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1. 发明授权

US4448131A Suspension system for rail vehicles 失效
标题翻译：铁路车辆悬挂系统
公开(公告)号：US4448131A
公开(公告)日：1984-05-15
申请号：US218693
申请日：1980-12-22
申请人： Emil Weiland , Christian Gunther
发明人： Emil Weiland , Christian Gunther
IPC分类号： B61F5/00 , B61F5/24 , B61F5/28 , B61F5/44 , B61F5/52 , B61H7/08
CPC分类号： B61F5/523 , B61F5/00 , B61F5/24 , B61F5/28 , B61F5/44 , B61H7/086 , Y02T30/38
摘要： A suspension system for rail vehicles which have at least two wheelsets hng axles which are supported in a frame and within which a cross member extends parallel to the axles. The cross member is supported in the vehicle frame in a spring-cushioned manner wherein the frame with the integrated cross member consists essentially of an H-shaped part made of resiliently elastic fiber-reinforced material.
摘要翻译：一种用于轨道车辆的悬挂系统，其具有至少两个具有轴的轮对，所述轮轴被支撑在框架中，并且横向构件平行于所述轴延伸。横向构件以弹簧缓冲的方式支撑在车架中，其中具有一体的横向构件的框架基本上由由弹性弹性纤维增强材料制成的H形部件组成。

2. 发明授权

US4183718A Rotor for a rotary wing aircraft 失效
标题翻译：旋翼机用于旋翼飞机
公开(公告)号：US4183718A
公开(公告)日：1980-01-15
申请号：US855668
申请日：1977-11-29
申请人： Karlheinz Mautz , Emil Weiland , Alois Schwarz
发明人： Karlheinz Mautz , Emil Weiland , Alois Schwarz
IPC分类号： B64C27/35 , B64C27/45 , B64C27/48
CPC分类号： B64C27/45
摘要： A rotor for a rotary wing aircraft includes a rotor head and an even number of rotor blades arranged in pairs about the rotor head. The rotor blades of each pair are located diametrically opposite each other and each blade has a root end positioned radially inwardly toward the head. Bearings carried by the rotor head pivotally support each of the rotor blades. A torsionally elastic connection member extends between and connects the roots of a pair of rotor blades, and the connection member is mounted at its longitudinal center in the rotor head for pivotal movement about its longitudinal axis.
摘要翻译：用于旋转翼飞行器的转子包括转子头部和偶数个转子叶片成对设置的转子叶片。每对转子叶片彼此沿径向相对，并且每个叶片具有朝向头部径向向内定位的根端。由转子头承载的轴承枢转地支撑每个转子叶片。扭转弹性连接构件在一对转子叶片的根部之间延伸并连接，并且连接构件在其纵向中心处安装在转子头部中，用于围绕其纵向轴线枢转运动。

3. 发明授权

US4201815A Shear transfer element 失效
标题翻译：剪切转印元件
公开(公告)号：US4201815A
公开(公告)日：1980-05-06
申请号：US972223
申请日：1978-12-22
申请人： Emil Weiland , Rudolf Schindler , Klaus Brunsch
发明人： Emil Weiland , Rudolf Schindler , Klaus Brunsch
IPC分类号： D03D3/00 , B29C57/00 , B29C67/00 , B29C70/06 , B32B5/08 , B64C27/33 , D04H3/07 , B32B5/12
CPC分类号： B64C27/33 , Y10T428/24058 , Y10T428/24124 , Y10T428/24132
摘要： Shear transfer elements can be formed by winding or weaving unidirectional fibers on a support structure. In a winding operation the support structure consists of two intersecting planes of winding mandrels with the planes arranged in angularly spaced relation. Each plane has two pair of mandrels with the mandrels in each pair located on the opposite sides of the line of intersection between the two planes. After the fibers are wound on the mandrels, each mandrel is axially disposed in the opposite direction relative to the other mandrel in the pair and also to the adjacent mandrel in the other pair in the same plane. Next, the fibers are pressed to form the shear transfer element. In a weaving operation, the support structure consists of a pair of pivotally interconnected frames. The fibers are woven onto holders on the sides of each frame extending parallel to the pivot axis of the frames. After placement of the fibers on the frames, the frames are pivoted apart and the fibers are pressed to form the shear transfer element.
摘要翻译：剪切转印元件可以通过在支撑结构上缠绕或编织单向纤维来形成。在卷绕操作中，支撑结构由缠绕心轴的两个相交平面组成，其中平面以角度间隔的关系布置。每个平面具有两对心轴，其中每对中的心轴位于两个平面之间的相交线的相对侧上。在纤维缠绕在心轴上之后，每个心轴相对于该对中的另一个心轴在相反方向上轴向地设置，并且在同一平面中的另一对中相邻的心轴。接下来，将纤维压制以形成剪切传递元件。在编织操作中，支撑结构由一对枢转互连的框架组成。纤维被编织到平行于框架的枢转轴线延伸的每个框架的侧面上的保持器上。在将纤维放置在框架上之后，框架枢转分开，并且将纤维压制以形成剪切传递元件。

