Abstract: A multi-blade rotor of a rotary wing aircraft, the multi-blade rotor comprising at least one rotor blade that defines a pitch axis and that is provided with an associated pitch-control lever that is operatively coupled to a pitch link rod, the pitch link rod defining a longitudinal axis, wherein the associated pitch-control lever comprises an accommodation that is located on the longitudinal axis of the pitch link rod at a predetermined distance from the pitch axis of the at least one rotor blade, the pitch link rod being operatively coupled to the associated pitch-control lever at the accommodation of the associated pitch-control lever, wherein the predetermined distance is adjustable in order to enable adjustment of track and balance of the multi-blade rotor.

Abstract: A vibration isolating device that is adapted for an elastic coupling of a first component to a second component and for vibration isolation in predetermined frequency ranges between the first and second components, the vibration isolating device comprising at least a first and a second elastically deformable plate that are attached to each other in at least two separate connecting points, the first elastically deformable plate comprising a first curvature and the second elastically deformable plate comprising a second curvature, wherein the first and second curvatures are respectively located in a region between the at least two separate connecting points and arranged such that a gap is defined between the first and second elastically deformable plates.

Abstract: A composite laminate for connection to at least one attachment component in a load-introduction joint, said composite laminate comprising an opening that is adapted to receive a load-introduction component of said load-introduction joint, wherein a prefailure indication element is provided in the region of said opening, said prefailure indication element being modifiable by said load-introduction component in a prefailure mode of said load-introduction joint for indication of an impending function-affecting failure of said composite laminate. The invention is further related to a corresponding load-introduction component.

Abstract: A flexbeam unit for a multi-blade rotor of a rotary wing aircraft, the flexbeam unit comprising a plurality of flexbeam elements defining a predetermined number of torsion elements that are connectable with associated rotor blades of the multi-blade rotor, at least one of the predetermined number of torsion elements comprising at least one flexbeam element having an associated longitudinal direction, the at least one flexbeam element comprising at least one twisted area in which the at least one flexbeam element is twisted in the associated longitudinal direction.

Abstract: A bearing arrangement with a first bearing layer comprising a first bearing support element and a second bearing layer comprising a second bearing support element, the first and second bearing layers being glidingly interconnected by at least one intermediate gliding element, wherein at least one first gliding surface is arranged between the first bearing support element and the at least one intermediate gliding element, and wherein at least one second gliding surface is arranged between the second bearing support member and the at least one intermediate gliding element, the at least one intermediate gliding element being elastically attached to the first bearing support element by means of at least one first flexible connector and to the second bearing support element by means of at least one second flexible connector.

Abstract: A beam for a rotorcraft rotor and particularly to a helicopter rotor. Said beam comprises a hub connection portion, a blade connection portion, a first flexure portion located between the hub connection portion and the blade connection portion and having a bending stiffness about a first axis which is orthogonal to the longitudinal axis of the blade, said bending stiffness being smaller than that of the hub connection portion and that of the blade connection portion and a shear portion located between the hub connection portion and the blade connection portion and having a shear stiffness parallel to a second axis which is orthogonal to the longitudinal axis of the blade and non-parallel to the first axis. Said shear stiffness is smaller than that of the hub connection portion and that of the blade connection portion.