Helicopter rotor control system with individual blade control

US7900869B2 · kind B2 · utility

Assignee

• ZF FRIEDRICHSHAFEN AG · DE

Inventors

• Christoph Keβler · Braunschweig, DE
• Daniel Furst · Kassel, DE

Key dates

• Filing date: May 6, 2005
• Grant date: Mar 8, 2011
• Expiry date: May 21, 2028

Classification

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

Abstract

Controlling the pitch of individual rotor blades of a helicopter to reduce control loads, vibration and noise in or from the rotating rotor control elements. The system generates blade dynamics signals representing dynamic forces acting on either or both of the rotating and non-rotating elements of the helicopter, including rotor blades of a rotating assembly. The system extracts information representing at least one dynamic force, generates a dynamic force compensation output that represents a compensation for the dynamic force, and generates, from flight control signals and the dynamic force compensation output, a compensated pitch actuator control signal for each rotor blade wherein the compensation factor of the pitch control signal compensates for the dynamic force.