4. 发明授权

US4163630A Helicopter rotor structure 失效
标题翻译：直升机转子结构
公开(公告)号：US4163630A
公开(公告)日：1979-08-07
申请号：US824241
申请日：1977-08-12
申请人： Emil Weiland
发明人： Emil Weiland
IPC分类号： B64C27/35 , B64C27/33 , B64C27/38
CPC分类号： B64C27/33
摘要： The rotor blades or wings of the present helicopter rotor structure are interconnected by tension or carrier bars so that diametrically opposite rotor blades or wings form a pair. The tension bars are substantially stiff against bending, but permit some bending. The blade angle bearings are movable in the blade flapping direction, as well as in the blade lead-lag direction. At least one blade angle bearing of a pair of such bearings permits an axial movement of the respective tension or carrier bar, whereby the latter is able to take up bending loads.
摘要翻译：现有直升机转子结构的转子叶片或翼片通过张力或承载杆相互连接，使直径相对的转子叶片或翼形成一对。张力杆基本上抗弯弯曲，但是允许一些弯曲。叶片角轴承可以在叶片拍动方向以及叶片前后延迟方向上移动。一对这样的轴承的至少一个叶片角度轴承允许相应的张力或承载杆的轴向移动，由此后者能够承受弯曲载荷。

5. 发明授权

US4154557A Helicopter rotor structure 失效
标题翻译：直升机转子结构
公开(公告)号：US4154557A
公开(公告)日：1979-05-15
申请号：US824240
申请日：1977-08-12
申请人： Emil Weiland
发明人： Emil Weiland
IPC分类号： B64C27/35 , B64C27/45 , B64C11/12
CPC分类号： B64C27/45
摘要： The blades or wings of a rotary wing aircraft are secured to the rotor headn a non-rigid manner by means of a carrier bar, however, without any flapping hinges and without any lagging hinges. The carrier bar is supported on the rotor head. The connection of each wing to the respective end of the carrier bar is such, that the longitudinal wing axis is excentrically displaced relative to the central longitudinal axis of the carrier bar in the direction in which the forces of the air are effective. The displacement or spacing between the two axes is such that at least a partial compensation of the occurring bending moments is achieved.
摘要翻译：旋转翼飞行器的叶片或翼片通过承载杆以非刚性的方式固定到转子头部，然而，没有任何振动铰链并且没有任何滞后的铰链。承载杆支撑在转子头上。每个翼片与承载杆的相应端部的连接是这样的，使得纵向翼片轴线在空气力有效的方向上相对于承载杆的中心纵向轴线偏心移位。两个轴之间的位移或间距使得至少可以实现出现的弯矩的部分补偿。

