Rotorcraft simulations have traditionally used a quasistatic approach to represent blade section aerodynamics in a blade element model. For aeroelastic analysis, it is essential to model the dynamic variation of airloads over a sufficiently broad frequency range to assess the impact on rotor vibratory loads. These broad range of frequency effects can also influence the stability of the flight vehicle so the need to model them properly in a free flight rotorcraft simulation is required. This paper describes a nonlinear unsteady airloads model based on unsteady thin airfoil theory and the ONERA dynamic stall equations for application in rotorcraft flight simulation. A finite state approach is used to facilitate combining this model with finite state representations of inflow and a modal representation of blade elasticity. This approach is then used in FLIGHTLAB to predict both the isolated rotor loads and the fully coupled rotor/fuselage stability in free flight and the results are compared with those obtained from a quasistatic representation of the blade airloads.
An unsteady airload model with dynamic stall for rotorcraft simulation
Ein unstetiges Luftbelastungsmodell mit dynamischem Strömungsabriß zur Simulation von Hubschrauberflugverhalten
Forum, Annual Forum, American Helicopter Society, 50 ; 2 ; 931-948
1994
18 Seiten, 24 Bilder, 2 Tabellen, 17 Quellen
Conference paper
English
An Unsteady Airload Model with Dynamic Stall for Rotorcraft Simulation
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