US17237813
申请日：2021-04-22
申请人： LEONARDO S.P.A.
发明人： Luigi Maria Bottasso
IPC分类号： B64C27/46 , B64C27/04 , B64C27/59 , B64C27/72
摘要： A rotor for a hover-capable aircraft is described that comprises: a hub rotatable about a first axis and at least two blades hinged to the hub; each blade comprises a main portion hinged to the hub and a tip portion, which is arranged radially outermost with respect to first axis with respect to the corresponding main portion; the tip portion of each blade is movable with respect to the corresponding main portion of that blade; the tip portion of each blade is selectively movable with respect to the corresponding main portion of that blade between a first position, in which it defines a dihedral or anhedral angle with respect to the corresponding main portion; and a second position, in which it defines a positive or negative sweep angle with respect to the corresponding main portion.

128. 发明授权

US11518506B2 Precision blade pitch adjustment 有权
公开(公告)号：US11518506B2
公开(公告)日：2022-12-06
申请号：US17198007
申请日：2021-03-10
申请人： Bell Textron Inc.
发明人： Andrew Paul Haldeman , Michael Seifert , Timothy McClellan Mosig , Aaron Acee , Diana R. Tinlin , Andrew Thomas Carter , Glenn Thornton Lancaster
IPC分类号： F04D29/36 , B64C27/59 , F01D7/00 , F01D5/30 , F01D5/02 , B64C11/06 , F04D29/32
摘要： A blade pitch adjustment mechanism includes a pitch cylinder having a first face and pitch slots extending longitudinally from the first face, a blade sleeve having a second face and a blade slot extending longitudinally from the second face, the blade sleeve is configured to be rotationally positioned in the pitch cylinder with the second face located with the first face, wherein the blade slot and the pitch slots are cooperative to form keyway, corresponding to a discrete blade pitch, when the blade slot is aligned with a pitch slot.

129. 发明申请

US20220380033A1 AIRCRAFT HAVING AT LEAST ONE PROPELLER AND A ROTARY WING PROVIDED WITH TWO ROTORS CARRIED BY TWO HALF-WINGS 有权
公开(公告)号：US20220380033A1
公开(公告)日：2022-12-01
申请号：US17745651
申请日：2022-05-16
申请人： AIRBUS HELICOPTERS
发明人： Paul EGLIN
IPC分类号： B64C27/26 , B64D35/06 , B64C27/59 , B64C11/00
摘要： An aircraft comprising two half-wings extending to either side of an airframe. The aircraft comprises at least one propeller arranged in the rear part of the airframe. The aircraft comprises a rotary wing provided with two synchronized counter-rotating rotors carried respectively by the half-wings. The aircraft comprises a power plant comprising at least one engine and a mechanical interconnection system connecting the power plant permanently to the rotors except in the event of failure and during training, and to the at least one propeller.

130. 发明授权

US11453487B2 Redundant helicopter pitch change bearing 有权
公开(公告)号：US11453487B2
公开(公告)日：2022-09-27
申请号：US16022162
申请日：2018-06-28
申请人： Sikorsky Aircraft Corporation
发明人： Kevin M. Wittke , Bertrand J. Howard
IPC分类号： B64C27/59 , B64C11/06 , B64C27/78 , F16C19/54 , F16C19/52 , F16C39/02
摘要： An aircraft rotor system includes a rotating pitch change shaft which rotates about an axis, a translating element disposed within the rotating pitch change shaft and movable along the axis and a pitch change bearing assembly which transfers movement of the translating element to the pitch change shaft. The pitch change bearing assembly includes a primary bearing and a secondary bearing coupled to the rotating pitch change shaft via the translating element when the primary bearing is in a first mode. A thrust shoulder is coupled to the translating element. The thrust shoulder is movable into engagement with the secondary bearing in response to failure of the primary bearing such that in a second mode, movement of the translating element is primarily transferred to the pitch change shaft via the secondary bearing.

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