Existing ground effect simulation models use a simple factor to modify the out-of-ground effect (OGE) inflow to get in-ground effect (IGE) inflow, which is found to be rather approximate. Though comprehensive in-ground effect models based on computational fluid dynamics (CFD) exist in the literature, such CFD models are not very useful for real-time simulation studies. A finite state inflow model for hovering in ground effect is developed by treating both the rotor and the ground surface as disturbances in the flow field. The ground disturbance potential coefficients are determined by imposing the non-penetration boundary condition at the ground surface. Analytical expressions for the mass flow parameter and the L-matrix are derived as functions of rotor height above the ground. Also, dynamic ground effect is modeled by considering only the vertical motion of the ground (representative of a heaving ship deck) and it is seen that the effect of ground velocity can be represented as an additional forcing term in the model. Validation of the proposed model is carried out using available experimental data.


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    Titel :

    Finite state inflow model for simulation of helicopter hovering in ground effect


    Beteiligte:
    Xin, Hong (Autor:in) / Prasad, J.V.R. (Autor:in) / Peters, D.A. (Autor:in) / Nagashima, T. (Autor:in) / Iboshi, N. (Autor:in)


    Erscheinungsdatum :

    1998


    Format / Umfang :

    8 Seiten, 11 Quellen


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Print


    Sprache :

    Englisch




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