Active load control of an articulated composite rotor blade via dual trailing edge flaps

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

Research output: Chapter in Book/Report/Conference proceedingConference contribution

1 Citation (Scopus)

Abstract

A new active load control method for blade bending moment reduction is introduced and evaluated via simulation. The concept involves straightening the blade by introducing dual trailing edge flaps in a conventional articulated rotor blade. An aeroelastic model is developed for a helicopter composite rotor with trailing edge flaps, and the rotor blade airloads are calculated using quasisteady blade element aerodynamics. Classical incompressible theory is employed to predict the incremental trailing edge flap airloads. The objective function, which includes vibratory hub loads, bending moment harmonics and active flap control inputs, is minimized by an integrated optimal control/optimization process. A numerical simulation has been performed for the steady-state forward flight of advance ratio 0.35. It is demonstrated that through straightening the rotor blade, which mimics the behavior of a rigid blade, both the bending moments and vibratory hub loads can be significantly reduced. The proposed active load control method with 1/rev control input can reduce the flapwise bending moment by 32% and the vibratory hub loads by 57%, simultaneously, without a significant change of trim condition. Hybrid design yields a 25% reduction of the required flap deflection when compared to the pure active control.

Original languageEnglish (US)
Title of host publication44th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
StatePublished - Dec 1 2003
Event44th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference 2003 - Norfolk, VA, United States
Duration: Apr 7 2003Apr 10 2003

Publication series

Name44th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

Other

Other44th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference 2003
CountryUnited States
CityNorfolk, VA
Period4/7/034/10/03

Fingerprint

Bending moments
Turbomachine blades
Rotors
Straightening
Composite materials
Helicopters
Aerodynamics
Computer simulation

All Science Journal Classification (ASJC) codes

  • Civil and Structural Engineering
  • Mechanics of Materials
  • Building and Construction
  • Architecture

Cite this

Kim, J. S., Smith, E., & Wang, K. W. (2003). Active load control of an articulated composite rotor blade via dual trailing edge flaps. In 44th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference (44th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference).
Kim, Jun Sik ; Smith, Edward ; Wang, K. W. / Active load control of an articulated composite rotor blade via dual trailing edge flaps. 44th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference. 2003. (44th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference).
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abstract = "A new active load control method for blade bending moment reduction is introduced and evaluated via simulation. The concept involves straightening the blade by introducing dual trailing edge flaps in a conventional articulated rotor blade. An aeroelastic model is developed for a helicopter composite rotor with trailing edge flaps, and the rotor blade airloads are calculated using quasisteady blade element aerodynamics. Classical incompressible theory is employed to predict the incremental trailing edge flap airloads. The objective function, which includes vibratory hub loads, bending moment harmonics and active flap control inputs, is minimized by an integrated optimal control/optimization process. A numerical simulation has been performed for the steady-state forward flight of advance ratio 0.35. It is demonstrated that through straightening the rotor blade, which mimics the behavior of a rigid blade, both the bending moments and vibratory hub loads can be significantly reduced. The proposed active load control method with 1/rev control input can reduce the flapwise bending moment by 32{\%} and the vibratory hub loads by 57{\%}, simultaneously, without a significant change of trim condition. Hybrid design yields a 25{\%} reduction of the required flap deflection when compared to the pure active control.",
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Kim, JS, Smith, E & Wang, KW 2003, Active load control of an articulated composite rotor blade via dual trailing edge flaps. in 44th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference. 44th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, 44th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference 2003, Norfolk, VA, United States, 4/7/03.

Active load control of an articulated composite rotor blade via dual trailing edge flaps. / Kim, Jun Sik; Smith, Edward; Wang, K. W.

44th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference. 2003. (44th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference).

Research output: Chapter in Book/Report/Conference proceedingConference contribution

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AU - Smith, Edward

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N2 - A new active load control method for blade bending moment reduction is introduced and evaluated via simulation. The concept involves straightening the blade by introducing dual trailing edge flaps in a conventional articulated rotor blade. An aeroelastic model is developed for a helicopter composite rotor with trailing edge flaps, and the rotor blade airloads are calculated using quasisteady blade element aerodynamics. Classical incompressible theory is employed to predict the incremental trailing edge flap airloads. The objective function, which includes vibratory hub loads, bending moment harmonics and active flap control inputs, is minimized by an integrated optimal control/optimization process. A numerical simulation has been performed for the steady-state forward flight of advance ratio 0.35. It is demonstrated that through straightening the rotor blade, which mimics the behavior of a rigid blade, both the bending moments and vibratory hub loads can be significantly reduced. The proposed active load control method with 1/rev control input can reduce the flapwise bending moment by 32% and the vibratory hub loads by 57%, simultaneously, without a significant change of trim condition. Hybrid design yields a 25% reduction of the required flap deflection when compared to the pure active control.

AB - A new active load control method for blade bending moment reduction is introduced and evaluated via simulation. The concept involves straightening the blade by introducing dual trailing edge flaps in a conventional articulated rotor blade. An aeroelastic model is developed for a helicopter composite rotor with trailing edge flaps, and the rotor blade airloads are calculated using quasisteady blade element aerodynamics. Classical incompressible theory is employed to predict the incremental trailing edge flap airloads. The objective function, which includes vibratory hub loads, bending moment harmonics and active flap control inputs, is minimized by an integrated optimal control/optimization process. A numerical simulation has been performed for the steady-state forward flight of advance ratio 0.35. It is demonstrated that through straightening the rotor blade, which mimics the behavior of a rigid blade, both the bending moments and vibratory hub loads can be significantly reduced. The proposed active load control method with 1/rev control input can reduce the flapwise bending moment by 32% and the vibratory hub loads by 57%, simultaneously, without a significant change of trim condition. Hybrid design yields a 25% reduction of the required flap deflection when compared to the pure active control.

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M3 - Conference contribution

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Kim JS, Smith E, Wang KW. Active load control of an articulated composite rotor blade via dual trailing edge flaps. In 44th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference. 2003. (44th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference).