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Power and Trim Estimation for Helicopter Sizing and Performance Analysis

  • Received : 2011.03.05
  • Accepted : 2011.04.02
  • Published : 2011.06.30

Abstract

The preliminary design stage of helicopters consists of various operations and in each operation design several detailed analysis tasks are needed. The analysis tasks include performance and the required power estimation. In helicopter design, those are usually carried out by adopting the momentum theory. In this paper, an explicit form of computational analysis based on the blade element theory and uniform/non-uniform inflow model is developed. The other motivation of the present development is to obtain trim and required power estimation for various helicopter configurations. Sectional and hub loads, power, trim, and flapping equations are derived by using a symbolic tool. Iterative computations are carried out till convergence is achieved in the blade response, inflow, and trim. The predictions regarding the trim and power estimation turn out to be correlated well with the experimental results. The effect of inflow is further investigated. It is found that the present prediction for the lateral cyclic pitch angle is improved with the non-uniform inflow model as compared to that by the uniform inflow model. The presently improved trim and power estimation will be useful for future helicopter sizing and performance analysis.

Keywords

Helicopter preliminary design;Non-uniform inflow;Trim;Power estimation

References

  1. Datta, A. (2004). Fundamental Understanding, Prediction and Validation of Rotor Vibratory Loads in Steady Level Flight. PhD Thesis, University of Maryland.
  2. Davis, S. J., Rosenstein, H., Stanzione, K. A., and Wisniewski, J. S. (1979). User's Manual for HESCOMP: The Helicopter Sizing and Performance Computer Program, Revision 2. Philadelphia, PA: Boeing Vertol Company.
  3. Ibrahim, A. A. S. and Jaafar, M. N. M. (2008). Power estimation for four seater helicopter. Jurnal Mekanikal, 27, 78-90.
  4. Johnson, W. (1980). Helicopter Theory. Princeton, NJ: Princeton University Press.
  5. Johnson, W. (2010). NDARC-NASA design and analysis of rotorcraft validation and demonstration. American Helicopter Society Aeromechanics Specialist's Conference on Aeromechanics, San Francisco, CA.
  6. Lim, J., Shin, S. J., and Kim, J. (2009). Development of an advanced rotorcraft preliminary design framework. International Journal of Aeronautical and Space Sciences, 10, 134-139. https://doi.org/10.5139/IJASS.2009.10.2.134
  7. Padfield, G. D. (1996). Helicopter Flight Dynamics: The Theory and Application of Flying Qualities and Simulation Modelling. Reston, VA: American Institute of Aeronautics and Astronautics.
  8. Panda, B. and Chopra, I. (1985). Flap-lag-torsion stability in forward flight. Journal of the American Helicopter Society, 30, 30-39. https://doi.org/10.4050/JAHS.30.30
  9. Payne, P. R. (1953). A method of estimating helicopter performance: the calculation of an estimated performance at the project stage. Aircraft Engineering and Aerospace Technology, 25, 344-348. https://doi.org/10.1108/eb032356
  10. Prouty, R. W. (1990). Helicopter Performance, Stability, and Control. Malabar, FL: Robert E. Krieger Publishing Co.
  11. Rand, O. and Khromov, V. (2004). Helicopter sizing by statistics. Journal of the American Helicopter Society, 49, 300- 317. https://doi.org/10.4050/JAHS.49.300
  12. Ribera, M. (2007). Helicopter Flight Dynamics Simulation with a Time-Accurate Free-Vortex Wake Model. PhD Thesis, University of Maryland.