Rotor blade connection

US6004099A · kind A · utility

Assignee

• Daimler-Benz Aerospace AG · DE

Inventors

• Horst Bansemir · Munich, DE
• Gerhard Hausmann · Hersbruck, DE

Key dates

• Filing date: May 21, 1997
• Grant date: Dec 21, 1999
• Expiry date: May 21, 2017

Classification

• Technology area (CPC B): Performing Operations; Transporting
• CPC primary: B64C27/33
• WIPO field: Transport
• WIPO sector: Mechanical engineering

Abstract

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.