Piezoelectric actuating device for controlling the flaps on the rotor blade of a helicopter

US6717333B2 · kind B2 · utility

Assignee

• EADS Deutschland GmbH · DE

Inventors

• Frank Hermle · Munich, DE
• Peter Jaenker · Garching bei München, DE

Key dates

• Filing date: Sep 16, 2002
• Grant date: Apr 6, 2004
• Expiry date: Sep 16, 2022

Classification

• Technology area (CPC Y): Emerging Cross-Sectional Technologies
• CPC primary: Y02T50/30
• WIPO field: Transport
• WIPO sector: Mechanical engineering

Abstract

A piezoelectric actuating device for controlling a flap on a rotor blade of a helicopter includes a piezo element arrangement including at least one piezoelectric stack actuator. A power transmission frame is coupled to the piezo element arrangement, the power transmission frame including an abutment and a driven element and generating a force therebetween from a change in length of the piezo element arrangement upon an excitation thereof, the force acting transversely to a direction of a centrifugal force of the rotor blade. A first holding device is provided including a pair of first flexible straps configured to fix the power transmission frame relative to the rotor blade in the direction of the centrifugal force and to allow the power transmission frame to move relative to the rotor blade transversely to the direction of the centrifugal force within a limited range. A second holding device is provided including a pair of second flexible straps configured to fix the abutment relative to the rotor blade transversely to the direction of the centrifugal force and to allow the abutment to move relative to the rotor blade in the direction of the centrifugal force within a limited ran…