The paper presents a study of the flight dynamics of an articulated rotor helicopter carrying a suspended load. The aircraft model includes rigid body dynamics, individual flap and lag blade dynamics, and inflow dynamics. The load is a point mass with a single suspension point. Results were obtained for load masses of up to 2000 kg, with load-to-helicopter mass ratios of up to 28 %, cable lengths from 3 m to 8 m, turn rates of up to 16 deg/sec, and advance ratios of up to 0.3. The load affects trim primarily through the overall increase in the weight of the aircraft; the influence of cable length is negligible. Substantial coupling can occur between the Dutch roll and the load modes. Because of this coupling, the Dutch roll damping can decrease with a deterioration of handling qualities. The effects on the phugoid are very small. A suspended load modifies the roll frequency response by adding a notch to the gain curves and a 180-degree jump in the phase curves at the pendulum frequencies of the load. The changes in bandwidth and phase delay are small.


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    Title :

    Flight dynamics of an articulated rotor helicopter with an external slung load


    Additional title:

    Die Flugdynamik eines Gelenkrotor-Hubschraubers mit einer externen Pendellast


    Contributors:
    Fusato, D. (author) / Guglieri, G. (author) / Celi, R. (author)

    Published in:

    Publication date :

    2001


    Size :

    11 Seiten, 20 Bilder, 1 Tabelle, 19 Quellen




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English





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