Airbus Helicopters Deutschland Gmbh

Victoria Otto

Gerald Kuntze-Fechner

Rupert Pfaller

Martin Ortner

Christeline Salmon

Eugen Rink

Julius Vogl

A pitch control device for a ducted tail rotor of a rotorcraft. The pitch control device comprises a control input member with a disc-shaped central component and at least two connecting arms that extend radially from the disc-shaped central component, wherein the disc-shaped central component is provided for being mounted to an associated pitch control shaft of the ducted tail rotor, and a control transfer member with a ring-shaped connector and at least two push rods that extend axially from the ring-shaped connector, wherein each one of the at least two push rods is provided for being coupled to an associated pitch lever of a rotor blade of the ducted tail rotor.

Pitch control device for a ducted tail rotor of a rotorcraft

A multi-blade rotor for a rotary wing aircraft, comprising a plurality of rotor that is connected to an associated rotor head via a plurality of flexbeam elements, wherein at least one flexbeam element of the plurality of flexbeam elements comprises an asymmetrical flexbeam root that is mounted to the associated rotor head.

Multi-blade rotor for a rotary wing aircraft

Growing community of inventors

Aix en Provence, France

Victoria Otto