In-Flight Rotorblade Tracking Control for Helicopters Using Active Trailing-Edge Flaps

King, Frank A.; Maurice, J.-B.; Fichter, Walter; Dieterich, O.; Konstanzer, Peter

doi:10.2514/1.59475

Cited by 6 publications

(2 citation statements)

References 8 publications

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“…The potential of this concept to decrease vibration, attenuate noise and improve rotor performance is shown by several studies. 7–10 Studies also show that multiple flaps are more effective in reducing vibration in comparison with single flap concepts within available actuator authority, 11,12 providing more flexibility in altering the aerodynamic loads acting on the helicopter rotor blade. Figure 1 shows a rotor-blade section with dual trailing-edge flaps.…”

Section: Introductionmentioning

confidence: 99%

Vibration reduction of helicopter with trailing-edge flaps at various flying conditions

Kodakkattu

Joy

Nair

2016

Proceedings of the Institution of Mechanical Engineers, Part G:

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The aim of this study is to find the optimal torsional stiffness and trailing-edge flap locations of the helicopter rotor blade for minimum vibration and flap control power at flap lengths of 6% and 9% of the rotor-blade length. A three level orthogonal array based response surface method using polynomial functions is used to describe both vibration and flap control power. Pareto points minimizing hub vibration and flap control power are found at flap lengths of 6% and 9% of the rotor length. This study also explores the variation in rotor hub vibration and flap control power with flying conditions such as the advance ratio and the thrust-to-solidity ratio at the optimum design points. This gives a useful improved design with about a 60% decrease in hub vibration with a penalization of increased flap power at the normal flying regime of rotor-craft flight.

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Section: Introductionmentioning

confidence: 99%

Vibration reduction of helicopter with trailing-edge flaps at various flying conditions

Kodakkattu

Joy

Nair

2016

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…Works in the HHC category, like those of Hall and Wereley (1992); ; consider the control forces to be applied to the swashplate by means of actuators. The IBC works (Bittanti and Cuzzola, 2002;Arcara et al, 2000;King et al, 2014;Shen et al, 2006) consider that each blade can be actuated independently. The main difference between the two approaches is the number of available degrees of freedom for the control action.…”

Section: Introductionmentioning

confidence: 99%

Control of Pitch-Flap Instabilities in Helicopter Rotors using Delayed Feedback

Cepeda-Gomez¹

2016

IFAC-PapersOnLine

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The problem of vibration suppression in helicopter rotors is the main topic of this paper. We revisit a strategy for the stabilization of such systems based on delayed feedback. By means of an improved analysis, made possible by recently developed mathematical tools, we present insights on how the delay can be used as stabilization tool for this problem. The results are supported with numerical simulations. For simplicity, only the case of hovering flight is considered.

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Delayed feedback control of pitch-flap instabilities in helicopter rotors

Cepeda-Gomez

2019

Stability, Control and Application of Time-Delay Systems

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In-Flight Rotorblade Tracking Control for Helicopters Using Active Trailing-Edge Flaps

Cited by 6 publications

References 8 publications

Vibration reduction of helicopter with trailing-edge flaps at various flying conditions

Vibration reduction of helicopter with trailing-edge flaps at various flying conditions

Control of Pitch-Flap Instabilities in Helicopter Rotors using Delayed Feedback

Delayed feedback control of pitch-flap instabilities in helicopter rotors

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