The role of rotor coning in helicopter proneness to collective bounce

Muscarello, Vincenzo; Quaranta, Giuseppe; Masarati, Pierangelo

doi:10.1016/j.ast.2014.04.006

Cited by 13 publications

(13 citation statements)

References 15 publications

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“…Within ARISTOTEL, a closed-loop aeroelastic experiment involving collective bounce was presented and discussed by Masarati et al in [13]. In [14], Muscarello et al pinpointed the phase margin reduction introduced by the main rotor coning mode in the collective pitch-heave loop transfer function as the key factor in the manifestation of collective bounce.…”

mentioning

confidence: 99%

Prediction and Simulator Verification of Roll/Lateral Adverse Aeroservoelastic Rotorcraft–Pilot Couplings

Muscarello¹,

Quaranta²,

Masarati³

et al. 2016

Journal of Guidance, Control, and Dynamics

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The involuntary interaction of a pilot with an aircraft can be described as pilot-assisted oscillations. Such phenomena are usually only addressed late in the design process when they manifest themselves during ground/flight testing. Methods to be able to predict such phenomena as early as possible are therefore useful. This work describes a technique to predict the adverse aeroservoelastic rotorcraft-pilot couplings, specifically between a rotorcraft's roll motion and the resultant involuntary pilot lateral cyclic motion. By coupling linear vehicle aeroservoelastic models and experimentally identified pilot biodynamic models, pilot-assisted oscillations and no-pilot-assisted oscillation conditions have been numerically predicted for a soft-in-plane hingeless helicopter with a lightly damped regressive lead-lag mode that strongly interacts with the roll mode at a frequency within the biodynamic band of the pilots. These predictions have then been verified using real-time flight-simulation experiments. The absence of any similar adverse couplings experienced while using only rigid-body models in the flight simulator verified that the observed phenomena were indeed aeroelastic in nature. The excellent agreement between the numerical predictions and the observed experimental results indicates that the techniques developed in this paper can be used to highlight the proneness of new or existing designs to pilot-assisted oscillations.

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confidence: 99%

Prediction and Simulator Verification of Roll/Lateral Adverse Aeroservoelastic Rotorcraft–Pilot Couplings

Muscarello¹,

Quaranta²,

Masarati³

et al. 2016

Journal of Guidance, Control, and Dynamics

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“…Figure 14 shows the vertical acceleration of the helicopter during a short transient before the maneuver is initiated, after the system has been perturbed impulsively. The figure shows that for nominal gear ratio (G = 1.0) the oscillations associated with the interaction between the main rotor coning mode (a major playing factor in collective bounce, as pointed out in [43]) and the pilot biodynamics quickly vanish. For G = 1.8 the oscillations persist, whereas for G = 2.0 they diverge.…”

Section: B Results Of the Coupled System Analysismentioning

confidence: 93%

A voluntary/involuntary pilot model for helicopter flight dynamics and aeroservoelasticity

Bernardini

Guglieri

Masarati

et al. 2014

AIAA Atmospheric Flight Mechanics Conference

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This work presents the integration of detailed models of a pilot controlling an helicopter along the heave axis through the collective control inceptor. The action on the control inceptor is produced through a biomechanical model of the pilot's limbs, by commanding the activation of the related muscle bundles. Such activation, in turn is determined by defining the muscle elongations required to move the control inceptor in order to obtain the control of the vehicle according to a high-level model of the voluntary action of the pilot acting as a regulator for the vehicle. The biomechanical model of the pilot's limbs and the aeromechanical model of the helicopter are implemented in a general-purpose multibody simulation environment. The helicopter model, the biomechanical model of the pilot's limbs, the cognitive model of the pilot and their integration are discussed. The integrated model is applied to the simulation of simple, yet representative mission task elements.

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“…Figure 14 shows the vertical acceleration of the helicopter during a short transient before the maneuver is initiated, after the system has been perturbed impulsively. The figure shows that for nominal gear ratio (G = 1.0) the oscillations associated with the interaction between the main rotor coning mode (a major playing factor in collective bounce, as pointed out in [52]) and the pilot biodynamics quickly vanish. For G = 1.8 the oscillations persist, whereas for G = 2.0 they diverge.…”

Section: B Results Of the Coupled System Analysismentioning

confidence: 99%

Voluntary Pilot Action Through Biodynamics for Helicopter Flight Dynamics Simulation

Masarati¹,

Quaranta²,

Bernardini³

et al. 2015

Journal of Guidance, Control, and Dynamics

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This work presents the integration of detailed models of a pilot controlling a helicopter along the heave axis through the collective control inceptor. The action on the control inceptor is produced through a biomechanical model of the pilot's limbs, by commanding the activation of the related muscle bundles. Such activation, in turn, is determined by defining the muscle elongations required to move the control inceptor in partial derivative of (♠) with respect to (♣)

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The role of rotor coning in helicopter proneness to collective bounce

Cited by 13 publications

References 15 publications

Prediction and Simulator Verification of Roll/Lateral Adverse Aeroservoelastic Rotorcraft–Pilot Couplings

Prediction and Simulator Verification of Roll/Lateral Adverse Aeroservoelastic Rotorcraft–Pilot Couplings

A voluntary/involuntary pilot model for helicopter flight dynamics and aeroservoelasticity

Voluntary Pilot Action Through Biodynamics for Helicopter Flight Dynamics Simulation

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