Helicopter rotor control system with individual blade control

US8201771B2 · kind B2 · utility

Assignee

• ZF FRIEDRICHSHAFEN AG · DE

Inventors

• Christoph Kessler · Munich, DE
• Daniel Furst · Kassel, DE

Key dates

• Filing date: Jan 7, 2011
• Grant date: Jun 19, 2012
• Expiry date: Feb 2, 2031

Classification

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

Abstract

A method of controlling rotor pitch in a helicopter comprising the steps of: generating at least one blade dynamics signal representing at least one dynamic force acting on at least one of a rotor blade rotating assembly and a helicopter non-rotating assembly, the rotor blade rotating assembly including a plurality of rotor blades and a pitch actuator for each rotor blade; extracting information representing the at least one dynamic force; generating a dynamic force compensation output representing a compensation for at least a portion of the at least one dynamic force; receiving flight control signals directing flight of the helicopter from flight controls of the helicopter; generating from the flight control signals and the dynamic force compensation output a compensated pitch control signal for each blade of the rotor blade rotating assembly, and providing a compensated pitch control signal to compensate for a portion of the at least one dynamic force.