Simulation of Flight Dynamics for Helicopter Icing

Conference paper
Part of the Lecture Notes in Electrical Engineering book series (LNEE, volume 318)


This allows unregistered users to read the abstract as a teaser for the complete chapter. The formulas for calculating the variation of aerodynamic coefficient of iced blade airfoil were introduced according to rotor icing test data from NASA and the formulas for aerodynamic force and moment of rotor icing were deduced. Further, the model of flight dynamics for helicopter icing was built. Icing effect on trim characteristics and stability of certain single-rotor helicopter in hover and forward speed was studied. The results show that whether in hover or forward flight, when the helicopter iced, the amount of the collective control, the longitudinal control, and the lateral control of the rotor, the tail rotor collective control as well as the roll angle increases, while the pitch angle decreases; the longitudinal long-period and short-period mode goes more stable, and the same as the lateral helical mode, while the roll mode and Dutch roll mode go more unstable.


Helicopter Icing Flight dynamics Rotor Trim Stability 


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Copyright information

© Springer-Verlag Berlin Heidelberg 2015

Authors and Affiliations

  1. 1.China Academy of Aerospace AerodynamicsBeijingChina

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