This paper presents a new simulation method for ground and air resonance stability analysis of helicopter rotor systems. The method presented is based on the formulation of the full non-linear equations of motion of three rigid offset blades with degrees of freedom in the flap and lead/lag and a hub that has two translational degrees of freedom for the body. The set of non-linear equations of motion is developed by the Lagrangian method using symbolic processing software for expanding the equations. In addition, the symbolic software automatically converts the equations of motion into a source code that is optimized for numerical integration. Part 1 of this paper addresses the derivation of the equations of motion for the rotor-body combination. Part 2 of this paper addresses the comparison of simulation output to referenced works and includes several unique applications that take advantage of the non-linear capability of the resulting simulation.


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    Title :

    Non-linear simulation of coupled rotor-fuselage response using symbolically derived equations of motion. Part 1: Derivation


    Contributors:
    Robinson, C S (author) / King, R L (author) / Wood, E R (author)


    Publication date :

    2004-01-01


    Size :

    9 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English