Helicopter vibration suppression via multiple trailing edge flaps controlled by resonance actuation system

Jun Sik Kim, Edward Smith, K. W. Wang

Research output: Contribution to journalConference article

21 Citations (Scopus)

Abstract

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 (μ=0.15̃0.35). 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%.

Original languageEnglish (US)
Pages (from-to)1611-1622
Number of pages12
JournalAnnual Forum Proceedings - American Helicopter Society
Volume2
StatePublished - Aug 30 2004
Event60th Annual Forum Proceedings - American Helicopter Society - Baltimore, MD, United States
Duration: Jun 7 2004Jun 10 2004

Fingerprint

Flaps
suppression
Helicopters
Actuators
simulation
flight
Turbomachine blades
Aerodynamics
Rotors
Helicopter rotors
Vibration control
Computer simulation

All Science Journal Classification (ASJC) codes

  • Transportation
  • Aerospace Engineering

Cite this

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title = "Helicopter vibration suppression via multiple trailing edge flaps controlled by resonance actuation system",
abstract = "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 (μ=0.15̃0.35). 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{\%}.",
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Helicopter vibration suppression via multiple trailing edge flaps controlled by resonance actuation system. / Kim, Jun Sik; Smith, Edward; Wang, K. W.

In: Annual Forum Proceedings - American Helicopter Society, Vol. 2, 30.08.2004, p. 1611-1622.

Research output: Contribution to journalConference article

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