公开(公告)号：US6004099A

公开(公告)日：1999-12-21

申请号：US861199

申请日：1997-05-21

申请人： Horst Bansemir ,  Gerhard Hausmann

发明人： Horst Bansemir ,  Gerhard Hausmann

IPC分类号： B64C27/33 ,  B64C27/51

CPC分类号： B64C27/33

摘要： The helicopter rotor blade connection has a support beam which connects the lift-generating wing section of the rotor blade with the rotor hub, and transmits centrifugal and lateral forces as well as bending and torsional moments. The connection is torsionally elastic and, at least in a main plane, bending elastic. A damping device for damping bending vibrations of the support beam is constructed alternately of elastomer layers and intermediate layers which are stiff in the direction of their extension. According to the invention, the damping device consists of a plurality of separate individual dampers which are arranged with their elastomer and intermediate layers in the direction of the main bending plane of the support beam. The individual dampers are in each case integrated in the support beam structure in slots extending from the exterior edge into the support beam interior essentially in parallel to one another, while the two exterior elastomer layers of each individual damper are coextensively bound to the adjoining support beam sections.

摘要翻译： 直升机转子叶片连接件具有将转子叶片的发电机翼部分与转子轮毂连接的支撑梁，并且传递离心力和横向力以及弯曲力矩。 该连接是扭转弹性的，并且至少在主平面中弯曲弹性。 用于阻尼支撑梁的弯曲振动的阻尼装置交替地由弹性体层和中间层构成，它们在其延伸方向上是刚性的。 根据本发明，阻尼装置由多个单独的阻尼器组成，它们在其支撑梁的主弯曲平面的方向上布置有它们的弹性体和中间层。 各个阻尼器在每种情况下都集成在支撑梁结构中，在从外部边缘延伸到基本上彼此平行的支撑梁内部的槽中，而每个单独的阻尼器的两个外部弹性体层共同地结合到相邻的支撑梁 部分。

公开(公告)号：US06886779B2

公开(公告)日：2005-05-03

申请号：US10691005

申请日：2003-10-22

申请人： Horst Bansemir ,  Jyrki Majamaeki ,  Walter Oefner ,  Anton Bergmann

发明人： Horst Bansemir ,  Jyrki Majamaeki ,  Walter Oefner ,  Anton Bergmann

IPC分类号： B64C27/00 ,  F16F7/12 ,  B64D27/00

CPC分类号： B64C27/006 ,  F16F7/12

摘要： An impact-absorbing, load-limiting connection device includes a first connection structure, a second connection structure, a guiding mechanism, and at least one impact-absorbing, load-limiting sacrificial element disposed between the first and second connection structure. At least one of the first and second connection structures is moveable with respect to the other in a predetermined direction of movement corresponding to an anticipated main impact direction. The guiding mechanism is configured to guide at least one of the first and second connection structures along the direction of movement and includes at least one transverse force-absorbing guide element configured to absorb a force in a direction transverse to the direction of movement. The sacrificial element is disposed as to be uncoupled from a transverse load path of the transverse force-absorbing guide element, and is configured to be deformed and destroyed by a relative movement between the first and second connection structures upon application of predetermined maximum load. In addition, a rotary-wind aircraft, especially a helicopter, that includes at least one such connection device.

摘要翻译： 冲击吸收负载限制连接装置包括第一连接结构，第二连接结构，引导机构以及设置在第一和第二连接结构之间的至少一个冲击吸收负载限制性牺牲元件。 所述第一和第二连接结构中的至少一个可以相对于另一个沿预定的主冲击方向的预定运动方向移动。 引导机构构造成沿着移动方向引导第一和第二连接结构中的至少一个，并且包括至少一个横向力吸收引导元件，其构造成沿横向于移动方向的方向吸收力。 牺牲元件被设置为与横向吸力引导元件的横向负载路径分离，并且被构造成在施加预定的最大负载时通过第一和第二连接结构之间的相对运动而变形和破坏。 另外，包括至少一个这样的连接装置的旋转式飞机，特别是直升机。

