A Comparison of Helicopter Main Rotor Features Due to Stiffness of Rotor Blade-Hub Connection

Jarosław Stanisławski 1
  • 1 Institute of Aviation, , 02-256, Warsaw, Poland


The paper presents results of simulation calculations concerning an influence of stiffness of blade-hub connection on rotor loads and blades deflections in hover, level flight and pull up maneuver. The three versions of rotor are considered with articulated, elastic and stiff connections of blades and hub. The blades with the same distributions of stiffness, mass and the same aerodynamic characteristics are applied for all rotor cases. The rotor loads are calculated applying Runge-Kutta method to solve the equations of motion of deformable blades. According to the Galerkin method, the parameters of blades motion are treated as combination of considered blade bending and torsion eigen modes. The results of calculations indicate for possibility to generate the greater rotor control moments and to improve helicopter maneuverability in the case of applying the non-changed blade of articulated rotor combined with elastic rotor hub.

If the inline PDF is not rendering correctly, you can download the PDF file here.

  • [1] Prouty R.W., 1988, More Helicopter Aerodynamics, Phillips Pub Co.

  • [2] Johnson W., 1980, Helicopter Theory, Princeton University Press, Princeton, New Jersey.

  • [3] Padfield G.D., 1996, Helicopter Flight Dynamics. the Theory and Application of Flying Qualities and Simulation Modeling, Blackwell Publishing Ltd.

  • [4] Warwick G., 1985, “Will rotors lose their bearings?”, Flight International, 29 June, no. 3966, vol.127, pp. 30-35.

  • [5] Braun D., Frommlet H., Schwarz A., 1990, “FEL – A New Main Rotor System”, Vertica, Vol. 14, No. 1, pp. 47-60.

  • [6] Schmit-Creton V., 2006, Successful Maiden Flight, Rotor on Line – A publication of Eurocopter, July/August, No. 67, from http://www.airbushelicopters.com/w1/jrotor/67

  • [7] Wilson M., 1974, “Westland-Aerospatiale Lynx”, Flight International, 29 August, No. 3416, Vol. 106, Supplement 1, pp. 19-22.

  • [8] Yeo H., Johnson W., 2005, “Comparison of Structural Loads Calculated Using Comprehensive Analysis”, 31st European Rotorcraft Forum, Florence, Italy, September 13-15.

  • [9] Nguyen K., Lauzon D., Anand V., 1994, “Computation of Loads on the McDonnell Douglas Advanced Bearingless Rotor”, American Helicopter Society 50th Annual Forum, Washington D.C., May 11-13.

  • [10] Gula P., Gorecki T., 2013,”Design, Experiments and Development of a Polish Unmanned Helicopter ILX-27”, 39th European Rotorcraft Forum, Moscow, Russia, 3-6 September.

  • [11] Stanisławski J., 2015, “Pattern of Helicopter Rotor Loads and Blade Deformations in Some States of Flight Envelope”, Transactions of the Institute of Aviation, No.1(238), pp. 70-90.

  • [12] Stanisławski J., 2016, “Simulation Investigation of Aerodynamic Effectiveness Reduction of Helicopter Tail Rotor”, Transactions of the Institute of Aviation, No.1(242), pp. 36-56.


Journal + Issues