An aeroelastic stability of three-degree flap-lag-torsion blade in forward flight is examined. Quasisteady aerodynamics with a dynamic inflow model is used. 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 as well as constant coefficient approximation in the fixed reference frame. Results are presented for both stiff-inplane and soft-inplane blade configurations. The effects of several parameters on blade stability are examined, including structural coupling, pitch-flap and pitch-lag coupling, torsion stiffness, steady inflow distribution, dynamic inflow, blade response solution and constant coefficient approximation.
Flap-Lag-Torsion Stability in Forward Flight
1985-11-01
Conference paper
No indication
English
Flap-Lag-Torsion Stability in Hover and Forward Flight with Three-Dimensional Wake
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|Flap-Lag-Torsion Stability in Hover and in Forward Flight With a Three-Dimensional Wake
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|Flap-Lag-Torsion Stability in Hover and in Forward Flight With a Three-Dimensional Wake
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