公开(公告)号：US06427945B1

公开(公告)日：2002-08-06

申请号：US09570355

申请日：2000-05-12

申请人： Horst Bansemir

发明人： Horst Bansemir

IPC分类号： B64C100

CPC分类号： B64C1/062 ,  B64C1/18

摘要： A subfloor structure of an aircraft airframe, particularly of a helicopter, includes longitudinal beams and crossbeams that intersect each other and are interconnected to form a grid that is fixedly attached to the floor and the bottom skin of the aircraft fuselage. Structural elements such as pyramid frustums and reinforcements are arranged on the beams. The longitudinal beam and the crossbeam have a trapezoidal cross-section that is preferably open on the wider base side, closed by a spine web along the narrow side, and bounded laterally by inclined leg webs that extend downwardly from the spine web at an angle outwardly relative to each other. The subfloor structure grid effectively absorbs the energy of a crash impact having both axial or vertical as well as non-axial or lateral impact force components.

摘要翻译： 飞机机身的地板结构，特别是直升机的底板结构包括彼此相交的纵向梁和横梁，并且互相连接以形成固定地连接到飞机机身的地板和底部皮肤上的格栅。 结构元件如棱锥体和加强件被布置在梁上。 纵向梁和横梁具有梯形横截面，该横截面优选地在更宽的基部侧开口，由沿着窄边的脊柱腹部封闭，并且由倾斜的腿腹板横向限定，该腿部腹板从脊柱腹向下延伸一定角度向外 相对于彼此。 地下结构网格有效地吸收具有轴向或垂直以及非轴向或横向冲击力分量的碰撞冲击的能量。

公开(公告)号：US5618076A

公开(公告)日：1997-04-08

申请号：US423509

申请日：1995-04-17

申请人： Horst Bansemir ,  Bernd Bongers ,  Hermann Eschbaumer

发明人： Horst Bansemir ,  Bernd Bongers ,  Hermann Eschbaumer

IPC分类号： B60B17/00 ,  B60B19/00

CPC分类号： B60B17/00 ,  B60B17/0003 ,  B60B17/0034

摘要： In the case of a rail wheel having a wheel disk made of plastic and a tire made of metal, these are connected with one another by way of a metallic intermediate ring onto which the tire is shrunk. In this case, the wheel disk has a conical cross-sectional profile on its circumference and the intermediate ring, which is form-locking therewith, is axially divided into two partial rings with a correspondingly partially conical interior surface. The partial rings are in a mutual force-locking connection and are glued to the wheel disk. This ensures a double safety connection between the intermediate ring and the wheel disk.

摘要翻译： 在具有由塑料制成的轮盘和由金属制成的轮胎的轨道轮的情况下，它们通过其上收缩的金属中间环彼此连接。 在这种情况下，轮盘在其圆周上具有锥形横截面轮廓，并且与其形成锁定的中间环轴向地分成具有相应部分圆锥形内表面的两个部分环。 部分环处于相互的力锁定连接并且胶合到轮盘。 这确保了中间环和轮盘之间的双重安全连接。

公开(公告)号：US06361278B1

公开(公告)日：2002-03-26

申请号：US09738222

申请日：2000-12-15

申请人： Horst Bansemir

发明人： Horst Bansemir

IPC分类号： B64C2732

摘要： A helicopter gimbal rotor arrangement includes a drive shaft with a rotor hub, a rotor blade holder arrangement, and a coupling membrane for transmitting the rotational drive moment from the rotor hub to the rotor blade holder arrangement. The coupling membrane includes a plate element made up of a plurality of concentric rings that are spaced apart radially by annular gaps and are connected to each other by respective connecting webs spanning across the gaps. This plate element as the coupling membrane provides torsional stiffness combined with bending flexibility to allow tilting motions of the rotor blade holder arrangement relative to the rotor hub. Plural plate elements connected in parallel provide a redundant fail-safe arrangement, while plural plate elements connected in series achieve increased flexibility for out-of-plane tilting.