6. 发明授权

US4252503A Rotor blade especially for rotary wing aircraft 失效
标题翻译：转子叶片特别适用于旋翼飞机
公开(公告)号：US4252503A
公开(公告)日：1981-02-24
申请号：US15311
申请日：1979-02-26
申请人： Peter M. Wackerle , Otmar Friedberger , Emil Weiland
发明人： Peter M. Wackerle , Otmar Friedberger , Emil Weiland
IPC分类号： B64C27/35 , B64C27/00 , B64C27/46 , B64C27/51 , B64C27/38
CPC分类号： B64C27/001 , B64C27/46 , B64C27/51
摘要： A rotor blade has a neck section which connects the blade proper to a rotoread at the blade root. The neck section is flexible against bending in the lead-lag direction and in the flapping direction. A carrier member is located alongside or inside the neck section but spaced from the neck section. The carrier member is resistant against bending at least in the lead-lag direction or in the flapping direction. The carrier member is rigidly connected at its one end to the blade proper. A layer of a damping material is operatively interposed between the carrier member and the neck section, preferably at the blade root end of the neck section, whereby blade vibrations preferably in the lead-lag direction are damped and substantially prevented from entering into the rotor head.
摘要翻译：转子叶片具有将刀片本体连接到叶片根部的转子头部的颈部。颈部在引导滞后方向和拍动方向上是弯曲的。载体构件位于颈部旁边或内侧，但与颈部间隔开。载体构件至少在前后延迟方向或者在拍动方向上是抗弯曲的。承载构件的一端刚性地连接到叶片本体上。阻尼材料层可操作地插入在承载构件和颈部之间，优选地在颈部的叶片根端处，由此优选地在超前滞后方向上的叶片振动被阻尼并基本上防止进入转子头。

7. 发明授权

US4195967A Rotor free of flapping hinges and free of lead-lag hinges 失效
标题翻译：转子没有摆动铰链，没有前置铰链
公开(公告)号：US4195967A
公开(公告)日：1980-04-01
申请号：US844317
申请日：1977-10-21
申请人： Emil Weiland
发明人： Emil Weiland
IPC分类号： B64C27/35 , B64C27/45 , B64C27/48
CPC分类号： B64C27/45
摘要： The present rotor for rotary wing aircraft is of the type which is free of flapping hinges as well as free of lead-lag hinges. Such rotor shall have a simple structure and a small structural weight while simultaneously having a high operational reliability. To this end the rotor hub comprises upper and lower support or carrier plates made of a fiber compound material arranged in such a manner that the fibers extend substantially radially. The upper and lower support plates are spaced from each other by thrust arms or lands and the blade angle bearings are supported between the carrier plates of a fiber compound material.
摘要翻译：目前用于旋转翼飞机的转子是没有拍动铰链以及没有前级铰链的类型。这样的转子应具有简单的结构和小的结构重量，同时具有较高的操作可靠性。为此，转子毂包括由纤维复合材料制成的上和下支撑或承载板，纤维复合材料以纤维基本上径向延伸的方式布置。上支撑板和下支撑板通过推力臂或平台彼此间隔开，并且叶片角轴承支撑在纤维复合材料的承载板之间。

8. 发明授权

US4028000A Blade connection for helicopter rotor blades 失效
标题翻译：直升机转子叶片的叶片连接
公开(公告)号：US4028000A
公开(公告)日：1977-06-07
申请号：US627702
申请日：1975-10-31
申请人： Emil Weiland , Alois Schwarz , Hubert Frommlet
发明人： Emil Weiland , Alois Schwarz , Hubert Frommlet
IPC分类号： B64C27/00 , B64C27/51 , B64C27/42
CPC分类号： B64C27/001 , B64C27/51
摘要： Resilient drive means for a helicopter rotor blade. The rotor blade is pivotally supported on a stub shaft which is in turn supported on the rotor hub. First means are fixed to the rotor blade and second means fixed to the stub shaft with resilient and adjustable means positioned therebetween for controlling the angular relationship between the rotor blade and the stub shaft. In this embodiment, said first means comprise a shoulder which projects from the rotor blade and the second means comprise a rectangular hollow frame which is fixed to the stub shaft. The shoulder projects into the hollow frame. Threaded means acting through resilient means holds the first and second means in selected pivotal adjustment with respect to each other but the resilient component thereof permits sufficient slight lead lag movement therebetween as to effect damping of the lead lag mode of the rotorblade. The adjustment capability permits sufficient adjustment of the blade with respect to the hub to ensure desired balance between the several blades of a given rotor.
摘要翻译：用于直升机转子叶片的弹性驱动装置。转子叶片枢转地支撑在短轴上，短轴又支撑在转子毂上。第一装置固定到转子叶片上，第二装置固定到短轴上，弹性和可调节装置位于其间，用于控制转子叶片和短轴之间的角度关系。在该实施例中，所述第一装置包括从转子叶片突出的肩部，并且第二装置包括固定到短轴的矩形中空框架。肩膀突入中空框架。通过弹性装置作用的螺纹装置将第一和第二装置相对于彼此保持在选定的枢转调节中，但是其弹性部件在其间允许足够的轻微的超前滞后运动，以实现转子叶片的牵引滞后模式的阻尼。调整能力允许相对于轮毂足够调节叶片，以确保给定转子的几个叶片之间期望的平衡。

