Simulation of Flight Dynamics for Helicopter Icing

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

Abstract

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.

Keywords

Helicopter Icing Flight dynamics Rotor Trim Stability 

References

  1. 1.
    Fu J (1999) Study on helicopter anti-icing. Flight dynamicsGoogle Scholar
  2. 2.
    Wang Z (2001) Helicoper anti-icing problem. Helicopter technologyGoogle Scholar
  3. 3.
    Flemming RJ, Lednicer DA (1983) High speed ice accretion on rotorcraft airfoils. In: Proceedings of 39th annual forum of the American Helicopter SocietyGoogle Scholar
  4. 4.
    Flemming RJ, Lednicer DA (1985) Correlation of airfoil icing relationships with two-dimensional model and full scale rotorcraft icing test dataGoogle Scholar
  5. 5.
    Gastinger DC (1983) FAA rotorcraft icing regulations and directions. Vertiflite 29:26–30Google Scholar
  6. 6.
    Baruzzi G, Tran P, Habashi WG, Akel I, Balage S (2004) FENSAP-ICE progress towards a rotorcraft, AIAA 2003-0024Google Scholar
  7. 7.
    Didier PG, Joseph JC, Luc SB(1985) Overview of icing research at ONERA, AIAA-85-0335Google Scholar
  8. 8.
    He Z, Chang S, Yuan X (2002) Rotor-water impact characteristics of helicopter in hover. Aeronaut JGoogle Scholar
  9. 9.
    Gao Z, Chen R (2003) The helicopter flight dynamics, PekingGoogle Scholar
  10. 10.
    Cao Y (2005) The helicopter flight dynamics, PekingGoogle Scholar
  11. 11.
    Xu X, Lin H, Xu X (1988) Research on trim and stability of “dolphin” helicopter. The flight dynamicsGoogle Scholar
  12. 12.
    Chen R, Xu X (1990) Helicopter esponse to the discrete gust. NUAA JGoogle Scholar

Copyright information

© Springer-Verlag Berlin Heidelberg 2015

Authors and Affiliations

  1. 1.China Academy of Aerospace AerodynamicsBeijingChina

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