High torque actuation system for an active rotor control system

US6196796A · kind A · utility

Assignee

• SIKORSKY AIRCRAFT CORPORATION · US

Inventors

• Steven A. Lozyniak · South Windsor, US
• Peter F. Lorber · Coventry, US
• Fred W. Kohlhepp · Hamden, US
• Lee A. Hoffman · Vernon, US
• Robert D. Morton · Kingwood, US
• Richard B. Ferraro · Northford, US

Key dates

• Filing date: Apr 22, 1999
• Grant date: Mar 6, 2001
• Expiry date: Apr 22, 2019

Classification

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

Abstract

An actuation system for pivoting a flap on a helicopter rotor blade to reduce the interaction of the blade with the preceding blade vortex. The actuation system includes a fluid supply which is connected to first and second fluid supply lines. The fluid supply lines convey flows of pressurized fluid from the fluid supply to an actuator. The actuator includes a housing mounted within the rotor blade and having a channel formed in it. A butterfly shaft is pivotally mounted within the channel and has laterally extending arms which separate the channel into four lobes. A first port connects the first fluid supply line with two diametrically opposed lobes in the channel. A second port connects the second fluid supply line with the other two diametrically opposed lobes in the channel. A torque coupling is attached to the butterfly shaft and engaged with the flap such that rotation of the torque coupling produces concomitant rotation of the flap. The pressurization of the first fluid supply line causes the torque coupling to rotate in a first direction. The pressurization of the second supply fluid line causes the torque coupling to rotate in the opposite direction.