Pattern of Helicopter Rotor Loads and Blade Deformations in Some States of Flight Envelope

Stanisławski, Jarosław

doi:10.5604/05096669.1151311

Cited by 4 publications

(4 citation statements)

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“…A frequently used mathematical model is the blade element model. It can be found both in classic books on helicopters [1][2][3] and in articles, for example [4][5][6].…”

Section: Introductionmentioning

confidence: 99%

“…To verify the analytical model, the calculated loads were compared with flight data for the Bell model 406LM helicopter. In [4] the equations of motion of the deformable blade were solved by applying Galerkin's method. The results of calculations were presented in the form of plots showing the time-run of the loads and the distributions of deformations due to the blade azimuth position on the rotor disk.…”

Section: Introductionmentioning

confidence: 99%

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Estimation of Extreme Loads of the Mi-24 Helicopter During Maneuvers Using Simulation Method

Kowaleczko¹,

Piątkowski²

2022

Preprint

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The aim of the study is to assess the loads that are transferred from the main rotor and the tail rotor to the helicopter fuselage. These loads change in the various phases of the transient flight as a result of the variable control of the maneuver and as a result of the variable flow around the blades. The knowledge of the loads allows for the proper selection of the level of excitations that should load the fuselage structure during fatigue and strength tests. The simulation model describing the helicopter flight is discussed. This model takes into account the motion of each blade relative to its hinges. Results are shown for two maneuvers - pullup/pushover and diving. The values of extreme loads transferred to the fuselage were obtained.

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“…A frequently used mathematical model is the blade element model. It can be found both in classic books on helicopters [1][2][3] and in articles, for example [4][5][6].…”

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Estimation of Extreme Loads of the Mi-24 Helicopter During Maneuvers Using Simulation Method

Kowaleczko¹,

Piątkowski²

2022

Preprint

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“…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%

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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“…The CSD part in proposed methodology incorporates dedicated inhouse Blade Deformation Solver (BDS), which is based on equivalent beam model of a blade. Similar structural simplification of a blade was used with less sophisticated aerodynamic model in [12,13], with good results. After describing the computational model in the first part of the paper, the second part focuses on validation process based on Wind Tunnel Test (WTT) data for a model rotor from a light helicopter.…”

Section: Introductionmentioning

confidence: 99%

Aeroelastic Analysis of Helicopter Rotor using Virtual Blade Model and Equivalent Beam Model of a Blade

Sieradzki

2016

Journal of KONES. Powertrain and Transport

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Modern helicopter rotor blades design requires taking into account complex aeroelastic phenomena. Sophisticated computational fluid dynamics and structural dynamics models, available on the market, coupled together enable such analysis with very high fidelity. However, the computational cost of this type of simulation is usually very high and for this reason, it cannot be used in interactive design process or optimization run. Complex Fluid Structure Interaction models are excellent tools for validation purposes, but the design process requires simpler models with lower computational cost and still relatively high accuracy and capabilities. The paper presents a new efficient methodology for calculating helicopter rotor loads, deformations and performance. It uses the well-known Navier-Stokes equations aerodynamic solver-ANSYS Fluent, and modified Virtual Blade Model (based on Blade Element Theory) for rotor flow calculation. This connection guarantees exceptional capabilities and fidelity in comparison with simulation time. The dedicated structural dynamics solver, based on equivalent beam model of a blade and Finite Difference Method, was developed and coupled with CFD part using User Defined Functions in Fluent software. The accuracy of created module was validated with wind tunnel tests data of IS-2 helicopter rotor model, performed in Institute of Aviation. The results of calculations were compared with experimental data for a hover state and a forward flight with three different flight velocities. The comparisons showed very good agreement of the data in most of the analysed cases and pointed out new research possibilities. The presented aeroelastic helicopter rotor model combines all advantages of using three-dimensional Navier-Stokes solver with relatively low computational costs and high accuracy, confirmed by wind tunnel tests. It could be used successfully in helicopter rotor blades design process.

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Pattern of Helicopter Rotor Loads and Blade Deformations in Some States of Flight Envelope

Cited by 4 publications

References 0 publications

Estimation of Extreme Loads of the Mi-24 Helicopter During Maneuvers Using Simulation Method

Estimation of Extreme Loads of the Mi-24 Helicopter During Maneuvers Using Simulation Method

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

Aeroelastic Analysis of Helicopter Rotor using Virtual Blade Model and Equivalent Beam Model of a Blade

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