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- W4382248201 abstract "To better understand the underlying physics of rotorcraft-pilot coupling events on the collective control chain, a hybrid modeling approach is proposed for the biomechanical response of the pilot's body. A condensed modal representation of the two most relevant mode shapes, obtained from multibody simulations, is employed alongside a physical representation of the loading factors. The enhanced pilot model response in the closed-loop system is compared to the established, one degree of freedom approach by coupling the pilot model to a simplified representation of the helicopter vertical dynamics, comprising the effects of the heave and collective flap degrees of freedom. The stability of the close-loop system is evaluated on the loop transfer function through the gain and phase margins. It is found that the added dynamics, even though it is not evident in the experimental biodynamic feedthrough transfer functions, has a non-negligible effect on the closed-loop stability of the pilot-vehicle system. The effect of the landing gear dynamics and of non-minimal muscular activation contribution on the closed-loop stability is also assessed." @default.
- W4382248201 created "2023-06-28" @default.
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- W4382248201 date "2023-05-16" @default.
- W4382248201 modified "2023-09-25" @default.
- W4382248201 title "Pilot Modeling and Sensitivity Analysis for Rotorcraft-Pilot Couplings Robust Design" @default.
- W4382248201 doi "https://doi.org/10.4050/f-0079-2023-18082" @default.
- W4382248201 hasPublicationYear "2023" @default.
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