This paper discusses the impact of different models of aerodynamic loads on rotorcraft-pilot couplings stability using a robust stability analysis approach. The aeroelasticity of the main rotor of a helicopter is formulated using aerodynamic models based on the blade ele- ment/momentum theory and boundary element method coupled to a finite element model of the blade. The resulting linearized models are used to determine stability limits according to the generalized Nyquist criterion, associated with the accelerations of the pilot’s seat caused by the involuntary action of the pilot on the control in- ceptors. The resulting stability curves are discussed considering examples of involuntary pilot transfer functions from the literature.
Quaranta, G., Tamer, A., Muscarello, V., Masarati, P., Gennaretti, M., Serafini, J., et al. (2013). Rotorcraft Aeroelastic Stability Using Robust Analysis. CEAS AERONAUTICAL JOURNAL, 5(1), 29-39 [10.1007/s13272-013-0082-z].
Rotorcraft Aeroelastic Stability Using Robust Analysis
GENNARETTI, MASSIMO;SERAFINI, JACOPO;MOLICA COLELLA, MARCO
2013-01-01
Abstract
This paper discusses the impact of different models of aerodynamic loads on rotorcraft-pilot couplings stability using a robust stability analysis approach. The aeroelasticity of the main rotor of a helicopter is formulated using aerodynamic models based on the blade ele- ment/momentum theory and boundary element method coupled to a finite element model of the blade. The resulting linearized models are used to determine stability limits according to the generalized Nyquist criterion, associated with the accelerations of the pilot’s seat caused by the involuntary action of the pilot on the control in- ceptors. The resulting stability curves are discussed considering examples of involuntary pilot transfer functions from the literature.I documenti in IRIS sono protetti da copyright e tutti i diritti sono riservati, salvo diversa indicazione.