9. 发明授权

US4292009A Hingeless rotor system 失效
标题翻译：无声转子系统
公开(公告)号：US4292009A
公开(公告)日：1981-09-29
申请号：US970740
申请日：1978-12-18
申请人： Emil Weiland , Klaus Brunsch
发明人： Emil Weiland , Klaus Brunsch
IPC分类号： B64C27/35 , B64C27/33 , B64C27/38
CPC分类号： B64C27/33
摘要： The present hingeless rotor system for helicopters has carrier spars or b each of which is subdivided into three functional sections substantially forming the blade neck connecting the lift producing portion of the respective rotor blade to the rotor mast. The carrier spar sections form a single structural blade neck member extending for about two tenths of the rotor radius from the rotor mast to the lift producing blade portions. About one half of the length of the blade neck adjacent to the rotor mast form the connecting zone proper. The spar sections comprise bands forming respective loops in the connecting zone proper. Two of the band loops are connected one above the other and a third band loop is displaced in the direction of rotation of the rotor from the first mentioned band loops. The third band loop is releasably connected to the rotor mast to allow a folding of the respective rotor blade. The spar sections are interconnected by shear resistant bridging webs having a T- or X cross-section.
摘要翻译：目前用于直升机的无铰链转子系统具有载体翼梁或杆，每个翼片或杆被细分成三个功能部分，其基本上形成连接相应转子叶片的提升产生部分到转子桅杆的叶片颈部。载体翼梁部分形成单个结构的叶片颈部构件，其延伸大约是从转子桅杆到提升产生叶片部分的转子半径的十分之二。与转子桅杆相邻的叶片颈部长度的大约一半形成连接区域。翼梁部分包括在连接区域中形成相应的环的带。两个带环之一彼此连接，并且第三带环沿着转子的旋转方向从第一个提到的带环移位。第三带环可释放地连接到转子桅杆以允许相应的转子叶片的折叠。翼梁部分通过具有T或X横截面的抗剪切桥接腹板相互连接。

10. 发明授权

US4153390A Helicopter rotor structure 失效
标题翻译：直升机转子结构
公开(公告)号：US4153390A
公开(公告)日：1979-05-08
申请号：US824093
申请日：1977-08-12
申请人： Emil Weiland
发明人： Emil Weiland
IPC分类号： F04D29/36 , B64C27/33 , B64C27/38
CPC分类号： B64C27/33
摘要： The present rotor structure for rotary wing aircraft, such as helicopters,s constructed to minimize the mass unbalance which normally occurs due to the lead-lag of the rotor blades or wings. For this purpose all the bearings supporting the rotors on the rotor heads are constructed as bearings permitting an axial movement of the tension bars which interconnect the wings of a pair of wings. In addition, the wing interconnecting bars are bending-resistant and connected with each other at their crossing point by a centering device which is freely movable in the rotor plane and relative to the rotor head. The connection of the bars by the centering device is rigid in the longitudinal, axial direction of the tension bars.
摘要翻译：目前用于诸如直升机的旋转翼飞行器的转子结构被构造成使得由于转子叶片或翼的超前滞后而通常发生的质量不平衡被最小化。为此，支撑转子头上的转子的所有轴承都被构造成允许相互连接一对机翼的张力杆的轴向运动的轴承。此外，翼互连杆是抗弯曲的并且在其交叉点处通过定心装置彼此连接，定心装置可在转子平面中并且相对于转子头自由移动。通过定心装置的杆的连接在张力杆的纵向，轴向方向上是刚性的。

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