The paper presents an approach for the active control of structural response (ACSR) and its implementation in a system for vibration reduction in a helicopter fuselage. Vibrations in the fuselage are simulated analytically using a recently derived coupled rotor/flexible fuselage aeroelastic response model. Baseline fuselage vibrations, are sensed as vibratory components of the acceleration at specific fuselage locations. These quantities are used to generate signals to four servo actuators located at the four corners of the ACSR platform. The servo actuators produce controlled vibratory forces, which when combined with the vibratory rotor loads produce vibration levels at various fuselage locations which are much lower than the baseline vibrations. The vibration levels, in the presence of the controller, display very substantial vibration reduction. This vibration suppression system, operates exclusively in the hub fixed nonrotating system, and therefore has no influence on vehicle airworthiness.
ACSR system for vibration suppression in coupled helicopter rotor/flexible fuselage model
System der aktiven Steuerung des strukturellen Verhaltens für die Schwingungsunterdrückung in einem gekoppelten Modell Hubschrauberrotor/flexibler Rumpf
1996
19 Seiten, 16 Bilder, 2 Tabellen, 20 Quellen
Conference paper
English
ACSR System for Vibration Suppression in Coupled Helicopter Rotor/Flexible Fuselage Models
British Library Conference Proceedings | 1996
|British Library Conference Proceedings | 1996
|A coupled helicopter rotor/fuselage aeroelastic response model for ACSR
Tema Archive | 1995
|A Coupled Helicopter Rotor/Fuselage Aeroelastic Response Model for ACSR
British Library Conference Proceedings | 1995
|