Abstract: 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.

Abstract: 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.

Abstract: A rotor blade has a neck section which connects the blade proper to a rotor ead 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: The blades or wings of a rotary wing aircraft are secured to the rotor head n 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.

Abstract: 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.

Abstract: A housing for an arrangement of mechanical gears which includes pairs of meshing gears for transmitting driving force between a drive shaft and a driven shaft. The housing comprises a high strength supporting structure carrying bearings for journaling the respective shafts for each of the gears. The supporting structure includes a plurality of individual bending resistant girder members extending between the bearings journaling the shafts for the gears of each pair of meshing gears. The girders which extend between the bearings correspond to and absorb the reaction forces acting between the bearings. The girders have reinforcing chords made of material which is rigid along the longitudinal direction thereof. A protective skin which is unstressed by the reaction forces encloses the entire arrangement of gears and the supporting structure.

Abstract: An elastomeric damping arrangement is constructed to provide a highly efficient damping of the vibrations of a vibration prone member, such as an airfoil, especially a helicopter rotor blade. The damping arrangement is applied directly on or to the vibration prone structural member in the region of dynamic deformation, as an integral component part of the structural member. At least one damping layer is covered by a protecting layer which merges smoothly into the surface of the vibration prone member. The damping layer is made of a viscoelastic material having a high internal damping action. The protecting or cover layer is made of high strength material having a high rigidity in the direction of the occurring damping force.

Abstract: A rotor blade is connected to a rotor hub, for example, in a helicopter, by t least one pair of damping elements and by a blade connector bolt. The damping elements comprise metal discs and layers of elastomeric material arranged in sandwich fashion. The damping elements are arranged symmetrically relative to the rotor blade, as well as to the blade connector bolt. Furthermore, the damping elements are connected in a force transmitting manner to the rotor blade on the one hand and to the rotor hub on the other hand.

Abstract: 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.