This paper discusses the comparison between the steady-state response of a helicopter rotor blade in forward flight computed using marching-in-time algorithms and computed using imposed-periodicity algorithm. The blade is represented as a two-degree-of-freedom rigid body. The motion of the blade is modeled with a system of ordinary, nonlinear, differential equations. Runge-Kutta and predictor-corrector methods are used for marching-in-time solutions. Time finite element method based on bilinear formulation is used for imposed-periodicity solutions. Differences between the steady-state solutions obtained using marching-in-time and imposed-periodicity methods has been observed. These differences affect also the results of motion about steady-state stability analysis. The same phenomenon has been observed for a simple two-degree-of-freedom, nonlinear mass-damper-spring system.
Comparison between imposed-periodicity and marching-in-time solutions of helicopter rotor blade steady-state response problem
Vergleich zwischen zwei Lösungsmöglichkeiten des Problems, das Verhalten von Hubschrauberflügeln im Gleichgewichtszustand zu berechnen
AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference, 33 ; 3 , Apr ; 1340-1349
1992
10 Seiten, 14 Bilder, 8 Quellen
Conference paper
English
Potential Panel and Time-Marching Free-Wake Coupling Analysis for Helicopter Rotor
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