The aeroelastic stability of a circulation control rotor blade undergoing three degrees of motion (flap, lag, and torsion) is investigated in forward flight. Quasi-steady strip theory is used to evaluate the aerodynamics forces; and the airfoil characteristics are from data tables. The propulsive and the auxiliary power trims are calculated from vehicle and rotor equilibrium equations through the numerical integration of element forces in azimuth as well as in radial directions. The nonlinear time dependent periodic blade response is calculated using an iterative procedure based on Floquet theory. The periodic perturbation equations are solved for stability using Floquet transition matrix theory. The effects of several parameters on blade stability are examined, including advance ratio, collective pitch, thrust level, shaft tilt, structural stiffnesses variation, and propulsive and auxiliary power trims.


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    Titel :

    Flap-lag-torsion aeroelastic stability of a circulation control rotor in forward flight


    Beteiligte:
    Chopra, Inderjit (Autor:in) / Hong, Chang-Ho (Autor:in)


    Erscheinungsdatum :

    01.05.1987


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    Aeroelastic characteristics for jet-flap helicopter rotor in forward flight

    White, Jr., R.P. / Trenka, A.R. | Engineering Index Backfile | 1962


    Flap-Lag-Torsion Stability in Forward Flight

    Panda, B. / Chopra, I. | NTRS | 1985



    THE AEROELASTIC CHARACTERISTICS OF A JET-FLAP HELICOPTER ROTOR IN FORWARD FLIGHT*

    Trenka, Andrew R. / White, Richard P. | SAE Technical Papers | 1962