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Airfoil-Section Rotor Blades

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Abstract

The work done in the previous chapter is further extended to the design of a two-cell airfoil cross-section which is a more realistic model of the helicopter rotor blade. Optimum actuator placement, the effect of the current active twist concept on key characteristics such as blade loads, aeromechanical stability and trim controls is investigated. Aeroelastic analysis of the rotor blade is very important in the case of any refinement in the structural or aerodynamic model. Since the incorporation of piezoceramic changes the blade structural characteristics, it is important to ensure that the benefits gained due to the refinement should not be detrimental to the other aspects of the rotor such as performance, trim, and stability.

Keywords

  • Rotor Blade
  • Vibration Reduction
  • Forward Flight
  • Airfoil Section
  • Advance Ratio

These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.

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  • DOI: 10.1007/978-3-319-24768-7_10
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References

  1. Thakkar, D., Ganguli, R.: Induced shear actuation of helicopter rotor blade for active twist control. Thin Walled Struct. 45(1), 111–121 (2007)

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  2. Bagai, A., Leishman, J.G.: Rotor free-wake modeling using a pseudo-implicit technique—including comparisons with experimental data. J. Am. Helicopter Soc. 40(3), 29–41 (1995)

    CrossRef  Google Scholar 

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Correspondence to Ranjan Ganguli .

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© 2016 Springer International Publishing Switzerland

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Ganguli, R., Thakkar, D., Viswamurthy, S.R. (2016). Airfoil-Section Rotor Blades. In: Smart Helicopter Rotors. Advances in Industrial Control. Springer, Cham. https://doi.org/10.1007/978-3-319-24768-7_10

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  • DOI: https://doi.org/10.1007/978-3-319-24768-7_10

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  • Publisher Name: Springer, Cham

  • Print ISBN: 978-3-319-24766-3

  • Online ISBN: 978-3-319-24768-7

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