An active vibration control method for the multiple trailing-edge flaps configuration is proposed and evaluated via simulation. The concept involves deflecting each individual trailing-edge flap using a compact resonance actuation system. Each resonance actuation system yields high authority, while operating at a single frequency. An aeroelastic model is developed for a helicopter rotor with trailing edge flaps. The rotor blade airloads are calculated using quasi-steady blade element aerodynamics with a free wake model for rotor inflow. A compressible unsteady aerodynamics model is employed to predict the incremental trailing edge flap airloads. Both finite wing effects and actuator saturation are included in the simulation. A numerical simulation has been performed for the resonance actuation system tuned to 4/rev frequency and the steady-state forward flight (My = 0.15-0.35). It is demonstrated that multiple trailing-edge flap configuration with the resonance actuation system can outperform single- and dual-flap configurations by achieving more vibration reduction within available actuator authority. An analysis and parametric study is conducted to explore the finite wing effect of trailing-edge flaps and actuator saturation. Within the available actuator authority, multiple-flap configuration reduces the vibration by 91 % and 79 %, in low- and high-speed flight conditions, while single-flap one does it by 35 % and 56 %.
Helicopter vibration suppression via multiple trailing edge flaps controlled by resonance actuation system
Schwingungsunterdrückung bei Hubschraubern mittels multipler Hinterkantenklappen und Resonanzansteuerung
AHS International Forum, 60 ; 1611-1622
2004
12 Seiten, 22 Bilder, 4 Tabellen, 27 Quellen
Conference paper
English
British Library Conference Proceedings | 2004
|Helicopter Vibration Reduction with Trailing Edge Flaps
British Library Conference Proceedings | 1995
|Helicopter Vibration Reduction with Trailing Edge Flaps
British Library Conference Proceedings | 1995
|Helicopter Vibration Reduction with Trailing Edge Flaps
British Library Conference Proceedings | 1995
|Helicopter vibration reduction with trailing edge flaps
AIAA | 1995
|