公开(公告)号：US06286782B1

公开(公告)日：2001-09-11

申请号：US09184548

申请日：1998-11-02

申请人： Horst Bansemir ,  Bernd Bongers

发明人： Horst Bansemir ,  Bernd Bongers

IPC分类号： B64C2700

CPC分类号： F16F7/104 ,  B64C27/001 ,  B64C2027/005 ,  F16F7/1028 ,  F16F2224/0241

摘要： Apparatus for damping vibrations of a structure such as the air frame of a helicopter wherein a spring system (1), which has an elastic wall structure forming a tube-shaped hollow body supports a weighted vibrating object (23). At least one region of the wall structure is constructed to be elastically deformable in its plane, with a spring stiffness, tuned to the frequency of the vibration to be damped. The wall structure is formed by several planar spring elements (11a, 11b, 11c, 11d), each of which can be elastically deformed in its plane by an arrangement of longitudinal strips (110a, 110b, 111a, 111b) and connecting cross pieces (120a, 120b, 121a, 121b). A battery of the helicopter can be used as the vibrating weight (23). The vibration damper containing the battery is installed at a location on the helicopter where clear structural vibrations occur in two directions perpendicular to each other and wherein the vibration damper is tuned to the vibrations frequencies in both directions.

摘要翻译： 用于减轻直升机的空气框架的结构的振动的装置，其中具有形成管状中空体的弹性壁结构的弹簧系统（1）支撑加权振动物体（23）。 壁结构的至少一个区域被构造成在其平面中可弹性变形，弹簧刚度被调谐到被阻尼的振动的频率。 壁结构由几个平面弹簧元件（11a，11b，11c，11d）形成，每个平面弹簧元件（11a，11b，11c，11d）可以通过纵向条（110a，110b，111a，111b）和连接横梁 120a，120b，121a，121b）。 可以使用直升机的电池作为振动锤（23）。 包含电池的振动阻尼器安装在直升机上的相互垂直的两个方向上发生明显的结构振动的位置处，并且其中振动阻尼器被调谐到两个方向上的振动频率。

公开(公告)号：US6039538A

公开(公告)日：2000-03-21

申请号：US5551

申请日：1998-01-12

申请人： Horst Bansemir

发明人： Horst Bansemir

IPC分类号： B64C27/35 ,  B64C27/32 ,  B64C27/33

CPC分类号： B64C27/32 ,  B64C27/33

摘要： A multi-blade rotor arrangement free of flapping hinges, for a rotary wing aircraft, includes a rotor head plate (2) made of fiber-reinforced composite material. The head plate (2) includes a plurality of blade connection arms (4) that are elastically flexibly bendable in the blade flapping direction, and at least one plate segment (16, 18) that holds each blade connection arm on two sides thereof radially spaced away from the rotor center in a manner that allows elastic bending in the blade flapping direction. The plate segment is rigidly connected to the rotor mast (122, 222) at mounting locations (20) that are offset in the circumferential direction from the blade connection arms. In this manner, the elastically yielding flapping connection between the rotor blades and the rotor mast is provided by both the elastic bending of the blade connection arms and the elastic deformation of the plate segment portions between the blade connection arms and the mast mounting locations. The fictitious flapping hinges formed thereby may be located relatively close to the rotor center, namely spaced away from the rotor center by about 5% of the rotor radius.

摘要翻译： 对于旋转飞行器而言，没有摆动铰链的多叶片转子装置包括由纤维增强复合材料制成的转子头板（2）。 头板（2）包括多个叶片连接臂（4），其在叶片拍动方向上弹性挠曲地弯曲;以及至少一个板段（16,18），其将每个叶片连接臂的两侧径向隔开 远离转子中心的方式允许在叶片拍动方向上弹性弯曲。 在从叶片连接臂沿圆周方向偏移的安装位置（20）处，板段刚性地连接到转子桅杆（122,222）。 以这种方式，通过叶片连接臂的弹性弯曲和叶片连接臂和桅杆安装位置之间的板段部分的弹性变形两者来提供转子叶片和转子桅杆之间的弹性屈服振荡连接。 由此形成的虚构的扑翼铰链可以位于相对靠近转子中心的位置，即与转子中心分开约5％的转子半径。

公开(公告)号：US20060193727A1

公开(公告)日：2006-08-31

申请号：US10551007

申请日：2003-12-13

申请人： Ulrich Denecke ,  Gerald Kuntze-Fechner ,  Horst Bansemir ,  Stefan Emmerling

发明人： Ulrich Denecke ,  Gerald Kuntze-Fechner ,  Horst Bansemir ,  Stefan Emmerling

IPC分类号： B64C27/46

CPC分类号： B64C27/33

摘要： A twist element for a bearingless rotor is made mostly of composite fiber material and has a cross section with a substantially symmetric, flattened shape that has approximately the contour of a horizontal, central section of a double cone. In addition, a bearingless rotor having at least one such twist element. and a rotorcraft, particularly a helicopter, having at least one rotor with at least one such twist element are provided.

