Messerschmitt-Boelkow-Blohm Gesellschaft MIT Beschraenkter Haftung

Messerschmitt-Boelkow-Blohm Gmbh

Messerschmitt-Bolkow-Blohm Gmbh

Messerschmitt-Bolkow-Blohm Gesellschaft MIT Beschrankter Haftung

Hubert Frommlet

Alois Schwarz

Emil Weiland

Karl-Heinz Mautz

Klaus Brunsch

Michael Hahn

Karlheinz Mautz

Hans Derschmidt

Ludwig Stangl

A flexible blade neck of a helicopter rotor blade is bridged by a torsion gid sleeve for the blade angle adjustments. The radially outer end of the blade neck and sleeve are rigidly connected to the wing section of the blade. The radially inner end of the blade neck forms a blade root which is secure to the rotor head or hub. Additionally, the radially inner ends of the blade root and of the sleeve are interconnected by a ball and socket arrangement permitting a universal movement between the sleeve and the blade neck, thereby decoupling sleeve movements from the blade neck and vice versa.

Wing mounting for a rotary wing aircraft

The wing blades of a helicopter rotor each are connected to the rotor hub a connection, e.g. a spar being .fwdarw..rarw. including a hinge which is at least fictitious to permit lead-lag movements of the blades &lt;yielding relative to torsion to permit the blade angle adjustment&gt;. A rod, which is stiff in the lead-lag direction and yielding against torsion, is connected in parallel to the connection between the blade root and the rotor hub. One connection of the rod is rigid, for example the connection to the blade root. The other connection of the rod is elastically yielding substantially only in the plane of the rotor whereby a substantial damping of blade movements in the lead-lag direction is accomplished.

Damping device for a helicopter rotor blade

The wing blades of a hingeless and bearingless multiblade rotor are connected to a substantially rigid rotor hub by spar sections elastically twistable and bendable in the flapping direction and in the lead-lag direction. The mounting positions on the periphery of the rotor hub for connection of the spar sections of the respective blades are off-set relative to the angular position of the corresponding blades to which they are connected. Further, the mounting positions for the spar sections of each rotor blade are situated on the periphery of the half side or far side of the rotor hub, facing away from the respective rotor blade. A rear spar section of each mounted rotor blade with reference to the direction of rotation, overlaps the front spar section of the immediately following rotor blade but with free clearance and spacing between the overlapping spar sections in the direction of the rotor axis so that the maximum bendable length of the elastic spar sections is afforded without interference between the blades. The effective or virtual flapping hinges and lead-lag hinges of each blade is shifted closer to the rotor axis thereby minimizing the masses necessary for propeller moment compensation, and static and dynamic balancing of the rotor blades, as well as reducing the required steering forces.

Hingeless and bearingless multiblade rotor for rotary wing aircraft

A bearing seal for the outer and inner blade angle bearings of a rotor hub of a rotary wing aircraft comprises a lubricating oil chamber interconnecting the inner and outer bearings and extending coaxially therebetween. The bearings are provided with sealing rings at their faces opposite the lubricating oil chamber. A shielding member is positioned in front of the face of the outer blade angle bearing facing the lubricating oil chamber. A receptacle is arranged as part of the chamber and positioned in operative relationship with the deflector member for entrapping particles contained in the lubricating oil and separated therefrom by the effect of centrifugal forces as the oil migrates from the inner blade angle bearing toward the outer bearing.

Bearing seal and lubricating device

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.

Apparatus for connecting a rotor blade to a rotor hub

One of two races of a roller bearing is equipped with a sliding ring exteng thereabout, with a melting ring formed of material having a melting point higher than the normal operating temperature of the bearing being interposed between the one race and the sliding ring. Malfunction of the bearing such as might occur by seizure of the bearing rollers will cause at least partial melting of the melting ring whereupon the one race is placed in relative sliding engagement through the melting ring with the sliding ring.

Roller bearing assembly with failsafe mechanism

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.

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Siegertsbrunn, Germany

Hubert Frommlet