Simulation investigation of aerodynamic effectiveness reduction of helicopter tail rotor.

Stanisławski, Jarosław

doi:10.5604/05096669.1202201

Cited by 2 publications

(2 citation statements)

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“…Notice: symbols used in Table 1 to sign blade eigen modes are as follows: F -out-of-plane bending mode, C -in-plane bending mode, T -torsion mode, digits after mode symbol are equal to the number of nodes, frequency values are related to the nominal rotational speed of rotor shaft ω nom =49.65rad/s Considering the blade flap oscillations, the rotor with stiff element connecting blade and hub can be, as model for analysis, replaced by an equivalent articulated rotor with the horizontal hinge located at greater distance l 0 measured from the rotor shaft axis. According to formula [12] the distance of horizontal hinge, allowing blade flapping, related to rotor radius depends on the value of frequency V F0 of the first out-of plane blade mode:…”

Section: Comparison Of Rotor Featuresmentioning

confidence: 99%

“…The rotor blades of similar characteristics were applied during ground and flight tests of the ILX-27 helicopter developed in Poland [10]. The method of calculation of rotor loads developed in Institute of Aviation was applied in earlier works [11], [12]. The performed calculations were focused on checking the possibility of usage the blades designed for articulated rotor, without changes their parameters, as an assembly with modified the elastic or stiff rotor head which should improve maneuverability of helicopter in comparison with one of articulated rotor.…”

Section: Introductionmentioning

confidence: 99%

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A Comparison of Helicopter Main Rotor Features Due to Stiffness of Rotor Blade-Hub Connection

Stanisławski

2018

Transactions on Aerospace Research

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The paper presents results of simulation calculations concerning an influence of stiffness of blade-hub connection on rotor loads and blades deflections in hover, level flight and pull up maneuver. The three versions of rotor are considered with articulated, elastic and stiff connections of blades and hub. The blades with the same distributions of stiffness, mass and the same aerodynamic characteristics are applied for all rotor cases. The rotor loads are calculated applying Runge-Kutta method to solve the equations of motion of deformable blades. According to the Galerkin method, the parameters of blades motion are treated as combination of considered blade bending and torsion eigen modes. The results of calculations indicate for possibility to generate the greater rotor control moments and to improve helicopter maneuverability in the case of applying the non-changed blade of articulated rotor combined with elastic rotor hub.

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Section: Comparison Of Rotor Featuresmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

A Comparison of Helicopter Main Rotor Features Due to Stiffness of Rotor Blade-Hub Connection

Stanisławski

2018

Transactions on Aerospace Research

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Data-driven analysis and new findings on the loss of tail rotor effectiveness in helicopter accidents

Saleh

Guvir

et al. 2022

Sci Rep

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Loss of tail rotor effectiveness (LTE) is an unstable dynamic phenomenon that affects single-rotor helicopters and frequently leads to accidents. LTE accidents recur with troubling regularity and show no sign of abatement. This work uncovers new data-driven findings pertaining to LTE and risk factors. First, a scorecard is developed covering a broad range of results to better understand LTE accidents. Second, the risk of LTE is derived for current helicopters. Third, a Deep Learning model is developed that captures the dependence between LTE risk and helicopter features. A danger zone is discovered in the design space for short tail rotor arm and high tail rotor RPM. The results challenge the prevailing narrative of LTE accidents as mere pilot errors and demonstrate an intrinsic propensity to these accidents is embedded in part in the helicopter design. The findings open the door to new, more effective safety interventions for LTE accident prevention.

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Simulation investigation of aerodynamic effectiveness reduction of helicopter tail rotor.

Cited by 2 publications

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A Comparison of Helicopter Main Rotor Features Due to Stiffness of Rotor Blade-Hub Connection

A Comparison of Helicopter Main Rotor Features Due to Stiffness of Rotor Blade-Hub Connection

Data-driven analysis and new findings on the loss of tail rotor effectiveness in helicopter accidents

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