摘要翻译： 用于无轴承转子的扭转元件主要由复合纤维材料制成，并且具有基本对称的扁平形状的横截面，其大致具有双锥体的水平中心部分的轮廓。 另外，具有至少一个这种扭转元件的无轴承转子。 并且提供具有至少一个具有至少一个这种扭转元件的转子的旋翼航空器，特别是直升机。

公开(公告)号：US06305640B1

公开(公告)日：2001-10-23

申请号：US09341195

申请日：1999-08-16

申请人： Horst Bansemir

发明人： Horst Bansemir

IPC分类号： F01D500

CPC分类号： B64C27/48 ,  B64C27/33

摘要： A spring component for support bearings of helicopter tail rotors or for support structures for use in outer space encompasses at least two contact support components (11a, 11b) for connecting with the members that are to be supported (e.g. a belt and a control sleeve of a helicopter tail rotor), as well as a web plate (20), which extends between the contact support components (11a, 11b) and which includes a pair of lengthwise webs (21a, 21b) extending in a longitudinal direction. The lengthwise webs are connected to each other by first connecting webs (22a, 22b). Respectively, a further connecting web (23a, 23b) is arranged at a section of the two lengthwise webs (21a, 21b) positioned between the first connecting webs (22a, 22b), wherein each further connecting web extends outwardly toward one of the support components (11a, 11b). In connection with a transverse bending moment acting on the spring component, a twisting of the lengthwise webs (21a, 21b) takes place. The spring component is flexible for transverse bending and comprises a high supporting force. A support bearing for a helicopter tail rotor or a support structure for use in outer space encompasses two or more of the spring components. In a control sleeve bearing of a helicopter tail rotor the belt is held in the control sleeve between two oppositely positioned spring components.

摘要翻译： 用于直升机尾部转子或用于外部空间的支撑结构的支撑轴承的弹簧部件包括用于与要被支撑的构件（例如，带和控制套管）的至少两个接触支撑部件（11a，11b） 直升机尾部转子）以及在所述接触支撑部件（11a，11b）之间延伸并且包括在纵向方向上延伸的一对纵向腹板（21a，21b）的腹板（20）。 纵向腹板通过第一连接腹板（22a，22b）彼此连接。 分别地，在位于第一连接腹板（22a，22b）之间的两个纵向腹板（21a，21b）的一部分处布置有另一个连接腹板（23a，23b），其中每个另外的连接腹板朝着支撑件 部件（11a，11b）。 关于作用在弹簧部件上的横向弯曲力矩，发生纵向腹板（21a，21b）的扭转。 弹簧部件对于横向弯曲是柔性的，并且包括高支撑力。 用于直升机尾部转子或用于外部空间的支撑结构的支撑轴承包括两个或更多个弹簧部件。 在直升机尾部转子的控制套筒轴承中，皮带保持在控制套筒中两个相对定位的弹簧部件之间。

公开(公告)号：US07296975B2

公开(公告)日：2007-11-20

申请号：US10551007

申请日：2003-12-13

申请人： Ulrich Denecke ,  Gerald Kuntze-Fechner ,  Horst Bansemir ,  Stefan Emmerling

发明人： Ulrich Denecke ,  Gerald Kuntze-Fechner ,  Horst Bansemir ,  Stefan Emmerling

IPC分类号： B64C11/12

CPC分类号： B64C27/33

摘要： A twist element for a bearingless rotor is made mostly of composite fiber material and has a cross section with a substantially symmetric, flattened shape that has approximately the contour of a horizontal, central section of a double cone. In addition, a bearingless rotor having at least one such twist element, and a rotorcraft, particularly a helicopter, having at least one rotor with at least one such twist element are provided.

摘要翻译： 用于无轴承转子的扭转元件主要由复合纤维材料制成，并且具有基本对称的扁平形状的横截面，其大致具有双锥体的水平中心部分的轮廓。 此外，提供了具有至少一个这种扭转元件的无转子转子和具有至少一个具有至少一个这种扭转元件的转子的旋翼航空器，特别是直升机。